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Flight Readiness Review Addendumf

1. H Vehicle Requirement Design Feature Verification Status Details 1 10 All teams shall successfully A test date for the full Full scale In The first full scale launch launch and recover their full scale rocket has been flight progress confirmed that the booster section scale rocket prior to FRR in its con scheduled for April is completely flight ready A final flight configuration 4 second full scale test will be completed on 4 19 or 4 20 to confirm the entire rocket is in its final flight configuration The team will need to The vehicle will contain Ground Full In A ground test was conducted to incorporate a fail safe system an ignition control scale test progress ensure that the RockeTiltometer2 into the sustainer to prevent system which monitors flight is able to safely airstart the sustainer ignition if the trajectory is off nominal the tilt of the rocket and inhibits the sustainer from igniting if outside of the critical angle sustainer within the accepted range Testing has concluded that the RockeTiltometer2 is successfully able to detect a tilt angle and to inhibit the igniter if outside of the critical angle 48 Citrus College Rocket Owls Flight Readiness Review 5 Safety and Environment Vehicle Safety Officer Joshua will act as safety officer for the Rocket Owls He is TRA Level 1 certified and has training in emergency medical treatment and hazmat response As the safet
2. Inspect igniter head ensuring it is free from cracks and damages Inspect igniter leads ensuring the wire is not exposed or broken Slightly bend the igniter lead under igniter head Use guide to mark igniter depth using a permanent marker Ensure all switches are in the off position Win BR GW NO For the e match that ignites the sustainer wrap the e match around a wooden dowel and tape it and then place the wooden dowel up through the motor grains until the e match head reaches the igniter pellet Install igniter ensuring that it is not caught on any fuel grains Ensure lead of igniter and end of motor casing is at the marked location Setup on Launcher Table 29 Checklist for Setup on Launcher Step No Details Check Safety 1 Lower launch rail 2 Slide booster section onto rail 3 Slide main airframe onto rail 4 Attach e match for sustainer 5 Put masking tape over sustainer motor 6 Attach main bay to booster section with shear pins 7 Raise launch rail to upright vertical position 8 Attach igniter to main motor 9 Attach launch system to igniter 10 Turn switches on 104 Citrus College Rocket Owls Flight Readiness Review Launch Procedure Table 30 Checklist for Launch Procedure Step No Details Check Safety 1 Clear lau
3. Risk Causes Consequence Mitigation Risk Level Motor ignition Improper handling or setup of Data collected will not High heat 3M foil tape will be used 8 failure motor high humidity failure of determine the benefit of staging to secure igniters in motors to keep igniter or launch system as a motor failed to ignite them in place throughout the launch Raven3 does Poor programming of the Data collected is not accurate Raven3 has been ground tested and 8 not separate Raven3 failure of battery launched in subscale prior to full stages scale launch Table 24 Tesseract Failure Modes Risk Causes Consequence Mitigation Risk Level Triboelectric charge on Rocket did not accelerate Voltmeter will not take any Coat the nose cone with a layer of 12 8 surface of the rocket is not fast enough or did not useful data carbon fiber to help acquire charge strong enough for travel far enough through The voltmeter will also be calibrated voltmeter to sense the atmosphere to optimize efficiency Voltmeter doesn t know Arduino doesn t know Once activated the voltmeter The voltmeter will be equipped with 5 when to start taking data when the rocket has will take data instantly an accelerometer that will tell the launched creating useless data and Arduino when the vehicle launches making calculations much The Arduino will then tell the more error prone voltmeter to start taking data The electromagnetic Unexpected interference Exper
4. Flight Readiness Review Figure 21 Third Full Scale Flight Altitude Data from Avionics Bay Raven3 Scale Flight 4 27 Avionics FlPa 75100 4060 3020 Altitude Baro Ft AGL ra EE TTAF MA ie 1980 Z940 100 00 0s 000017 000917 000027 Time sec The data generated from the third flight is extremely close to the flight profile simulations generated by RockSim the closest out of all three test launches The apogee reached is still about 2000 ft short of the predicted apogee This however is due to the relatively strong wind speeds that pushed the rocket s trajectory about 22 degrees off the vertical thus preventing the rocket from attaining its maximum height Under calmer conditions the rocket would have matched the simulations generated Mass Report Figure 22 below shows the mass distribution of the launch vehicle initially determined by RockSim values and then adjusted to fit actual measured values Figure 22 Mass Distribution Chart Mass Report Miscellaneous Motor Casings 2 11 Payload 25 Propulsion 11 Recovery 10 Structure 41 E Motor Casings M Propulsion Structure E Recovery E Payload E Miscellaneous 33 Citrus College Rocket Owls Flight Readiness Review 00 osz 2 Recovery Subsystem Robustness of Recovery System Structural Elements The recovery harnesses used in the vehicle will be constructed of 1 inch tubular nylon webbing rated f
5. Citrus College Table of Contents A A aaseadestet 1 A Summary o as e E PR as aa tat 1 a Vehicle Summary A A E AN 1 PIO SUMAN tos 1 M Changes Made Smee COR td A a 2 1 Changes Made to Vehicle Criteria so id cated tances va debe ts suites te dan sata ects taka eases 2 2 Changes Made to Payload Cotorra 2 Hazard Detection ic is 2 o A A A A Pe ea ar ae 3 3 Changes Made to Project Pl das 3 4 CDR FC CAB ACK tinon ao iea nres nanie AEAT ELTE KAER aT AA ATEA AETA EEA EARST 3 MAO Vehicle Criteria sarna ae ccc ct ea IN ee a a aa anaes 5 1 Design and Construction Y sa 5 Design and Construction of Launch Vehicle ccccccccescceeeceeseeeeeeeseceeeeeeeeeeaeecueceeeneeeenaees 5 BOG siipi stasis eid Saas o e da da 5 Centering Rings Bulkheads and Fins 00 c cc eeccecceeeceeeeeesceceeeceeeeeeeeeseecaeceeeseeeenseecaeens 6 Era Elements is att ce do E AAA a acne 6 Qe A RO 6 Bx 101 51 5c ps 14 0 rene epg ESN e RE ere eee a Ree Ur ROT ee ee 7 c WW ELC LLG Ieee e R E e A E E a a an 8 Gi COMME CLOTS a ia a A aaa aa eA aA ai 9 e gt Battery Retortillo dada 9 Drawings and Schema is 10 di Nose Coneand Drogue Ba AAA a a eines 11 B AVIONICS Bay a A A ca ea 12 E gt Main AY 2 ir A tri 13 de Booster Section creierii iiiar eiea etude aes 14 Flight Reliability and Confidence iia dd 15 A de 15 Construction ae a a aguas 15 se EM ds died 16 b A E 16 c Guillotine Fin Alignment Jig a 17 O 17 A tas
6. Citrus College Rocket Owls Flight Readiness Review Flight Reliability and Confidence The team s primary objective is to design construct and successfully launch a high power rocket capable of compiling data with the potential to improve future Space Launch Systems SLS technology Project Lambda is directed towards research pertaining to the lateral vibrations of a rocket during its thrust phase the ramifications of triboelectric charging on communications signals and the effectiveness of utilizing an edge detection system to relay potential landing hazards The rocket will reach but not exceed an altitude of 7000 ft after which the dual deploy recovery system will bring the rocket to a safe landing within 2500 ft of the launch pad All safety regulations defined by NASA s University Launch Project competition as well as team and NAR Tripoli guidelines will be followed when building and operating the rocket The Rocket Owls plan to utilize their limited resources to positively represent their school and community while providing competition for veteran teams All the requirements defined by the mission directorate were used to guide the Rocket Owls design decisions The team s plan for meeting these requirements will be discussed in the Requirements and Verification section of the Vehicle Criteria detailing how each design requirement has been met The team will consider their mission a success after they have both launched
7. Payload Analysis of Failure Modes Table 22 Hazard Detection Failure Modes Risk Causes Consequence Mitigation Risk Level Residue from black Black powder charges can Unable to detect A cover is placed over the porthole to 2 powder charges cover easily leave residue on the hazards invalid edges prevent damage or residue from the black camera porthole surfaces in the tube where it detected powder was deployed Other sections of the Poor recovery design Camera images of The altimeter bay will have a longer 4 rocket obscure the improper lengths of shock landing zone shock cord than that of the main parachute hazard detection cord used in the rocket obscured bay to allow the altimeter bay to hang system during descent lower during descent with a clear view of the ground The detachable Black powder in tether didn t The camera will not Ground testing of detachment using black 6 bulkhead not ignite tether gets stuck on take any valid pictures powder to cut nylon line separating correctly quicklinks for hazard detection Battery failure or Didn t charge battery No power to system Ground testing of rechargeable batteries 2 overload manufacturing defect battery left in extreme temperatures damage to electronics and use of new 9 volt batteries 98 Citrus College Rocket Owls Flight Readiness Review Table 23 In Line Motor Failure Modes
8. Research in building Glendora Direct College Science and mousetrap cars GATE interaction Engineering students Grades 5 9 RISE Workshop Science Class Classroom 12 17 2013 6 8 grade 65 65 Education Slauson C presentation Slauson Direct Middle STEM activity Middle interaction School building School Grades 5 9 spaghetti towers students Rocketry Rocketry 1 11 2014 6th grade 19 19 Education Citrus A Outreach Event Workshop Edison Direct College Academy interaction GATE Grades 5 9 students Edison 1 1 Education Academy Direct educators interaction grades 5 9 Educators Grades 5 9 RISE Workshop STEM activity 1 25 2014 6th 8th grade 34 34 Education Citrus A building Edison Direct College mousetrap cars Academy interaction and egg drop GATE Grades 5 9 experiments students 113 Citrus College Rocket Owls Flight Readiness Review Event Activity Date of Audience No of NASA Type of Location E F Event Participants Outreach Interaction Type Count STEM Outreach Classroom 1 31 2014 6th Sth grade 147 147 Education Edison A presentation Edison Direct Academy STEM activity Academy interaction building GATE Grades 5 9 spaghetti towers students Edison 3 3 Education Academy Direct educators interaction grades 5 9 Educators Grades 5 9 Science and Rocketry 2 8 2014 5 8 grade 28 28 Education Citrus C Technology Workshop Glendora Di
9. portion of code to have the Arduino collect data from one of the sensors store it onto the SD card and send the data via Serial communications link to the ground station Additionally we will conduct a similar test but with the Hazard Detection system with close proximity and functioning to see if any interference occurs Testing will be done up to a range of 4 miles to imposter the distance of the team s vehicle Advanced serial data loggers are currently being looked into Humidity Temperature Sensor functional Test To ensure that this component records accurate data during flight data A section of code has already been written to operate this component and display the data This component will also be used during flight in of the team member s personal rockets The collected temperature and humidity data will be compared with readings from local weather stations Altitude Pressure Sensor Functional Test To ensure that this component records reliable during flight data A section of code has already been written to operate this component and save the collected data Additionally this component will be tested during flight in one of the team member s personal rockets along with the Raven3 to compare the altitude measurements of both products This will allow the team to simulate changing atmospheric conditions during flight Since altitude is determined through formulas using pressure only one nee
10. 1 Successfully debug edge detection algorithm 2 Perform static and motion tests with objects in the system s line of sight 3 Test communication of data with the ground station specifically looking for time delays Launch Day 1 Integrate Hazard Detection System into Project Lambda Avionics Bay 2 Receive real time data sent from XBee at ground station LVIS The experiment process procedure for this payload is listed below 1 Component Functionality Test a Test Raven3 for airstart capabilities 2 Subscale Test Flight a Ensure booster section separates from sustainer b Test ability of Raven3 to airstart sustainer 3 Static Ejection Charge Test a Determine amount of black powder required to separate main bay from booster section 75 Citrus College Rocket Owls Flight Readiness Review 4 Full Scale Test Flight a Verify that the motor propulsion system that worked for subscale still works for full scale b Test that Raven3 can measure lateral Gs 5 Launch Day a Launch rocket 6 Post Launch a Analyze data to determine which motor produces the most lateral Gs per Newton of net force provided Tesseract 1 Research a Look into various methods for recording charge or measuring a potential difference 2 Design process a Design a circuit that is able to accurately measure the triboelectric charge 3 Component Testing COMPLETE a Voltmeter i Sensors tested for functionality ii SD card checked to ensure d
11. Raven3 will be used to eject the booster parachute Figures 4 and 5 show the electrical schematics for the Raven3 altimeters and the RRC2 Mini The Raven3 altimeters will be connected to black powder charges inside of each of the bays The connection scheme for the parachutes can be found in Figure 24 pg 37 35 Citrus College Rocket Owls Flight Readiness Review Figure 23 Seperation of Rocket Sections with Shock Cord Attachment Figure 23 shows how the sections of the vehicle will separate It also shows where the shock cord will be attached for the parachute There are five separate sections that will be recovered through three parachutes The leftmost shock cord will hold the drogue parachute The middle shock cord will hold the main parachute and the rightmost shock cord will hold an additional parachute to recover the booster section The Raven3 in the avionics bay which is between the drogue and main parachute will ignite black powder charges to deploy both parachutes Rocket Locating Transmitters Within the body of the vehicle three different transmitters will be used in order to locate the three sections of the rocket that will separate After the booster burns out the booster section will separate from the rest of the rocket so that the sustainer can ignite The booster section will have its own GPS to track its location for recovery The next GPS will be housed in the avionics camera bay This section of the rocket
12. as well as the sustainer section will detach from the drogue bay and nose cone after the main parachute deploys The last GPS will be housed in the drogue bay specifically within the CubeSat The GPS within the Avionics Camera Bay will be the Adafruit Ultimate GPS This GPS runs on a frequency of L1 1575 42 MHz and will be connected to the Raspberry Pi Module The GPS data will be sent to the ground through an XBee wireless transceiver This transceiver will be programmed to communicate with an XBee connected to the hazard detection ground station through XCTU The GPS within the CubeSat and the Drogue Bay will be the EM 406 A Sirf III The Arduino Mega microcontroller will be operating this GPS unit and runs on the L1 1575 42 MHz frequency The data from this device will be transmitted to the ground station through an XBee wireless transceiver This transceiver will be programmed to communicate with an XBee connected to the Tesseract ground station using XCTU The GPS that will be housed within the Booster will be the RoamEO GPS This GPS is a standalone device that will transmit the data that it acquires to a dedicated receiver The data will be sent through radio frequencies The receiver will determine the distance from the GPS to the receiver as well as the direction that the signal is coming from 36 Citrus College Rocket Owls Flight Readiness Review Sensitivity of Recovery System to Onboard Devices The recovery systems
13. 2 120 000 084 or ez 29 Citrus College Rocket Owls Flight Readiness Review The rocket reached apogee at 1717 ft AGL about 12 seconds into flight The two downward spikes seen on the graph can be attributed to two events first the black powder charge that separated the rocket airframe for the deployment of the main parachute at 1200 ft AGL and second the rocket body landing on the ground When compared to the flight profile simulation generated by RockSim which can be found in the flight profile simulation section under mission performance predictions in this report it becomes apparent that the apogee is much lower than intended This is largely due to the fact that the sustainer motor did not ignite throwing off the expected values Second Test Flight On Sunday April 20 2014 the team conducted a second full scale test flight of Project Lambda Based on the results from the first test flight there were two main objectives for this flight to ensure that all parachutes deploy so the rocket is successfully recovered and to ensure the sustainer motor is capable of being airstarted With these two goals in mind the launch day procedures heavily focused on proper packing of the parachute Each parachute was folded carefully and after being placed inside the rocket the fit of each parachute was manually tested to ensure a reasonably small amount of force could easily pull out the parachute The parachute was then repa
14. All the jigs were built with laser cut pieces and carefully assembled 15 Citrus College Rocket Owls Flight Readiness Review a Fin Marking Jig Figure 13 Fin Marking Jig The Fin Marking Jig shown in Figure 13 was used to mark the body tube for the fin slots precisely 120 degrees apart This simple jig consists of a laser cut birch plywood piece with a 6 inch diameter circle cut out of it and marked every 60 degrees with laser precision 1 40 of a millimeter The body tube is placed inside the circular cutout and a line is simply drawn up the side to mark the position of the fin slots b Tube Slotting Jig The Tube Slotting Jig shown in Figure 14 was used to create the slots for the fins on both the booster section and the main bay The body tube was held in place inside the jig while the router was inserted through the cutout at the top to make a precise slot for the fins Figure 14 Tube Slotting Jig 16 Citrus College Rocket Owls Flight Readiness Review c Guillotine Fin Alignment Jig Figure 15 Guillotine Fin Alignment Jig Figure 15 depicts a Guillotine Fin Alignment Jig constructed based on a design provided to the team by Ted Macklin of Apogee Rockets The rocket s airframe rests inside the jig while the fin is inserted through the steel guiderails at an angle precisely 90 degrees from the rocket airframe The fin is then held firmly in place until the epoxy cures thus ensuring maximum p
15. Jig usario sine nio o 16 Figure 15 Guillotine Fin Alignment Jig ooooonocccnocnnoncconncconaconnnonnnconncconoconnnonnccon cono no cnn nnrancconncos 17 Figute 16 Risk Matrix A E a Le ES LE 24 Figure 17 Project Lambda on the Launch Pad cocaina 28 Figure 18 The Rocket Owls and Project Lambda ooonconnconncnnncnocononcncnonncnnncnnanononononononncnnncnncnnnos 28 Figure 19 First Full Scale Flight Altitude Data from Avionics Bay Raven ooooonncnccnocinccconccnnos 29 Figure 20 Second Full Scale Flight Altitude Data from Avionics Bay Rave oooonccniccnccconccnno 31 vi Citrus College Rocket Owls Flight Readiness Review Figure 21 Figure 22 Figure 23 Figure 24 Figure 25 Figure 26 Figure 27 Figure 28 Figure 29 Figure 30 Figure 31 Figure 32 Figure 33 Figure 34 Figure 35 Figure 36 Figure 37 Figure 38 Figure 39 Figure 40 Figure 41 Figure 42 Figure 43 Figure 44 Figure 45 Figure 46 Third Full Scale Flight Altitude Data from Avionics Bay Raven33 eeeeeeeeeeeeeee 33 Mass DISTIN A A A a a a a iiO 33 Seperation of Rocket Sections with Shock Cord Attachment ooooonccnnnconoccciccnonnnconnonns 36 ANA A veeaainn ce 37 Fhght Profile Sim lati n enso an a a a a 39 Actual Flight Data sti dial 40 Cesaroni K1620 Vmax Thrust Curve iii id cies 40 Cesaroni BOSS TI Thrust CUVE SN SAN 41 Project Lambda Coefficient of Drs ii da did 42 CG and CP with Booster Seco iii bas 44 CG and CP without Booste
16. Review Writing Editing and Revisions Slide Development Reports and Presentation Posted on Web Presentation Practice Presentation la le E k le ls lo Critical Design Review Writing Editing and Revisions Slide Development Question and Answer Reports and Presentations Posted on Web Presentation Practice Presentation Flight Readiness Review 64 Writing s Editing and Revisions 66 Slide Development 67 Question and Answer 68 Reports and Presentation Posted on Web 69 Presentation Practice Presentation 71 _ Post Launch Review 72 Writing l Editing and Revisions 74 Report Posted on Web 75 Testing 25 Scale Prototype Test Launch Tesseract Payload Testi Hazard Detection Payload Testi LVIS Payload Testing Full Scale Test Launches Rocket Launch Days Completed Days Remaining Project Section Project Subsection 111 Citrus College Rocket Owls Flight Readiness Review 4 Educational Engagement Plan Within the past four months the Rocket Owls have participated in numerous community outreaches In total the team has reached out to a total of 737 individuals so far 94 of whom have been 6th 8th grade students The Rocket Owls have three main goals for every outreach To spread awareness of the NASA Student Launch competition To build lasting relationships within the community To inspire
17. able to withstand the conditions of a successful flight and will hold the CubeSat electronics safely within it The voltmeter electronics will be housed within the nose cone and will rest on a bulkhead and electronics sled Both the bulkhead and electronics sled were made from birch plywood which also has a high shearing strength The battery as well as the sensors and components of the voltmeter will be connected to the electronics sled and the Arduino will be connected to the bulkhead This bulkhead and electronics sled will be mounted into the nose cone so that no movement of these components is possible These bulkheads also survived the crash of the initial test flight and were deemed fit to hold the components safely throughout a successful flight 66 Citrus College Rocket Owls Flight Readiness Review Figure 35 Tesseract Payload Integration Figure 35 demonstrates the integration of the Tesseract payload into the vehicle The red objects shown in the figure were made to represent the electronics of this payload The integration of the payload starts with the electronics of the Voltmeter being attached to the electronics sled labeled two and the Arduino being attached to the bulkhead labeled one Also the components of the CubeSat will be attached to the shelves within the chassis The bulkhead labeled one and the electronics sled labeled two will then start being mounted into the vehicle Two all threads will slide into each of the oute
18. as laser cutting or welding was done at either closed the schools automotive department or at a local build shop with appropriate tools Build up a professional relationship with local shops for our team and future teams Personnel Health concerns time Loss of momentum in the Strong communication between team members Shortage constraints personal build process increase in and advisors No part of the project is issues job offer workload or remaining understood by only one team member so all members resulting in a parts are still covered in the absence of a team decrease in workmanship member Failure to maintain Insufficient fundraising Lower quality of parts The budget is regularly checked during 4 budget efforts poor overall design requiring expensive components repair costs of failed flight reducing the overall quality of the rocket and its safety factors meetings and managed by the faculty advisor Work hard as a team to follow all mitigations to prevent need for repairs 27 Citrus College Rocket Owls Flight Readiness Review Full Scale Launch Results First Test Flight EP 2 E A A o O eS Figure 17 Project Lambda on the Launch Pad On Sunday April 13 2014 the team conducted a full scale test launch of Project Lambda at Lucerne Valley The primary purpose of the launch was to verify that the rocket meets every single requirement specified in the SOW and also to determine
19. collide during their descent Then the loop made from the knot will be inserted into the quicklink in addition to the parachute itself Finally the third attachment point will be manufactured in a similar fashion as the first however it will not be a Nomex sleeve or square as it has been deemed unnecessary and would require excess room in the rocket body which the team cannot spare Electrical Elements The electrical elements of the recovery system are the same as those of the entire vehicle The details of the electrical elements can be found in the electrical elements segment of the design and construction of the vehicle Redundancy Features The redundancy features of the recovery system include backup black powder deployment charges for both the drogue and main parachutes connected to a redundant altimeter The redundancy features have been selected with the utmost consideration for a safe landing recovery in mind The second altimeter that will be utilized is an RRC2 mini which was used previously in last year s USLI competition The redundant altimeter has been programmed with flight logic and tested statically using a bell jar with a vacuum to alter the pressure and simulate an increase pressure similar to that within the recovery of the landing Throughout the last year s competition and testing this year it proved itself extremely effective at detecting changes in barometric pressure as well as its ability to send a curr
20. filed down at angles on the ends This was to create better conditions for the welding The angles provide more surface for the filler rod to weld to The pieces were welded together to form two identical rectangular walls Next two rods will join the two walls together by drilling two holes at the base and top of each of the walls The holes were cut out so that a screw would sit flush in them The two extra rods had holes cut out on each end These holes were then tapped Finally four screws brought the whole assembly together The walls of the CubeSat were decided to be polycarbonate sheets to reduce the chance of creating a Faraday cage Each wall was locked into place with 1 16 inch screws and thread lock One of these walls was designed to have hinges to allow the team to have easy access to the components Slots were also made along the walls to hold a piece of polycarbonate sheet that mounts the electronics and camera system Polycarbonate sheets were cut to fit on the outside of the CubeSat chassis Small holes were drilled into the polycarbonate walls and the chassis Then self tapping screws were used to connect three of the walls A hinge was used to connect one wall to the chassis for ease of access to the electronics within the CubeSat Voltmeter The Arduino based voltmeter was designed to be used to measure the potential difference across the nose cone capacitor as well as the extra capacitor that the team has implemented The analog in
21. four 1 4 inch bulkheads that were identical The four pieces were glued and clamped together to ensure that none of the pieces would be misaligned Electrical Elements a Avionics Bay The recovery system incorporates the use of redundant altimeters and black powder charges for both main and drogue parachute bays in attempt to negate the risks of deployment failure The scoring altimeter will be comprised of a Raven3 altimeter This microcontroller has the capability of handling up to four events and can be set to trigger deployment at a specified altitude as pressure is increasing adjustable in 32 foot increments or a time delay after initial thrust A Missile Works RRC2 mini will be employed as a redundancy This altimeter also has the capability of triggering deployment at a specific altitude as pressure is increasing adjustable in 100 foot increments or a time delay after a specified altitude The Raven3 is set to fire its drogue charge at apogee and the main charge ate 1200 ft AGL The RRC2 mini is set to deploy its drogue and main parachutes 2 seconds after apogee and 1200 ft AGL respectively Each altimeter is equipped with its own power source and the two are wired independently as shown in Figure 4 below 6 Citrus College Rocket Owls Flight Readiness Review Figure 4 Official Scoring Altimeter Schematics 9V Battery RRC2 Mini B U Altimeter Drogue Redundant E match Raven3 Altimeter Primary 9V
22. from the aft end of the bay This will allow the detachable bulkhead to sit flush with fore end of the bay and allow extra room in the aft end of the bay for the main parachute External interfaces such as arming switches will be located on the 14 inch portion of airframe housing the e bay allowing the payload bay itself to slide easily into the fore and aft sections of the vehicle Moreover Y inch long 2 56 nylon shear pins will be connected to the fore and aft coupling sections of the e bay to prevent any premature separations during the vehicles ascent The 11 1 4 inch internal portion of the payload bay has been divided into a 7 inch forward bay and a 4 inch aft bay by a inch birch plywood bulkhead The official scoring and redundant altimeters along with their corresponding power sources will be located in the aft bay while the Raspberry Pi camera GPS XBee and their power sources will be located in the fore bay Blue tube 2 0 coupler was specifically selected due its compatibility with the Blue tube 2 0 airframe of the vehicle The very small marginal gap of 0 03 inches between the outer diameter of the coupler and the inner diameter of the airframe requires very precise manufacturing and therefore was ordered from the Blue tube manufacturer s themselves to mitigate any risks of payload integration Likewise special consideration has been given to the space inside the bay Although space is limited and the bay will house several electr
23. holes for screws to be placed and the Arduino will be held tight enough to withstand the forces that it will experience during flight 83 Citrus College Rocket Owls Flight Readiness Review The CubeSat is a more complicated system and requires more wiring to operate The SD shield and GPS shield will both be mounted onto the Arduino Uno microcontroller The GPS Receiver EM 406 will be mounted on top of the GPS shield and a 32 GB microSD card will be used to store all data logging The humidity temperature sensor is connected to analog pins 0 and 1 and the altitude pressure sensor is connected to analog pins 4 and 5 Additionally each will be connected to the 3 3 V and ground pins of the Arduino The XBee will be connected to the 3 3 V and ground pins but it will also be connected to the digital pins 5 and 6 The camera will have its own dedicated 3 7 V power source that will be connected to pins 1 and 2 The digital pin of the Arduino will be connected to the switch button pin will be connected to the Arduino so that the Arduino can act as the switch Finally an LED will be connected to pins 7 and 9 on the camera to indicate whether or not the camera is recording The Arduino and the shields will be connected to the uppermost shelf of the CubeSat chassis In a similar way that the voltmeter Arduino was mounted to the bulkhead The Xbee and sensors will be connected to the lower shelf of the CubeSat chassis and the camera will be connected t
24. of the CubeSat and voltmeter The following diagrams will show how they are connected Figure 42 Simplified Version of Voltmeter Vee 47 uF GND Figure 43 Wiring Assembly of Voltmeter Subsystem Arduino Uno microcontroller and microSD shield h ADXL 193 Single Axis Accelerometer 27 wo unpueds a CUE GSSSSE a 47 uF capacitor SSS 86 Citrus College Rocket Owls Flight Readiness Review Figure 44 Wiring Assembly of CubeSat Subsystem a Humidity Tem perature GPS Reciever EM 506 on GPS Shield 5 MicroSD card on aiy oar Sa Altitude Pressure Sensor T E woun weds a wos unpeds a Arduino Mega 2560 AAA ASS The chassis is a 10 x 10 x 20 cm square made of aluminum Polycarbonate sheets will be used to mount the components into the chassis The following diagram shows the assembly of the chassis 87 Citrus College Rocket Owls Flight Readiness Review Figure 46 3D Drawing and Actual CubeSat Chassis Polycarbonate walls Polycarbonate shelf Aluminum frame Precision of Instrumentation and Repeatability of Measurement LVIS The Raven3 contains an accelerometer which is user calibrated and can be up to 5 error due to this calibration After speaking to the manufacturer it has the potential of more error in axial acceleration if the flight is low velocity or off axis This percent error will not affect the data collected a
25. of the rocket include the Raven3 microcontrollers the RoamEO GPS the EM 406 A the Adafruit Ultimate GPS and the XBee transceivers In the nose cone the XBee transceiver has been tested in close proximity of the EM 406 A GPS The XBee transceivers worked properly and the GPS unit still collected data with a fair amount of accuracy During launch the recovery system for the nose cone is expected to work properly since no signal interruption was seen in this test The hazard detection system makes use of the same transceiver and antenna to transmit data This system will employ the Adafruit Ultimate GPS for recovery Based on the test from the CubeSat system the Adafruit Ultimate GPS is predicted to operate without any problems However testing will be performed soon to support this prediction The RoamEO GPS uses transmitters and receivers for locating This device is not in close proximity with any other recovery systems and will not threaten any device related to the recovery of the vehicle Suitable Parachute Size The diameter of each parachute was determined by the equation 8m pa pC qV T where D is the diameter of the parachute g is the acceleration due to gravity p is the air density Cais the coefficient of drag of the parachute shape and v is the terminal velocity This equation can also be rearranged to determine the velocity of the rocket when determining how much kinetic energy the rocket lands with Figure 24 below details th
26. separate from the rest of the rocket including the main avionics bay after main motor burnout it is necessary to incorporate a separate mini avionics bay into the booster section for parachute deployment This mini avionics bay will contain a Raven3 microcontroller that will both control the separation of the booster section from the main bay and deploy the recovery system for the booster section using the multiple programmable pyro channels and the barometric sensor This Raven3 will also be recording the lateral acceleration experienced by the rocket throughout the flight which will allow the team to cross reference the data collected during the burning of the main motor by the primary Raven3 in the avionics bay The mini avionics bay is housed in a 4 5 inch stiffy tube bonded with epoxy to the inside of the 14 inch long coupler made out of blue tube This coupler is adhered with epoxy to the body tube and is accessible via a detachable bulkhead on the side facing the sustainer The Raven3 in the SMART bay above the sustainer has two functions first to ignite the sustainer if the RockeTiltometer deems the angle of attach to be safe Second and most relevant to the LVIS payload the Raven3 will record the lateral vibrations experienced throughout the flight of the rocket during both the main motor stage and the sustainer stage Although this is not the primary data collecting Raven3 the data collected by the Raven3 in the SMART bay will be used
27. the in trajectory Out motor Motor igniter not Insertion of the igniter Prevention of complete The igniters will be marked with a permanent 1 reaching the end without the use of an motor burnout or lack of marker at the length of the motor Igniters will of the motor insertion tube motor ignition influencing also be inserted using an insertion tube to the trajectory of the allow pushing the igniter all the way in rocket without damaging it Exploding of the Missing O ring faulty Loss of motor casing loss Static testing of motors 5 motor during motor failure in motor of rocket ignition handling Motor mount Not enough epoxy to hold Motor launches into the Proper construction and installation of the 4 failure the load bearing centering body of the rocket motor mount The main and sustainer motors rings in place damage to payloads loss have a thrust plate of rocket Motor retention Motor not assembled Motor falls out during Both the ProX and Animal Works motor 4 failure properly retention bolt not launch casings have built in motor retention systems fully screwed into the that allow the motors to be easily bolted into motor mount the vehicle Motor thrust block Motor launches into the Motor fires into the rocket Proper construction and installation of the 4 failure rocket damage to body damage to thrust block components and vehicle body payloads loss of rocket 54 Citrus College Rocket Owl
28. the team will ensure that all components of the recovery system are placed within the rocket carefully so that the parachute will deploy properly Safety and Failure Analysis The safety and failure analysis of the recovery system is included with the main vehicle safety section 38 Citrus College Rocket Owls Flight Readiness Review 3 Mission Performance Predictions Mission Performance Criteria Project Lambda s mission will be deemed successful if and only if it meets the following criteria during launch Separation of stages occurs safely The booster section of the rocket detaches safely from the main rocket body without forcing the rocket off course The booster section parachute deploys when the booster section reaches its own apogee The sustainer motor is airstarted by the Raven3 without swaying the rocket off course The Raven3 records measurable data on the vibrations produced during the burning of the 98mm motor as opposed to the vibrations produced during the burning of the 54mm motor The nose cone conducts enough triboelectric charge to alter electromagnetic waves being emitted from the CubeSat near and at apogee e The ground station is able to identify these alterations The Hazard Detection System relays the images and hazards to a ground station in real time The rocket must be safe and stable before during and after its flight The rocket must reach an altitude of 7000 ft AGL give or take 50 ft e The drogu
29. this project is undoubtedly high In order to enable mission success everything that is completed must be done as best as possible The team values its work and puts all its efforts into doing a proficient job In designing the rocket simulations were carefully examined to ensure that the rocket performed safely and efficiently When building the full scale rocket the team understands that everything must be precisely manufactured for the flight to follow the predictions of the models as well as those of the subscale flight The team is taking every necessary precaution to ensure that the rocket is constructed properly Before construction began the team researched the best possible methods of construction Then those who wanted to make the components practiced using the tools needed The rest of the team determined that the work was up to standard before that person was allowed to proceed to manufacturing The team wants the rocket to function exactly as planned The rocket must reach the intended height the separations must occur at the times that have been decided the recovery systems must deploy properly every phase of construction must be done right in order for the rocket to perform the way it is supposed to The team intends to keep a close eye on the construction and assembly of every piece in order to ensure that everything can be assembled correctly and functions properly Safety and Failure Analysis The following chart is a stan
30. to double check and verify the data from the Raven3 in the avionics bay The Raven3 in the avionics bay is the official scoring altimeter responsible for deploying both the drogue and the main parachutes For the purposes of this payload the lateral vibrations data collected by this Raven3 is also the primary data that will be analyzed post flight Tesseract The triboelectric effect analysis payload has two subsystems that are housed in the nose cone and fore end of the drogue bay The system is easily integrated through an arrangement of all threads bulkheads centering rings nuts wing nuts and washers Beginning with the nose cone a single all thread is centered and fixed into place inside the nose cone with epoxy Two additional all threads measuring at 18 5 inches will be non fixed and used along the side of the vehicle body to secure all the bulkheads and centering rings for the system The nose cone bulkhead has a diameter of 5 8 inches and has three 0 25 inch holes along the diameter to allow the all threads to fit into place One hole is exactly centered and the outer two holes are spaced 2 25 inches apart 65 Citrus College Rocket Owls Flight Readiness Review from the center hole The center hole is where the all thread from the nose cone will fit into place and the two outer holes are what will fit the non fixed all threads The voltmeter subsystem is the first step in the assembly It will be mounted onto a 5 5 inch by 3 5 in
31. where Q is the stored charge and V is the voltage potential difference across the capacitor one can see all that is needed to find the charge stored are the capacitance and the voltage With these two values the total accumulated charge acquired throughout the flight of the rocket can be determined For this reason the team has implemented an Arduino based voltmeter to continuously measure the potential difference across the capacitor and assigning each value with a time stamp The team will know the capacitance of the capacitor used and have measured values of voltage Other measurements that are relevant to the experiment include the altitude readings GPS coordinates and time from the CubeSat subsystem Altitude will be measured through an altitude pressure sensor This data will also be time stamped and will be compared with data from the voltmeter Relevance of Expected Data Hazard Detection The expected data for the Hazard Detection Payload is relevant in real time as it will be completely dependent on the landing zone for each flight The data from test flights will be used to better calibrate the system As each component in the system has its own acceptable error allowance the system as a whole will have slight error in the height of each point on the ground Due to the limited processing power of the system and that data being sent to the ground station in real time there may be slight delay from when the system detects a hazard and
32. will fit together The main bay contains 5 centering rings designed to fit a 54 mm sustainer motor Also 3 delta fins will fit into slots in the body tube There will be a bulkhead that will sit directly above the sustainer motor and a second bulkhead at the very top of the main bay Between these bulkheads will be the Sustainer Motor and Raven3 Trigger SMART bay which contains the electronics to control the ignition of the sustainer as well as the recovery system There will be conduit that will go through the centering rings so that the electronics will have a direct line to the sustainer motor Figure 11 Exploded View of the Main Bay 13 Citrus College Rocket Owls Flight Readiness Review d Booster Section Figure 12 shows different components and how they will be come together to form the booster section of the rocket This section is comprised of two body tubes which are the upper and lower cylindrical pieces There is also a coupler tube which will connect the upper section of the booster to the sustainer and the lower section of the booster There are 4 centering rings that will hold the motor in the body tube There are 3 delta fins that will fit into slots in the lower booster section There are also three bulkheads A recovery system will fit between the middle and lower bulkhead The electronics for this section will fit between the upper and middle bulkheads da R Y Figure 12 Exploded View of the Booster 14
33. with much higher kinetic energy than allowed with a high possibility of extreme damage to the rocket proper packing procedures to mitigate the likelihood of it occurring As long as the procedures for packing the parachute are followed any error in packing should be caught before launch 50 Citrus College Rocket Owls Flight Readiness Review Risk Likelihood 1 5 Severity 1 5 Consequences Mitigations Failure of Electronics non recovery 3 This failure is very broad and relies on many components all working flawlessly As it is so all encompassing the likelihood of it occurring is still high despite mitigations 4 In the event that non recovery electronics fail there is the possibility of the loss of all experimental data If experimental data is lost the rocket holds very little scientific value Each electronic component is tested and each system and subsystem have their own hazard mitigations that help prevent an overall failure Vehicle Testing Failure 3 Vehicle testing is a mandatory element of this project Only a small failure in one systems or subsystems could cause the entire test to fail 3 Damage to the rocket could be small or large in the event of a test launch failure For this reason a middle severity was decided Ranging from failure to meet timeline to extreme damage to the rocket high stress on team members to make up for a fai
34. 2 5 270 35 9 motor GPS coordinates voltmeter continues to ignites collect triboelectric charge in the capacitor and camera continues recording Landing Data from systems stop recording capacitor 0 stored the maximum amount of charge and the voltmeter recorded measurable potential differences and GPS are continued to be sent to the ground station Workmanship The payloads that have been designed for this rocket have evolved as this project has moved on Extensive research has been done in order to come up with payloads that suits the requirements of this project As the project has progressed testing has been performed on these payloads to ensure that they functioned properly However some of the payloads have required changes The team has been working hard to make the payloads work the way they were intended but has also realized that some of the objectives weren t feasible in the span of this project The loss of the parallel boosters and the drop of the signal to noise ratio calculations serve as examples of drastic changes made in order to complete the project Throughout this project the systems that have been designed have gone through extensive testing to ensure that they are not only functional but also accurate A lot of research has also gone into programming the components and many hours of troubleshooting have gone into making the systems of the Tesseract payload operate properly Testing has even gone into the test flights The R
35. 20 Second Full Scale Flight Altitude Data from Avionics Bay Raven3 Scale FLight 4 20 Avionics FlPa 71400 A im I a f j de Baro Ft AGL naa Ep 3 500 Oe ES gt 100 000 00 El7 00974 00 6 7 00257 00 S9 Time sec Again this data differs greatly from the simulations generated by RockSim in large part because the sustainer still did not ignite The dramatic peaks and fluctuation in pressure around 1200 ft AGL are due to the black powder charges that deployed the main and the drogue parachute around the same time Third Test Flight On Sunday April 27th 2014 the team conducted a third full scale test launch of Project Lambda at Lucerne Valley This was the last possible day for the rocket to have a successful launch and thus allow the Rocket Owls to continue in the NASA Student Launch competition The team originally planned to launch on Saturday however the weather conditions on Saturday were too extreme to permit a launch wind speeds were upwards of 50 mph and the weather forecast also predicted rain Thus the team made the decision to launch on Sunday instead The weather on Sunday was mild compared to Saturday but still wind speeds varied with the wind growing 31 Citrus College Rocket Owls Flight Readiness Review stronger throughout the day Nonetheless the team worked around the weather conditions and attempted to launch as early as possible to have the most favo
36. 388 The Rocket Owls can be reached at Website http amiwa com rocketowls Email citrusrocketowls gmail com Address 1000 W Foothill Blvd Glendora CA 91741 2 Launch Vehicle Summary The team s rocket Project Lambda will be 144 inches in length with a 6 inch diameter and a total pad weight of 52 4 lbs The vehicle will have two motors staged in line The first motor the main motor will be a Cesaroni K1620 Vmax The second motor the sustainer will be a Cesaroni L985TT An 85 inch hexagonal shaped ripstop nylon drogue chute will be deployed at apogee to slow the descent to 54 ft s At 1200 ft AGL a 120 inch main parachute will deploy and bring the rocket s descent to 15 ft s The booster section that detaches to allow the sustainer to airstart will contain its own 60 inch hexagonal shaped parachute The rail size for this rocket is 12 ft and the button size is 1 5 inches The Milestone Review Flysheet can be found in the documents section of the team website 3 Payload Summary The team has chosen to incorporate the following payloads in the launch vehicle Table 1 Payload Selections Payload Title SOW Requirement Number Hazard Detection Sale AZ 33 CubeSat System Tesseract 3 2 2 3 Lateral Vibration In Line System LVIS 3 2 1 1 The primary objective of Project Lambda is to study triboelectric charging research and analyze solid propellant rocket motors for in line and parallel staging a
37. 50 00 1562 50 mm 300 00 1339 29 250 00 a O 1116 07 200 00 892 86 N asnay 150 00 669 64 100 00 gt 446 43 50 00 223 21 Action Time Total Impulse 2680 77 N s 602 66 Ib s Action Time 2 709 sec Action Time Average Thrust 989 21 N 222 38 Ib Maximum Thrust 1470 22 N 330 52 Ib TES Classification 4 6 L A 0 00 TS 00 Time Seconds 0 000 0 280 0 560 0 840 1 120 1 400 1 680 1 960 2 240 2 520 2 800 Thoroughness and Validity of Analysis The proper design and construction of the vehicle is essential to the team s success In the designing process the team used different resources including the team mentor to ensure that the proposed design was strong enough structurally to withstand the conditions that the rocket is going to endure During the rockets construction multiple team members inspected each component as it was being manufactured Once manufacturing of a component was completed the piece was test fitted to ensure that the dimensions were correct Small changes were made where necessary The team took note of these changes so that the simulations could be altered if needed During analysis of the recovery systems the weights of the different sections of the rockets were double checked with the predicted weights If the weight of the sections weren t close to the predicted weights RockSim was used to determine the impact velocity of that independent s
38. Avionics Subsystem Static To ensure proper Flight simulation was The Raven3 flight Successful Bay LVIS Raven3 functionality of successful without simulation was completed Ground Raven3 with use anomalies using the manufacturer s Test of a flight flight profile software simulation The flight simulation showed that the Raven3 was properly functioning Avionics Component Functional To ensure Raven3 barometer Tested using a bell jar Successful Bay Raven3 barometric detected change in with an LED in the pyro Barometer Ground pressure sensor pressure pin of the Raven3 and Test functions programmed to send a properly for current if the barometric deployment of pressure within the bell the drogue and main parachutes jar is between 22 Citrus College Rocket Owls Flight Readiness Review Location Componentor Test Type Purpose Results Details Status Subsystem Avionics Component Functional To ensure RRC2 mini Tested using a bell jar Successful Bay RRC2 mini barometric barometer detected with an LED in the pyro Barometer Ground pressure sensor change in pressure pin of the RRC2mini and Test functions programmed to send a properly for current if the barometric deployment of pressure within the bell the drogue and main parachutes jar is between 23 Citrus College Rocket Owls Flight Readiness Review Workmanship The precision that is involved with
39. Battery Switch b Booster Section The booster section is designed to jettison from the main airframe of the rocket after main motor burnout For that reason it will require its own recovery subsystem This includes a Raven3 altimeter which will be located in the booster system to execute all necessary separation commands This Raven3 is set to separate the booster section from the sustainer two seconds after liftoff or 0 47 seconds after main motor burnout It is also programmed to deploy the booster section parachute once pressure starts to increase or as the booster section reaches its relative apogee The fourth channel of the altimeter will be programed will detonate the back parachute e match 2 seconds after the booster section reaches its relative apogee The wiring schematic for the booster section s recovery electronics are shown below in Figure 5 7 Citrus College Rocket Owls Flight Readiness Review Figure 5 Booster Section Altimeter B U Parachute E Match Raven3 Altimeter Primary Parachute E Match 9V Battery Switch c Switches The on board altimeters are each controlled by independent 2 pole rotary power switches which are installed on the exterior of the payload bays These heavy duty switches are equipped with high detent spring loaded cams to ensure that launch forces do not flip them Additionally they are rated for up to 250 V at 6 3A which will accommodate the altimeter s requireme
40. ES A ta A ET ca ada hed Tau Sasi 70 Mission A e a e bad 70 Hazard Dc in td ca io ala tech ack 70 E o a a o de 71 Testers o ol idas 71 Experimental Logic Scientific Approach and Method of Investigation ceeeeseeeeees 71 AA O A A doe Ne Rn ne TE Pes en 71 OSS CVACH A RS tadastn aca Nahe i 72 Test and Measurement Variables and Controls oocononoconcnocinnnanananananccnnncnnananononocccnonannnana 73 A festa a act sad ea was E TE E eM Sd ech eat eh ide 73 TESS CTAC oars hist iat ea 73 Rel vance of Expected Datas suiii sisne sec O einen teed aaie 74 Hazard Detection scsi tas Oe OES 74 EDYAN nO ne A a MES eR A ROSES Saran eR 74 WE SS OFAC dd 74 Experiment Process Procedures A Sauces A a A wea e ieee avaee 75 Hazard Detection sein aes ae eA ws 75 A O Se ckneS 28 Aha tat ee Ape ante 75 MT o AAA hin rauch a ane eased ali Awe edad eee ae 76 3 Payload DET nd nad 78 111 Citrus College Rocket Owls Flight Readiness Review Design and Construction of the Rayioad e ds 78 A Nac ae edie ics nace conc e cu dustes va eens cay anigeeahe a acne mine e aE tees 78 a Hazard Detecta 78 O A A 79 c Tesseract Er a e chee a a Sole A e a N e EA 79 Electrical Elentir at 81 A Hazard Detection enaa aaa a a a E Aaa 81 be VTS ocean dat cts da lios 81 c TESSETACT in E E aa E E E ecg Ad a R E ag EEEE 83 Drawings and Schematics n iinn a 84 di Hazard Detecta 84 b IS o SS iia 85 c VES A A A ii ta bs eterna n a a 86 Preci
41. Education members of Direct community interaction Grades 12 Total number of participants 881 726 115 Citrus College Rocket Owls Flight Readiness Review VID Conclusion Over the past five months of the Student Launch competition the Citrus College Rocket Owls have been working diligently to produce the best overall project possible In order to ensure that Project Lambda has a safe and successful flight on launch day the Rocket Owls have had to adjust several aspects of the project since its original conception however the team regards this as an indication of strength and adaptability rather than weakness Despite limited resources the Rocket Owls have prospered largely due to the hard work of its members and the invaluable community support Three full scale test launches have been conducted with significant results marking another milestone in the project plan The Rocket Owls are extremely proud of their progress so far and the team eagerly anticipates launching Project Lambda on the Salt Flats in May 116 Citrus College Rocket Owls Flight Readiness Review
42. Electronic Contruction CubeSat Housing Construction Tesseract Component integration Hazard Detection System Hazard Detection Electrical Component Construction Hazard Detection Housing Construction LVIS LVIS Electrical Component Construction Motor and Electronic Integration Recovery System Main Parachute Construction Drogue Parachute Construction 8 Booster Section Parachute Parallel Motor Parachute Airframe System Body Tubes and Fin Construction Centering Rings Coupler Tube and Stuffy Tube Construction Nose Cones Construction Integration of All Rocket Components Peer led Rocketry Lab at Citrus College 2 Hands On Workshop with GATE Students at Citrus College 30 Classroom Presentation at Slauson Middle School 31 Classroom Presentation at Ontario Montclair School District Classroom Presentation at Ontario Montclair School District Hands On Workshop f aa hands on Workshop at citrus College 35 Hands On Information Booth at Azusa Majors Fair 36 Hands On Workshop at Temple City Unified School District Hnads On Workshop at Citrus College Physics Students Hands On Information Booth at HTCC UC Irvine Hands On Workshop at Glendora Public Librar 0 41 Reports and Presentations Proposal a Writing Editing and Revisions Submission School Notification Team Teleconference a Web Presence Established as Preliminary Design
43. OEE A TTR 45 5 Safety and Environment Veni bd 49 Safety OFFICEN roires aniier i EE E AER R O EEEE AEE E EEE EREET R 49 Analysis of the Failure Modes Payload Integration and Launch Operations 006 49 Listing of Personnel Hazards and Safety Hazard Data ooooconiccnnccoccnoconononononnnnancnnn conan nonnnonos 58 E acess test cuneacews aaeeaneseeceetekGetes ve cteadeceapencmamereteeeteereteiens 58 E 58 Motor and Black Powder Handling and Storage oocoonccinociconoconnnonnnonncconaccono cono cono conocio cancnnnos 58 AMES Ni 59 A E EE E E E E E E EE spies 59 Environmental Concerns ia 60 Disposal of AS AUC CIE aaa 61 Disposal of Rocket Motor unica 61 Disposal of ACHesiv ee isorine iienaa a E E EEEE EENE EEKE E 61 11 Citrus College Rocket Owls Flight Readiness Review Impact of Environment on A etna ea eased 61 6 Payload Integration A A sous skates ase inca ees 62 Payload Integration nenian taps levis copy E E atelectasis 62 A E A 62 A a eee 65 o OT 65 TV Payload CA Ae 68 l Experiment once o hc 68 Creativity and Oni NA aaa 68 Hazard DIS en har s5 ce sn ssid esas doe tess sed sbaranip E toa ULAR TSS 68 A O EE te ne er er eee eee ne ee 68 TESSA nd DN A A A AR 68 Uniqueness or Significance it A A AI 68 Hazard DA de e e oa AER 68 E e e nT RC 69 Tesseract nenn an a tenet eased otal nas ere aan ea creo at a ea eng a Set es esas 69 A o Nr Is Ae Na 70 Science Payload ODE INES ias 70 Hazard DECO dida 70 A A aN 70 V
44. a The vehicle will have a Raspberry pi Test launches on the full scale In camera system that scans the camera board in conjunction with a vehicle will confirm the progress surface during descent in order to Raspberry pi model B The recovery successfulness of reorienting the detect landing hazards system will reorient the position of the vehicle payload bay so the face of the camera is directed toward the intended landing surface 3 1 2 The data from the hazard Edge detection algorithms will be Elevated ground static and motion Complete detection camera shall be programmed into the Raspberry tests will be performed with analyzed in real time by a custom pi OpenCV will be utilized as a source of stationary objects in its line of designed on board software reference sight to demonstrate accuracy and package that shall determine if precision of edge detection landing hazards are present 3 1 3 The data from the surface hazard A pair of XBee Pro 900 RPSMA willbe Elevated static and motion tests Completed detection camera and software system shall be transmitted in real time to a ground station used to transmit data from the vehicle to a ground station in real time will be performed with communication system focusing on any time delays 92 Citrus College Rocket Owls Flight Readiness Review LVIS Table 19 LVIS Functional Requirements Subsystem Functional Requirements Verification St
45. a ground and a new voltmeter system will measure the potential difference across each end of the capacitor The signal to noise ratio measurements were also scrapped due to the complexity of measuring such signals Research did not show how something like this could be done so the team decided to move in a different direction and change the research question The team is now investigating the relationship between triboelectric charging and altitude Now the altitude sensor data is directly related to the experiment The coating on the outside of the nose cone has been changed from carbon fiber to carbon paint due to the cost of having a carbon fiber nose cone manufactured The nose cone no longer has an aluminum tip because of the lack of availability of resources and 3 Changes Made to Project Plan Several outreaches were added to the project plan schedule including the Chinese Institute of Engineers STEM Seminar and an outreach at the Glendora Public Library 4 CDR Feedback 1 We like that the team has taken the initiative to make the decision to get rid of the parallel boosters It s a good learning experience to actively back off of a technical challenge in order to meet the project requirements The team sincerely appreciates the feedback as this is the type of experience and feedback the members were hoping to gain from participating in this research project 2 What altitude will the rocket be when the booster motor burns out bo
46. achieve the high altitudes required for its rockets LVIS will determine whether the rocket to motor diameter ratio of the motors used has any effect on how much vibrations are produced These findings can significantly impact future methods of staging rockets to place the least amount of stress on avionics Tesseract The triboelectric effect caused by clouds rubbing against the surface of rockets has in the past been a source of delay for NASA launches For example the Ares I X was supposed to be launched on Oct 27 2009 but the launch was suspended due to cloud coverage above the launch site This payload will collect data that can help understand triboelectric effect in greater depth The design utilizes three subsystems to try and accomplish this goal a CubeSat voltmeter and ground station The CubeSat is both designed and will be programmed by the team The voltmeter was suggested as an alternative by the team s electromagnetism professor It is simple yet effective It is designed and programmed by the team and is customized for the purposes of this experiment A program for the ground station will also be developed in order to receive and read signals sent out from the CubeSat subsystem 69 Citrus College Rocket Owls Flight Readiness Review 2 Science Value Science Payload Objectives Hazard Detection The objectives of the Hazard Detection System are as follows i Scan the surface of the landing site during descent ii A
47. ack powder for the drogue parachute ejection The L2 Recovery Tether will contain two 1 8 inch 316 stainless steel quicklinks on each side which will be secured to the forged eyebolts on the detachable bulkhead and the fore bulkhead of the avionics bay The recovery tether is intended for use on rockets weighing up to 60 Ibs with a max deployment load of 500 lbs and a max shock load of 200lbs The recovery tether will 78 Citrus College Rocket Owls Flight Readiness Review contain a compartment in which 0 25g manufacturer recommended black powder charge of black powder will be stored The compartment is then sealed with a pin lock system which secures the quicklinks on either side At the event time when main parachute is deployed the official scoring altimeter will send a charge to the tether system which will fully disengage the detachable bulkhead from the avionics bay and allow the vehicle to reorient itself so the hazard detection camera can scan the landing surface The tether system will have a cord attached to it to prevent the pin lock system from separating from the tether system Additionally the recovery tether will be covered with a Nomex tether sheath which will restrain the pins from hitting the airframe and will also add protection from hot ejection charges escaping and damaging obstructing the camera and or its line of sight Lastly the tether system is ordered from Fruity Chutes a well known and trusted supplier of hig
48. ae le e SE 105 Troubleshooting ri odias 105 Post Flight Inspection niesie teinin els Mesias 105 2 Safety and QUITA UAM NA rt as 106 VI Project Plah O ens a 107 l B dget Plan nonar RERA aE AE E AT E A a aR aian 107 DU PO a a da cxay an aa a a i i 109 A O E A A A E ARE uaa AE A ea ae 111 4 Educational Engagement Plain iii cd dis 112 VTA a e o i 116 List of Tables Table 1 Parto das e da ea ee 1 Table 2 Component TE E O aa 19 Table 3 Safety and Failure Analysis E 25 Table 4 Parachute Sizes Mass of Sections Descent Rates and Kinetic Energies 00 35 Walle Se Stability WAR OTs sce cassditct peta n a a a atest otic sack A aad Gata a ehal asc 43 Table 6 Drift TAS 44 Table 7 Requirements and V chificationtesscis icy ce earthiness eate ieee wantin 45 Table 8 Greatest Vehicle Risks o dla roads 50 Table 9 Vehicle Failure Modes ccc scot nots ete aera uses aa i a ia a aaah Aa 52 Table 10 Propulsion Failure Modes nus da 54 Table 11 Recovery Failure Modos ada 55 Tabled Too LS i aai A O E a en cutest e a aA 59 Table 13 Environmental Impact on the Rocket ccccssscssscccesscseccssecesscceesscseccseecesncesenseneceeaes 61 Table 14 Accuracy oF Meastitemienits meristation 75 Table 15 Hazard Detection Flight Performance Predictions ccceseeceeseeeeeeeeceseceeeeneeeeeeeeees 89 Table 16 LVIS Flight Performance Predicas 89 Table 17 Tesseract Flight Performance Predictions ccscccsscssscc
49. and recovered a high powered rocket built in accordance with the listed design requirements The members of the Citrus Rocket Owls have grown vastly in all aspects of rocketry since the beginning of the NASA Student Launch Project Maturity in design aptitude particularly is trait that has been acquired through a great deal of trial and error Consequently much of the originally intended design has been scaled back to accommodate all safety concerns and the reliability and confidence of flight success has increased enormously With less risk to mitigate the team was able to focus attention on two key factors testing and assembly which ultimately lead to vehicle reliability and confidence in mission success Airframe Blue Tube 2 0 was utilized for the assembly of the airframe of the vehicle This composite material has a high sheer strength and has been an essential component of many successfully flown rockets nationwide Nonetheless it is important to implement a great level of precision during the construction process For the purposes of this research project the correct tools were always employed where the correctness of a tool depends on its accuracy and precision All body tubes and couplers were carefully cut and sanded Other critical pieces such as the fins were laser cut with 1 40 of a millimeter of precision Construction Jigs The team constructed jigs to ensure proper placement and alignment of fin slots and fins
50. arate safeguard the onboard electronics during the housing of each subsystem to analyze their flight and upon landing to allow for use in durability and strength multiple launches Payload must be recoverable The Tesseract payload will make use of a Ground tests have been done that ensure the USGlobalSat EM 406A GPS that will store GPS is within the team s accuracy and the data onto the SD card and assist in the expectancy recovery process Analysis Inspection and or Test Hazard Detection The Hazard Detection was tested in two steps Step one the algorithm was tested In this test a random 800x600 pixel image was uploaded to the raspberry pi This image was then ran through the algorithm generating a similar image were surfaces were displayed as black and edges were clearly defined white lines The raspberry pi and algorithm passed the test of processing an image The second test was to get the raspberry pi to access the RockSoul webcam to take a picture and process it through the algorithm This test did not pass on the first few tries Interfacing between the camera and Pi required multiple changes to the OpenCV code used by the raspberry pi The requirement is met but further tweaking is needed to improve efficiency LVIS The testing for the LVIS payload included ground testing operations prior to flight The first ground test included the use of a 9 volt battery to ensure adequate current is sent outputs to ignite black powder char
51. as poured into the tip nose cone and an all thread was placed inside the epoxy and centered into place with the use of the intended bulkhead for that section A bulkhead was used to center the all thread while the epoxy cured E i Figure 37 Nose Cone with All Thread Assembled 79 Citrus College Rocket Owls Flight Readiness Review Once cured the assembly was constructed using two all threads extending below the nose cone bulkhead These all thread allow the CubeSat subsystem to be centered and fixed into place during flight The set of all thread were marked to be cut right below the end of the assembly where the lower bulkhead is epoxied into place This allowed for the whole assembly of the nose cone and CubeSat to be locked into place by use of wing nuts and thread lock All the bulkheads will have two 1 4 inch holes marked 2 92 inches apart from one another along the diameter of the bulkhead to allow the all threads to with regular nuts wing nuts and washers CubeSat Chassis The CubeSat was designed to be 1 5U with an added compartment for the power sources The frame needed to be simple yet strong For this reason the frame was chosen to be 6061 aluminum adhering to a compact rectangular frame The CubeSat chassis started out as a single aluminum square rod The pieces were measured out and a metal saw was used to cut them to their desired lengths The pieces were grouped together by size and filed evenly Certain pieces were
52. ata is stored b CubeSat i Sensors tested for functionality ii SD card checked to ensure data is stored iii GPS tested for functionality and accuracy iv XBee tested to ensure communication between CubeSat and ground station 4 System Testing COMPLETE a Voltmeter i System is programmed ii Voltmeter tested to ensure that a potential difference on the nose cone capacitor and extra capacitor can be measured b CubeSat i System is programmed ii All components assembled and tested to ensure the system works as a whole 5 Full Scale Test Flight IN PROGRESS a Systems are prepped using launch day procedures b Nose cone and drogue bay are assembled with specific system components inside c Ground station prepped to communicate with CubeSat 6 Launch Day a Systems are prepped using launch day procedures b Nose cone and drogue bay are assembled with all systems inside c Ground station prepped to communicate with CubeSat d Data is recovered post flight for analysis 76 Citrus College Rocket Owls Flight Readiness Review 7 Analysis INPROGRESS a Graph CubeSat data b Convert electric potential data into charge data c Compare the two sets of data and make conclusions 77 Citrus College Rocket Owls Flight Readiness Review 3 Payload Design Design and Construction of the Payload Structural Elements a Hazard Detection The avionics payload bay is designed to have two main functions It will house the official sc
53. atus In Line Motor Reach 1350 ft AGL before main motor burns out Full scale test In progress Stage and detaches from rocket so sustainer can ignite launch Featherweight Record lateral G force produced by motor stages Subscale test Full Completed Raven3 during the flight scale test Successfully recorded lateral Gs for subscale Full scale testing in progress Tesseract In light of the Tesseract payload changing since the CDR the team has had to modify the payload success criteria In order for this system to be considered a success the outer conductive paint must allow for the nose to collect enough triboelectric charge to be stored by the capacitor and the voltmeter can record a measurable potential difference The functional requirements for the system to perform as expected are that the CubeSat and voltmeter must initialize their data logging simultaneously upon ignition Additionally the CubeSat must establish a communication line with the ground station at the beginning of the launch to transmit the GPS coordinates Most importantly the two onboard subsystems must store and save their data during their defined time intervals to allow the team to analyze the collected data post launch The following table expands on the requirements for each subsystem to contribute to the success of the Tesseract payload Table 20 Tesseract Functional Requirements Requirement Compliance Status Detect record and collect data pertaining to the a
54. ausing the vehicle to weather cock and deviate from a perfect vertical flight trajectory Upon sustainer ignition the data from the RockeTiltometer indicated the vehicle s trajectory to be 22 degrees off from vertical which was still in range However because the rocket now had a ballistic flight trajectory the vehicle started losing altitude and pressure at high speeds When the altimeter deployed the parachutes the vehicle was still at relatively high speeds horizontally causing a high force load to be applied to the parachute In turn this caused the recovery harness to shred through the airframe The vehicle s booster section along with all internal components of the vehicle remained intact and in perfect condition The results of this flight demonstrate the successful events and stability of Project Lambda s flight trajectory Without high winds present Project Lambda would have displayed an exceptional and stable flight performance However since that day April 27 2014 was the last day to qualify for the competition the team deemed it necessary to proceed with the flight of Project Lambda even under unfavorable weather conditions Given the opportunity to proceed in the competition the team is ready to repair all damages to the airframe of the second stage and have it ready to launch by competition Figure 21 below shows the barometric altitude data gathered by the Raven3 in the avionics bay 32 Citrus College Rocket Owls
55. aven3 microcontrollers have been tested within the body of the rocket to ensure that they are fully capable of performing the necessary task that they were chosen for The team understands that effort in creating a payload that can help further research in aerospace related topics is just as important as creating a vehicle that can carry these payloads The team has put forth all its efforts into ensuring that the payloads work This includes many hours of research building and testing These efforts have led to payloads that are nearly complete and will add to the scientific understanding of the world of today 90 Citrus College Rocket Owls Flight Readiness Review Test and Verification Program The test and verification of the payloads follow a simple plan use to verify if a component meets a requirement or is needed by a system to meet a requirement a Component to be tested b Features to be tested c Approach d Test e Risks involved with using component f Approval 91 Citrus College Rocket Owls Flight Readiness Review 4 Verification System Level Functional Requirements Hazard Detection In order for Hazard Detection System to be considered a success the design must satisfy the system level functional requirements detailed in Table 18 below Table 18 Hazard Detection Functional Requirements Payload Requirement Design Feature Verification Status 3 1 1 The payload shall incorporate
56. bulkhead in with and without load Detach vehicle descent Total kinetic energy hazard only on landing should be unaffected Early Poor programming of Increase in velocity on main Load testing of the quicklinks connecting 8 Separation of altimeter that ignites the black vehicle between drogue and the two bulkheads and static testing of 4 Detachable powder in the tether Failure main deployment Potential the recovery system Bulkhead of quicklinks to hold the zippering of the airframe tether together Nose cone Separation of nose cone Under an acceptable stability The nose cone is constructed from 4 failure during flight nose cone for flight damage to payload fiberglass painted in conductive paint cracks due to previous damage unable to relaunch rocket The nose cone will always be inspected after every launch 53 Citrus College Rocket Owls Flight Readiness Review Table 10 Propulsion Failure Modes Risk Causes Consequence Mitigation Risk Level Total Motor Faulty motors failure of Failure to launch Redundant igniters proper motor assembly 1 Ignition Failure igniters failure of ignition unstable flight or change equipment in trajectory Motor Ignition Improper setup of rocket Failure to launch High heat foil tape to hold igniters securely in 1 Failure due to on launch pad igniter not unstable flight or change place Igniter Falling fully inserted into
57. ccumulation of triboelectric charging on the nose cone of the rocket card The voltmeter will be located in the nose cone and is designed to drain the build up of static charge into a capacitor and record the potential difference across the capacitor onto an SD Ground test have been made to confirm the voltmeter can measure an accurate potential difference Scale flight tests are planned before competition to allow time for any last minute adjustments to the measuring Atmospheric measurements with emphasis on altitude must be made and recorded during defined intervals throughout the flight analysis The CubeSat s microcontroller incorporates a loop structure that defines intervals of ten measurements per data set Each set of data will be saved onto an SD card for post flight Sensors used for atmospheric data have been tested individually and as a single system 93 Citrus College Rocket Owls Flight Readiness Review Requirement Compliance Status At the end of the launch the XBee The Arduino is programmed to begin Testing for the XBee Pro 900 have been made must begin to send GPS communication upon launch with the use of at various distances sending out GPS data sets coordinates to the ground station the altitude pressure sensor and 900 MHz This allows XBee Pro wireless modules Payload must be reusable Housing for each subsystem is designed to Ground tests have been done with the sep
58. ced by the rocket during the burning of each motor Then the data gathered will be expressed as the amount of lateral Gs of vibrations produced per Newton of net thrust experienced This ensures that the different amounts of thrust and different weights of the airframe are taken into consideration when computing the data to verify that the difference in vibrations produced is indeed due to a difference in motor size rather than a difference in forces experienced Also to ensure the most accurate data is collected every single Raven3 will be measuring the lateral Gs experienced The primary data collecting Raven3 is the one located in the avionics bay however the data will be cross referenced with the data collected by the Raven3 in the SMART bay The Raven3 in the mini avionics bay will only record the data for the lateral vibrations produced by the main motor but this data will also be taken into account and used for cross reference Tesseract The method used to measure the accumulation of charge is simulating a simple capacitor circuit The exterior of the nose cone will be coated with MG Chemicals 838 Total Ground Carbon Conductive Coating paint that will allow the nose cone to accumulate charge acting as source for the capacitor This source will then be grounded by the other side of the capacitor to draw the static charge Referring to the fundamental equation for capacitance 73 Citrus College Rocket Owls Flight Readiness Review
59. ch electronic sled made from birch plywood The electronic sled has two shelves extending along the 5 5 inch side spaced 1 0 inch from one another This will serve as the point of insertion for the all threads Each shelf will extend 0 75 inches perpendicular to the sled These shelves will have three 0 25 inch holes placed the exact distances as the previously described bulkhead for the nose cone Once the voltmeter and its power source have been secured the electronic sled will slide into the center all thread of the nose cone and the two outer all threads will slide in until the outer all threads extend 1 5 inches above the electronic sled At this point a set of nuts will be placed on both sides of the shelves to secure the sled on top of the nose cone bulkhead Once secured the bulkhead will slide into the nose cone and the center all thread of the nose cone will fit into the center hole of the bulkhead A washer and wing nut will then be placed to the bottom of the bulkhead to the all thread and secure the bulkhead inside the nose cone Next is the placement of the CubeSat subsystem that will be housed in the aft end of the drogue bay just below the nose cone bulkhead Once the subsystem has been declared ready for launch a bulkhead centering ring is placed on top of the CubeSat and will slide into the outer all threads by two 0 25 inch holes spaced 4 5 inches apart along the diameter It will be 6 inches in diameter and have a 4 33 inch x 4 33 inc
60. cked and the shock cord was neatly gathered and folded into S folds with a single piece of masking tape holding the folds together This was done to ensure the parachute s shock cord could not get tangled and prevent the parachute from coming out of the rocket In our first full scale flight the rocket s sustainer motor did not airstart The team hypothesized that this was due to insufficient current from the battery To fix this the team used a 9 volt lithium ion battery that was tested and determined to provide enough current to light the igniter The launch was conducted under ideal conditions with minimal wind or cloud cover Just like the previous launch the main motor ignited the booster section separated and the booster parachute deployed exactly as planned Data from the Raven3 altimeter in the booster section places apogee for the booster section at about 825 ft AGL At this point the sustainer was supposed to ignite but the sustainer never ignited The rocket simply reached apogee at 1363 ft AGL and began descent back to earth Unlike the first launch both parachutes deployed but it appeared that the main parachute and the drogue parachute deployed simultaneously even though the drogue was supposed to deploy at apogee and the main at 1200 ft Nevertheless the entire rocket was safely recovered with no damage done to any of the payloads or electronics onboard Post flight analysis showed that the sustainer s e match had i
61. confirm or refute the hypothesis that the 98mm main motor will produce fewer vibrational disturbances Tesseract Upon further research pertaining to the measurement of static charge it was deemed that the triboelectric effect analysis payload needed a more reliable method of recording charge The previous method yielded inconsistent sets of data Even without the presence of an electric field the system would read values and would also fluctuate When a charged object would be brought near the values that the sensor measured would jump very high and then slowly sink down even if the charged object was not moved Further investigation suggested that measuring a signal to noise ratio would not be possible with the current methods outputting in accurate data The signal to noise ratio research question had to be set aside and new methods of measuring charge were investigated After discussing alternatives with the team s electromagnetism professor and aiming for a different goal it was proposed to try and mimic a circuit using the nose cone as a source for charge Instead of determining how triboelectric charging effects transmitters within the body of a vehicle the team decided to investigate the relationship between altitude and the charge that accumulated on the surface of the rocket This will be accomplished by coating the outside of the nose cone with a conductive paint placing one end of a wire to the nose cone and the other end to a capaci
62. ct Lambda as it ascends into the air at a high velocity the particles in the air will rub against the nose cone and rest of the airframe of the vehicle stripping away electrons from the air and giving the vehicle an overall negative net charge This payload uses a unique method to investigate the triboelectric charge that builds up on high power rockets integrating topics from different disciplines Concepts from the study of waves and electromagnetism will be applied to rocketry unusual in high power rocketry In the process the team will study radio and satellite communications and construct a CubeSat to be included as a payload in the rocket another unique feature Uniqueness or Significance Hazard Detection The edge detection hazard detection system is creative in its own simplicity of design and efficiency Carrying only the Raspberry pi camera transceiver and a GPS it is the simplest and most cost effective of the three payloads Due to much less data being sent to the ground station the process of detecting hazards and the system making the team aware of them will be a much smoother process 68 Citrus College Rocket Owls Flight Readiness Review LVIS When solid propellant rocket fuel is burned vibrations travel up and down the length of the rocket These vibrations create a dangerous environment for electronics onboard the rocket especially when multiple motors are being used in one rocket as NASA often has to do to
63. d to bring the rocket to was higher than the actual altitude that was recorded by the Raven3 The mass of the rocket was higher than the predicted value and adjustments have been made to the simulations to determine if the mass played a role in the difference in simulated and actual altitude It turned out that these adjustments brought the predictions much closer to the actual flight data The next test flight will be used to verify these predictions and more adjustments will be made if necessary Stability Margin Table 5 below shows the center of gravity and pressure of both stages of the launch vehicle Figures 30 and 31 demonstrate these values The blue dot represents the center of gravity and the red dot represents the center of pressure Table 5 Stability Margin Stability Margin Stability Margin Center of Gravity Center of Pressure With Booster 1 68 87 6 in 98 0 in Without Booster 1 14 65 8 in 72 8 in 43 Citrus College Rocket Owls Flight Readiness Review Figure 30 CG and CP with Booster Section Figure 31 CG and CP without Booster Section Kinetic Energy The kinetic energies for each section of the launch vehicle can be found on Table 4 Launch Vehicle Altitude and Drift Calculations Table 6 below shows how far from the launch pad the rocket body will land These val
64. dard risk matrix used to identify and rate risks in this project This risk matrix utilizes a 1 to 5 scale for both the severity and likelihood of each where 1 is trivial or remote and 5 is fatal or certain Risks are ranked by the product of its two scores The risks are also color coded by risk level where green requires little to no mitigations yellow requires some mitigations for the success of the project and red is absolutely critical for the team to be successful This method of ranking is used for all tables with a Risk Level column throughout the FRR Numbers in parentheses under Risk Level is a reevaluated level after significant mitigation is done to a medium or high risk Likelihood 1 2 3 4 5 Remote Unikely Possible Likely Certain 1 Trivial 2 Minor Severity 3 Lost time 5 Fatal Figure 16 Risk Matrix Chart 24 Citrus College Rocket Owls Flight Readiness Review Table 3 Safety and Failure Analysis Risk Causes Consequence Mitigation Strategy Risk Level Vehicle Testing Poor launch day Damage to parts vehicle Rigorous tests at a system and subsystem level 16 Failure procedures poor overall or payloads Falling far All static testing is to be completed before test 9 rocket design failure of behind the timeline because launches A backup rocket body of the same ignition and recovery of the need to rebuild dimensions in the event the airframe is electronics Replacement parts do
65. day procedures The team holds pre and post briefings for each launch to go over and improve procedures The team will continue testing of all components to further calibrate all the systems The team will ensure that the launch site is always left clean with no trash or debris All hazardous materials will be disposed of correctly based on the relevant MSDS reports 106 Citrus College Rocket Owls Flight Readiness Review VI Project Plan 1 Budget Plan Table 34 Overall Budget Budget Expected Expenses General Rocket Materials 899 50 Motor Materials 2763 50 Camera and Hazard Detection Materials 436 Tesseract 637 Travel Budget 2000 Total 6736 Table 35 General Rocket Materials Budget Breakdown General Rocket Materials Quantity Expected Cost Blue Tube 6 inch diameter 3 118 50 Fin Material Baltic birch plywood 6 sheets 80 Fiberglass nose cone 6 inch diameter 1 100 Centering Rings 5 35 Motor Tube 2 31 Payload Bay 1 50 Miscellaneous couplers transitions etc N A 100 Black Powder 1 pound can 30 Fiberglass amp Resin N A 40 Igniters N A 15 Epoxy N A 150 Misc Sensors N A 50 Misc Wireless Equipment N A 100 Total 899 50 Table 36 Motor Materials Budget Breakdown Motor Materials Quantity Expected Cost Parachute material ripstop nylon 36 inches by 60 inches 13 58 50 Shroud line 100 ya
66. ds to be tested to determine the accuracy of both 96 Citrus College Rocket Owls Flight Readiness Review Component Test Rationale Test SD Card Functional Test To ensure that data can be saved from any sensor that needs data recorded For every section of code that was written to operate a sensor part of the coded loop was made to save the data it collects to the onboard SD card Functional testing is performed with the SD card and shield connected to the Arduino so that testing performed for each sensor is being saved on the SD card It is later checked to see if the data was being properly saved CubeSat Subsystem Testing To ensure that the CubeSat s components can successfully operate together as a single unit As functional testing continues the different components that have already been tested will be tested in the CubeSat on the ground This is to ensure that the code written for multiple components functions accordingly Further testing will also be done during the control test Ground Station Functional Test To ensure the custom program collects the incoming serial data and compiles the data The custom program will be ground tested with the XBee Pro transceivers primarily to establish the communication Then during the control experiment and functional testing of sensors the ground station will run the custom program to ensure its functionality Voltmeter Static Test T
67. e The sections were measured out and a Miter saw was used to cut the tubes into the desired sizes The coupler tube was manufactured in the same way Five different body tube sections were cut and two coupler sections were cut Extra body and coupler sections were cut out to make two stiffy tubes This was done by cutting the extra pieces down the length of the tube Then another cut was made down the length of the tube The distance from the first cut to the second cut was calculated so that the stiffy tube would fit perfectly within the coupler or body tube Using epoxy the coupler sections were attached to their respective body tube sections The stiffy tube was also epoxied in but only after the electronics mounts were built and successfully fit to their sections 5 Citrus College Rocket Owls Flight Readiness Review Centering Rings Bulkheads and Fins Figure 2 Laser Cut Centering Rings Bulkheads and Fins me Figure 3 Bulkheads drying All the centering rings bulkheads and fins were drawn out on a Computer Aided Design CAD program The drawings were used by a laser cutter and all of these materials were then cut with a precision of 0 025 mm Due to the restriction of the thickness of the wood used each centering ring and bulkhead was made up of two or four individually cut pieces For example the drogue bulkhead which will experience a significant amount of force during parachute deployment was made up of
68. e actual attachment scheme of the recovery system Each end of the recovery harness will be attached to one inch bulkheads to ensure that each attachment point has a sufficient capability to withstand the forces of the ejection charges Figure 24 Recovery Attachment Scheme 37 Citrus College Rocket Owls Flight Readiness Review Each parachute will be deployed with the primary use of a Raven3 altimeter The Raven3 altimeters will be connected to switches on the body of the rocket and will not be turned on until the rocket is ready for launch Also they will be connected to a black powder charge placed on the attached bulkhead For the booster parachute the Raven3 has been programed to deploy its parachute when the booster section achieves its own apogee pressure increasing and altitude above 512 ft AGL For the drogue parachute the next Raven3 has been programmed to deploy the parachute when the sustainer section reaches apogee pressure increasing and altitude above 2528 AGL However during the test flight since the sustainer motor did not ignite the rocket was unable to reach an altitude of at least 2528 and the drogue parachute was unable to deploy Due to this finding the team has determined to program the Raven3 to deploy the drogue parachute when pressure is increasing and the rocket has reached an altitude of at least 1504 ft Finally the main parachute with the same Raven3 altimeter as the drogue has been programmed to de
69. e electrical systems can be found in the next section Figure 39 Conductive Nose Cone The Voltmeter system will start with the conductive paint on the nose cone that will act as a source for charge One end of the wire will be connected to this painted surface then connecting to a capacitor at the other end The opposite side of the capacitor will be connected to one of the ground pins on the Arduino Uno microcontroller The analog input pins 0 and 1 will be soldered to opposite sides of the capacitor to read the potential difference that is created between the two ends of the capacitor The single axis accelerometer will be soldered onto the SD card shield and be connected to the 3 3 V pin the ground pin and analog input pin 3 of the Arduino The battery source for the Arduino will be connected to an enclosure on the electronics sled The enclosure consists of four birch plywood walls two for the sides one a for the top and one for the base with a polycarbonate sheet that is held on by hinges The four pieces of plywood were sanded and epoxied onto the electronic sled first Then the hinges were placed onto the polycarbonate sheet and one of the side walls The opposite side then secures the door closed with a screw for launch day The top of the enclosure is cut out to allow the cable to run to the Arduino The Arduino will be mounted onto a polycarbonate sheet separated by spacers and then screwed onto the electronic bed The Arduino has four
70. e end of the 4 inch coupling section Please note all electrical components are fully wired and mounted to payload sleds prior to integration assembly Lastly the bay as a whole is inserted into the drogue and main bay of the vehicle where it is fastened with 4 inch 2 56 nylon screws acting as shear pins Figure 34 below displays the components and assembly technique of the payload integration Figure 34 Hazard Detection Payload Assembly 64 Citrus College Rocket Owls Flight Readiness Review LVIS This payload is integrated very simply into the airframe of the vehicle through three bays the mini avionics bay in the booster section the Sustainer Motor and Raven3 Trigger SMART bay located directly above the sustainer and the avionics bay above the main bay Each bay will carry one Featherweight Raven3 altimeter used both to trigger flight events and to collect data on lateral vibrations Once each Raven3 has been programmed it is mounted to a 4 inch x 5 inch x 0 5 inch payload sled constructed out of birch plywood using two small bolts eight washers and two nuts to keep it vertical throughout the flight The Raven3 will be powered using a brand new 9 volt lithium ion battery attached to the payload sled using 4 small zip ties to keep the battery in place throughout the flight Each payload sled is then slid into place inside its respective bay using the all threads that run through each bay Since the booster section must
71. e is also placed across the sustainer before launch to prevent premature ignition In addition a PerfectFlite miniTimer4 is being used as a redundant timer to ignite the sustainer This will be hooked up in parallel with the Raven3 and one lead will go out from that circuit to the RockeTiltometer The PerfectFlite miniTimer4 is programmed to send out a charge at 2 75 seconds 0 25 seconds after the Raven3 is supposed to ignite the sustainer This system ensures that a secondary charge can ignite the sustainer if the Raven3 is unable to do so 2 Changes Made to Payload Criteria Hazard Detection The mechanism of detachment for the detachable bulkhead has changed In lieu of using nylon cords to secure the detachable bulkhead the team has devised a safer and more practical method A heat treated copper toned anodized aluminum recovery tether will be used to attach the detachable bulkhead to the forward bulkhead of the avionics bay The tether will contain a set of quicklinks on either side attached to the detachable bulkhead and forward bulkhead of the avionics bay that are interlocked via a pin system A compartment for black powder will be internally located within the tether system and when the main parachute is deployed a charge will also be sent to the tether system The black powder charge will then pressurize the compartment and separate the pin lock system which in turn will disengage the detachable bulkhead Further details on the s
72. e parachute will deploy at apogee e Upon reaching 1200 ft AGL the main parachute will deploy Each rocket component tethered and untethered will land with a kinetic energy of 75 ft lbs or less Flight Profile Simulations Figure 25 below shows the flight profile simulation as generated by RockSim Figure 25 Flight Profile Simulation 8000 7000 6000 5000 Altitude Feet o s Ss 3000 2000 1000 Apogee Lambda Altitude Feet Time 39 Citrus College Rocket Owls Flight Readiness Review Figure 26 below show the altitude recorded by the Raven3 in the avionics bay which is our official scoring altimeter This altitude is much lower than that determined by RockSim because the sustainer did not ignite during flight Scale Flight 4 13 Avionics FlPa 1800 Ww Altitude Baro Ft AGL A r W D S 120 600 a a a a a a S aa 51 nmac Figure 26 Actual Flight Data Figure 27 below is the thrust curve of the main motor a Cesaroni K1620 Vmax Project Thrust File 04090824 gra fad mau Mon 16 Jun 2008 Page 1 of 1 10 03 AM Figure 27 Cesaroni K1620 Vmax Thrust Curve 40 Citrus College Rocket Owls Flight Readiness Review Figure 28 below shows the thrust curve of the sustainer motor a Cesaroni L985 TT Figure 28 Cesaroni L985TT Thrust Curve Project Thrust File 04090816 gra 400 00 26811989 4 6 L 1788 71 3
73. e two bulkheads will be fixed together resting against the stiffy tube via two 14 inch x 4 inch stainless steel all threads with corresponding nuts and washers on the inside of the bulkheads and wing nuts on the exterior of the bulkheads The aft bulkhead will contain a centrally located 3 8 inch U bolt with a working load limit of 1090 Ibs of force which will be fastened with nuts and RocketPoxy This will act as a mounting point for the main parachute Also this bulkhead will contain two inch PVC caps epoxied with RocketPoxy which will house the black powder for the main parachute ejection The forward bulkhead of the two will have a inch porthole for the scanning camera and a 3 8 inch forged eye bolt mounted to it The forged eyebolt has a rated capacity of 1 300 lbs of force and will be fastened with a washer and corresponding nut which will also be reinforced with epoxy The forged eyebolt will act as a mounting point between the Anodized Aluminum L2 Recovery Tether and the third detachable bulkhead The detachable bulkhead will also contain an identical U bolt fastened in the same manner as the U bolt mounting the drogue parachute Additionally this bulkhead will also contain an identical forged eyebolt oppositely directed of the U bolt which will act as a mounting point between the tether and the stationary bulkhead Lastly the detachable bulkhead will also contain identical PVC caps secured in the same fashion which will house the bl
74. eacuien salts caasinn eat S A A E E inn a A E 17 IRGCOVELY sea la Gls as 18 Test Data and Analysis m ienne ne n E E a semana a saere 18 Airframe Ste G1 A a a a n iaaa 18 Component Testing o 19 i Citrus College Rocket Owls Flight Readiness Review ANOS 24 Safety and Pallares 24 Full Sca l La nch Rel an nn a a aa nti 28 First Test Flight PP ACCCI ope e o PEO O A 28 Mass Reportin erare EEE ATAR E EAEE EEE TEE EEEa 33 2 Recovery A e io E E E EE EEEE EEE TEN aE 34 Robustness of Recovery System ona 34 Structural Ele iii in 34 Electrical Ele id 34 R dundancy PORME DA A ors E REE ER 34 Parachute Sizes and Descent Rates nin bid 35 Drawings and Schematics of the Electrical and Structural Assemblies ooncononinn 35 Rocket Locating Transmitters rinde 36 Sensitivity of Recovery System to Onboard DeviceS oooconoccnnocccoccconncconcconnconnccon cono nocnnnnonnno 37 Suitable Parachute aia 37 Safety and Lats A 38 3 Mission Performance Predictions ssccccisenssnasnesnceesnenssasaasareaGevensweeesaunencarennsncenasannessuncensanbanenases 39 Mission Performance CA 39 Flight Profile OS ee 39 Thoroughness and Validity of Analysis s cissicssssassssccssdesscasrsssnccansassen cous iaectessastansabatedenvisncciasss 41 scale Modeling Relais 43 A o An a AEE ATEEN EESE 43 KNEE ENRETE il is 44 Launch Vehicle Altitude and Drift Calculations ooooccnnnccnoccnoccnnncnnnonconnccono cono cono cono nocnnonnnos 44 JNV oe A O A AE Eo E EOE E
75. ection and calculations were performed to determine if the kinetic energy was still within the required limit of 75 ft lbs The drag analysis was done using the graph of the coefficient of drag that RockSim had simulated for the rocket RockSim gave us the coefficient of drag for the overall rocket as well 41 Citrus College Rocket Owls Flight Readiness Review as specific sections of the rocket The drag on the rocket was determined at specific points throughout the rockets flight The coefficient of drag was taken from the overall coefficient of drag that the graph provides The main concern was with the stresses on the rocket The team wanted to ensure that the body could withstand the forces that would be applied on the surface of the rocket All the data from the full scale test flight was analyzed and compared with simulations First the simulations were adjusted to model the mass more accurately Then the velocities and altitudes were compared and the difference in actual and simulated values were determined The error in the simulations was noted and this knowledge was applied to our predictions of how the actual flight would perform The team wants to be sure that the flight characteristics are known as accurately as possible to adjust the payload and vehicle components correctly Drag Assessment The following figure shows the coefficient of drag for the various sections of the rocket as well as the rocket as a whole This co
76. efficient is plotted against the altitude of the rocket Predcted Cd 0 435 Cd Nose Body Base Fins Lugs Lambda Sustainer plus one booster 0 a qy Ty a So 0 1000 2000 3000 4000 5000 6000 7000 8000 Figure 29 Project Lambda Coefficient of Drag Using the graph of the coefficient of drag the force of drag was determined for different points in the booster and sustainer flight The coefficient of drag graph that is shown in red was used to determine drag for the different points This was determined using the drag equation V2 D Ca TA where D is the force of drag Ca is the coefficient of drag p is the air density V is the velocity and A is the reference area With the booster the rocket will travel at a max speed of V ft s and the coefficient of drag ranges from about 0 34 to 0 44 for this stage of the rocket For the second 42 Citrus College Rocket Owls Flight Readiness Review stage of the rocket the booster will fall off and the coefficient of drag will change The velocity will reach a max of V ft s and the coefficient of drag increases to around to 0 7 and decreases as the flight continues This creates a much larger force due to drag since the V max has a much larger thrust than the previous motors The full scale test flight was used as a basis to determine whether the drag would have negative effects on the vehicle and none were found so fat Scale Modeling Results Project Lambda has currently und
77. enough black powder to eject landing is too high for charges static testing of recovery system 4 section drogue tangle in shock cord each section Damage parachute wedges between parachute and to booster body tube wall blocking the parachute from ejecting Parachute Nomex cloth does not cover the Damage to rocket loss Proper protection from ejection charges 6 melt parachute during packing the of ground testing of recovery system parachute 3 parachute is wrapped too narrow and allows flames from black powder charges to wrap around the Nomex cloth parachute rapid descent resulting in higher than maximum kinetic energy packing done by the recovery specialist only and signed off by the safety officer before launch 56 Citrus College Rocket Owls Flight Readiness Review Risk Cause Consequence Mitigation Risk Level Parachute Sharp edges in the parachute bays Damage to rocket loss Safety check the parachute for damage clear 5 tear catch during deployment of parachute bays for any possible defects the parachute rapid parachute could catch proper packing of the descent resulting in parachutes higher than maximum kinetic energy Parachute Parachute packed wrong Parachute packed Follow proper procedure for packing 16 lines tangle improperly lines snag parachute design inner airframe with minimal 8 on airframe protuberances inspect shroud lines and obstruction on re
78. ent to the igniter which was statically tested using an LED in place of an igniter The drogue and main bays each have two PVC caps containing the same amount of black powder one for redundancy with 4 32g and 3 45g 34 Citrus College Rocket Owls Flight Readiness Review respectively The Raven3 altimeter located in the avionics bay has been programmed to send a charge to the first PVC containing black powder for deployment of the drogue at apogee which will be detected using the factory calibrated barometer with an additional condition that the rocket is above 1504 ft This condition was set in the event that the sustainer motor does not light the rocket will still be recovered safely Also the redundant PVC in the drogue bay connected to the RRC2 mini has the same flight logic with the addition of a two second delay The estimated amount of distance at which the rocket may fall within the two seconds is 66ft not including air resistance Thus keeping the height requirement of 1504 ft AGL is more than sufficient as the full scale launch went an altitude of approximately 1700ft AGL Furthermore the atmospheric pressure exposed to the redundant altimeter is the same as that of the primary altimeter ensuring the deployment charges occur as programmed The flight logic programmed for the main parachute also uses the barometric sensors and the height requirement is less than 1216ft AGL In addition the RRC2mini is programmed with the same f
79. eploy the drogue parachute As for the main parachute although the rocket body separated to allow the main parachute to unfurl the shock cord had gotten tangled preventing the parachute from deploying As a result the rocket landed with excessive kinetic energy and thus suffered damage to its airframe However none of the electronics or components inside the rocket were damaged in any way and almost everything except a section of the body tube was salvageable The results of this flight were essential in helping the team recognize areas of the project that need improvement for example packing the parachute properly in launch day procedures However the flight also demonstrated that if the team can improve in this area and use a better battery the rocket is aerodynamically sound and should be able to successfully and safely conduct a multistage flight To verify this fact beyond a doubt the team intends to conduct a second full scale launch on Sunday April 20 2014 This time the team will take precautions to pack the shock cord correctly and to use a battery that provides enough current to ignite the sustainer Figure 19 below shows the barometric altitude data gathered by the Raven3 in the avionics bay which will act as the official scoring altimeter Figure 19 First Full Scale Flight Altitude Data from Avionics Bay Raven3 Scale Flight 4 13 Avionics FlPa 71800 1320 840 N Altitude Baro Ft AGL Sa 7360 a
80. ered components will be handled without wearing an anti static wristband All batteries will be stored where they will not reach below 10 C or higher than 50 C Soldering of various electrical circuits is also hazardous Before the team begins to work on the construction of payloads the safety officer will give a briefing on how to avoid burns while using the soldering irons Only those whose soldering skill is approved by the team leader safety officer and one other member will be allowed to work on the soldering the components to mitigate both hazards to the team member and the electronics Welding Safety The CubeSat was constructed from aluminum square bar welded together into a frame All construction that requires welding is complete Welding would only be required for repairs to the CubeSat during the remainder of this project All welding was done by the Citrus College CAPE Owls team Members of the CAPE Owls have completed the safety test required by the Citrus College Automotive department to weld on campus All welding was done in the Citrus College machine shop and in the presence of both team s safety officers Welding masks and gloves were worn at all times during welding Fire extinguishers are within immediate reach in the event that a fire is caused during welding Environmental Concerns All environmental concerns have been addressed under the vehicle safety section 102 Citrus College Rocket Owls Flight Readiness Revie
81. ergone one test flight and has another test flight planned for Saturday April 19th The first test flight was deemed unsuccessful due to a malfunction in two areas The booster section performed flawlessly and successfully showed that the vehicle was capable of a stable flight The booster ejected at the intended time and the parachute opened properly However a lack of current from the batteries that were used to power the Raven3 caused the igniter for the sustainer to fail to ignite Since the sustainer did not light the rocket reached apogee much too early The drogue parachute was programmed to eject under the conditions that the vehicle had reached apogee and the vehicle was at least 6000 ft AGL Since the second condition was never met the drogue never ejected However the ejection charge for the main did go off Unfortunately due to an error in the packing of the shock cord the parachute never came out of the rocket even though the section separated The shock cord got stuck in the rocket when it tangled behind the parachute Everything above the sustainer came crashing to the ground The sustainer and avionics bay was completely destroyed and the nose cone and drogue bay were fairly damaged Data from the flight has been discussed in the full scale flight section The team has a new rocket ready for flight and has made the necessary adjustments for a successful flight It was found that the predicted altitude that the booster was suppose
82. ery Parachute for human error This rocket slightly once the can receive high damage as specialist has done research on failure occurred during a detachable bulkhead is well Without the recovery proper packing techniques and test launch and released the main body of the rocket the mission is will be the only one to pack the of the rocket will fall not successful and most of parachutes This process will be with no parachute the experimental data will supervised by the safety officer Despite the strength of be lost This will reduce the likelihood construction damage of of human error to cause a crash will still be deployment failure The main significant bay will also be cleared of protuberance within the bay to prevent the parachute and shock cord from being caught The body of the rocket is also constructed from Blue Tube 2 0 and the fins are fiber glassed tip to tip to better withstand some damage The severity value was not reduced however as we saw during a failed test launch the rocket body will still be highly damaged in the event of a crash Parachute 2 Parachute lines can 4 This is rated as such If the lines of the This hazard also relies on Lines Tangle be easily tanged if proper packing technique is not followed for the same reasons as Failure to Eject Main Parachute is rated The damage if this was too occur would be great parachutes tangle the rocket will fall at
83. et Owls Flight Readiness Review containing data There will also be a ground station to receive the signals Together these three systems will help determine the relationship between altitude and triboelectric charge Test and Measurement Variables and Controls The following sections explain the testing process for the lateral vibration and Tesseract payloads Although the Hazard Detection System is also one of Project Lambda s payloads it is not an experimental payload but rather is designed specifically to send landing zone data to the ground station As such there is no testing associated with this payload LVIS This payload tests the effect of motor staging on lateral vibrations which is measured in lateral Gs As such the independent variable being used is the diameter of the motor in use 98mm for the main motor and 54mm for the sustainer while the dependent variable is the amount of lateral Gs produced The amount of lateral Gs produced is also dependent on the type of motor being used which is why both the main and the sustainer are Cesaroni motors However the two motors provide different amounts of thrust which is a confounding variable in the experiment In addition because the booster section will jettison from the rocket after the main motor burns out the two motors will be supporting two different amounts of weight To account for this the team will calculate the net force of the weight and thrust experien
84. et motors generally contain highly flammable substances such as black powder or ammonium perchlorate Therefore they are considered to be hazardous materials or explosives for shipment purposes by the US Department of Transportation DOT The team is aware of and will follow all DOT regulations concerning shipment of hazardous materials These regulations are contained in the Code of Federal Regulations CFR Title 49 Parts 170 179 and specify that it is illegal to send rocket motors by commercial carriers or to carry them onto an airliner NFPA 1127 Section 4 19 contains the storage requirements of motors over 62 5 grams All high power rocket motors motor reloading kits and pyrotechnic modules will be stored by the Citrus Physical Science department ensuring they are all at least 7 6 meters 25 feet from smoking open flames and other sources of heat These will only be transported by the safety officer or team mentor who will follow all state and local laws in the transportation of low explosives 58 Citrus College Rocket Owls Flight Readiness Review California Designation of Cargo Section 27903 a Subject to Section 114765 of the Health and Safety Code any vehicle transporting any explosive blasting agent flammable liquid flammable solid oxidizing material corrosive compressed gas poison radioactive material or other hazardous materials of the type and in quantities that require the display of placards or markings on the veh
85. f rocket or payloads in progress and changes are always checked to requiring more custom There is also a risk of ensure the needed parts are available before parts buying cheaper parts that they are finalized are not ideal for the overall plan of the rocket Shipping Budget constraints can t Delay to vehicle or payload All parts are ordered early to ensure they arrive 4 delays missing afford expedited construction and testing before they are needed Extra body materials parts shipping Failure to meet timeline are ordered to accommodate for missing parts and changes to design Access to required Specialized tool is Delays in the fabrication of General construction was completed at team 1 tools required vehicle parts failure to meet timeline members houses where a safe work area was available More specialized construction such as laser cutting or welding was done at either the schools automotive department or at a local build shop with appropriate tools 26 Citrus College Rocket Owls Flight Readiness Review Risk Causes Consequence Mitigation Strategy Risk Level Access to Faculty at the schools Delay in fabrication failure General construction was completed at team 1 sufficient automotive department to meet timeline members houses where a safe work area was workspace or is not available to open available More specialized construction such machine shop the shop School is
86. ges or the sustainer The system of utilizing three Raven3 microcontrollers was tested in the full scale flight The test flight resulted in two of the three Ravens working flawlessly The booster section separated and deployed its parachute exactly as designed The Raven3 used as the scoring altimeter did ignite the ejection charges for the main parachute however the parachute didn t deploy due to an error in packing Unfortunately the 9 volt battery used in the SMART bay did not supply enough current for the igniter to light This was not a problem with the last Raven3 itself but a combination of the e match and low current battery It did not light the sustainer motor at all resulting in a much lower apogee than planned with the sustainer firing Another test launch should allow for any corrections to allow full a completely successful set of 94 Citrus College Rocket Owls Flight Readiness Review Raven3 altimeters Testing of the LVIS payload also includes testing the barometric sensor of the Raven3 by use of a sealed tube a buzzer and a bicycle pump Tesseract The Tesseract payload utilizes many components to meet its requirements verification Table 21 Tesseract Verification Test Table 21 shows the component and the test used for Component Test Rationale Test Humidity To ensure that this component functions within A section of code was written to run this component on the Temperature Sensor the accuracy of the ma
87. h power rocketry components Figure 36 displays a visual representation of the tether system used Figure 36 L2 Recovery Tether b LVIS The structural design of LVIS involves the three bays of Project Lambda the mini avionics bay in the booster section the SMART bay located above the sustainer and the avionics bay Each of the bays carries a Raven3 microcontroller that will be recording the amount of lateral vibrations experienced by the rocket Each Raven3 is mounted on a 4 inch x 5 inch birch plywood payload sled and a 9V lithium battery is also attached to the payload sled using zip ties The payload sled is then inserted into the all threads that run through the bay to keep the Raven3 oriented vertically throughout the duration of the flight The payload sled is significant for mission success as the Raven3 needs to be upright during flight to gather accurate data on lateral vibrations c Tesseract Mount The mounts for both the voltmeter and CubeSat were designed to fit together inside the nose cone and drogue bay sections The mount is made up of _ bulkheads for the nose cone and CubeSat one all thread inside the nose cone two all threads extending below the bulkhead of the nose cone and centering rings to restrict the CubeSat from displacing itself during flight The construction of the bulkheads can be found in the design and construction section of the vehicle criteria In order to fix the nose cone all thread epoxy w
88. h square etched out in them to allow the CubeSat top side to fit into place A set of washers and nuts will be added to both all threads to secure the bulkhead centering ring from moving during flight A similar centering ring with the same dimensions except having the square from the center cut out will be placed around the CubeSat through the all threads The Tesseract systems are housed in the nose cone and drogue bay The CubeSat components will be housed in a chassis made out of 6061 aluminum with polycarbonate walls The components will rest on polycarbonate sheets that slide into grooves in the aluminum walls The shear strength of the aluminum used for the chassis is about 30000 psi and the polycarbonate has a shear strength of 9200 psi The shearing strengths of the polycarbonate and the aluminum is much higher than the intended load experienced by the housing during launch In the first test flight the housing was put to a test that was never intended The CubeSat chassis was implemented in this flight with mass simulators in place of electronics Due to an error with shock cord packing the parachute that would allow the safe recovery of the payload did not deploy and the section containing the chassis came crashing to the ground However upon investigation of the components within the nose cone and drogue bay it was found that the CubeSat chassis was intact with no damage It can be assured with great confidence that this component will be
89. he charge cannot be detected the payload will fail as a whole Failure of Tesseract payload reduction of scientific value for the project The nose cone is coated in several coats of carbon paint Raven3 does not separate stages 2 The Raven3 has a built in redundancy so it is unlikely to happen 4 If the stages don t separate the sustainer will still light and force off the booster section Significant damage to the booster section due to the motor s thrust Data on lateral vibrations might be flawed The Raven3 s own redundancy The black powder charges are measured to have enough force to break the shear pins and separate the booster from the sustainer The detachable bulkhead not separating correctly 2 The recovery tether used to detach the bulkhead we shipped late and as such the device has had been tested very little 3 If the bulkhead does not detach the hazard detection camera won t be able to see the ground If the bulkhead doesn t detach it will block the view of the camera This will cause the payload to have no valid data The recovery tether used to detach the bulkhead it trusted by the team s mentor to detach consistently Further testing will be done during more full scale flights 100 Citrus College Rocket Owls Flight Readiness Review Risk Likelihood 1 5 Severity 1 5 Consequences Mitigations Circuitr
90. how the actual flight compared to the subscale and the simulations performed prior to the full scale launch Figure 18 The Rocket Owls and Project Lambda Wind speeds were between 5 mph and 10 mph at ground level The rocket was assembled and readied for launch in a little over an hour None of the payloads were placed inside the rocket meaning the only avionics on board were the Raven3 altimeters The first stage of the flight was immensely successful The booster section separated after main motor burnout just as planned and the recovery system deployed when the booster section reached its own apogee at 850 ft AGL The booster section was cane s successfully recovered with no damage whaeoner ie the NETO or the NETET inside 28 Citrus College Rocket Owls Flight Readiness Review Unfortunately the main motor did not ignite as planned following the detachment of the booster section This was not because of any fault in programming the Raven3 but rather due to insufficient current provided by the battery This will be resolved by using a lithium ion battery that will provide more current enough for sustainer ignition This by itself would not have affected the recovery of the rocket body as the drogue parachute was Set to deploy at 2500 ft and the main parachute was set to deploy at 1200 ft if the sustainer did not ignite However since the rocket reached apogee at 1717 ft AGL it never reached the height required to d
91. icle exterior by the United States Department of Transportation regulations 49 C F R Parts 172 173 and 177 shall display the placards and markings in the manner and under conditions prescribed by those regulations of the United States Department of Transportation 62 b This section does not apply to the following 1 Any vehicle transporting not more than 20 pounds of smokeless powder or not more than five pounds of black sporting powder or any combination thereof The Tripoli Rocketry Association and the National Association of Rocketry have adopted the National Fire Protection Association NFPA 1127 as their safety code for all rocket operations A general knowledge of these codes will be required of all team members All members of the team will demonstrate competence and knowledge in handling storing and using high powered motors These include all reloadable motors regardless of power class motors above the F class and those which use metallic casings Adhesive Safety Construction requiring adhesives is currently complete for Project Lambda however minor touch ups may be required after any test launches to repair damages When uses adhesives the team member will always wear gloves and work in a well ventilated area Curing adhesives like epoxy will also require a dust mask to help prevent the inhalation of any fumes Tool Safety The construction is complete so the use of power tools should now be at a minimum In the event
92. ight previously been tested in flight the main scoring during last year s USLI altimeter and an competition Additionally the team additional RRC2 mini has tested the primary altimeter barometric altimeter during the subscale and first full included for redundancy scale launch The second full scale launch shall carry both altimeters 1 2 1 The official scoring altimeter Both the Raven3 and Subscale test Complete Both altimeters have been tested in shall report the official competition flight competition altitude via a series of beeps to be checked after RRC2 mini altimeters report altitude via a series of beeps flight Full scale flight test flight The altitude was communicated via a series of beeps 45 Citrus College Rocket Owls Flight Readiness Review Vehicle Requirement Design Feature Verification Status Details 1 2 2 3 At the launch field to aid in All audible electronics Full scale test Complete During the first full scale test only determination of the vehicle s will contain a switch the Raven3 reported the altitude apogee all audible electronics which will be turned off via a series of beeps During the except for the official altitude after landing second full scale launch the team determining altimeter shall be Additionally both will use both altimeters and switch capable of being turned off altimeters have external the redundant in the off po
93. ily harm all the locks and rotations to properly position the blade so that it cuts at the angle needed Always use the blade guard to prevent being cut on the open blade Protective eyewear instruction on how to safely use the tool read the user s manual Jigsaw Eye or respiratory The jigsaw can shake a lot if the material being cut is not irritation bodily harm clamped down When using the jigsaw the correct blade for the material being cut Protective eyewear instruction on how to safely use the tool read the user s manual Hacksaw Bodily harm Use a steady back and forth motion and clamp down the material that is being cut to prevent slipping Eyewear only cut things that are securely clamped down Belt Eye or respiratory Correct placement of the belt and sand so the belt Sander irritation pushes away Protective eyewear and gloves Power Eye or respiratory Wear protective eyewear instruction on how to safely drill irritation bodily harm use the tool read the user s manual Solder Inhalation may cause Research soldering methods always work with a wet Iron pneumoconiosis tin cloth to wipe solder off the iron work in a well poisoning or lung ventilated area under bright light irritation Laser Irritation or damage to Team members doing laser cutting will take a class at cutter eye the local build shop before doing any cuts for the team Environmental Concerns The team will keep all our work environments a
94. iment will be Ground testing will be conducted to 12 6 waves sent out by the component failure incomplete All other data make sure that the ground station can CubeSat cannot be cannot be analyzed and receive signals while the CubeSat is detected conclusions cannot be made far and moving Circuitry wiring comes Poor soldering strong The CubeSat will not take Wires and circuitry components will 9 6 loose during flight forces during thrust the data that 1t is required to take and the experiment fails due to lack of data need to be soldered together Everything will need to be mounted properly so that movement during flight is prevented or minimized 99 Citrus College Rocket Owls Flight Readiness Review Risk Causes Consequence Mitigation Risk Level Barometer activates data Poor programming poor Timings will be off and data Ground testing will be required to 8 acquisition sequence too early or too late wiring is no longer reliable test the barometer for accuracy Careful soldering by the most experienced members of the team Failure Modes and Effects Analysis Table 25 Failure Modes and Effects Analysis Risk Likelihood 1 5 Severity 1 5 Consequences Mitigations Triboelectric charge on surface of the rocket is not strong enough for voltmeter to sense 3 Difficulties reading the charge on the nose cone accurately 4 If t
95. ket Risk Consequence Mitigation Risk Level Rain Cannot launch Check the predicted weather often 1 before launch day High Motor or black powder Proper storage of motors and black 1 temperature become very hot and might powder keep an eye on the weather ignite to launch ideal conditions Below Freezing Freezing on motor epoxy California is unlikely to experience 1 Temperatures and other parts can become extremely cold temperatures The brittle if cold enough safety officer will check the weather before all launch days Bird Strike The trajectory will be Only launch when the sky is clear of 2 altered birds and planes Humidity Motor can fail if it gets wet Motors will be carefully stored and 2 even if that water is from all electronics will not be left high humidity Damage to plugged into a battery for long electronics periods of time in high humidity 61 Citrus College Rocket Owls Flight Readiness Review 6 Payload Integration Payload Integration Hazard Detection The vehicle s avionics and hazard detection system payload are integrated through a typically designed rocket electronics bay of extended length This setup will be composed of a tube with a slightly smaller diameter than the main airframe of the vehicle which is nested inside and held in place by an attached section of the body tube Upon firing the drogue ejection charge the aft end of the bay will remain in the vehic
96. le s airframe and act as a mounting point between the vehicle and drogue parachute At the event time when the main parachute is deployed the bay will be completely separated from the fore end of the vehicle via a detachable bulkhead and act as a mounting point between the sustainer section of the vehicle and main parachute Accordingly this will allow the bay to reorient itself so the scanning camera has a clear view of the landing surface Due to the fact that this system is integrated with the vehicle s recovery system it is simple compact reliable and does not add additional steps to the assembly procedure The main component of the electronics hazard detection payload bay of the rocket is a 22 inch long section of blue tube 2 0 with the following dimensions 6 inch x 0 077 inch wall which will be housed in a 14 inch portion of body tube extending 4 inches on either side This tube serves as the coupler tube for the vehicle and has reinforced bulkheads fixed on each end of an 11 1 4 inch stiffy tube also constructed of blue tube 2 0 The aft end bulkhead of the avionics bay will secure the recovery harness for the main parachute and the fore end bulkhead will be attached to a recovery tether which also attaches to the detachable bulkhead The detachable bulkhead will secure the recovery harness for the drogue parachute The stiffy tube will be epoxied inside the coupler tube 6 inches from the fore end of the avionics bay and 4 3 4 inches
97. led test The vehicle body has been carefully designed and simulated on RockSim Launch site procedures and checklist help to catch all mistakes before they become hazards Sustainer Motor Fires at Unacceptable Angle of Attack 1 With the RockeTiltometer all current from the altimeter for ignition will be blocked if the rocket has an angle of attack greater than 25 degrees 5 If someone were to be hit by a downward firing rocket it would result in a fatality If the sustainer were to fire at a large angle of attack it could thrust horizontally or it could hit someone If the rocket thrusts horizontally the rocket will land very far and will likely be unrecoverable If the motor fires downwards towards an observing crowd it could result in a fatality The RockeTiltometer works much like a switch If the angle of attack is greater than 25 degrees then the ejection is set to off No current will be allowed to pass through the igniter preventing any unsafe launches If the angle of attack is within an acceptable degree the RockeTiltometer will switch to the on position and current will be allowed to pass through the circuit The various risks to the team and launch vehicle during a launch the consequences of the risk and the mitigation plan for each risk are outlined for the vehicle failure propulsion failure and recovery failure in Tables 9 10 and 11 respectively 51 Citrus Co
98. light logic with the addition of a two second delay Finally though the redundant altimeter has proven itself effective in previous flights ground testing and static testing the team will functionally flight tested as the redundant altimeter on the weekend of April 19 20 Parachute Sizes and Descent Rates The following table summarizes parachute dimensions vehicle masses descent rates and kinetic energies Table 4 Parachute Sizes Mass of Sections Descent Rates and Kinetic Energies Parachute Parachute Vehicle Section Mass of Descent Kinetic Size Section Rate Energy Booster 60 inches Booster Section 6 lbs 22 6 ft s 50 ft lbs Mini Avionics Bay 3 lbs 22 6 ft s 24 ft lbs Drogue 85 inches Drogue amp Main 29 5 lbs 54 ft s Bay Drogue Bay 11 lbs 17 5 ft s 52 6 ft lbs Main 120 inches Avionics Bay 8 lbs 15 ft s 28 ft lbs Main Section 8 5 Ibs 15 ft s 30 ft lbs Drawings and Schematics of the Electrical and Structural Assemblies The rocket will utilize a Raven3 altimeter as the official scoring altimeter as well as an RRC2 mini altimeter for the required redundant altimeter Each altimeter will obtain its own 9 volt lithium battery and be wired independently of one another to guarantee this redundancy Raven3 altimeters will be deploying the main and drogue parachutes The Raven3 will set off an ejection charge which will separate the booster section for the parachute to eject Another
99. llege Rocket Owls Flight Readiness Review Table 9 Vehicle Failure Modes Risk Cause Consequence Mitigation Risk Level Center of Poor overall rocket design Under an acceptable stability Room is left in the nose cone to add 3 gravity is too for flight mass to the nose cone around the far aft CubeSat Center of Poor overall rocket design Under an acceptable stability Proper simulation testing Increase the 3 pressure is too for flight size of the fins to lower the center of far forward pressure Rail button Rocket lifts off at an Rocket lifts off at an Check to see of the rail button fits on the 2 failure unacceptable unsafe angle unacceptable unsafe angle launch rail pre launch sand the button if rocket falls off does not fit or rocket falls off the rail it fits too tight on the rail replace with is too tight on the rail another button if it is too loose in the rail Buttons screwed into rocket through the body tube and a centering ring Fin failure Poor construction damage Unstable flight further damage A jig was laser cut to give precise 6 during previous flights to the rocket placement of the fins to ensure there isa 2 120 separation between each fin fully slotted and given ample time for epoxy to cure Fins are further strengthened with fiberglass running from tip to tip for all fins Fins will be checked over after every flight and any repairs will be made before the Shearing of Forces
100. load was slightly altered until it became what it is today This payload still studies the lateral vibrations produced by the burning of solid propellant rocket motors however now it studies the correlation between motor diameter and the vibrations produced The rocket s inner diameter is a uniform 6 inches throughout however the main motor is 98mm in diameter while the sustainer is 54mm in diameter The team hypothesizes that the larger the difference between the motor diameter and the rocket diameter the greater the vibrational disturbances produced because the greater space between the motor and the rocket s inner diameter means that even with centering rings the motor is not gripped in place as firmly 71 Citrus College Rocket Owls Flight Readiness Review and thus has more room to move Therefore the team expects the 98mm main motor to produce fewer vibrational disturbances than the 54mm sustainer Research was conducted to determine how lateral vibrations could be measured and recorded The Raven3 microcontroller was recommended by the team s mentor as a possible solution The Raven3 is the perfect fit for the rocket because of its multiple capabilities and cost efficiency Not only will the Raven3 separate the booster section from the main and deploy the recovery systems it will also measure the lateral acceleration experienced by the rocket during each phase of the flight The team will analyze the data post flight to
101. loss of rocket appropriate parachute size Parachute Shearing of the nylon cord or shock Loss of parachute loss Strong retention system load testing 4 separation cord of rocket extreme damage to rocket and all payloads 55 Citrus College Rocket Owls Flight Readiness Review Risk Cause Consequence Mitigation Risk Level Failure to Poor programming of altimeter not Rocket decent velocity Tested altimeters calculated amounts in black 4 eject drogue enough black powder to eject is too high main powder charges static testing of the recovery parachute drogue tangle in shock cord parachute deployment system and anti zipper ball on the shock wedges between parachute and causes zipper in cord Shock cord is carefully wrapped in an S body tube wall blocking the airframe pattern and taped with easily sharable tape parachute from ejecting just to prevent tangling and knotting Failure to Poor programming of altimeter not Rocket landing kinetic Tested altimeters calculated black powder 12 eject main enough black powder to eject energy is too high charges static testing of recovery system test 8 parachute drogue tangle in shock cord severe damage to launches wedges between parachute and airframe and payloads body tube wall blocking the parachute from ejecting Failure of Poor programming of altimeter not Kinetic energy on Tested altimeters calculated black powder 8 booster
102. move any potential hindrances parachute shroud lines Rocket fails Too many shear pins used Insufficient black Conduct static ejection tests to verify the 4 to separate insufficient black powder failure powder charges correct amount of black powder of avionics to ignite black powder Damage to Too much black powder unsafe Ejection charges burn Provide only enough black powder to provide 2 the rocket work during launch setup and or damage ejection charge to prevent air frame damage body airframe unable to reuse rocket body 57 Citrus College Rocket Owls Flight Readiness Review Listing of Personnel Hazards and Safety Hazard Data A thorough evaluation of the possible hazards associated with the vehicle has been made with respect to the user as well as the environment The hazards associated with the vehicle involve the storage of flammable substances such as motors and black powder as well as the igniters and adhesives The material safety data sheets pertaining to every aspect of the vehicle have been compiled and thoroughly studied for all completed and planned construction With the construction of the rocket complete many of the safety hazards involved with construction are no longer as much of a concern However minor alterations may be made after further test launches and all tool and material safety should still be considered by the entire team Launch Site Safety Launch site safety is a primary concern no
103. nalyze data in real time and determine if landing hazards are present 111 Transmit data from the hazard detection system to a ground station in real time LVIS The main objectives of the Lateral Vibrations In Line System are i Record the lateral vibrations produced while rocket is being powered by the main motor 11 Record the lateral vibrations produced while rocket is being powered by sustainer iii Analyze data to determine which rocket to motor diameter ratio is safer for avionics Tesseract The main objectives of the triboelectric effect analysis payload are i Design a circuit that is capable of accurately measuring the accumulation of triboelectric charge 11 Effectively integrate the designed circuit into the vehicle as to maximize the amount of triboelectric charging readings 111 Measure and record triboelectric charge data with an associated time iv Measure atmospheric conditions as well as the GPS location throughout the flight v Analyze how the accumulation of charge relates to the altitude and time during the rocket s flight The purpose of this payload is to simply measure data that will help the team understand the triboelectric effect and how altitude plays a role in the acquisition of this charge The subsystems will need to work in conjunction with one another to achieve this goal and will rely heavily on user programming to perform the necessary operations The first objective will allow the team to acqui
104. nc ns 107 Motor Materials Budget Breakdown ecccccccceseceseceesceeeecaeceeeneeeesseecaeeneeeeeeensees 107 Hazard Detection BUE A tits 108 Tesseract Bud oe ta de ec aan aa 108 Travel a a e 108 Fundraising BRO do ia 110 Types of Evaluation Used in Outreach sciccccdiscsuicccsscsncssescsnsdetodeodstesvacovesciaceovcdevetens 112 Outreach and Educational Engagement EvVentS oooooccinocicococoncnonononnncnnnocononnnn cono cc nncns 112 List of Figures Figure J C t Blue ID sc ses epee len aie ecoeta ena dy mais wh a ns badd vate a oat esa 5 Figure 2 Laser Cut Centering Rings Bulkheads and Fins oooooccninccnocococccononcnonoconoconn cono ccon nono nonnnos 6 Figure 5 Bulkheads dry is aiiin a a thal ae naa cacao aah oui cs sina 6 Figure 4 Official Scoring Altimeter Schematics rieron diia asiendo didas 7 Figure S Booster Section Altimeter sas eaaa e T E E sehen 8 Fig te Os Rotary Power SWiteh da oe ee emai esses 8 Figure 7 Micro Connector A eneen e e R test nt 9 Figure Full Diagram of Project Lambda 0 22 sci 5 4sccesseoncesacesavasconds casesedaedeaessdesnnesacshande desde 10 Figure 9 Exploded Viewof Nose Us aah ale os cd 11 Figure 10 Exploded View of Avionics Bay vitrina a 12 Figure 11 Exploded View of the Main Bayis cc s cccssesecaassteseeassssacencodecnadosdusacsatuesnsnistudeesctetnaaies 13 Figure 12 Exploded View of the Boost Ei ai 14 Figure 13 Fin Marking Jig a A cose a a a a a AR 16 Figure 14 Tube Slotting
105. nch area 2 Assign team members to watch specific sections of the rocket 3 Obtain all clear from Range Safety Officer 4 Check air traffic 5 Begin ten count 6 Launch 7 Keep an eye on all independent rocket sections at all times 8 Alert any bystanders who may be in the vicinity of possible landing zones 9 Wait for rocket to land on ground before recovery Troubleshooting Table 31 Checklist for Troubleshooting Step Details Check Safety No 1 If motor does not ignite wait five or more minutes before approaching launch pad 2 Check all connection points between wires that are soldered or fit into place are not loose or faulty 3 Check for solid points of connection for all power sources 5 Make sure there is no excess wire when sliding in electronics to minimize the possibility of wires being caught onto all threads 6 At ground station check to see if GPS units have gotten a lock on the rocket Post Flight Inspection Table 32 Checklist for Post Flight Inspection Step Details Check Safety No 1 Turn of all audible electronics excluding the scoring altimeter 2 Check to airframe and fins for any type of damages or cracks 3 Measure the final potential difference across the capacitor in the voltmeter subsystem with a digital multi meter 4 Check all electronics onboard for any damages 105 Citrus College Rocket Owls Flight Readiness Review 2 Safety and Quality Assurance Table 33 Launch Operations Procedures Risks and Mi
106. nd fly it in test launch 5 altimeter avionics not correctly secured on payload sleds and failure to score before competition Housed in the center of the avionics bay on its own circuit to minimize any effect by other components motors or parachute deployments 25 Citrus College Rocket Owls Flight Readiness Review Risk Causes Consequence Mitigation Strategy Risk Level Battery low failure Use of drained or Recovery electronics Appropriate large capacity batteries are used 4 depleted batteries use cannot deploy parachutes for payloads to provide power longer than of batteries with payloads cannot collect flight and time on launch pad Always use a excessive output data and lose scientific new battery for altimeters Checklist has the value safety officer and one other member check all batteries Hazards During Unsafe procedures Damage to motor resulting Motors and black powder is only handled by 5 Transportation and smoking near explosive in unusable motor failure certified members with the ok of the safety Handling of materials to launch injury and burns officer Both will be transported and stored by Motors or Black the team mentor or safety officer only No Powder smoking within 25 feet of any flammable or explosive materials Availability of Damage to current Delay or stop construction Design of the main rocket has constantly been 3 Parts parts complex design o
107. nd implement a Hazard Detection System for the safe landings of launch vehicles In order to complete these objectives Project Lambda will be designed with a Hazard Detection System for safe landings a CubeSat system for triboelectric studies and will utilize a multi stage flight system for staging and motor analysis 1 Citrus College Rocket Owls Flight Readiness Review II Changes Made Since CDR 1 Changes Made to Vehicle Criteria To ensure all parachutes and electrical components have enough room within the rocket the length of the rocket has been increased from 130 inches to 144 inches As such the pad weight has also changed from 45 5 lbs to 52 4 lbs This has also changed the predicted altitude from 8000 ft AGL to an altitude closer to 7000 ft AGL The separation of the booster section from the main bay no longer uses a black powder charge located between two centering rings of the sustainer motor Instead the team has opted to use a simpler method where the black powder charge is located on the bulkhead at the very end of the coupler that connects the booster section to the main bay However the PVC case that contains the black powder charge is inverted and small holes have been drilled through the side of the PVC pipe so when the charge is ignited the hot gases will travel outwards to over pressurize the compartment instead of traveling up and accidentally igniting the sustainer As a precaution a piece of masking tap
108. nd launch sites free of trash and dispose of all waste safely and responsibly With respect to the environment the team has made efforts to recycle all the materials from the previous rocket owls and will continue to work efficiently without creating excess waste Any materials that are disposed of will be checked to see if they can be thrown away normally or if it needs to be done through special methods or through specific channels 60 Citrus College Rocket Owls Flight Readiness Review Disposal of Batteries Alkaline batteries can be safely disposed of with everyday waste Never dispose of a battery in a fire because they can explode Rechargeable batteries packs will be reused by labs at Citrus or by future Rocket Owls In the event that they need to be disposed of it will be done through a local electronics recycling center Disposal of Rocket Motors All used or misfired rocket motors will be disposed of by soaking them in water until the propellant grains fall apart The materials used in the motors are not harmful to personnel or to the environment and are therefore safe to dispose of normally after being soaked Disposal of Adhesives No adhesives will be disposed of through any drain Disposal methods will be checked on a material by material basis Impact of Environment on the Rocket Below is a table of risks and mitigations for the environment s effect on the rocket Table 13 Environmental Impact on the Roc
109. ndeed lit but had failed to ignite the sustainer This indicates that during the launch of the rocket the e match had fallen away from the igniter pellet which was why the sustainer did not ignite To prevent this the team will conduct a third full scale flight where the sustainer s e match will be taped around a wooden dowel that will guide the e match into the igniter pellet to ensure the e match lights the sustainer 30 Citrus College Rocket Owls Flight Readiness Review As for the simultaneous deployment of the two parachutes at first the main hypothesis was that the pressure from the black powder charge was causing the Raven3 altimeter s barometric pressure sensor to detect a lower altitude than it really was and thus deploying the main parachute a little too early To remedy this the team decided to use gorilla tape to seal up the gaps between the bays so the overpressurization of one compartment could not affect the Raven3 After analyzing the Raven3 altimeter however it became apparent that the simultaneous deployment of the two parachutes was actually due to a programming error the altimeter was mistakenly set to deploy the main parachute after velocity exceeded 4 ft s downward This has been corrected and the Raven3 has been double checked to ensure the correct programming is in use for the third subscale flight Figure 20 below shows the barometric altitude data gathered by the Raven3 in the avionics bay Figure
110. ng the functionality lifetime were critically configuration for 1 hour as timed of any critical on board considered Computer by team members The Raven3 component programming will assist altimeters and the in minimizing redundant RockeTiltometer2 are capable of data remaining on for two hours with a new 9 volt lithium battery 1 6 The launch vehicle shall be The igniter used to ignite Ground Complete Subscale model and full scale capable of being launched bya the main motor will be Subscale rocket successfully launched with standard 12 volt direct current capable of burning with Test Full cold standard 12 volt DC firing firing system The firing a standard 12 volt DC scale Test system system will be provided by the firing system NASA designated Range Services Provider 1 8 The launch vehicle shall usea All motors being used in Researched Complete Motors have been purchased from commercially available solid motor propulsion system using ammonium perchlorate composite propellant APCP which is approved and certified by the National Association of Rocketry NAR Tripoli Rocketry Association TRA and or the Canadian Association of Rocketry CAR test and competition flights are commercially available ammonium perchlorate composite propellant Animal Motor works which is a commercial retailer of APCP rocket motors 47 Citrus College Rocket Owls Flight Readiness Review
111. nics Raven3 barometric planned with an LED in the pyro Bay Barometer Ground pressure sensor pin of the Raven3 and Test functions programmed to send a properly for current if the barometric deployment of pressure within the bell booster jar is between parachute Mini Component Functional To ensure that the Stages separated at Tested using the full scale Successful Avionics Raven3 Timer stages separate at two seconds as flight time gt 2secs Bay Full scale two seconds planned Flight using flight logic 19 Citrus College Rocket Owls Flight Readiness Review Location Component or Test Type Purpose Results Details Status Subsystem Mini Subsystem Functional To ensure flight Parachute deployed at The pressure increasing Successful Avionics LVIS Raven3 logic was designated altitude and the altitude greater Bay Full scale properly using flight logic than 512ft Flight programmed for stage separation and parachute ejection SMART Component Static To determine Live data from the Live data determined by Successful Bay Raven3 proper accelerometer was manufacturer should be accelerometer Ground accelerometer 0 95 axial G s 8 1 2 axial G s to ensure Test calibration to properly calibrated ensure data collected is accurate SMART Subsystem Static To ensure proper Flight simulation was The Raven3 flight Successful Bay LVIS Raven3 functionality of successful without simulation wa
112. not damaged beyond use fit into the budget Testing Delays Inclement weather Falling behind projected Multiple launch sites available to use FAR 6 weather or issues failure to secure FAA timeline or inability to test Lucerne Valley Santa Fe Dam Have contacts 4 at the launch site waiver launch by deadline at each of the nearby launch sites or clubs Plan multiple potential test dates early to avoid bad weather Failure of Poor programming Failure to retrieve data and Multiple tests of all electronics The CubeSat 16 Electronics non usage of drained or reduction to the overall voltmeter hazard detection recovery 12 recovery depleted batteries poor science value of the electronics and scoring altimeter are all on handling of electronics project separate circuits Also in order to work on the causing a short electronics in the rocket a member of the team had to pass several trials demonstrating proper technique and electronics safety to minimize failure due to construction Failure of Poor programming of Failure of main or drogue Use of altimeters with built in redundancy that 5 Electronics avionics poor wiring to parachutes have passed ground tests Launch with avionics recovery battery avionics not that have been flown in test launches and correctly secured on retested to ensure functionality payload sleds Failure of scoring Poor wiring to battery Failure to report altitude Test scoring altimeter a
113. nts Figure 6 Rotary Power Switch 8 Citrus College Rocket Owls Flight Readiness Review d Connectors A 4 conductor Micro Connector F04 200 has been added to each bulkhead and switch wire Not only does this guarantee a great deal of ease with regards to electronic hardware integration but it allows for the altimeters and bulkheads to be detached without the removal of any wiring Furthermore these connectors are equipped with a positive locking mechanism Therefore the fastener cannot work loose from vibrations induced by the rocket flight el Figure 7 Micro Connector e Battery Retention All of the batteries used for the altimeters that control the recovery events of the vehicle will be mounted with Philimore 9 V battery holders These will be screwed into the electronic sleds of each section using 4 40 screws and nuts The battery allows for soldering points on top of the holders so the wires do not become loose They also restrict horizontal movement but the team will add additional cable ties for positive retention The batteries will be oriented in such a way as to have the battery push into place during the thrusting phase 9 Citrus College Rocket Owls Flight Readiness Review Drawings and Schematics The following drawings show the full rocket as well as different components of each section and how they will come together to form the different sections of the rocket Figure 8 Full Diagram of Pr
114. nufacturers Arduino Mega The component will be static tested on the Component Test ground and have its measured values compared to local weather station values to measure the accuracy Altitude Pressure To ensure this component records data within A section of code has been written to record atmospheric Sensor Component the manufacturer s accuracy pressure and output the current altitude This data will be Test cross referenced with known local altitude values Single Axis To ensure that this component functions records A section of code still needs to be written to run this Accelerometer data and is within the manufacturers accuracy component on the Arduino Uno When this has been Component Test completed it will be ground tested to measure the acceleration due to gravity with a series of drop tests The collected data will be analyzed and cross referenced with the manufacturer accuracy 95 Citrus College Rocket Owls Flight Readiness Review Component Test Rationale Test XBee Pro Wireless To ensure that two of these components will The XBee transceivers being used in the CubeSat and at Transceiver communicate with one another during flight the ground station will be ground tested first by writing a Functional and Static Test and do not interfere with the XBee transceivers from the Hazard Detection System Additionally we want to ensure they can communicate at the distances we require
115. o a polycarbonate sheet that stands between the upper and lower shelf The components will be connected to a grid style board that is screwed onto the shelf The camera also has places for screws and these will connect it to the polycarbonate sheet There will be two batteries that will be within the CubeSat The bigger of the two will stand up and fit through a cutout on the lower shelf The battery will then be strapped down with zip ties The smaller battery will simply lie in the lower compartment of the CubeSat chassis and will also be strapped down with zip ties Drawings and Schematics a Hazard Detection Figure 40 Hazard Detection Schematics The Hazard Detection payload includes four electronic components a Raspberry Pi RockSoul USB webcam Adafruit Ultimate GPS Breakout Board and a XBee Pro 900 Powering all of these components is a Kmashi 11200 mAh USB battery The Raspberry Pi is connected to the battery with a USB cable on the battery side and the other end of the wire soldered onto the lead for the mini B power port The Adafruit GPS is connected using UART to the Raspberry Pi This requires a cross connection between the TX and RX pins on both board Power from the battery is supplied to the GPS through the VIN pin from the 5V pin The RockSoul camera is a common 84 Citrus College Rocket Owls Flight Readiness Review USB webcam connected to the Pi s USB port The port itself is not used instead the wire between the
116. o ensure that this subsystem can detect any electrical potential difference The transistor still needs to be purchased so the circuit can be assembled Once assembly is completed objects with a potential difference across two sections will be will be measured by the voltmeter and the data will be monitored for any charge that it detects Voltmeter Functional Test To ensure that this subsystem can accurately detect a potential difference Different objects with a known potential difference on two spots will be measured by the voltmeter and the data will be carefully analyzed to ensure that the data that is collected is accurate Full Scale Test Launch To ensure the functionality of certain systems within the body of a rocket The Arduino for the CubeSat as well as the GPS and XBee will be launched in the full scale test flight to ensure that the recovery subsystem of the payload works properly 97 Citrus College Rocket Owls Flight Readiness Review 5 Safety and Environment Payload Safety Officer Joshua will act as the safety officer for the Citrus Rocket Owls The safety officer s main responsibilities are outlined in the vehicle safety section With the payloads the safety officer is to oversee the team in the construction of the payload components and also ensure that the electronics are not interfering with each other or running the risk of setting off any black powder charges prematurely
117. ocket Owls To ensure that commands will be executed as planned during flight the software was heavily tested not only through static tests but also in motion as to simulate flight conditions Further information about software testing and reliability can be found in the payload testing portion of the design review 17 Citrus College Rocket Owls Flight Readiness Review Recovery System In compliance with vehicle requirement 2 3 in the Statement of Work all parachute systems in the vehicle were designed and manufactured by the team Precession in assembly of the recovery subsystem was crucial in contributing to flight reliability and confidence The team designed parachutes were carefully sown with nylon thread Rather than being attached to grummets the shock cords were sown into the seams of the parachute such that they converge to the center This design allows the shock cords to have many points of contact with the parachute so that the forces distribute properly A proper technique was established and tested for the folding and packing of all parachutes with their accompanying harnesses In addition all separation charges were tested statically prior to test flights Further detail regarding construction methods and recovery testing can be found in the recovery subsystem section of the design review Test Data and Analysis Airframe Staging During the flight of Project Lambda the booster section will separate from the main bay
118. oject Lambda 10 Citrus College Rocket Owls Flight Readiness Review a Nose Cone and Drogue Bay Figure 9 shows the order that the different components of the nose cone and drogue bay will fit together This section consists of four bulkheads two of which have a square indentation to hold the CubeSat There is also a centering ring with a square cutout and an electronics sled All of these will be held in by three all threads These all threads will go through 0 25 inch holes cut out in specific places in the bulkheads and centering ring Figure 9 Exploded View of Nose Cone 11 Citrus College Rocket Owls Flight Readiness Review b Avionics Bay Figure 10 shows the order that the different components of the avionics bay will fit together The coupler tube is longer than the body tube and will hold the electronics A stiffy tube will be inside and will prevent the electronics from sliding up and down There will be four bulkheads in this section All threads will create a solid connection between two of the bulkheads and the stiffy tube and the top most bulkhead will be detachable It will hold onto another bulkhead through nylon cord The avionics for the rocket will fit between two bulkheads and the hazard detection will fit between two other bulkheads Figure 10 Exploded View of Avionics Bay 12 Citrus College Rocket Owls Flight Readiness Review c Main Bay Figure 11 shows how the different components of the main bay
119. on the rocket on Loss of rocket Blue Tube 2 0 was selected for the body 3 airframe sections damaged in previous tubes and couplers for strength Rocket is flights checked for damage after every flight Premature Poor programming of Failure to reach target altitude Follow checklist to see ifthe shear pins 2 rocket altimeters None or too few failure of recovery system are secure before launch test the timers separation shear pins placed at in test launches calculated black powder separation points charges 52 Citrus College Rocket Owls Flight Readiness Review Risk Cause Consequence Mitigation Risk Level Centering ring Cracks in centering rings Reduced stability damage to Check construction of centering for a 2 failure from previous flights not payloads good fit check for damage to centering enough epoxy on the rings pre and post launch centering rings Bulkhead Not enough epoxy for Damage to payload avionics Proper construction extensive ground 2 failure bulkheads that are epoxied in failure of recovery testing of removable bulkheads not enough length left on the all thread allowing the wing nuts to be pulled off Failure of Not enough black powder to Nose cone and drogue bay Significant testing of appropriate black 6 Detachable separate the tether remain connected to the main powder to separate the tether holding the 3 Bulkhead to body of the vehicle during
120. one in the main pin and the other in 3 The igniter in the main pin is able to deploy the booster section parachute using the 81 Citrus College Rocket Owls Flight Readiness Review flight logic of pressure increasing and altitude above 512ft AGL The igniter in 3 is in charge of the stage separation which is set to ignite 2seconds after liftoff The Raven3 detects liftoff when the axial accelerometer detects 3G s which according to the user s manual translates to 3mph upward velocity Even though the Raven3 is able to detect liftoff the battery will not be switched on until the rocket is ready on the launch pad The Raven3 in the SMART bay is connected to the RockeTiltometer2 using a 22 gage insulated copper wire from 3 output of the Raven3 to the ground pin2 of the RockeTiltometer2 in terminal 2 The flight logic used for the Raven3 is a pure timer of 2 5 seconds after liftoff detection occurs The wiring for the Raven3 with the RockeTiltometer2 can be seen in the electrical diagram below 82 Citrus College Rocket Owls Flight Readiness Review Lithium lon 9V Ignition Arming Switch Indicator Diode Lithium lon 9V Raven3 _ Altimeter Ignition Battery Switch Lithium lon 9V Figure 38 Electrical Diagram of Raven3 and RockeTiltometer Configurations c Tesseract The Tesseract payload has two subsystems that require electrical assembly The schematics for thes
121. onfirms in the user heard manual that the ignition battery switch functions properly SMART Component Static To ensure that the Ground test showed The ignition arming Successful Bay RockeTiltometer ignition arming one switched on the switch was turned on and Ground switch functions ignition arming the beeping changed from Test properly switch functioned two to one beep This properly by the sound confirms that the system of one beep is properly armed as stated in the user manual SMART Component Static To ensure igniter Ground test Tested using a 6 volt light Successful Bay RockeTiltometer will ignite within confirmed that the bulb and simulated launch Ground critical angle igniter would light if conditions Test angle of attack is within the critical angle 21 Citrus College Rocket Owls Flight Readiness Review Location Componentor Test Type Purpose Results Details Status Subsystem SMART Component Static To ensure igniter RockeTiltometer2 did The component was Successful Bay RockeTiltometer will not light if not send current to allowed to dynamically Ground outside of the the light bulb after calibrate in a vertical Test critical angle the component was condition next a manual outside of the critical launch was triggered and angle the RockeTiltometer was put outside of the critical angle and the ignition signal was sent but no light appeared as expected
122. onics for tracking hazard detection and deployment charges all of the components have been carefully organized to fit properly inside the bay In the aft bay where the official scoring and redundant altimeters are housed the altimeters will be mounted to the top portion of the 4 inch payload sled while the 62 Citrus College Rocket Owls Flight Readiness Review lithium ion batteries powering them will be mounted on the underside of the sled Similarly in the fore bay the Raspberry Pi GPS and XBee will be mounted to the top of the sled and the Anker battery pack will be mounted to the underside of the sled The camera will be fixed to the outer portion of the securing bulkhead in order to acquire images to be processed for hazard detection Lastly in the interest of conserving space cables wires connecting payload components have been carefully minimized and secured Figure 32 below shows the payload interface visual Figure 32 Hazard Detection Payload Interface Visual The integrity of the avionics hazard detection payload bay has been tested during the first full scale test flight Although the flight was not considered a full success due to a malfunction in the recovery system the internal payload bays remained intact The vehicle flew stable in its first stage however it crash landed and the 4 inch coupling portions of the payload bay sustained major damage However the internal payload bays did not sustain any damage to its
123. or 4000 Ibs of tensile force The drogue harness will be 20 ft in length the main will be 30 ft in length and the booster will be 10 ft in length Each of these shock cords will be insulated from hot ejection charges by a Nomex sleeve located in front of the parachute followed by a Nomex square to protect the parachutes Additionally each shock cord will be attached to its corresponding parachute by 5 16 inch quicklinks which have a safe working load of 1 760 lbs of force Respectively the shock cords will be attached to 3 8 inch U bolts with a working load limit of 1090 lbs of force These U bolts will be attached to 1 inch bulkheads constructed out of birch Plywood There will be three attachment points on each recovery system and the attachment procedure are detailed as follows First a U bolt will be screwed and secured with epoxy onto a 1 inch bulkhead The recovery harness will then be attached to the described bulkhead using a figure 8 follow through knot and with a normal figure 8 knot below it to ensure the knot does not unravel itself during the rockets recovery Once the knots have been completed the recovery harness will be fitted with a Nomex sleeve to protect the shock cord and a Nomex square will follow to protect the parachute from ejection charges Second another figure 8 follow through knot will be tied 2 3 of the way up from the first attachment point This precaution is made to guarantee that the rocket bodies will not
124. oring and redundant altimeters along with the hazard detection system The bay will be split internally into two compartments by a Y inch Birch plywood bulkhead The forward compartment housing the hazard detection system will extend 7 inches in length and the aft compartment housing the altimeters will extend 4 inches in length The bay itself is constructed of a 14 inch blue tube 2 0 airframe with a 22 inch coupler of the same material The coupler will extend 4 inches past the 14 inch airframe on each side and produce a gap of 0 03 inches between its outer diameter and the inner diameter of the airframe This will provide an easy and secure fit with both the main and the drogue bays Located inside the coupler a stiffy tube will act as a stop for the bulkheads The stiffy tube will be constructed of blue tube 2 0 coupler which will be cut straight down to produce a 5 9 inch diameter leaving a gap 0 023 inches between the coupler and the stiffy tube The stiffy tube will then be epoxied 6 inches below the forward compartment and 4 3 4 inches below the aft compartment G5000 RocketPoxy will be used to secure the stiffy tube which has a tensile strength of 7 600 psi and compression strength of 14 800 psi The bay will contain a total of 3 external bulkheads constructed of 1 inch birch plywood Two of these bulkheads will remain fixed on each end of the stiffy tube which will enclose and protect the electronics aboard both compartments of the bay Thes
125. oster separates at 730 ft Due to a larger heavier rocket the booster now separates at 360 ft therefore the booster motor burns out at about 230 ft 3 How long after main motor burnout will the command be sent to light the second stage igniter The second stage will ignite 2 5 seconds after liftoff which is 0 97 seconds after main motor 3 Citrus College Rocket Owls Flight Readiness Review burnout 4 The RockeTiltometer2 actively records the angle of attack of the rocket What are the constraints within that algorithm According to the user s manual time constraints have been improved from the first RockeTiltometer as the Direction Cosine Matrix used is specific to attitude transformation and therefore are faster and no longer contain null solutions 5 Why wait 1 5 seconds after Ist stage burnout to separate the stages There will now be a 0 97 second delay between main motor burn out and sustainer ignition 6 We recommend separating the stages just after main motor burnout then I to 1 5 seconds after main motor burnout send the command to light the 2nd stage The motors will probably not come up to full pressure immediately so the time table from Ist stage burnout to 2nd stage ignition will be close to the same After taking this advice into account the team has changed the delay between the main motor burnout and sustainer ignition to be 0 97 seconds 7 Are all of the electronics for the sustainer m
126. otal 637 Table 39 Travel Budget Travel Accommodations Quantity Expected Cost Hotel expenses 3 rooms 4 nights 1500 Gas 5 tanks of gas 500 Total 2000 108 Citrus College Rocket Owls Flight Readiness Review 2 Funding Plan The Rocket Owls have raised a total of 7080 of its 11 000 00 goal The team set up a donations page on their web site with options for people to fund a specific part of the project or fund any amount to be applied to the rocket Through various donations both monetary and in the form of supplies the team has funded almost the entire cost of the project so far The team would like to thank the following sponsors for their support and generosity e Rick Maschek e Professor Lucia Riderer e Professor Brian Waddington e Dr Eric Rabitoy Dean of Physical and Natural Sciences e Citrus College Foundation e Citrus College RACE to STEM e Fuller John and Norsleter e Faraj Juma and Elina e Jermaine Wilson e Popla International Inc e Saiful Bouquet Consulting Structural Engineers Inc e Friends Foundation e Glendora Public Library 109 Citrus College Rocket Owls Flight Readiness Review The funding chart below outlines the funding of the project thus far Table 40 Fundraising Breakdown Funding Brief description Date Expected Percentage of Current Percent amount final goal amount received of expected Citrus College Existing grant awa
127. oth bays allows the information which is collected by the Raven3 to remain unaffected by the sleds The Raven3 located in the main avionics bay relies on a similar sled configuration For details on the retention of the main avionics bay please see page 61 Each of the sleds contains a front side which all of the electronics are mounted to using screws washers and nuts and a back side where batteries can be attached In the mini avionics bay and the SMART bay the batteries are attached by drilling eight holes two on each side of the battery and using four zip ties through the holes the team can secure all batteries This mitigates the risk of the electronics failing to turn on from lack of connectivity to a battery and assists in a safe flight An additional safety consideration is the arming of igniters and pyro charges for this reason each Raven3 utilizes a switch which attaches to the rocket body and can be armed outside of the rocket This switch mitigates the risk of an igniter or pyro charge igniting prematurely The RockeTiltometer2 also has uses three switches accessible from the outside of the rocket body The first of which is to turn on the system and set the zero angle The second is an igniter battery switch and lastly is the igniter arming switch The switches uses for the RockeTiltometer2 ensure that the proper zero angle is selected and a safe ignition of the igniter occurs The Raven3 in the booster section has two igniters
128. otor in the sustainer Yes the electronics include a RockeTiltometer2 a Raven3 for the airstart ignition and a backup PerfectFlite miniTimer4 in the event that the Raven3 malfunctions will all be housed in the Sustainer Motor and Raven3 Trigger SMART bay above the sustainer motor 4 Citrus College Rocket Owls Flight Readiness Review HI Vehicle Criteria 1 Design and Construction of Vehicle Design and Construction of Launch Vehicle Project Lambda is specifically designed to research the following topics the lateral vibrations of a rocket during its thrust phase the ramifications of triboelectric charging on communications signals and the effectiveness of utilizing an edge detection system to relay potential landing hazards In order to successfully accomplish Project Lambda s mission key vehicle design features were implemented These features include multiple stages to study lateral vibrations a conductive nose cone working in conjunction with a CubeSat and voltmeter to study triboelectric charging and a detachable bulkhead that allows the vehicle to reorient itself during its descent phase in order to scan and detect potential hazards on the intended landing surface The construction methods used to complete these key design features are further detailed below Body Figure 1 Cut Blue Tube The main sections of the body started as two 48 inch and one 72 inch body tube The coupler section started out as one 48 inch tub
129. ploy the main parachute when pressure is increasing and when the rocket has reached 1216 ft Both the drogue and main parachutes will also have separate ejection charges connected to the RRC2 mini altimeter for redundancy with the same flight logic plus a 2 second delay Each altitude was determined by multiples of 32 due to the Raven3 altimeter s limitations For static testing of the ejection charge the team has determined to use these amounts of black powder 3 80g for the booster parachute 4 32g for the main parachute and 3 45g for the drogue parachute Each component separated as planned however for the main parachute the parachute was not wrapped fully and completely with the Nomex blanket and got singed slightly The main parachute has been repaired following this incident and will be packed into the body tube more efficiently for future flights During the test flight the booster section had a perfect flight therefore the team has decided to keep the same flight logic and amount of black powder Since the sustainer did not light the rocket was unable to reach an altitude of at least 2528 ft After analyzing the test flight data the rocket reached apogee of 1700 ft so the team has come to a consensus and change the flight logic of the altimeter from 2528 ft to 1504 ft The amount of black powder will remain the same for the drogue For the main parachute the flight logic and amount of black powder will also remain the same but
130. puts of the Arduino will be used to measure the potential on each side of the capacitors The capacitors were put in parallel to increase the capacitance and allow more charge to be stored The single axis accelerometer became a part of the circuit due to the need for a self starting data acquisition sequence Hence once motor ignition has begun the single axis accelerometer will record these changes and initialize the data logging sequence CubeSat The CubeSat electronics required no construction however some of the components needed to be assembled All the shields required the soldering of stackable headers The wires that were required for communication between components were also soldered to ensure no loose connections All the components that require to be connected to the Arduino board will be soldered onto the SD card shield to assure the team the connections do not jostle loose during flight The XBee altitude pressure sensor and humidity temperature sensor will be mounted to grid style boards The grid style board and Arduino are each mounted to a piece of polycarbonate 80 Citrus College Rocket Owls Flight Readiness Review that fits in the slots of the CubeSat chassis The camera will be mounted onto the polycarbonate sheet with the components The components were chosen to perform specific tasks to help with the mission However the camera and humidity temperature sensor were not intended to help further the research Elec
131. r Secti0OM oooooccnococonnononoonnconncconocnnnnnnncconcocono conc nonnnconncns 44 Hazard Detection Payload Interface Visual oononinccnnicinccnoncconccconoconnnonnccnnnccononanc conos 63 Hazard Detection Payload Layout cicsscsscccstscccssstacerectsadsienssvndsesaissncscatasutenstedeasnestens 64 Hazard Detection Payload Assemblviaa i 64 Tesseract Payload Imntesraitin cass ceccasneshendedenncsunteeshovetstaciua NahaudeReutcavaceass 67 E2 RGCOV a de o a 79 Nose Cone with All Thread Assembled ooonoocnnoccnococonnconnnonnnconecconoconn nono cconccconocnnos 79 Electrical Diagram of Raven3 and RockeTiltometer Configurations ooooonccocnococonons 83 Cond ctive Nose CI ad 83 Hazard Detection Schematics a od 84 EVIS D Dr E se Sete UA ww au aca ea eevee A a 85 Simplified Version of Voltmeter miii iii ade 86 Wiring Assembly of Voltmeter Subsystem ooooooocococonoonnnonnconecconocona nono conn coc nocnnnnnnnnos 86 Wiring Assembly of CubeSat SUbSyYSteM ooooconoccnococonoconcconnnconncconoconn nono ccon coco nonnnncnnnno 87 Ground Station SUBSy Ma ia bit 87 3D Drawing and Actual CubeSat Chassis 0ooooocococccococononcconcconononnnonnnconno cono cnnn cnn ccnnnoos 88 vii Citrus College Rocket Owls Flight Readiness Review I Summary of Report 1 Team Summary The Citrus Rocket Owls are a team of 8 students from Citrus College a team advisor and a team mentor The team mentor Rick Maschek is Tripoli Level 2 certified TRA 11
132. r holes on bulkhead one and will be locked into place with wing nuts on either side The electronics sled will then slide onto the 3 inch side of the all threads and will be locked into place with regular nuts This assembly will then slide into the nose cone so that the all thread slides through the center hole in both the bulkhead and the electronics sled A wing nut will be screwed onto the center all thread which will prevent the assembly from being pulled down Two wing nuts will be screwed on upside down at the other end of the all threads The bulkhead labeled three will then be slid onto the all thread This bulkhead has a square indentation to hold the CubeSat Next two regular nuts will be screwed onto the all threads and the centering ring labeled four will slide onto the all thread Two more nuts will lock this centering ring into place The CubeSat will then be slid into the centering ring so that it rests on bulkhead three The bulkhead labeled five which will have a square indentation like bulkhead three will slide onto the all threads and wing nuts will lock this into place Finally the whole assembly will slide into the drogue bay and the two all threads will slide into holes in the bulkhead labeled six Two wing nuts will lock the entire assembly together and the nose cone and drogue bay will be attached together 67 Citrus College Rocket Owls Flight Readiness Review IV Payload Criteria 1 Experiment Concept Creativity and O
133. rable conditions possible The primary purpose of the launch was to verify that the rocket meets every single requirement specified in the SOW and also to ensure the team has devised a proper method for ignition of the sustainer motor At the time of launch wind speeds were roughly about 15mph 18mph The rocket was assembled and readied for launch in a little over an hour The Tesseract payload was integrated in the vehicle along with the RockeTiltometer which was set to inhibit the charge of sustainer motor ignition if the vehicle s flight trajectory was 40 degrees off from vertical and official and redundant altimeters Raven3 and RRC2 Mini were also integrated during flight Both flight stages of the vehicle were extremely successful During the first flight stage the booster section separated after main motor burnout just as planned and its parachute deployed successfully During the second flight stage the sustainer motor ignited properly and the drogue parachute deployed successfully at apogee which was at 4996 ft AGL The main parachute also deployed successfully and the vehicle was recovered upon landing Unfortunately upon recovering the vehicle the team found the airframe of the second stage of the vehicle sustained damaged due to ziplining The recovery harness for the drogue and main parachutes ripped through the airframe of the vehicle This occurred because upon takeoff winds pushed against the fin section of the rocket c
134. rded for Existing 3 000 27 3 3 000 100 Foundation completing the 2012 2013 rocket project Local Business Monetary donations as a source of Ongoing 2 000 18 2 1 000 50 Donations solicitation Private Donations Monetary donations as a source of Ongoing 1 000 9 1 500 50 solicitation Physics Supply donations received from Existing 1 800 16 4 1 800 100 Department Citrus College Physics Department Donations STEM Event STEM fundraising outreach Ongoing 1 800 16 4 1 815 100 8 Fundraisers activities STEM Monetary awards Ongoing 0 0 600 Presentation Awards Fundraising Applebee s fundraiser Upcoming 400 3 6 0 0 activity Fundraising Misc activities such as car washes Ongoing 1 000 9 1 0 0 activity bake sales raffles California Space Awarded to Citrus College Rocket Existing 0 0 1 500 Grant Owls Total 11 000 Current amount 10 215 92 funded Expected 110 Citrus College Rocket Owls Flight Readiness Review 3 Timeline November 2013 December 2013 January 2014 February 2014 March 2014 April 2014 Task Name 11 10 11 17 11 24 12 1 12 8 12 15 12 22 12 29 1 5 1 12 1 19 1 26 2 2 2 9 2 16 2 23 3 2 3 9 3 16 3 23 3 30 4 6 4 13 4 20 4 27 J afer OOOO 2 Manufacturing 3 25 Scale Prototype Construction Full Scale Construction Tesseract CubeSat Chassis Contruction Cubesat Electrical Component Construction Electrometer
135. rds _ 30 Shock Cord 69 ft 140 Shock Cord Protector 3 sleeves 60 18 inch Parachute Protector 3 30 Main motor First in line motor Cesaroni K1620 Vmax 4 Reloads 520 Sustainer Second in line motor Cesaroni L985TT 4 Reloads 680 Animal Motor Works Motor Casing 54 2550 1 Casing 150 Cesaroni Motor Casing Pro98 1 grain 1 Casing 380 Raven3 microcontroller 3 465 RockeTiltometer 2 1 250 Total 2763 50 107 Citrus College Rocket Owls Flight Readiness Review Table 37 Hazard Detection Budget Camera and Hazard Detection Materials Quantity Expected Cost Raspberry Pi Model B with Pi camera module 1 78 RockSoul Webcam 1 17 L2 Recovery Tether and Sheath 1 106 Adafruit Ultimate GPS breakout board 1 35 Misc equipment nylon cords antennas 200 Total 436 Table 38 Tesseract Budget Triboelectric Effect Materials Quantity Expected Cost Hack HD Camera 1 160 Humidity Temperature Sensor 1 17 Arduino Mega 2560 1 60 Transceiver XBee Pro 900MHz 2 76 microSD Shield 2 30 Single Axis Accelerometer 1 30 Altitude Pressure Sensor 1 15 11200mAh External Battery Pack 1 28 16 GB Micro SD Card 3 60 EM 406A GPS 1 40 GPS Shield 1 15 900kHz Duck Antenna RP SMA 2 16 9V to Barrel Jack Adapter 1 3 Carbon Paint 1 20 Polycarbonate Sheet 600 sq inch 57 Rectangular Aluminum Bar 48 inches 6 Square Aluminum Bar 60 inches 4 T
136. re and time The voltmeter measures a potential difference across capacitors time and also makes use of a single axis accelerometer The accuracy of the altitude is 30 cm The accuracy of the temperature sensor is 1 C The humidity can be determined to 88 Citrus College Rocket Owls Flight Readiness Review 5 RH The voltmeter can measure with an accuracy 5 mV Both systems can measure time with an accuracy of 1 millisecond The precision of the single axis accelerometer is not relevant because the data from this sensor is not being recorded This sensor is being used to activate the acquisition of data from the voltmeter when an acceleration is detected The only component that needs calibration is the humidity sensor This component must be re hydrated if the conductive polymer within the sensor gets to dry This sensor must be place in an area that is room temperature under ambient conditions The two systems can record as many flights as needed to allow the team maximum data The only limit is the capacity of the SD cards The voltmeter has been tested on capacitors and has yielded precise results trial after trial The sensors from the CubeSat have also shown precision in data acquisition Assuming the programming doesn t change and similar conditions between trials multiple experiments should yield similar results Flight Performance Predictions Hazard Detection Table 15 Hazard Detection Flight Performance Predic
137. re reliable data pertaining to triboelectric charging The second of these will then add soundness to the payload assuring the team of the most optimal point to obtain valuable data The third and fourth objectives are what will allow the team to analyze the effects of triboelectric charging post flight The last of these objectives permit the team to make a supported conclusions of the payload as a system Mission Success Criteria Hazard Detection This payload will be deemed successful if it meets the following criteria e Detachable bulkhead will fully disengage from avionics bay and e bay will reorient itself so scanning camera is directed toward landing surface e Custom designed on board software analyzes acquired data in real time to determine if landing hazards are present 70 Citrus College Rocket Owls Flight Readiness Review e The ground station will be notified in real time if a landing hazard is detected LVIS This payload will be deemed successful if it meets the following criteria e The booster section separates from the sustainer and deploys a recovery system e The sustainer airstarts successfully e The Raven3 microcontroller measures and records the lateral Gs produced throughout the flight Tesseract The success of the following criteria constitute a successful mission to understand the triboelectric effect e Voltmeter is activated by the single axis accelerometer e Voltmeter gathers and stores measurable da
138. recision in fin alignment Hardware All electronic hardware pertaining to the scientific payloads and recovery systems were thoroughly tested before implementation into the full scale rocket This includes but is not limited to the Raven3 altimeters responsible for all black powder separations the RRC2 mini altimeter utilized as a redundancy for main and drogue bay separations and the PerfectFlite miniTimer4 which will be used as a redundancy to airstart the sustainer motor Testing and calibration was performed to ensure that all hardware functioned accurately and precisely according to manufacturer specifications Furthermore all electronic beds were carefully assembled so as to ensure that expensive electronic equipment is not damaged or dislodged during flight Test results particularly from the subscale test show that the accelerometer based altitude readings recorded by the Raven3 altimeter were not accurate However further research indicated that the manufacturer expected a high level of inaccuracy in these values As a result barometric altitude data is utilized in post flight analysis Testing also revealed that the onboard camera that accompanied the Raspberry Pi did not work in collaboration with the custom edge detection algorithm to scan for potential landing hazards Instead a USB webcam was integrated and the hardware problem was alleviated Software All software packages were custom designed by members of the Citrus R
139. rect College Day GATE interaction students Grades 5 9 Azusa 8 Grade STEM Activity 2 27 2014 8 grade 373 373 Direct Memorial C Majors Fair building paper Glendora interaction Park North airplanes students Grades 5 9 Recreation Center Azusa Rocketry Rocketry 3 8 2014 6 8 grade 25 25 Education Emperor C Workshop Workshop Emperor Direct Elementary Elementary interaction students Grades 5 9 Emperor 2 2 Education Elementary Direct educators interaction grades 5 9 Educators Grades 5 9 114 Citrus College Rocket Owls Flight Readiness Review Event Activity Date of Audience No of NASA Type of Location E F Event Participants Outreach Interaction Type Count Chinese STEM 3 15 2014 Community 20 0 Outreach Mount San C Institute of Presentation college Direct Antonio Engineers students interaction College STEM Seminar Grades 12 Honors Transfer STEM 4 5 2014 Community 25 0 Outreach UC Irvine C Council of Presentation college Direct California students interaction Student Grades 12 Research Conference Physics Peer led 4 9 2014 Physics 47 0 Education Citrus C Rocketry Lab rocketry lab students Direct College interaction Grades 12 Outreach Event Presentation 4 12 2014 Middle school 5 5 Education Glendora A STEM Activity students Direct Public building paper interaction Library airplanes Grades 5 9 Interested 20 0
140. riginality Hazard Detection From a soccer mom parallel parking a van full of kids to a space shuttle docking aboard the International Space Station hazard detection systems are used to keep vehicles and people safe In space travel safety technologies such as a hazard detection system can mean life or death for astronauts With that in mind the improvement of hazard detection systems or devices carries with it an endless level of significance Project Lambda s Hazard Detection System will help build on this technology and test this kind of system s ability to work aboard high powered rockets LVIS The LVIS payload maximizes the full potential of in line staging by analyzing and comparing the efficiency of two motors during a single rocket launch While most studies of lateral vibrations have been aimed towards determining how best to dampen the vibrations this payload takes a different perspective on the problem to study the connection between the diameter of the motor and the amount of vibrations produced by the motor per Newton of thrust provided The unique multistage design of the vehicle was created largely because of the requirements of this payload Tesseract The team has chosen to conduct an analysis on the effects of triboelectric charging This is a phenomenon that occurs when two particles rub against one another transferring electrons from one particle to the other creating an overall net charge In regards to Proje
141. s Flight Readiness Review Risk Causes Consequence Mitigation Risk Level Premature burnout Motor manufacturer s Failure to reach target Static testing of motors 2 error ignition causes the altitude motor to burn irregularly not from top to bottom Motor failure Improper motor storage Unstable flight failure to Assembly of motors by certified members 4 missing components in reach target altitude loss only motor assembly of motor casing Sustainer motor High winds launch rail at Failure to meet projected Sustainer ignition is controlled by both the 25 fires at larger angles poor altitude inability to Raven3 altimeter and the RockeTiltometer 5 unacceptable aerodynamic design recover rocket danger to The Raven3 will send the ignition charge but angle of attack personnel on the ground this charge will be inhibited by the RockeTiltometer if the angle of attack is 25 degrees Table 11 Recovery Failure Modes Risk Cause Consequence Mitigation Risk Level Rapid Holes in parachute poor Damage to airframe Redundant altimeters verification testing of 3 Descent manufacturing of parachutes and payloads loss of the recovery system simulation to determine rocket appropriate parachute size Slow Poor parachute design parachute is Rocket drifts out of Redundant altimeters verification testing of 2 Descent too big intended landing zone recovery system simulation to determine
142. s completed Ground Raven3 with use anomalies using the manufacturer s Test of a flight flight profile software simulation The flight simulation showed that the Raven3 was properly functioning SMART Component Static To ensure that the Ground test Jerk test was performed to Successful Bay Raven3 Timer charge is sent to confirmed timer lit simulate a launch and the Ground the pyro pin at the LED at 2 5 Raven3 was set to send Test the designated seconds current to the pyro pin time of connected to an LED at 2 5seconds 2 5 seconds Current approximately 1 9 Amps 20 Citrus College Rocket Owls Flight Readiness Review Location Componentor Test Type Purpose Results Details Status Subsystem SMART Component Static To ensure proper Ground test Circuitry was set up as Successful Bay RockeTiltometer circuitry of confirmed circuitry specified by manufacturer Ground component properly connected as and throughout the Test the series three beeps system s checks the showed no anomalies system had three beeps which confirms that the circuitry was properly connected SMART Component Static To ensure Ground test showed The ignition battery Successful Bay RockeTiltometer ignition battery that once switched switch was turned on and Ground switch functions on the battery was the beeping changed to Test properly functioning properly only two beeps This by the two beeps c
143. s payload is charge time altitude humidity and temperature The data that are critical to the experiment are altitude time and charge Together this data can help understand how triboelectric charging effects aircraft traveling at different altitudes The altitude measurements have an accuracy of 30 cm The Arduino can only read voltages between 0 V and 5 V This electric potential is mapped to values between 0 and 1024 This suggests an accuracy of 5 mV The time increments that the Arduino 74 Citrus College Rocket Owls Flight Readiness Review can record is accurate to 1 millisecond Although the humidity and temperature data sets are not relevant to the experiment the accuracy was found to be 4 RH and 1 C respectively Table 14 Accuracy of Measurements Measurement Accuracy Altitude 30 cm Electric Potential 5mV Time 1 millisecond Humidity 4 RH Temperature A Knowing the accuracy of these components the error in charge calculations is determined to be as great as 5 depending on the potential differences that are recorded The altitude measurements are determined to be below 1 for a great portion of the flight This is within tolerance to make conclusions based on the information we collect Experiment Process Procedures Hazard Detection The experiment process procedures for the successful outcome of the Hazard Detection System are bulleted below Pre Launch Day
144. s the team is only concerned with the lateral vibrations produced by the rocket motors while burning However the manufacturer did state that the lateral acceleration can have up to 5 error from calibration which will be taken into account when analyzing the data In order to mitigate the user calibrated error the team has calibrated all Raven3 altimeters on a level surface using a protractor to ensure the microcontroller is exactly 90 degrees The Raven3 uses a factory calibrated barometric sensor which is extremely accurate when sensing pressure and has a percent error of 0 1 This however increases when converting pressure to temperature as the calculation is based off of the International Standard Atmosphere model This conversion will not directly affect the data collected as the team does not use the temperature in neither the flight logic nor data analysis The Raven3 can hold up to five flights of data which allows the team to repeat the launch and compare results Additionally the Raven3 allows the user to customize and save specific flight logic which then can be uploaded to other Raven3 altimeters or used for future launches The Raven3 specifications directly from the manufacturer s web site are listed in the table below Tesseract The triboelectric effect payload can be split into two systems Each of these systems have their own instruments used for measuring different sets of data The CubeSat measures altitude humidity temperatu
145. sion of Instrumentation and Repeatability of Measurement coonoccnnccnoccnonninnnconncconacnnos 88 e N a a cae ee ea 88 A Sak Sa aN Bh a aN a tat os ans aca Sad aaa 88 Flight Performance Predictions A e O nas tat eins tenet aes 89 Hazard Detecta AA eee ie eae E E ow ages ows 89 A A Fr Ger eR OR les Vr Sern SOE 89 Tesseract enn ah ladles o pee a atl ek Saleh la det nies Coating 90 O vetoes wees eos ae 90 Lest and Verification Progra da 91 A VietINIC AMM sets E Pune RR 92 System Level Functional Requirement cccsccsssssceeccssccesceessccseccssccssacesneseseccseeeesaces 92 Hazard Detecta 92 MS A NRO 93 Analysis Inspection and or Ted A a a a a aa 94 Hazard Detection tess A ea ae cleo ale AA AAA AAA 94 ENTS NE EE E E ANEA E 94 Tessera ia 95 5 Safety and EnvironmentiParioa ad 98 UM CT LC RE E E EEE EE A E lade AE TAA EE EAT 98 Payload Analysis of Failure Modes sis a 98 Failure Modes and Effects AA y Sis ainia ins 100 HA o a A UD 102 Electronie A O 102 Welding Safety sseni nenien A a e ac ahe te ha Cie cess a he ace At taal ee 102 Environmental Concerns didas 102 V Launch Operations Procedures ia it Guan adsl ae aaa ae 103 A cestatounalewatacesbaaectaagyicisaseerieraoareaier tio 103 iv Citrus College Rocket Owls Flight Readiness Review R covery PEC ill Al OND e a de ce Sct Sch 103 Motor Preparation stew e O iS NN Nin naci 103 Igniter ta yeas 104 Sa O A see a a a a eaten A ET 104 ME AUC PROCES o a al ah alas al
146. sition to switches so that one can ensure that the only audible device be turned off after is the Raven3 landing 1 3 The launch vehicle shall be All rocket components Subscale test Complete Subscale was successfully designed to be recoverable and other than those flight launched and recovered without reusable pertaining to black damage to any of its components powder charges are designed to be recoverable and reusable 1 4 The launch vehicle shall be Hatches and detachable Scale test Complete The launch vehicle was prepared capable of being prepared for bulkheads were included flight Full for flight within 2 hours for both flight at the launch site within 2 in project design to scale the subscale and the full scale hours from the time the Federal Aviation Administration flight waiver opens assist in ease of payload and airframe assembly on launch site launches 46 Citrus College Rocket Owls Flight Readiness Review Vehicle Requirement Design Feature Verification Status Details 1 5 The launch vehicle shall be In selecting electrical Subscale test Complete Subscale model was successfully capable of remaining in launch components for rocket flight Full launched and fully functional ready configuration at the pad subsystems storage scale test subsequent to remaining on the for a minimum of 1 hour space and battery flight launch pad in launch ready without losi
147. sscsssecesscssancssscssacesstssneneaes 90 Table 18 Hazard Detection Functional Requirements ooooooccnnocononoconoconnnonnnonnnccono cono nonnnonnnccnnccnnos 92 Table 19 LVIS Functional Ke quirenien diia 93 Table 20 Tesseract Functional Requirements Sd 93 Table 21 Tesseract Verification da A e queers tacos A aees 95 Table 22 Hazard Detection Failure Modest is 98 Table 23 In Line Motor Failure Modest deis 99 Table 24 Tesseract Failute Mods sa Oe al 99 v Citrus College Rocket Owls Flight Readiness Review Table 25 Table 26 Table 27 Table 28 Table 29 Table 30 Table 31 Table 32 Table 33 Table 34 Table 35 Table 36 Table 37 Table 38 Table 39 Table 40 Table 41 Table 42 Failure Modes and Effects Analysis cevircseias alsues tac senwslncdrastiuecd een ue neha 100 Checklist for Recovery Preparation 3s iS sais 103 Checklist for Motor Preparate ey htees Ma Os 103 Checklist for Igniter Instala ira 104 Checklist for Setup on Larco casks ad arcdttonen syle Sandieak case e aeass 104 Checklist for Launch Procedure 2 4 c9anfasaestedstahouva spaentiass ardereaoaavands tatentaathantiassannegatad 105 Checklist for Troubles hootin 2 iia 105 Checklist for Post Flight Inspection AA 105 Launch Operations Procedures Risks and Mitigations ooooonconoconoconoconcncnncnnnconanononnnonos 106 Overall B dget seisten A ab ties 107 General Rocket Materials Budget Break doWN ooooocconoccnococococonocinnnconnoconocnnn cono nc n
148. structural elements nor its electrical components The vehicle was flown with altimeters and their power sources and were recovered undamaged and still functioning In turn the success of the first flight stage and the forceful impact of the bay upon landing demonstrate the structural and housing integrity of the bay s capability to sustain forces acting on it during ascent as well as landing Figure 33 displays the avionics hazard detection payload bay layout post launch The electrical components are not displayed to emphasize structural integrity 63 Citrus College Rocket Owls Flight Readiness Review Figure 33 Hazard Detection Payload Layout The avionics hazard detection payload bay utilizes a mechanically simple assembly procedure The procedure is detailed as follows First the aft end of the bay is inserted 4 3 4 inches into the aft end of the coupler where it sits fixed on the stiffy tube and arming switches are then connected Second guide rails are placed on the protruding all threads and fore bulkhead is inserted 6 inches into the fore end of the bay where it sits fixed on the opposite of the stiffy tube The fore avionics bay is then fastened with wing nuts and recovery tether is attached to a 3 8 inch forged eyebolt located on the fore bulkhead and detachable bulkhead via 1 8 inch 316 stainless quicklinks The detachable bulkhead is then slid in the remaining free space of the fore end of the bay where it sits flush with th
149. students to pursue STEM and rocketry careers Every outreach event has included some form of evaluation to gain better insight into how the team s educational engagement events have impacted the community The overall response has been exceedingly positive so far with the majority of students at every event indicating that they not only enjoyed themselves but also gained insight into STEM fields at the same time The following table details the different types of evaluation used in the outreaches Table 41 Types of Evaluation Used in Outreach Evaluation Designation Type Middle School Level Post Activity Survey Questionnaire Elementary School Level Pre and Post Activity Survey Questions Verbal Feedback The details of every single outreach can be found in the following table Table 42 Outreach and Educational Engagement Events Event Activity Date of Audience No of NASA Type of Location E F Event Participants Outreach Interaction Type Count Physics Peer led 12 4 2013 Physics 43 0 Education Citrus C Rocketry Lab rocketry lab students Direct College interaction Grades 12 112 Citrus College Rocket Owls Flight Readiness Review Event Activity Date of Audience No of NASA Type of Location E F Event Participants Outreach Interaction Type Count Citrus College STEM activity 12 14 2013 ERA grade 24 24 Education Citrus A
150. ta in flight e Data is recorded and stored onto by CubeSat sensors e CubeSat sends GPS coordinates wirelessly to the ground station for recovery e Voltmeter data is successfully interpreted post flight using excel The mission success criteria was determined based on what was required to answer the research question that has been proposed The measurement of specific variables as well as interpretation of these variables is crucial to successfully furthering the knowledge of the triboelectric charging and its effect on aircraft Experimental Logic Scientific Approach and Method of Investigation The following section describes the experimental thought process in developing rocket payloads Although the Hazard Detection System has been referred to above as a payload it has no experimental purpose Instead it is designed to perform a specific task For that reason its data cannot be classified as experimental LVIS During the research period the team read about problems that arose during the space shuttle launch of the Ares I X due to excessive lateral vibrations caused by the motors that could harm the astronauts and avionics aboard the spacecraft The team therefore devised a payload that was aimed at determining if either parallel or in line staging could mitigate the vibrations produced However such a payload required both a parallel and an in line stage which was deemed to be too risky to execute safely Therefore the focus of the pay
151. tantly and successfully without damaging the interior in any way During the first full scale flight the team yet again used 1 35 g of black powder for the airframe separation The booster section and main bay separated exactly as predicted in flight without excessive force The rocket was not damaged whatsoever by the black powder charge Further details on the results of the full scale flight can be found under full scale launch test results 18 Citrus College Rocket Owls Flight Readiness Review Component Testing Table 2 Component Test Data Location Component or Test Type Purpose Results Details Status Subsystem Mini Component Static To determine Live data from the Live data determined by Successful Avionics Raven3 proper accelerometer was manufacturer should be Bay accelerometer Ground accelerometer 0 83 axial G s 8 1 2 axial G s to ensure Test calibration to properly calibrated ensure data collected is accurate Mini Subsystem Static To ensure proper Flight simulation was The Raven3 flight Successful Avionics LVIS Raven3 functionality of successful without simulation was completed Bay Ground Raven3 with use anomalies using the manufacturer s Test of a flight flight profile software simulation The flight simulation showed that the Raven3 was properly functioning Mini Component Functional To ensure Raven3 worked as Tested using a bell jar Successful Avio
152. that an alteration requires power tools the safety guidelines will still be followed by the team Each team member using a tool must still demonstrate how to appropriately use the tool in question and follow all required safety protocols Detailed in Table 12 are the tools used in construction of the full scale rocket their hazards and risk mitigation Table 12 Tool Safety Tool Risk Risk Mitigation Table Eye or respiratory The table saw does have an open blade that can be Saw irritation bodily harm extremely dangerous if used carelessly Another piece of wood was used to push the pieces to be cut across the table while keeping hands away from the blade Proper use of guide rail on the table saw Protective eyewear instruction on how to safely use the tool read the user s manual 59 Citrus College Rocket Owls Flight Readiness Review Tool Risk Risk Mitigation Band Eye or respiratory A small band saw meant for cutting through metal pipes Saw irritation bodily harm and rods Once the rod has been secured into the machine will take over and slowly push the blade down as it cuts through This tool is very safe and does not require hands to be anywhere near the blade while it is moving Protective eyewear instruction on how to safely use the tool read the user s manual Miter Eye or respiratory Anyone using the miter saw must learn how to operate Saw irritation bod
153. tigations Category Risk Causes Consequences Mitigation Recovery Premature Unsafe handling of Burns or bodily harm The safety officer or mentor must be present Preparation ignition of black powder open during the handling of black powder There will be black powder flame or smoking near no smoking within 25 feet of black powder charges black powder Motor Premature Unsafe handling of Bodily harm severe The safety officer or mentor must be present Preparation ignitionofthe the motor open flame burns death during the handling of motors No smoking within motors or smoking near the 25 feet of black powder motor Igniter Premature Connecting the Minor burns potential Igniters are inserted and connected to long wires Installation ignition battery to a to ignite the motor which are only connected to the power supply once everyone has moved to a safe distance and the countdown has finished Launch Rail Launch rail Launch rail not Potential injury to Rail provided by NASA will be used As many Setup falls over secured with guide personnel and damage members as allowed out to the rail will set up the lines depending on the rail used to the rocket and rail rocket Launch day checklist will be carefully followed so the rocket is completely ready to go out on the launch pad so no extra setup is required The safety officer Joshua is responsible for all procedure checklists during the launch
154. tions Flight Event Payload Operation Altitude Velocity ft of Rocket ft s Main Parachute The vehicle will reorient itself so that the 1200 54 Ejection Detachable forward compartment of the avionics bay is Bulkhead Separation directed toward the landing surface Following reorientation the scanning camera will capture images of the landing surface where the data captured will be analyzed for potential landing hazards and sent to a ground station in real time LVIS Table 16 LVIS Flight Performance Predictions Propulsion Payload Operation Time into Velocity of Mass of Event Flight s Rocket ft s Rocket lbs Main motor The three Raven3 microcontrollers 0 0 52 4 ignites measure lateral vibrations produced by main motor Sustainer The two Raven3 microcontrollers 2 5 270 35 9 motor ignites one in the SMART bay and one in the avionics bay measure lateral vibrations produced by the sustainer 89 Citrus College Rocket Owls Flight Readiness Review Tesseract Table 17 Tesseract Flight Performance Predictions Propulsion Payload Operation Time Velocity of Mass of Event into Rocket Rocket Flight ft s lbs s Main motor CubeSat and Voltmeter data acquisition 0 0 52 4 ignites sequence activated camera starts recording and XBee sends GPS coordinates to ground station Sustainer CubeSat continues to collect data and send
155. tor and the opposite end of the capacitor will be grounded to serve as a drain for the collected charge The nose cone will accelerate through the air accumulating charge which will then tend to drain towards the ground allowing the charge to move along the wire to charge the capacitor The other side of the capacitor will be grounded to ensure that the charge on the nose cone moves towards the capacitor The analog inputs of an Arduino based voltmeter will measure the potential difference across the capacitors The capacitance of the capacitor is known and using the potential difference data the charge that has accumulated on the surface of the rocket can be determined The potential difference will have time measurements to go along with them The CubeSat will be measuring the altitude and this will also have time measurements to go along with them The potential difference measurements will be converted to charge The charge and altitude measurements with corresponding time measurements will be graphed together and the final graph with all altitude and charge measurements will be analyzed to determine the relationship between the two variables For this payload an Arduino based voltmeter will be used to determine the charge that has built up on the surface of the rocket A CubeSat has been designed to measure atmospheric data record the flight determine the position of this payload and send out electromagnetic signals 72 Citrus College Rock
156. trical Elements a Hazard Detection A Raspberry Pi computer as the controller and processing unit for the Hazard Detection payload This computer will connect to a RockSoul USB webcam through USB with wires soldered directly to the four lead on the ports to prevent detachment during flight There is also an Adafruit Ultimate GPS Breakout Board connected to the Pi through a TTL Serial connection b LVIS LVIS utilizes two Raven3 altimeters outside of the main avionics bay to gather the most amounts of lateral vibrations These locations are the mini avionics bay located in the booster section and the SMART bay located above the sustainer motor Each of these bays is 4 inches in length with a diameter slightly smaller than 6 inches and each bay contains a removable payload sled made from birch plywood The payload sled is the retention board for avionics and its dimensions are as follows the sled is 4 x 5 x inches and contains two inch pieces of plywood that is wood glued to two slots within the board Additionally there are two 1 4inch holes in each of the plywood pieces that are wood glued to the sled and have been sanded to allow for inch all thread rods to fit inside Each bay contains two 1 4 inch all thread rods attached on one side by epoxy to a 1 inch bulkhead and sealed from any black powder charges using a removable bulkhead with washers nuts and nut lock to keep the bay sealed Using the same materials and configurations in b
157. two components is soldered into the 4 leads used by the USB port The XBee Pro is connected by wire soldered to the 4 leads of the second USB port on the Pi b LVIS Figure 41 LVIS 3D Diagram The primary difficulty in constructing a two stage rocket is ensuring the proper orientation of the igniter and smart devices that are intended to air start the sustainer motor Figure 41 shows a 3 dimensional drawing of the sustainer tube and main parachute bay Directly above the motor mount their lies a 1 inch thrust plat that will simultaneously act as a bottom bulkhead for the SMART bay represented in Figure 41 by a black box In order for the igniter to be controlled by the smart ignition electronics a steel electric conduit represented in blue in the diagram was placed through the thrust plate and down past the bottom centering ring surrounding the sustainer motor mount Electric wire slides through easily and the igniter for the motor can be connected from the bottom The top bulkhead of the SMART ignition electronic bay serves as a tether point for the main parachute These bulkheads are extremely resilient and can withstand all forces induced by parachute deployment Two separate Y inch all thread rods will connect the two bulkheads A stiffy tube is placed in between them to secure the bay into place 85 Citrus College Rocket Owls Flight Readiness Review c Tesseract The payload that is to be launched in the rocket consists
158. ues were determined by RockSim and will be compared with the values of the test launch Table 6 Drift Table Drift Table 0 mph 5 mph 10 mph 15 mph 20 mph Range 0 ft 1050 ft 2284 ft 3654 ft 4515 ft Altitude 7089 ft 7078 ft 7043 ft 6981 ft 6888 ft 44 Citrus College Rocket Owls Flight Readiness Review 4 Verification Vehicle Table 7 Requirements and Verification Vehicle Requirement Design Feature Verification Status Details 1 1 1 The target altitude shall not The selected motors will Rocket Complete Flight simulations project apogee exceed 20 000 feet above allow the rocket to reach Simulation at 7000 ft AGL Full scale test ground level a maximum altitude of program flight with just the booster motor 7000 ft AGL Full scale test reached apogee at approximately flight 1700 ft AGL This is less than the simulated prediction which ensures that the final launch altitude will be less than 20 000 ft 1 2 The vehicle shall carry one The avionics bay is Pressure test Complete The altimeters have passed ground commercially available equipped with a Raven3 Subscale test pressure tests using a pressure barometric altimeter for altimeter which contains flight Full changing bell jar and a light source recording the official altitude an extremely accurate scale test to act as an igniter and have used in the competition scoring barometric altimeter as fl
159. via a black powder charge 0 47 seconds after the main motor burns out The black powder charge is located on the top bulkhead in the coupler that connects the booster section and the main bay Testing was conducted to determine exactly how much black powder was required to ensure the separation occurs without damaging the rocket in any way To determine the amount of black powder required the following equation was used Amount of black powder g diameter of compartment in inches x length of compartment in inches x 0 006 As the diameter of the compartment is 6 inches and the length of the compartment is 2 25 inches the total amount of black powder needed was calculated to be 1 35 g After construction the rocket was laid on the rocket stand and a inch PVC cap was filled with 1 35 g black powder Unlike usual black powder charges the PVC cap was inverted and small holes drilled through the side This was done so that when the black powder charge ignites to over pressurize the compartment there is no chance of it also igniting the sustainer motor which is located directly above the coupler An igniter was inserted and the booster section and main bay were connected Two shear pins were also inserted At this point the team performed a safety check to ensure the area was clear and that no hazardous substances were located anywhere near the rocket After the all clear the black powder charge was ignited The rocket separated ins
160. w V Launch Operations Procedures 1 Checklist Recovery Preparation Table 26 Checklist for Recovery Preparation Step No Details Check Safety Untangle shroud lines Fold parachute Attach quicklink to recovery harness and parachute Wrap parachute in protective blanket Fold recovery harness and wrap with masking tape Place exposed recovery harness into body tube Place wrapped parachute in body tube Attach body tubes DO COND MH BIW NI Apply shear pins around designated rocket body Motor Preparation Both the main motor and sustainer were prepared following the directions found on Cesaroni s website at http www pro38 com pdfs Pro98 _Instructions pdf Table 27 Checklist for Motor Preparation Step No Details Check Safety 1 Grease o rings and place around nozzle 2 Insert nozzle into nozzle holder 3 Grease inside of both ends of the motor casing 4 Insert nozzle holder into motor casing 5 Place snap ring into motor casing to prevent nozzle holder from sliding out 6 Insert motor tube into motor casing 7 Place snap ring into motor casing 8 Slide motor casing into the motor retainer and install into the airframe of the rocket 103 Citrus College Rocket Owls Flight Readiness Review Igniter Installation Table 28 Checklist for Igniter Installation Step No Details Check Safety
161. w that the project is moving from the design and construction and into its final stages Much of the remaining work will be done through test launches and launch day preparation The team will continue to meet before each launch and hold prelaunch briefing lead by the team leader and safety officer This briefing will focus on safety for the tools and materials required on launch day as well as a reminder of the NAR Safety Code Before launch day the team will receive training in hazard recognition and accident avoidance on the day of the launch the safety officer will perform a safety check on the motor payload and recovery subsystems The team will conduct a safety briefing both before and after each launch where the recognized hazards will be discussed as well as methods for mitigation Certification An individual must be certified by either the NAR or the TRA to purchase and use high power rocket motors This certification is designed to ensure that the high power motors are being used only for the purpose for which they were designed Team member Chris TRA 14610 and the team s mentor Rick Maschek TRA 11388 are TRA Certified Level II The certified members of the team are aware of the risks of high power rocketry and will help the safety officer ensure a safe launch environment Motor and Black Powder Handling and Storage Project Lambda includes 2 motors with the largest being an L class reloadable rocket motor High power rock
162. when that information is received on the ground LVIS The expected data is relevant to SLS technology because the way that the rockets are staged can have a major impact on the payloads therein The extent of this impact can be further determined after analysis of the data collected by the Raven3 The data collected is measured in G force which is the same as weight per unit mass The Raven3 is accurate to 0 045 Gs and the investigation method requires that the data collected during separation of sections be excluded to ensure that the data collected only includes lateral vibrations from thrust Another factor that will be taken into account is that the thrust of the motors is differs from the first to the second stage Tesseract The data the team expects to get is applicable to any system that experiences the phenomenon of triboelectric charging or any type of charging by friction The static charge can build on the exterior of the system and can then create a potential difference with any type of metal or circuitry within the system or in the case of Project Lambda the nose cone electronics This potential difference can present itself as a hazard to communication signals onboard sensors or short any other piece of electronics For this reason the team is investigating the magnitude of charge accumulated during flight at various altitudes and how this charge is stored on the exterior as a function of time The data that is being recorded by thi
163. y officer Joshua will be responsible for providing technical leadership for the safety quality and mission assurance in the construction and launch of Project Lambda and other activities conducted by the Rocket Owls These responsibilities include the direct oversight of the team during manufacturing when safety is of concern as well as the independent assessment of the rocket s safety To fulfill those responsibilities the safety officer will ensure that all team members have access to and have read relevant safety rules for all equipment and materials they are using while enforcing safe practices while building and at the launch site Other responsibilities include maintaining MSDS reports and having them on hand for all used material and ensure the proper use and storage of chemicals and motors Analysis of the Failure Modes Payload Integration and Launch Operations The 5 greatest risks based on the risk matrix are discussed in the table below Likelihood and Severity values have been adjusted to reflect completed and ongoing mitigations 49 Citrus College Rocket Owls Flight Readiness Review Table 8 Greatest Vehicle Risks Risk Likelihood 1 5 Severity 1 5 Consequences Mitigations Failure to Eject Main 2 Packing a parachute can leave a lot of room 4 While the drogue should slow down the The rocket body will take extreme damage Payloads To prevent the likelihood of this happening again the recov
164. y wiring comes 3 The rocket 3 All of the Failure of payloads or All connection points will be loose during flight experiences a maximum electronics will have subsystems in each securely soldered Batteries of 8 1 g which cause easily cause wires to become disconnected multiple connections points for many components payload Loss of power to avionics and components will be either zip tied or screwed to the payload sleds to prevent movement The electromagnetic waves sent out by the CubeSat cannot be detected 3 The XBee transceivers are able to communicate with each other and send data but can still lose connection 4 Data cannot be collected if the radio waves are not detected this includes GPS data Failure of Tesseract payload possible loss of nose cone section and CubeSat without GPS data Multiple tests in various layouts within the CubeSat have been completed Tests will be continued until the official launch to calibrate the XBee transceivers to get the best results 101 Citrus College Rocket Owls Flight Readiness Review Hazards Electronic Safety Most electronic components have not be made permanent yet so much of the soldering is not complete All testing was done using breadboards Due to the abundance of electronics components in all systems of the rocket and their cost the team will handle all electronics with extreme care No pow
165. ystem are located in Payload Design portion of the report Additionally the payload sleds in the avionics bay have been changed from polycarbonate to birch plywood Birch plywood is easy to machine with the laser cutter which produces more precise and exact results Also the official scoring altimeter has been changed to a Raven3 accelerometer and its power source has been changed from a standard 9V battery to an advanced lithium 9V battery The Raven3 can perform multiple tasks so in order to conserve space the Raven3 will act as the official scoring altimeter and measure lateral vibrations simultaneously The advanced lithium battery will produce 25 more mA than a standard 9V which will help prevent failure of the sustainer motor ignition 2 Citrus College Rocket Owls Flight Readiness Review Lastly the camera used for the hazard detection system has changed Instead of using the Raspberry pi camera board a RockSoul USB webcam will be used The reason for this change is because the Raspberry Pi itself does not recognize its camera board as a webcam whereas the edge detection algorithm is reliant on a webcam Tesseract Changes have been made to the Tesseract payload as well Upon testing of the electrometer this system was deemed unfit to record charge due to major discrepancies in recorded measurements The system has been replaced with a new circuit that contains a capacitor The capacitor will be connected to the nose cone and

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