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User's Manual Version 4.0 To be used with Rev CPlus EyasSat April

1. Patent Pending Pin RowA Row B Pin 1 1 2 2 3 3 4 Ambiant temp PF7 4 5 Experiment temp PF6 5 6 Bat temp PF5 5V reg temp PF1 6 7 Analog GND 7 Row D Row C Pin 8 8 Exp Exp Interboard Interboard 0 9 Exp Exp Interboard Interboard 1 10 SS PBO Solar pnl2 Solar pnl2 2 11 SCK PB1 2 Z 3 12 MISO PB3 T R X 4 13 MOSI PB2 IHU PWM 13 T R Y T R Y 5 14 14 Therm B Therm B 6 15 15 Therm W Therm W 7 16 16 Panel temp Paneltemp 8 17 17 Solar pnll Solar pnll 9 18 18 Sep SW Sep 5W 10 19 Gen I O 7 PA7 19 Sun Bottom Sun Bottom 11 20 Gen I O 6 PA6 20 Sun Top Sun Top 12 21 Gen I O 5 PA5 21 Enable Enable 13 22 Gen I O 4 PA4 22 Case reserved Yaw 1 14 23 Gen I O 3 PA3 23 Yaw 2 Yaw 3 15 24 Exp Serial TTL RXD XStr CTS 24 Yaw 4 Yaw 16 25 Exp Serial TTL TXD XBee CTS 25 Charge Charge 17 26 RF serial RX TTL PD2 RF speed select 26 Charge Charge 18 27 serial TX TTL PD3 27 EyasSat User s Manual 5 0 27 May 2011 98 Case reserved N C 19 28 GPSIPPS 29 30 I2C data PD1 XBee RSSI EyasSat User s Manual 5 0 12 clk PDO 27 May 2011 GND GND 99 Appendix C Importing Data Files into Excel To open the file in Excel and graph the data do the following Open Exce
2. 14 3 7 SYSTEM MOMENT OF INTERTIA 000000 17 4 ELECTRICAL POWER SUBSYSTEM eeeeee esee seen eene neto setas 18 41 EYASSATEPS LAB OVER VIEW 18 42 BYASSATEPS LAB OBJECTIVES ceni nrar ee 18 4 3 BACKGROUND KNOWLEDGE REQUIREMENTS 0 0000 18 4 4 BYASSAT EPS SUBSYSTEM BLOCK DIAGRAM 044400 1 19 4 5 LAB MATERIALS AND EQUIPMENT 19 4 6 EYASSAT BATTERY PACK ACCEPTANCE TESTS 20 4 6 1 EyasSat Battery Pack Inspection uia i 20 4 6 2 EyasSat Battery Pack Functional Testi dete 21 4 6 3 EyasSat Battery Pack Characterization Charging Procedures 22 4 7 EYASSAT SOLAR ARRAY ACCEPTANCE TESTS 4 23 4 7 1 Removal of Remove Before Flight RBF 23 4 7 2 Eyasbat Solar Array Inspection a i eiae 23 4 7 3 EyasSat Solar Array Abbreviated Functional Test AFT 27 4 7 4 EyasSat Solar Array Fundamentals eee eese enne 28 4 7 5 EyasSat Solar Array Characterization eese 29 4 8 EYASSAT EPS MODULE ACCEPTANCE 8 8 40 enne 33 4 8 1 EyasSat EPS Module Inspection tr I ete eo RE 39 4 6 2 EyasSat EPS Module Functio
3. factory reset of coeffients zeroize gyroscope and accelerometers Experiment Module 1 922 22 Passed through to experiment 4 characters 2 Experiment Module 2 2 3 Passed through to experiment 4 characters Experiment Module 3 Passed through to experiment 4 characters FLEXIBLE EXPERIMENT BOARD EyaFlex Exp Set the pulse width of PWM output 2 1024 number p 0 1024 full on Set the pulse width of PWM output 1 1024 0 1024 full on 3 10 Turn off 3 3V output number 1 11 Turn on 3 3V output number 1 20 Turn off 3 3V output number 2 21 Turn on 3 3V output number 2 5 10 turn off 5V output number 1 low current EyasSat User s Manual 5 0 27 May 2011 105 b 11 20 21 30 31 40 41 50 51 60 61 70 71 80 81 10 11 20 21 Ol 01331 32767 32767 32767 32767 turn on 5V output number 1 low current turn off 5V output number 2 low current turn on 5V output number 2 low current turn off 5V output number 3 low current turn on 5V output number 3 low current turn off 5V output number 4 low current turn on 5V output number 4 low current turn off 5V output number 5 high current turn on 5V output number 5 high current turn off 5V output number 6 high current turn on 5V output number 6 high current turn off 5V output number 7 high current turn on 5V output number 7 high current turn off 5V output number 8 high current turn on 5V output nu
4. 66 AIT Observe the movement of EyasSat It may take moment or two to react 67 AIT Turn the EyasSat Torque Rod X off by clicking on the X off button 68 AIT Repeat the previous steps for the EyasSat Torque Rod Y using the appropriate control buttons 69 AIT Demonstrate the concept of momentum dumping Turn on one of the EyasSat Torque Rods and allow EyasSat to become inertially stable Try to bring the wheel speed up slowly without moving the satellite body 70 AIT Turn the torque rods off and store the magnet 8 6 5 EyasSat Closed Loop Attitude Control Test 71 AIT Steady EyasSat with your hand 72 AIT Bring the wheel speed up to 500 while continuing to hold EyasSat steady 73 AIT Release EyasSat without disturbing it 74 AIT Click on the Engage Auto Yaw button The status of the button will change to Disable Auto Yaw when ready 75 AIT Usea flashlight to illuminate EyasSat Yaw Attitude Sensor at a 45 degree angle to sensor 1 and 2 76 AIT Move the light slowly side to side and EyasSat will follow 77 AIT Stop the demo by clicking on Disable Auto Yaw and turning the wheel off 78 AIT Remove EyasSat from the line or stand hook and place it on the table EyasSat User s Manual 5 0 27 May 2011 94 8 7 EyasSat Thermal and Solar Characterization During this section of the lab your team will simulate the on orbit thermal cycling and solar environment You will also correlate thermal c
5. CYASSAT User s Manual Version 4 0 To be used with Rev CPlus EyasSat April 2010 EyasSat LLC www EyasSat com Acknowledgements EyasSat is a fully functional nanosatellite designed for teaching spacecraft systems engineering in the classroom and laboratory The name EyasSat has its roots in falconry as eyas means baby falcon or fledgling bird The falcon is the mascot of the US Air Force Academy where the concept of EyasSat was born EyasSat was co developed under a Cooperative Research and Development Agreement USAF CRDA NUMBER 04 AFA 239 1 25 August 2004 by the U S Air Force Academy Colorado USA and Colorado Satellite Services Parker Colorado USA It is currently owned by EyasSat LLC This concept and the embodiment of the idea have been submitted for U S patent consideration and are currently in the patent pending status Significant contributions of funding and course development were provided by the National Security Space Institute Colorado Springs Colorado USA Original Author David J Barnhart U S Air Force Academy Colorado USA Contributing Authors James J White Timothy L White and Gregory D White Colorado Satellite Services Parker Colorado USA John B Clark Consultant Colorado Springs Colorado USA Jerry J Sellers Teaching Science and Technology Incorporated Manitou Springs Colorado USA Jesse Gossner David W Deist and David M Syndergaard
6. The purpose of this test is to verify that the software running in the onboard microcontroller is able to correctly process commands turn on and off the power switch hardware report telemetry voltage and current of the battery input solar panel input 5 and 3 3 VDC regulated lines Separation switch telemetry will also be checked 64 EPS Ensure the EyasSat Data Interface shown in Figure 4 12 EyasSat Data Interface to USB is connected to your computer Figure 4 12 EyasSat Data Interface to USB 65 EPS Connect the EyasSat Data Interface to the EyasSat EPS Module UMB port see Figure 4 11 66 EPS USB users only Record the COM ports in your workbook for the EyasSat Data Interface and MaxStream Module by consulting your instructor or using X CTU 67 EPS Open the EyasSat Control CPlus Graphical User Interface version must match icon on the desktop the icon has a picture of a galaxy on it note that previous versions of the EyasSat GUI will not work properly because of extensive changes in the power subsystem design between rev C and rev CPlus 68 EPS Check the COM port to the umbilical by clicking the Comm tab then the Port Configuration button change setting as needed usually selected the highest port number works if you are unsure go to the device manager and see which port number was allocated by the sysem then change the selected port to match then click Save Next click the Text Only
7. 01 oll 01 oll 01 oll IHU Core Settings Set callsign number Attach compass exp board Attach accel gyro board Attach experiment 3 Attach power board Attach ADCS board Command timeout 0 lockout 331 enable radio amp coeff programming telemetry scaling on off Telemetry Settings Telemetry Delay Radio Module Settings Set channel number Set acknowledge deliver retrys Real time Clock module Settings Set the hours in the on board real time clock Set the minutes in the on board real time clock Set the seconds in the on board real time clock Test Module 1 pin X pulled low 1 pin X pulled low 1 pin X pulled low 1 Power Switch 1 On 1 Power Switch 2 On 1 Power Switch 3 On 1 Power Switch 4 On 1 Power Switch 5 On 1 Power Switch 6 On 1 Power Switch 7 On 1 Power Switch 8 On 27 May 2011 103 a a 9 N QF 01 float float float float float float float float float float float float float float float float 01331 112 telemetry scaling on off BV a coefficient BV b coefficient BI a coefficient BI b coefficient SPV a coefficient SPV b coefficient SPI a coefficient SPI b coefficient 5V a coefficient 5V b coefficent SI a coefficient SI b coefficient 3V a coefficient 3V b coefficient 3I a coefficient 3I b coefficent O coefficient lockout 331 enable zset BVz10 5V 5 3 3V 3 3 2 set SPI 10 set current
8. X Gnd Gnd 19 ADCS Measure the resistance of each miniature sensor under no light cover the cell with your finger Record the measurement IN O M IHR 92 IN 20 ADCS Measure the voltage of each cell under ambient room light Record the measurement 2 ADCS Measure the voltage under full illumination using a flashlight torch Record the measurement 22 ADCS Disconnect all wiring used in this test 7 5 7 EyasSat ADCS Module Inspection The purpose of this test is to ensure that your EyasSat ADCS Module was delivered in the proper configuration EyasSat User s Manual 5 0 27 May 2011 77 Torque Rod LEDs BEDS Power LEDs J 3V 5V 9V 5V Power 5 nen Ce 3 wmm Port Gyro amp Accel sensors 3 3V Power aL LANE Power Port TTL level Data Port UMB Reaction Wheel Hardware Version Serial number Figure 7 9 EyasSat ADCS Module 23 ADCS Visually inspect the module to ensure that there are no loose wires connectors or solder connections Assure no black jumpers are present on the 2 pin jumper posts 24 ADCS Compare your EyasSat ADCS Module to the one in Figure 7 9 Ensure that the type and location of components match There may be some difference in the way the reaction wheel is mounted 25 ADCS Record the hardware version software version and serial number of the module hardware version is printed on the board softwar
9. 9 Expmt 24 9 Solar Array 19 3 Telemetry in Deg 4 7 points not connected Figure 8 1 EyasSat Control Panel Thermal Pane EyasSat User s Manual 5 0 27 May 2011 84 6 3 EyasSat Thermal Subsystem Block Diagram Figure xxx illustrates the Thermal Subsystem for EyasSat With exception of local monitoring of some temperatures by the C amp DH board all temperatures are read out by the power board Review the EyasSat EPS Subsystem Block Diagram on page 19 the EyasSat Communication Subsystem Block Diagram on page 61 and the EyasSat ADCS Subsystem Block Diagram on page 70 The system level block diagram is a culmination of the subsystem block diagrams and is shown on page 97 Block diagram to be supplied Figure 8 2 EyasSat Thermal Subsystem Block Diagram 8 4 Lab Materials and Equipment EyasSat EPS Module EyasSat Solar Array EyasSat C amp DH Module EyasSat Comm Module EyasSat Antenna EyasSat ADCS Module EyasSat Torque Rod X EyasSat Torque Rod Y EyasSat Thermal Panel EyasSat Structure EyasSat Top Assembly EyasSat Sun Sensor T EyasSat Yaw Attitude Sensor EyasSat GSE Harness EyasSat Lifting Lug EyasSat Antenna Cable EyasSat Bottom Assembly EyasSat Separation Switch EyasSat Sun Sensor B EyasSat Stack Rods EyasSat Mounting Feet EyasSat Structural Screws amp Nuts Computer EyasSat User s Manual 5 0 27 May 2011 85 Halogen lamp Latex or cotton gloves 8 5 EyasSat Assembly and Integration It is
10. EyasSat Top Sun Sensor to the one in Figure 7 4 8 ADCS Look at the bottom of the EyasSat either turning the entire structure on its side or by looking at just the bottom of the power board and base plate assembly You should see the bottom sun sensor as illustrated in Figure 7 5 Figure 7 5 EyasSat Bottom Sun Sensor EyasSat User s Manual 5 0 27 May 2011 73 7 5 4 EyasSat Sun Sensor and B Functional Test The purpose of this test is to ensure that the EyasSat Sun Sensors meets the basic performance requirements and will indeed detect the difference between light and dark 9 ADCS Set your multimeter to resistance mode 10 ADCS For the Top sun sensor connect the 8 pin cable which runs from the top unit to the breakout box as shown in Figure 7 6 The Top sun sensor is brought out to test points tbd and tbd Connect the Ohm meter to that point 11 ADCS Measure the resistance of the EyasSat Sun Sensor T in no light put your thumb over the sensor Record this Now remove your finger and shine a high intensity flashlight on the sensor Record this value 8 2 qe 5 E 3 uuo utd Figure 7 6 EyasSat sensor breakout box 12 ADCS Resistance of the bottom sun sensor is measured in the same manner See Figure 7 7 13 ADCS Measure the resistance in full illumination using a flashlight torch Record this value Measure the resistance with light blocked off you can do this simply by settin
11. National Security Space Institute Colorado Springs Colorado USA Gerry Murphy Chuck Allen Co Owners EyasSat LLC Current information and technical support for the EyasSat program can be found at http www eyassat com Please send any suggested corrections or improvements to this manual to Gerry Murphy at gmurphy design group com The views expressed in this document are those of the authors and do not reflect the official policy or position of the United States Air Force Department of Defense or the U S Government Cleared for public release distribution unlimited USAF Academy Department of Astronautics EyasSat User s Manual 5 0 27 May 2011 2 Table of Contents L1 QGGEFLPINGSEAXRTED 9 2 hui neo di ve eaa viene tyres iR pe eir ve nine 10 9 555555 08 13 3 EYASSATSTRUCTURES LAB 255 13 3 5 5 2 HR OR He E SEES NL 14 3 3 BACKGROUND KNOWLEDGE REQUIREMENTS 14 3 44 LAB MATERIALS AND BQUIPMENT 5 e iie eeet seinen ruso 14 3 5 SYSTEM MASS BUDGET DETERMINATION eese enne 14 3 6 SYSTEM CENTER OF MASS CM
12. Verify that the green light on the board is now active instead of the red light you are on satellite internal power instead of GSE power 79 EPS Remove the green plug from the EPS connector to power down the EyasSat EPS Module EyasSat User s Manual 5 0 27 May 2011 41 A separation switch is used to tell the spacecraft and operators when it has from the launch vehicle There are two different types logic and ower in the loop We are demonstrating power in the loop type where the power to run the satellite is connected through the sep switch which acts like a power on switch when the satellite is separated from the launch vehicle This is OK for very small satellites but larger satellites which consume a lot of power use a logic switch which via some circuitry enables power to come for the space vehicle 4 8 4 EyasSat EPS Module Solar Panel Power Input Test This test will demonstrate what happens on orbit when a spacecraft goes through the sunlight and eclipse cycles Our EyasSat Solar Array which we will integrate and test shortly is approximately TBD efficient and is enough to provide help to the battery in powering the bus or if the bus is using very low power can actually charge the battery it is not the intent to use the SA to fully charge the battery however because we do not at this point have the proper software to control battery charging so this is an exercise only to illustrate the prin
13. You should get a window similar to the one in Figure 5 4 CE xni Please press the right mouse button for the S 0 94569986 graphing features menu Press F1 for help 0 99990302 Y Axis units 0 0 57 6 115 1 172 7 230 3 287 8 345 4 X Axis units Figure 5 4 Curve Expert Linear Fit 27 C amp DH Click on the info button to get the b slope and a intercept values for your calibration as shown in Figure 5 5 EyasSat User s Manual 5 0 27 May 2011 51 Model Information Linear Fit 4 Linear Fit Coefficients a 2 4537422 b 0 46849918 y at bx The parameters for the above model equation are given to the right in the coefficient list Figure 5 5 Curve Expert Solution 28 C amp DH Use the 331 command to unlock coefficient setting You will get a response that says coefficient programming has been enabled 29 C amp DH Use the mX XXXX command where X XXXX is the coefficient to set the intercept for I 5V You may copy and paste from the spreadsheet to avoid errors 30 C amp DH Use the nY YYYY command where Y Y Y YY is the b coefficient to set the slope for I 5V 31 C amp DH Finish the commands to set V 5V k l During this process you can query the coefficient value by just sending the command character for the coefficient 32 C amp DH Send an s1 command 33 C amp DH Re insert the 150Q resistor or value close to it as the load on the 5volt b
14. are as expected and record the total bus power being consumed 57 ADCS Click on the Text Only Interface on the EyasSat Control Panel 58 ADCS Send the ial command from the Text Only Interface to power up and add the EyasSat ADCS Module telemetry 59 ADCS Send the a 331 then azl commands to zeroize 60 ADCS Go back to the EPS panel and record bus power value and note that it has gone up from the previous reading 61 ADCS Click on the Text Only interface tab 62 ADCS Turn on the wheel with an aw400 command The maximum range is 600 to 600 which is a relative wheel speed 63 ADCS After the wheel has spun up Record the total bus power value again 64 ADCS Stop the wheel by using the aw0 command 65 ADCS Reverse the wheel direction with the aw 400 command 66 ADCS Click on the Attitude Determination and Control tab Figure 7 11 and experiment with different wheel speeds Note that for very slow speed commands there is not sufficient torque to overcome the static friction in the bearings This is normal behavior EyasSat User s Manual 5 0 27 May 2011 82 EyasSat Control Panel Data Handling DH Flex Experiment EXP ADCS Yaw Axis Closed Loop Controller 7 Actuators Torque Rods Wheel Set counts TLM rps 5 Set Dead Band a B zWwheel poo 0 r 250 Set Wheel Delta Alg 0 Off Off Engage Auto Yaw em Sensors Sun Top 0 Yaw Sensor 1 0 AccelX 00
15. cases there are two yellow LEDs that indicate the 5V and 3 3V supplies are operating normally When the battery is armed but the sep switch not activated only a single green LED is on Last of all note on Figure 5 that there are current and voltage monitors on a number of key test points All of these analog signals are routed either though an external multiplexor MUX first or directly to one of the Analog to Digital Converter ADC channels on the micro controller The EPS also provides signal conditioning and reads all of the thermistors on the thermal panel more on that in the thermal section Each EyasSat board uses an Atmega 128 microcontroller programmed in C to operate All communication over the backplane connector is via an SPI bus if the student is interested they are encouraged to investigate SPI just google Standard Peripheral Interface For those interested in programming their own controller and going into more detail EyasSat has exercises and equipment in development to challenge even the seasoned professional With that background let us now proceed to test out the EPS in detail 47 EPS Power up the EyasSat EPS Module with GSE and the 9V supply by using the red plug attached to the EPS EGSE and connecting to the EyasSat external connector 48 EPS Verify that the red Power LED illuminates and that the two yellow 5V and 3 3V also illuminate 49 EPS Set your multimeter to the VDC V mode and configu
16. of Mass Picture to be supplied Figure 3 4 Measuring CM on the Z axis EyasSat User s Manual 5 0 27 May 2011 16 3 7 System Moment of Intertia Determination EyasSat is a single axis spinner Spacecraft It is stable in space because is has a certain angular momentum about its z axis When we design spacecraft our attitude determination system must be sized to work well with the moments of interia of the spacecraft in order to provide the proper control Typically in addition to overall mass the center of mass the designers must also worry about the moments and even products of intertia of the completed system This is managed by where the mass 15 distributed Modern day spacecraft which are designed with comprehensive tool chains provide methods of calculation of all of these parameters real time Although managing the moment of intertia is really the job of the structures and integration engineer in the case of EyasSat we will use the ADCS system and the reaction wheel to actually measure the moment Because this requires knowledge of the ADCS system we will postpose this activity until later in the course As a matter of information although we have no specific exercise for this one more very stringent and important aspect of the Spacecraft structure design is that it must have a minimum natural frequency This is the lowest fundamentatal frequency that the structure will ring at This requirement is in place to assure t
17. shown in Figure 4 14 EyasSat User s Manual 5 0 27 May 2011 39 EyasSat Control Panel Attitude Det Control ADCS Communications Comm Orbit Determination GPS Flex Experiment EXP Text Only Interface Thermal Electrical Power EPS Data Handling DH EyasSAT Status EyasSAT Power Startup Firmware Version 5 2 5 13 11 P Sep 1 V Batt 7 83 I Batt 84 00 V SA 7 65 I SA 6 00 I MB 72 00 T Batt 22 61 V 5v 4 83 I 5v 98 00 V 3v 3 18 I 3v 16 00 T TopA 4 71 T TopB 4 71 T Base 4 71 T Wht 4 71 T Blk 4 7 S 0 Telemetry Command Received Manual Telemetry Command Window Data Logging Idle t Send Command CAEyasSatMyEyasSATFile bx T Enable File Log Status EyasSAT Idle Figure 4 14 EyasSat Control Panel Showing EPS Module Telemetry The fields in the EPS telemetry line are as follows Sep Separation switch status 0 or 1 V Batt Battery module voltage V I Battery module current mA is charge and is discharge V SA Solar panel voltage V I SA Solar panel current mA I MB Main bus current T Batt Battery Temperature V 5v SV converter output I 5v 5V EPS line current mA all lines combined V 3v 3V converter output EyasSat User s Manual 5 0 27 May 2011 40 73 EPS Verify that the five 5V switched lines the three 3 3V switched lines are able to switch on and off in the order shown below Verify that the appropriate blue LED illuminates be sure to v
18. the I 5V telemetry point as an example If you decide to use the spreadsheet fill in the values for V 5V and I 5V if you have not already then skip to step 28 C amp DH on page 52 24 C amp DH Open the shortcut on the desktop to Curve Expert It is a tool that will give you the polynomial expression that best fits the curve representing the calibrated telemetry data You may download this tool from http curveexpert webhop net Or you may use Microsoft Excel where a INDEX LINEST B3 B8 C3 C8 2 b INDEX LINEST B3 B8 C3 C8 1 The 8 cells are where the metered data is entered Vor mA The C3 C8 cells are where the corresponding raw counts are entered You may expand the series to include as many data points as you wish 25 C amp DH Enter your raw counts in the X column and the current from the meter in the Y column as shown in Figure 5 3 Delete the bottom row of 075 by selecting them and then right clicking and selecting cut EyasSat User s Manual 5 0 27 May 2011 50 M CurveExpert 1 3 UNTITLED DAT Ioj x File Edit Data Interpolate Apply Fit Tools Window Help nelasa selee Kliclre s afF Rank Regression Data Plot E E gt X Atli uniti CurveExpert 1 3 UNREGISTERED COPY UNTITLED DAT Figure 5 3 Curve Expert Data Entry Screen 26 C amp DH From the top menu choose Apply Fit then Linear
19. to design their own payload and learn about control operation and data acquisition The instructor will find a wide range of exercises in this manual some are more advanced than others and the intent is to provide a set of base exercises that illustrate the operation of all the elements of EyasSat The instructor will need to tailor these exercises to the needs of their students Through the EyasSat organization instructors can exchange ideas and laboratory exercises To learn more about that and how we plan to create a user community for EyasSat please consult our website or contact the EyasSat organization It is important to point out that EyasSat is designed such that it can be used in courses that provide high level overviews of Spacecraft subsystems and their interrelationships but it can also be used and is used to teach principles of systems engineering and even detailed design engineering The student experience level ranges from AP level high school activities to people who have been in the industry for years but need refresher courses and hands on experience with inexpensive hardware before they have to handle real space critical itesm There are many excellent references available to the instructor that can provide background and context for design and test of the various spacecraft subsystems Some of these are listed is the suggested reference section and are available through EyasSat should the instruction not have acce
20. wires connectors or solder connections 42 C amp DH Compare your EyasSat C amp DH Module to the one in Figure 5 6 Ensure that the type location and number of components match exactly Ensure the ambient temperature sensor connected to the rightmost thermistor input EyasSat User s Manual 5 0 27 May 2011 53 43 C amp DH Record the hardware version software version and serial number of the module hardware version is printed on the board software version is on a label on the square 64 pin integrated circuit the serial number is hand written in the bottom corner 44 C amp DH Verify that there are no loose wire clippings or other material in the EyaBus connectors on the bottom of the module and that the connector pins are not bent 5 7 2 EyasSat C amp DH Module Functional Test The purpose of this test is to ensure that the EyasSat C amp DH Module meets the basic performance requirements N Only use the provided 5V Power Supply in this lab exercise 45 C amp DH Connect the 5V Power Supply shown in Figure 5 7 5V Power Supply to the EyasSat C amp DH Module power port Figure 5 7 5V Power Supply 46 C amp DH Verify that the red Power LED illuminates 47 C amp DH Disconnect the 5V Power Supply from the power port of the EyasSat C amp DH Module EyasSat User s Manual 5 0 27 May 2011 54 5 7 3 EyasSat C amp DH Module Software Functional Test The purpose of this test is to verify that the software running in the
21. with another lab reassemble the EyasSat and remount the protective covers EyasSat User s Manual 5 0 27 May 2011 45 5 Data Handling Subsystem 5 1 EyasSat C amp DH Lab Overview 1 C amp DH This lab will expose you to a miniaturized spacecraft Command and Data Handling subsystem C amp DH Acceptance tests will be performed on the heart of the C amp DH subsystem the EyasSat C amp DH Module to verify physical compliance and workmanship of the contractor The EyasSat C amp DH Module will then be characterized individually Once the component level testing is complete it will be integrated to create the EyasSat stack For the engineering course you will begin with a calibration and characterization exercise on the EyasSat EPS Module before starting on the EyasSat C amp DH Module 5 2 EyasSat C amp DH Lab Objectives Objective 1 Perform calibration of selected EyasSat EPS telemetry channels Objective 2 Characterize the performance of the EyasSat EPS Module by determining its efficiency Objective 3 Perform acceptance and verification tests on the EyasSat C amp DH Module Objective 4 Integrate EyasSat C amp DH Module with current stack Objective 5 Verify integrated EyasSat operational status 5 3 Background Knowledge Requirements It is assumed that the student is familiar with basic principles of data acquisition calibration and command management Several of the references give here are useful tools for the instructor Should t
22. 011 12 3 Structural Subsystem 3 1 EyasSat Structures Lab Overview The structure of a spacecraft like any structure has both requirements and constraints in its design Requirements may be driven by the need to support certain subsytems or payloads handle the loads iniducted by the launch vehicle provide for ease of assembly etc Constraints include things like a limit on its mass specifications about its center of gravity limits on the lowest natural frequency etc This lab will introduce you to the concept of a spacecraft mass budget using EyasSat Additional exercises are available to understand and practice verifying certain constraints in this case the center of gravity E n X EyaS BAT LLC 2011 Figure 3 1 EyasSat Stucture without Electronics or Sensors EyasSat User s Manual 5 0 27 May 2011 13 3 2 EyasSat Structures Lab Objectives Objective 1 Review the mass budget of EyasSat Objective 2 Analyze the mass budget of EyasSat Objective 3 Determine if EyasSat meets Center of Mass Requirements 3 3 Background Knowledge Requirements It is assumed that the student is familiar with basic principles of mass management for Space hardware and understand how center of mass is determined 3 4 Lab Materials and Equipment Disassembled EyasSat 1 kg scale Center of Mass test kit available through EyasSat LLC 3 5 System Mass Budget Determination Objective 1 The mass budget has been determined for EyasSat bas
23. 1 EyasSat C amp DH Module amp EPS Integration 57 5 8 2 EyasSat C amp DH Module amp EPS Integrated Test esses 57 6 COMMUNICATIONS 50 8 61 6 1 EYASSAT COMM LAB OVERVIEW Pee ents uideo 61 6 2 EYASSAT COMMUNICATIONS LAB 400 61 6 3 BACKGROUND KNOWLEDGE REQUIREMENTS ene 61 6 4 EYASSAT COMMUNICATION SUBSYSTEM BLOCK 61 6 5 EYASSAT COMM MODULE ACCEPTANCE TESTS eee 62 6 5 1 EyasSat Comm Module Inspection eee eee eese nte 62 6 5 2 EyasSat Comm Module Functional Test eene 63 6 6 EYASSAT COMM MODULE INTEGRATION AND 58 024424222 1 66 6 6 1 EyasSat Comm Module C amp DH and EPS Integration 66 6 6 2 EyasSat Comm Module C amp DH and EPS Integrated Functional Test 66 6 6 3 EyasSat Comm Module Acknowledged Delivery Functional Test 67 7 ATTITUDE DETERMINATION AND CONTROL SUBSYSTEM 69 7 1 EYASSAT ADCS LAB OVERVIEW iiit uiii poatea 69 EyasSat User s Manual 5 0 27 May 2011 4 7 2 EYASSAT ADCS LAB 2 4000000000 69 7 3 EYASSAT ADCS SUBSYSTEM BLOCK DIAGRAM eee eene 70 74
24. 6 1 EyasSat Communications System Block Diagram Lab Materials and Equipment EyasSat EPS Module EyasSat C amp DH Module EyasSat User s Manual 5 0 27 May 2011 61 EyasSat Comm Module EyasSat Antenna 5V Power Supply Multimeter Computer w power supply Wire jumper kit EyasSat RF GSE 6 5 EyasSat Comm Module Acceptance Tests m 58 A 2 E x Hu 9 O BE Maxstream 2AXStrean 24 GHz 600 Baud Wireless Voce 5 4 20 2 XBee Experiment 1 4992 Radio cod C ne Oe this lab gt nma 2007 Number Maxstream 5V Power Port Data Radio 3 3V Power Port XBee ERAN C CA COUCH m lt _ lt Loopback B ss Jumper Points T io ME 71200 Serial Number 6 HW Version Figure 6 2 EyasSat Comm Module 6 5 1 EyasSat Comm Module Inspection The purpose of this test is to ensure that your EyasSat Comm Module was delivered in the proper configuration EyasSat User s Manual 5 0 27 May 2011 62 1 COMM Compare your EyasSat Comm Module to the one in Figure 6 2 Ensure that the type location and number of components match It should be noted that not all systems my include the XBee module this is dependent on options purchased Assure no black jumpers are present on the 2 pin jumper posts 2 COMM Visually inspect the EyasSat Comm Module to ensure that there are no loose wires connectors or solder connections 3 COMM Ve
25. EX experiment boards they should not be in the stack at this time 44 ADCS Carefully line up the bus pins and have a lab partner cross check your alignment in both directions 45 ADCS Once they are properly aligned gently push the EyasSat ADCS Module all the way down on the EyasSat Comm Module 46 ADCS Gently Insert the EyasSat LED Test Module into the EyaBus connector on the EyasSat ADCS Module 7 6 2 EyasSat ADCS Comm C amp DH and EPS Integrated Functional Test 47 ADCS USB users only Change COM port setting for EyasSat RF GSE connection 48 ADCS Connect the serial interface to the C amp DH board and set the GUI to the Text only panel 49 ADCS Power up the EyasSat EPS Module with the GSE You should see the standard power up message If you do not verify your COM configuration Note that by design the 5VSW6 and TBD will illuminate dimly at this point 50 ADCS Now click on the Data Handling DH tab on the EyasSat Control Panel 51 ADCS Verify that you can set the time HH MM and SS 52 ADCS Verify that you are getting a thermistor temperature reading from the C amp DH 5vR and Ambient telemetry points 53 ADCS Click on the EPS tab in the EyasSat Control Panel 54 ADCS Click on Attach EPS EyasSat User s Manual 5 0 27 May 2011 81 55 ADCS Use the EyasSat Control Panel EPS Tab pushbutton to turn on several of the 5v and 3v switches Record your results 56 ADCS Verify that the current and voltage readings
26. EyasSat 55 AIT Decrease the wheel speed to 250 56 AIT Observe the movement of EyasSat 57 AIT Experiment with your ability to control EyasSat using this technique 58 AIT Turn the wheel off set to zero speed before proceeding Again steady the EyasSat in a state where it is not rotating wheel This means that the wheel is normally spinning and increases or decreases speed to cause an attitude change 2 The previous exercise demonstrated the use of a positive bias momentum 59 AIT Now we are going to test the integrated functionality of the EyasSat Torque Rod X and EyasSat Torque Rod Y Due to the weak and disturbed magnetic field from the earth in most buildings we are going to use a permanent bar magnet at your bench to create a stronger localized field 60 AIT Place the bar magnet directly below your suspended EyasSat EyasSat User s Manual 5 0 27 May 2011 93 61 AIT Record the value of total bus power before the next step A not play with the magnets or allow magnets to touch each other these are very strong magnets 62 AIT Click on the X button This exercises the EyasSat Torque Rod X with normal polarity Note green LED on ADCS module 63 AIT Record the new bus power value with the X torque rod on 64 AIT Observe the movement of EyasSat It may take a moment or two to react 65 AIT Click the X button This exercises EyasSat Torque Rod X with reverse polarity Note red LED on ADCS module
27. Interface tab 69 EPS Power up the EyasSat EPS Module with the red plug and 9v power supply via the EPS GSE connector on EyasSat EPS Module if you had the EyasSat sitting on a book put it back on the flat table EyasSat User s Manual 5 0 27 May 2011 38 70 EPS You should see a startup message such as Power EyasSat Power Startup Firmware Version 5 0 2 23 2011 as shown in18 Your version number and date may be newer If you do not get a startup message re verify your COM configuration EyasSat Control Panel He Attitude Det Control ADCS Communications Comm Orbit Determination GPS Flex Experiment EXP Text Only Interface Thermal Electrical Power EPS Data Handling DH EyasSAT Status EyasSAT Power Startup Firmware Version 5 2 5 13 11 P Sep 1 V Batt 7 83 I Batt 84 00 V SA 7 65 I SA 6 00 I MB 72 00 T Batt 22 61 V 5 4 83 5v 98 00 V 3v 3 18 I 3v 16 00 T TopA 4 71 T TopB 4 71 T Base 4 71 T Wht 4 71 T Blk 4 7 S 0 Telemetry Command Received Manual Telemetry Command Window Data Logging Idle ft Send Command CAEyasSat MyEyasSATFile bt Enable File Log Status EyasSAT Idle Figure 4 13 EyasSat Control Panel Showing EPS Module Startup 71 EPS On the computer enter t case sensitive in the Manual Telemetry Command Window box and click Send Command or hit the enter key as shown in Figure 4 13 72 EPS You should then see a line of telemetry from the module as
28. LAB MATERIALS AND EQUIPMENT 70 7 5 BYASSAT ADCS HARDWARE ACCEPTANCE TESTS eee 71 7 5 1 EyasSat Torque Rod X and EyasSat Torque Rod Y Inspection 71 42s EyasSat Torque Rod X and EyasSat Torque Rod Y Characterization 72 7 5 3 EyasSat Sun Sensor T and EyasSat Sun Sensor B Inspection 72 7 5 4 EyasSat Sun Sensor and B Functional Test esses 74 7 3 95 EyasSat Yaw Attitude Sensor Inspection eese 76 7 5 6 EyasSat Yaw Attitude Sensor Functional Test 77 7 7 EyasSat ADCS Module Inspection 77 7 5 8 EyasSat ADCS Module Functional Tesi ee er PER ERR 78 7 5 9 EyasSat ADCS Module Software Functional Test eese 79 7 6 ADCS MODULE INTEGRATION AND TEST seen 81 7 6 1 EyasSat ADCS Comm C amp DH and EPS Integration sess 1 7 6 2 EyasSat ADCS Comm C amp DH and EPS Integrated Functional Test 81 8 THERMAL SUBSYSTEM amp STRUCTURAL 84 Boe JEXEGOVERVIEW 5 a diis oue etu DUNG LA ta sb ac URS 84 8 2 EYASSAT STRUCTURAL INTEGRATION LAB OBJECTIVES eee 84 8 8 EYASSAT THERMAL SUBSYSTEM BLOCK 85 8 4 LAB MATERIALS AND EQUIPMENT istos tester S QUSS 85 8 5 EYASSAT ASSE
29. MBLY AND nenne 86 8 5 1 Final EyasSat Stack 86 8 6 EYASSAT FULL FUNCTIONAL INTEGRATED TEST eee 89 6 6 1 Eyassat Power Up T8513 educ e cote dnos 89 8 6 2 EyasSat Sun Sensor Integrated Functional Test esses 92 8 6 3 EyasSat Yaw Attitude Sensors Integrated Functional Test 92 8 6 4 EyasSat ADCS Test the Freefall Environment esses 92 6 6 5 EyasSat Closed Loop Attitude Control 5 94 8 7 EYASSAT THERMAL AND SOLAR 95 8 7 1 EyasSat Baseline Thermal Characterization eese 95 8 7 2 EyasSat Solar Array Thermal Characterization eese 95 8 7 3 EyasSat Thermal Control Surface Thermal Characterization 95 EyasSat User s Manual 5 0 27 May 2011 5 EyasSat User s Manual 5 0 27 May 2011 List of Figures Figure 2 1 EyasSat Subsystem Stack aic e nS Eta do aee 11 Figure 2 2 Basic EyasSat System rev C pictured sese 12 Figure 3 1 EyasSat Stucture without Electronics or Sensors 13 Figure 3 2 EyasSat Mass oec tat dees tere aM Un dita sae OR PUER 15 Figure 3 3 Measuring for Center of Mass die eo bead 16 Figure 3 4 Measur
30. Manual 5 0 27 May 2011 100 For Step 3 click on Finish Text Import Wizard Step 3 of 3 This screen lets you select each column and set Column data format the Data Format General General converts numeric values to numbers date C Text values to dates and all remaining values to text C MDY Advanced Data preview Do not import column skip Cancel Back Once the Excel spreadsheet opens select the entire sheet click on the grey box to the left of A and above 1 Choose Data then Sort Select Column C Click on OK Use the Excel graphing function to plot your data You will need to make the timestamps in Column B the label for the X axis EyasSat User s Manual 5 0 27 May 2011 101 Appendix D EyasSat C amp DH Software Flowchart initialize get USART ISRs main while loop rx counterx Yes gt 0 EyasSat User s Manual 5 0 process command send telemetry haveTelemetry 0 27 2011 Increment telemCount telemCount get telemetry haveTelemetry 1 telemCount 0 0 ISR 102 Appendix E EyasSat Command List EyasSAT COMMANDS Command Setting Values V 4 1 5 28 2009 Description DATA HANDLING DH O N A Un U N EyasSat User s Manual 5 0 oll oll
31. SB 5 0 4 Flow Control NONE Data Bits Stop Bits Test Query Host Setup User Com Ports Ethemet Ports AT command Setup ASCII Hex Command Character cc 28 Guard Time Before 1000 Guard Time After AT 1000 r Modem Flash Update No baud change Figure 6 4 X CTU Setup Screen 10 COMM Click on the Range Test tab at the top of the screen You will see a screen similar to that shown inFigure 6 5 EyasSat User s Manual 5 0 27 May 2011 64 PC Settings Range Test Terminal Modem Configuration Start Clear Stats Advance gt gt gt Test Loop Back 0123456789 38ABCDEFGHIJKLMNO Transmit Receive 32 COMI 9600 8 N 1 FLOw NONE Figure 6 5 XCTU Com Test Screen 11 COMM Enable the grayed RSSI Received Signal Strength Indicator bar graph by clicking the check box below it 12 COMM Click Start once then wait a few seconds 13 COMM You should get repeated Time out waiting for data in the data window The Bad counter should also start incrementing Wait a few seconds 14 Click Stop 15 COMM Click the Clear Stats button 16 COMM Click Start 17 COMM Connect the 5V Power Supply to the EyasSat Comm Module power port 18 COMM You should start seeing data in the window The Good counter should start incrementing 19 COMM Restart the test and all
32. age Figure 4 9 I V curve amp Peak Power Point for the Solar Array The purpose of finding an I V curve of an assembled solar array is to determine at which point maximum power is delivered from the solar array and to understand how match an array to a battery Most EPS systems use a method called direct energy transfer In this method the engineer designs and tunes the system to operate most efficiently under expected flight conditions On more complex system where power must be optimized peak power racking PPT is used where dynamic measurements are made and the interface adjusted to assure peak power delivery in all lighting and load conditions 4 7 5 EyasSat Solar Array Characterization The Solar array test kit see EyasSat website is needed for this procedure These tests achieve the best results when performed outdoors in bright sunlight however a sun LED lamp available as part of the test kit may be used if going outdoors is not convenient or if the weather does not permit Halogen lamps can work as well BUT once you illuminate the EyasSat Solar Array you need to proceed quickly but safely in making all the measurements because a halogen lamp raises the array temperature rapidly lowering its efficiency EyasSat User s Manual 5 0 27 May 2011 29 See Figure 4 8 which illustrates the set up for this solar array test See Figure 4 10 fora circuit drawing of this configuration e Voc open circuit voltag
33. al value 86 AIT Turn the halogen lamp off 87 AIT Allow the solar array to cool and reach thermal equilibrium 8 7 3 EyasSat Thermal Control Surface Thermal Characterization During this portion of the lab your team will characterize the performance of the two thermal control surfaces EyasSat User s Manual 5 0 27 May 2011 95 88 AIT Illuminate the EyasSat Thermal Panel B and EyasSat Thermal Panel W with the halogen lamp at your bench at a distance of approximately 6 89 AIT Record the initial temperature of the thermal surfaces and allow them to achieve thermal equilibrium then record that temperature again Also observe if any other internal components show thermal changes and allow for full system thermal equilibrium 90 AIT Turn the halogen lamp off 91 AIT Allow all EyasSat components to cool off and reach thermal equilibrium Save your session file to a USB drive or network drive for later use Follow the steps in appendix on page 100 to learn how to correctly import this data into Excel for graphing 92 AIT Power down EyasSat by taking it off of the free fall stand and setting it on the table Stow all other equipment as required EyasSat User s Manual 5 0 27 May 2011 96 Appendix A Block Diagram Wireless Link 5 VDC fixed TTL RX from IHU TTL TX to IHU ETTPTFTTT EyasSat User s Manual 5 0 27 May 2011 97 Appendix B EyaBus Description
34. assumed that the EyasSat is in a disassembled state at this point in the exercise Ser Figure 8 3 During this section of the lab your team will integrate your existing EyasSat Stack with the spacecraft structure In addition all sensors actuators and other devices will be electrically connected to the appropriate points on the stack 8 5 1 Final EyasSat Stack Assembly 1 AIT It is recommended that you use cotton or latex gloves before handling the EyasSat Structure in order to keep it clean 2 AIT Disconnect the EyasSat Antenna from the EyasSat Comm Module if it has been left in that configuration Set it aside you will mount it on the EyasSat Top Assembly shortly Figure 6 3 EyasSat Structure Ready for Integration EyasSat User s Manual 5 0 27 May 2011 86 D C n Figure 8 5 Assembly of the structure to the electronics stack 3 AIT Make sure that the front cover of the structure is removed as shown in the figure this allows access needed to engage cables for the thermal solar and top panels 4 AIT Insert and finger tighten the four black stack rods as shown in Figure 8 7 Note they are different lengths as required Figure 8 7 87 EyasSat User s Manual 5 0 27 May 2011 5 Lift the structure by its lift point this is a two person job While holding the structure above the electronics stack as shown in Figure 8 4 have your partner reach in through the front of the structure and connect the t
35. ated look on the bottom of EyasSat and you will see the switch You have already looked in detail at the battery and array so lets examine the other main parts of the EPS The power from the battery is distributed to two voltage converters that create a 5V bus and a 3 3V bus The five volt bus and the raw battery power are both supplied to the long PCI connector at the back of the unit so that power is distributed EyasSat User s Manual 5 0 27 May 2011 35 the stack to other boards Other than the SEP switch this power is not switched anywere is the system in other words it is always active This is called the essential bus of the spacecraft I can t turn it off Note that the 5v and 3 3v outputs from the converters are also routed through switches and then to the same PCI connector These are sources of power which you can control by command They activates parts of the satellite or its payload that you don t need to have on all the time If you look at Figure 16 and compare to the actual board you will see a series of 8 blue LEDs that will come on when you activate these switches There are four other LED indicators that you should understand They tell you when the EPS is operating as it should When under ground power the 9V supply you will see a red LED indicating that the red plug is connected When operating on the battery power you will see a green LED indicating that the green plug is connected In both
36. budget table and note the slightly increased value from the readings you saw in the EPS lab 72 C amp DH Verify that you can command the EyasSat C amp DH Module by repeating steps 53 C amp DH through 55 C amp DH of the EyasSat C amp DH Module Software Functional Test on page 55 73 C amp DH Click on the Data Handling DH tab on the EyasSat Control Panel 74 C amp DH Use the EyasSat Control Panel pushbutton controls shown in Figure 5 9 instead of text commands to verify steps 53 C amp DH through 55 C amp DH of the EyasSat C amp DH Module Software Functional Test on page 55 Update the clock if necessary and set the Telemetry Delay to 1 second EyasSat User s Manual 5 0 27 May 2011 58 I EyasSat Control Panel lo xi Attitude Det Control ADCS Communications Comm Orbit Determination GPS Experiment EXP Data Handling DH Text Only Interface Thermal Electrical Power EPS Exp 3 Unattached System Settings System Time 23 02 52 Telemetry Delay 2 00 setH 1 Update TD Command Timeout 3 0 setM 1 Update cTO Call Sign 0 00 sets 1 Update Callsign Errors Battery Voltage 9 5 V EyasSAT Response Power Module Attached Understanding Space 3rd Edition Status EyasSAT Communicating Figure 5 9 EyasSat Control Panel Data Handling Pane 75 C amp DH Click on the Text Only Interface tab in the EyasSat Control Panel 76 C am
37. ciples of the system the battery should always be charged with the charger provided 80 EPS Setup the system so that the solar array is in its test stand or a lab assistant is holding it stable get your light source ready ideally use sun through the window or alternatively the 1 sun LED source Use the extension jumper cable in the EyasSat kit to connect the solar array to the power board being careful to plug it in properly it will only go one way 81 EPS Install the Green flight plug in the power board external connector 82 EPS Restart the GUI and make sure the serial connector and USB plug is hooked up 83 EPS Start the system by installing the jumper across the sep switch 84 EPS Verify the start up message on the text page 85 EPS Send the 4 command to get telemetry 86 EPS Using a sheet of dark paper or cloth cover the array so This Red that not light is on it Jumper is used to 87 EPS Record V Batt V SA I Batt I SA and I MB activate the EPS 88 EPS Now illuminate the array with a bright light source EyasSat User s Manual 5 0 27 May 2011 42 89 EPS Repeat step 87 and note the differences how much of the main bus current is being supplied by the SA Is the battery still discharging What should the sum of the currents look like for this case 90 EPS Disconnect the EyasSat solar array from the EyasSat EPS Module if you are not going to proceed with the next set of lab instruction
38. ck together put them where they won t get lost 44 EPS Now carefully work the top set of boards loose from the bottom power board at the EyasSat Bus connection These are tight so be careful and don t wiggle too much try to pull straight up You may want your lab partner to help you the power board is now ready for stand alone testing 45 EPS Visually inspect the EyasSat EPS Module to ensure that there are no loose wires connectors or solder connections 46 EPS Compare your EyasSat EPS Module to the one in Error Reference source not found Depending on which version you have the location of detailed electrical components or the values may vary however the connectors test points battery mounting location of the bottom sun sensor and other major features will be the same The version number is stamped on the board as shown its serial number is also indicated written by hand On the Atmega 128 processor we have placed a sticker indicating which software version is loaded Please record oll of these in your notebook To gain a better understanding of the hardware review the EyasSat EPS block diagram in Figure 4 1 and compare it to the physical hardware shown in Figure 4 11 4 6 2 EyasSat EPS Module Functional Test The purpose of this test is to verify that the EyasSat EPS Module can deliver 5 and 3 3 VDC Before we begin this test in earnest it may be useful to go over a more detailed view of the EyasSat powe
39. coefficients to stored user coefficients set current coefficients to 10 off for exercise set stored user coefficients to current coefficients factory reset of coeffients a w 900 to 900 5 900 to 900 6 900 to 900 x 0 1 2 y 0 1 2 v 0 1 2 s d n c n u 1 EyasSat User s Manual 5 0 Z axis wheel speed X axis wheel speed Y axis wheel speed X torque rod off polarity X polarity Y torque rod off Y polarity Y polarity Z torque rod off Z polarity Z polarity telemetry scaling on off Set the dead band for auto Z control Set the wheel speed delta for auto Z control Turn off high speed telemetry Turn on high speed telemetry to UMB 27 May 2011 104 Turn on high speed telemetry to Payload Radio 1 0H Activate closed loop Z wheel control Send one tlemetry string to UMB 01331 32767 to 32767 32767 to 32767 32767 to 32767 32767 to 32767 O coefficient lockout 331 enable set X accel coeff a set X accel coeff b set Y accel coeff a set Y accel coeff b i 32767 to 32767 set yaw rate gyro coeff j 32767 to 32767 set yaw rate gyro coeff b k 32767 to 32767 set roll rate gyro coeff 1 32767 to 32767 set roll rate gyro coeff b m 32767 to 32767 set pitch rate gyro coeff a n 32767 to 32767 set pitch rate gyro coeff b set Z accel coeff a 32767 to 32767 32767 to 32767 set Z accel coeff b
40. e and Is short circuit current are the endpoints on your I V curve on the axes If you are getting bad or no readings from the multimeter in current measuring mode consult with your instructor as the meter s internal fuse could be blown The remaining points on the I V curve will be found by measuring current and voltage when various load resistors are connected to the array Begin by getting the data for a point near the maximum power point The voltage associated with this point Vmp can be approximated as 0 7 Voc Imp is approximately Isc Using Ohm s law the load resistance that should be near the max power point is Rmp Vinp Imp You should find a resistor in your kit closely matching that value Higher values of resistance lower current will produce data points right of the knee of the curve while lower values of resistance will produce data points left of the knee of the curve higher current EyasSat User s Manual 5 0 27 May 2011 30 Schematic to be provided Figure 4 10 Solar Array Characterization Schematic Always handle the array with gloves and keep dust and finger prints off the surface Never lay the solar array down on a hard surface with the cells facing downward you can lay it down but put it on a soft cloth 32 EPS Measure and record by reading the voltage off the meter designated as V with no load e leave the load terminals open The meter designated as A should show 0 mA 33 EPS Measur
41. e 4 15 Close up of EyasSat EPS Module connected to SA and Thermal Panel 4 9 2 _EyasSat EPS Integrated Functional Test 92 EPS Make sure the GUI is set up hooked up and ready to record TLM 93 EPS Connect the thermal panel to the EPS using the extension cable EyasSat User s Manual 5 0 27 May 2011 44 94 EPS Connect the solar array to the EPS if not already connected from the previous section using the extension cable and lay it face up on the table 95 EPS Using the Green plug and the red jumper activate the EPS 96 EPS Verify that the green Power LED illuminates and that the two yellow LEDs illuminate N Be careful in the next two steps to use extreme delicacy while removing these components or the bus pins will bend and possibly break 97 EPS Connect the EyasSat Data Interface to the UMB port of the EyasSat EPS Module 98 EPS Send a t and record all of the telemetry notice now that you also have telemetry from the thermal panel These are labeled T BLK T WHT T BASE T TOPA and T TOPB 99 EPS Shine a light source on the panel and see if the temperature changes 100 EPS Using some cold spray from the accessory kit spray the base of the two copper rods where they join and note how T BASE changes 101 EPS Keep sending 4 so you can watch the cold propagate to the top sensors as well Record your observations 102 EPS The EPS as a Subsystem has now completed checkout If you are not proceeding
42. e 4 7 EyasSat Solar Array Back panel View Solar Array jumpers for string configuration Solar Array Connector to SA GSE or Power board 2 EPS Visually inspect the EyasSat Solar Array to ensure that there are no loose parts wires connectors or solder connections EyasSat User s Manual 5 0 27 May 2011 26 4 7 3 EyasSat Solar Array Abbreviated Functional Test The purpose of this test is to ensure that the temperature sensor thermistor and power wiring to the solar cells of the EyasSat Solar Array are properly connected Later a more detailed test can be performed using the solar array test kit The test kit consists of a stand which will hold the array when it has been removed from the structure a small electrical box EGSE or Electrical Ground Support Equipment and a light source for testing the array when the sun is unavailable The stand enables you to tilt the array so that it can point at a light source room light the LED light source which comes with the solar array study kit a halogen work light or the sun The EGSE breaks out the signals which come from the array and enables you to put various loads on the array and develop an I V curve more on that later For this first test called an abbreviated functional we are really just testing aliveness of the array We will make sure that the thermistor is hooked up and working It is glued to the back of one of the solar cells If you look between
43. e 5 3 Curve Expert Data Entry Screen eade eens anid 51 Ligure 4C urve Expert Einer n ooa Ore do estas a 51 Figure 5 5 Curve Expert Solution i a eii od e e e ie ende pe ete 52 Figure 5 6 ByasSat CC DII Module ideis 53 Figure 5 7 5V Power Supply siue aec tu UI e D t RES aa 54 Figure 5 8 Proper EyasSat Module 57 Figure 5 9 EyasSat Control Panel Data Handling Pane eee 59 Figure 5 10 EyasSat Control Panel Electrical Power Subsystem Pane 60 Figure 6 1 EyasSat Communications System Block Diagram esse 61 Figure 6 2 EyasSat Comm Module iD tob tecto edic e audes 62 Figure 6 9 EyasSat RP GSE iacere eii IR e ina et Reece 64 d XC TL Setup Sereen oic dad niri ui ue 64 Figure 6 5 XCTU Com Test Screen 2 55 Uie bii eb a 65 EyasSat User s Manual 5 0 27 May 2011 7 Figure 7 1 EyasSat ADCS Block 22 2 1 70 Figure 7 2 EyasSat Torque Rod Mounted to Base PCB sse 71 Figure 7 3 Torque Rod Test Points on Power 72 Figure 7 4 EyasSat Top Sun Sens OP utei n des 73 Figure 7 5 Bottom Sun Sensor ues eic dicet e tedio deed raga 73 Figure 7 6 EyasSat sensor breakout repe dt D ead 74 F
44. e and record off the meter designated as A by shorting out the test leads where the load resistor Rz will be placed The meter designated as V should show 0 VDC 34 EPS Use a resistor with a value close to Rmp in your test setup and record I and V If you are unclear how to read the values of a resistor use another multimeter to verify if available 35 EPS Repeat the previous step but choose other resistor values to get data points on either side of the max power point 36 EPS Disconnect the wiring used in this test and turn off the LED or halogen lamp if used EyasSat User s Manual 5 0 27 May 2011 31 37 EPS Optionally repeat steps 22 EPS through 36 EPS for other combinations of cells see the circuit board on the back of the array to configure the combination that you want 38 EPS Disconnect the wiring used in this test Once you have collected enough data points plot two curves using Excel s XY scatter plot One curve should show I vs V The other should show P vs V e Your I V curve should be similar to the one in Figure 4 9 however your data points will be different Do not proceed with the lab until you have a good curve Your instructor may provide additional resistors to make a smoother curve EyasSat User s Manual 5 0 27 May 2011 32 4 8 EyasSat EPS Module Acceptance Tests Fyps r Distribution Figure 4 11 EyasSat EPS Module 4 8 1 EyasSat EPS Module Inspection Th
45. e purpose of this test is to ensure that your EyasSat EPS Module was delivered in the proper configuration 39 EPS Before beginning this section we will need to do some disassembly of the EyasSat The steps are all described here however if the instructor is interested a short video will soon be available on our website The first step is to remove the four thumbscrews the hold the clear front cover this is so you can reach inside and disconnect various components Place the cover on a cloth or paper towel to prevent scratches and place the screws in a cup or holder of some sort so they are not lost EyasSat User s Manual 5 0 27 May 2011 33 40 EPS Once the front cover is removed you can reach inside and disconnect the following A remove the antenna and if you have one the GPS cable these are on the front and extend up to the top panel Just unscrew the SMA type connectors and leave the cable hanging there B reach around the right side and disconnect the thermal panel connector at the bottom power board C likewise disconnect the solar panel cable and top panel cable on the left side 41 EPS Now remove the four thumbscrews at the base of the EyasSat these are in the center bottom of each of the side panels 42 EPS You are now able to lift the EyasSat structure by its lifting handle off of the base which contains the electronic stack 43 EPS Now you are able to remove the four plastic screws that hold the electronics sta
46. e removing these components or the bus pins will bend and possibly break 55 COMM_GENTLY remove the EyasSat LED Test Module by slowly wiggling it out 56 COMM _ Stow all of your EyasSat hardware in the appropriate lab bench storage bins and drawers Power down your workbench and ensure it is ready for the next users The acknowledged delivery function uses 16 bit Cyclic Redundancy Check CRC protocol to detect an error If the receiver detects an error in the message it requests that the transmission be sent again It will retry the communication up to the number of configured times e EyasSat User s Manual 5 0 27 May 2011 68 7 Attitude Determination and Control Subsystem 7 1 EyasSat ADCS Lab Overview This lab will expose you to a miniaturized spacecraft attitude determination and control subsystem ADCS which is composed of the EyasSat ADCS Module with integrated solid state three axis gyroscope and accelerometers two actuators reaction wheel and torque rod set and three external sensors top bottom sun sensor and yaw attitude sensor Acceptance tests will be performed on the EyasSat ADCS Module actuators and sensors to verify physical compliance and workmanship of the contractor The EyasSat ADCS Module will then be characterized individually Once the component level testing is complete the EyasSat ADCS Module will be integrated to create the final EyasSat stack The torque rods and external sensors wi
47. e version is on a label on an integrated circuit the serial number is hand written in the bottom corner 26 ADCS Verify that there are no loose wire clippings or other material in the EyaBus connectors on the bottom of the module and that the connector pins are not bent 7 5 8 EyasSat ADCS Module Functional Test The purpose of this test is to ensure that the EyasSat ADCS Module meets the basic performance requirements EyasSat User s Manual 5 0 27 May 2011 78 27 ADCS Connect the 5V Power Supply to the EyasSat ADCS Module 5 VDC power port 28 ADCS Verify that the red VCC5 LED illuminates 29 ADCS Disconnect the 5V Power Supply from the power port of the EyasSat ADCS Module 7 5 9 EyasSat ADCS Module Software Functional Test The purpose of this test is to verify that the software running in the onboard microcontroller is able to properly start up display telemetry and properly interpret commands 30 ADCS Connect the EyasSat Data Interface to the UMB port on the EyasSat ADCS Module 31 ADCS Open the EyasSat Control Panel shortcut on the desktop USB users verify COM port setting for umbilical connection and go to the text only tab 32 ADCS Reconnect the 5V Power Supply to the 5VDC power port of the EyasSat ADCS Module 33 ADCS Connect the 3 3V Power Supply to the 3VDC power port 34 ADCS You should see the ADCS EyasSat ADCS Startup Firmware Version 4 0 12 26 2007 startup message Your version number and date
48. ed on an over launch mass of 3kg See Figure 3 2 How much margin for growth is there Using the scale provided in the accessory kit weight the various components of EyasSat and compare to their individual subsystem budgets make sure you know if you are measuring kg or lb Are some over Some under How would management deal with these overages If the launch vehicle has given a 3Kg budget to EyasSat as its launch mass should we have any additional reserve on that 3Kg If so how could this be used On real satellite systems one usually establishes estimates of your subsystem or component at various stages in the design process Initially at the requirements review a budget is established and margin and reserves established At PDR CDR and then finally at the pre integration review these numbers are updated It is not uncommon for Spacecraft to encounter mass problems that is why the reserve is larger at the beginning of the program and typically gets used up as the system matures what matters in the end is the not to exceed mass allocated by the launch vehicle 3 6 System Center of Mass CM Engineering Objective 2 and 3 One of the other important factors is getting the satellite to have the right center of mass This matters to the launch vehicle frequently has stringent requirements for this In this exercise we are going to take our initial measurement performed above then determine the center of mass of EyasSat Last of a
49. edges Command ES7 10 32 13 R Radio Acknowledges Command 45 COMM You should again get the normal scrolling telemetry EyasSat User s Manual 5 0 27 May 2011 67 46 COMM Disconnect from the C amp DH telemetry port and connect the USB to the GSE instead we will now operate through the radio link 47 COMM Change COM port in X CTU for EyasSat RF GSE connection 48 You should now get telemetry but you will be getting multiple copies depending on how many retries you selected 49 COMM Talk directly to the EyasSat RF GSE by typing in X CTU the following commands use the Assemble Packet window as before remembering the enter keystroke wait 1 sec for you are now talking to the RF GSE unit 50 COMM ATRRX lt enter gt X is the number of retries 1 9 ATRN lt enter gt enables feature ATWR lt enter gt this writes the channel number to memory ATCN lt enter gt this closes the session 51 COMM The telemetry stream should return to normal you should now only get one copy This verifies acknowledged delivery function 52 COMM Close X CTU do not minimize 53 COMM Once you have collected and recorded all the data you need for the lab power down and disconnect all cabling Leave the EyasSat integrated as a stack 54 DOMM Remove the red jumper from the 2 pin connector to power down the EyasSat EPS Module and remove the green plug Be careful in the next step to use extreme care whil
50. ell 17 C amp DH Sendan 51 command 18 C amp DH Senda command 19 C amp DH Record the calibrated values of the I 5V and V 5V telemetry points in the appropriate before columns in the workbook or spreadsheet 20 C amp DH Finally record the corresponding voltage and current readings from the multimeters in the appropriate Calibration meter column in the workbook or spreadsheet 2 C amp DH Calculate the efficiency at this load by determining the power in from the battery and out on the 5V line of the EyasSat EPS Module use the calibrated EyasSat values for I Batt and V Batt and the meter values for I 5V and V 5V The difference between power in and power out is consumed by the power conversion circuitry Efficiency Pin Pout Pin EyasSat User s Manual 5 0 27 May 2011 49 Pin is the product of I and Poy is the product of I 5 5V on the 5V supply side e Ideally V SV will remain constant by voltage regulation despite variations to the system load conditions and changing conditions of the input power In reality 5V will dip slightly under load 22 C amp DH Repeat steps 14 C amp DH through 21 C amp DH but use 51 100 and 150 or similar value load resistors 23 C amp DH Atthis point you may use the example spreadsheet to automatically determine the a and b coefficients for each data point or follow the instructions below to use Curve Expert which uses
51. eptance Tests EyaBus Connectors Figure 4 2 EyasSat EPS Subsystem Block Diagram 4 6 1 EyasSat Battery Pack Inspection The purpose of this test is to ensure that your EyasSat Battery Pack was delivered in the proper configuration The Lithium Ion EyasSat Battery Pack is attached to the bottom of the EyasSat EPS Module the bottom most layer of the electronics stack and the largest of all the boards by Velcro patches for easy changeout It will be tested later First we will need access to the test points on the power board The whole EyasSat doesn t have to be disassembled The clear bottom allows inspection of the battery 1 EPS Remove the four thumbscrews from the front clear access panel 2 EPS Remove the front clear access panel and store it so that it will not be scratched 3 EPS Store the thumbscrews in a secure location so that they are not lost 4 EPS Visually inspect the battery pack through the case to ensure that there are no loose parts wires connectors or solder connections the battery solders to the bottom of the board you can see the joints clearly Compare your EaysSat with Figure 6 provide power during eclipse times and to provide peak power when the payload and or subsystems draw the greatest load 3 The purpose of secondary rechargeable batteries on a spacecraft is to EyasSat User s Manual 5 0 27 May 2011 20 4 6 2 EyasSat Battery Pack Functional Test The purpose of this test is t
52. erify your command being sent before sending Command Text Response Verify proper blue light is on 11 lt gt Power 3 3v 1 On 10 lt send gt Power 3 3v 1 Off 21 lt gt Power 3 3v 2 On 20 lt send gt Power 3 3v 2 Off 31 lt gt Power 3 3v 3 On 30 lt send gt Power 3 3v 3 Off 41 lt gt Power 5v 4 On 40 send Power 5v 4 Off 51 lt gt Power 5v 5 On 50 lt send gt Power 5v 5 Off 61 send Power 5v 6 On 60 lt send gt Power 5v 6 Off 71 lt gt Power 5v 7 On 70 lt send gt Power 5v 7 Off l send Power 5v 8 On 0 send Power 5v 8 Off Reference the EPS block diagram so that you can see what you are really doing here Each of these switches is connected to a different pin on the bus connector and provides power to different devices which can be plugged into the stack A blue light on indicates that the switch has closed and voltage is provided to that bus pin 74 EPS You have been operating on GSE power Verify that the SEP variable is listed as 0 75 EPS Disconnect the red plug and connect the green flight plug which will enable the battery and solar array to connect to the bus 76 EPS Lift the EPS assembly connected to its baseplate about or more off of the table and support on edges with a book or some other spacer 77 EPS Senda 4 command and verify that the Sep telemetry has a value of 1 78 EPS
53. g Yaw 00 deg sec Yaw Sensor 2 0 5 Sun Bottom 0 Yaw Sensor 3 0 AccelY 00 g Pitch 00 deg sec Yaw Angle 0 Yaw Sensor 4 0 AccelZ 00 g Roll 00 deg sec Attach ADCS Errors EyasSAT Response Power Command 6 Sent a 1 000000 Status EyasSAT Stalled Figure 7 11 EyasSat Control Panel ADCS Pane 67 ADCS Remove the GSE power plug to power down the stack EyasSat User s Manual 5 0 27 May 2011 83 8 Thermal Subsystem amp Structural Integration 8 1 Lab Overview This lab will take you through the process of structural integration of the EyasSat Stack with the EyasSat Structure and all other components that have been tested and verified throughout the lab You will then perform an integrated functional test complete ADCS testing and then end with a thermal analysis test 8 2 EyasSat Structural Integration Lab Objectives Objective 1 Perform acceptance and verification tests on the EyasSat Structure Objective 2 Integrate the full EyasSat Stack into EyasSat Structure Objective 3 Verify integrated EyasSat operational status Objective 4 Verify ADCS functionality Objective 5 Perform thermal response test EyasSat Control Panel Attitude Det Control ADCS Orbit Determination GPS Electrical Power EPS Flex Experiment EXP Data Handling DH Text Only Interface EyasSat Thermal Panel EyasSat Temperatures us Ambient 22 7 Battery 25 69 DH 23
54. g the power board and bottom structure panel on the table 14 ADCS Do not disconnect the test setup to the top set of sensors You will use it again in the next exercise EyasSat User s Manual 5 0 27 May 2011 74 218 9 Figure 7 7 Bottom Sun sensor test point Power Board EyasSat User s Manual 5 0 27 May 2011 75 7 5 5 EyasSat Yaw Attitude Sensor Inspection The purpose of this test is to ensure that your EyasSat Yaw Sensor is working properly Figure 7 8 EyasSat Yaw Attitude Sensor on Top Panel 15 ADCS Compare your EyasSat Yaw Attitude Sensor to the one in Figure 7 8 Styles may vary 16 ADCS Visually inspect the EyasSat Yaw Attitude Sensor and make sure that the extension cable is fully engaged in the connector The yaw sensor is composed of four small photo diodes that can precisely determine the location of a bright light source by using the power output cosine rule EyasSat User s Manual 5 0 27 May 2011 76 7 5 6 EyasSat Yaw Attitude Sensor Functional Test The purpose of this test is to ensure that the EyasSat Yaw Sensor meets the basic performance requirements 17 ADCS Verify your multimeter is in Resistance mode 18 ADCS Use the Test breakout box connected to the top panel as shown in Figure 7 6 the mapping of each yaw sensor to the various pins on the breakout box are given in the table below TBR Sensor pin Sun sens Sun sens Yaw 2 Yawl X Yaw 4 Y Yaw3
55. ghts are active Verify the startup message on the text interface page of the GUI EyasSat User s Manual 5 0 27 May 2011 48 If you do not get a startup message verify your COM configuration 9 C amp DH computer send a t command You should then see a line of telemetry from the module as was shown in Figure 4 14 EyasSat Control Panel Showing EPS Module Telemetry 10 C amp DH Send an 51 command You should get a Power Telemetry Scaling On message This is the normal mode 11 C amp DH Senda 4 command again you will see a line of telemetry just like you saw two steps previously 12 C amp DH Send s0 command You should get a Power Telemetry Scaling Off message 13 C amp DH Senda t command to get a line of telemetry This time the telemetry will be shown in what is called raw counts which is the decimal equivalent of the binary value representing the converted analog signal ranging from 0 to 1023 We are going to check these values across a range of loads for the Battery Current I Batt and separately for the 5 volt supply current I 5V 14 C amp DH Connecta 300 resistor or value close to it as the load as shown in Figure 5 2 on the 5V bus 15 C amp DH Senda t command 16 C amp DH Record the raw count values in the columns labeled Calibration Counts for I 5V and V 5V telemetry points You should enter the values into the calibration spreadsheet as w
56. hat the structure does not interact with the control system of the launch vehicle This is a very complex process and beyond the scope of discussion and demonstration using EyasSat but the student should understand that it is yet another constraint on the design of a real system EyasSat User s Manual 5 0 27 May 2011 17 4 Electrical Power Subsystem 4 1 EyasSat EPS Lab Overview This lab will expose you to a design typical of a operational spacecraft electrical power subsystem EPS containing a solar array a battery and a power control switching module Acceptance tests will be performed on each component to check physical compliance and basic functionality Verification tests will then be performed to ensure that the components perform as specified The solar array will then be characterized as each unit will have its own personality Once the component level testing is complete they will be integrated to create the EyasSat EPS More detailed exercises are available though our EyasSat user group for solar array studies and power transfer 4 2 EyasSat EPS Lab Objectives Objective 1 Perform acceptance and verification tests on the EyasSat Battery Pack includes battery charging Objective 2 Perform acceptance and verification tests on the EyasSat Solar Array Objective 3 Characterize the performance of the EyasSat Solar Array by creating an I V curve Objective 4 Perform acceptance and verification tests on the EyasSat EPS M
57. he clock set commands To set the time send the following commands separately chXX set hour 24 hour format cmXX set minute and csXX sets seconds Leading Os are optional for single digits 56 C amp DH Notice that there are a pair of telemetry lines one starting with an I and one starting with a T the third line with is just a separator line 57 C amp DH The first line is the I line which is telemetry from the C amp DH and is described next EyasSat User s Manual 5 0 27 May 2011 55 The fields in the C amp DH telemetry line are as follows TelemDelay number of seconds between TLM reports CmdTimeOut number of seconds DH waits for cmd e Pwr indicates if power board attached ADACS indicates if ADACS board attached Expl indicates if Experiment 1 board attached Exp2 indicates if Experiment 2 board attached Exp3 indicates if Experiment 3 board attached 58 C amp DH The second line is the T line which is the thermistor input bank on the C amp DH The telemetry values are in and are explained below The fields in the Thermal telemetry line are as follows DH EyasSat DH Module Qu EyasSat Solar Array Exp Experiment this is the thermistor plugged into the connector on the side of the board Amb Ambient temperature 59 C amp DH Verify that the C amp DH temperature is at or slightly above the ambient or room temperature 25 27 C 60 C amp DH Disconnect the 5V power supply from the p
58. he instructor need additional backup information they should contact EyasSat LLC EyasSat User s Manual 5 0 27 May 2011 46 5 4 EyasSat C amp DH Subsystem Block Diagram Figure 5 1 EyasSat Data Handling Block Diagram 5 5 Lab Materials and Equipment EyasSat EPS Module EyasSat C amp DH Module EyasSat Power Test Harness EyasSat Data Interface Multimeter 2 Computer w power supply 5V Power Supply Wire jumper kit Red and Black banana to mini hook test leads Red and Black banana to banana test leads Ceramic load resistors 150 100 51 39 180 or closest values 5 6 EyasSat EPS Module Calibration and Characterization With your understanding of the process of collecting analog data and storing it on a digital system we need to pause and re visit the EyasSat EPS Module Each EyasSat EPS Module is built with resistors op amps and ADC s designed to measure and record EyasSat User s Manual 5 0 27 May 2011 47 analog telemetry such as a voltage current or temperature Each component will vary slightly within the manufacturer s tolerances When all these devices are connected to collect our telemetry the errors can cascade dramatically which could have a serious impact on the mission To reinforce your understanding of this end to end data collection process including the software necessary to accomplish this which resides on the slave microcontroller on the EyasSat EPS Module we will calibrate the I 5V telemetr
59. hee cables as shown Make sure you engage them well they are polarized and only go one way 6 AIT Gently lower the structure over the base assembly note you will have to do so at an angle to allow the GSE connector to go through the hole in the side of the structure Figure 8 6 Attaching EyasSat Stack to EyasSat Bottom Assembly Figure 8 7 Securing EyasSat Stack with the stack rods EyasSat User s Manual 5 0 27 May 2011 88 7 AIT Attach the EyasSat Bottom Assembly to the EyasSat Top Assembly using four plastic thumbscrews as shown in Figure 8 8 Figure 6 8 Securing EyasSat Top Assembly to Electronics stack 8 AIT Connect the antenna cable to the EyasSat Comm Module 9 AIT Connect the antenna to the EyasSat Top Assembly 10 AIT Place the cover on the front of the EyasSat Structure and secure it with the plastic thumbscrews 11 AIT Plug the GSE power supply into the EyasSat and verify that the proper power lights come on 12 AIT Congratulations You have now fully integrated the EyasSat Stack into the EyasSat Structure 8 6 EyasSat Full Functional Integrated Test During this section of the lab your team will verify that all systems are functioning properly on EyasSat after structural and electrical integration 8 6 1 EyasSat Power Up Test Your team has repeated the following steps after adding a new component throughout the lab process These steps must be repeated one final time now that assembly and integra
60. ick on attach EPS 30 AIT Confirm that the Separation Switch Status telemetry indicates Separated 31 AIT Confirm that power is now being supplied by the battery EyasSat User s Manual 5 0 27 May 2011 91 8 6 2 EyasSat Sun Sensor Integrated Functional Test The EyasSat Sun Sensors have previously been inspected and given a basic electrical functional test Now that they are integrated with the EyasSat ADCS Module we must verify correct operation 32 AIT Click on the Attitude Determination and Control ADCS tab 33 AIT Click on Attach ADCS 34 AIT Record the Sun Top telemetry in ambient light 35 AIT Iluminate the EyasSat Sun Sensor T with full illumination using a flashlight and record the change in the reading 36 AIT the test but cover the EyasSat Sun Sensor 37 AIT Repeat the three measurement points for the EyasSat Sun Sensor B record the Sun Bottom telemetry note it is useful to use a small mirror to get more light into the bottom sensor alternatively your lab partner may tilt the EyasSat in its stand so that you can shine the light in better there is a narrow black tube that surrounds the bottom sun sensor so the light needs to be almost normal in its illumination 8 6 3 EyasSat Yaw Attitude Sensors Integrated Functional Test The EyasSat Yaw Attitude Sensors have previously been inspected and given a basic electrical functional test Now that it is integrated with
61. igure 7 7 Bottom Sun sensor test point on Power Board eese 75 Figure 7 9 EyasSat ADCS Module ooo tetro pota 78 Figure 7 10 EyasSat Control Panel Showing ADCS Module Telemetry 80 Figure 8 1 EyasSat Control Panel Thermal Pane eene 84 Figure 8 2 EyasSat Thermal Subsystem Block 85 Figure 8 3 EyasSat Structure Ready for eere 86 Figure 8 6 Attaching EyasSat Stack to EyasSat Bottom Assembly 88 Figure 8 7 Securing EyasSat Stack with the stack 88 Figure 8 8 Securing EyasSat Top Assembly to Electronics stack 89 Figure 8 9 Thermal control panel expected outputs eene 90 Figure 8 10 EyasSat on Free fall stand diee eb 91 EyasSat User s Manual 5 0 27 May 2011 8 1 Getting Started EyasSat was designed to provide students a laboratory for understanding and exploring concepts in electrical design mechanical design software design and systems engineering by using the subsystems and functionality of a spacecraft EyasSat is built at least at its functional level much like many small spacecraft are built today The hardware and exercises are meant to provide students of engineering hands on experience in test and operation EyasSat even provides board level products that allow advanced students
62. ing CM on the Z aXis us o a costi 16 Figure 4 1 EyasSat EPS Subsystem Block Diagram eee 19 Figure 4 2 EyasSat EPS Subsystem Block Diagram 20 Figure 4 3 EyasSat power board test points 21 Ligure 4 4 Power Subsystem GSE ganes d 22 Figure 4 5 Eyassat RBF Cover intei ee Petite una dee FU ae ese 23 Figure 4 6 EyasSat Solar Panel front 25 Figure 4 7 EyasSat Solar Array Back panel 26 Figure 4 8 EyasSat Solar Array GSE Connection 28 Figure 4 9 I V curve amp Peak Power Point for the Solar Array sess 20 schemate to tec a miht cu adr TU aUo tieu 31 Figure 4 10 Solar Array Characterization Schematic eee 3l Ligure 4 11 EyasSat EPS too nd OH gete ei 33 Figure 4 12 EyasSat Data Interface to USB inei ee rad eee tette 38 Figure 4 13 EyasSat Control Panel Showing EPS Module Startup 39 Figure 4 14 EyasSat Control Panel Showing EPS Module Telemetry 40 Figure 4 15 Close up of EyasSat EPS Module connected to SA and Thermal Panel 44 Figure 5 1 EyasSat Data Handling Block Diagram 47 Figure 5 2 EyasSat EPS Module Characterization 48 Figur
63. k thumbscrews unscrewed they remain captured on the panel the side RBF cover can be removed Set the RBF panel aside for now placing it on a clean surface so it is not scratched Figure 4 5 EyasSat RBF Cover 4 7 2 EyasSat Solar Array Inspection The purpose of this test is to ensure that your EyasSat Solar Array made of a single panel with six cells was delivered in the proper configuration On the inside of the panel are a EyasSat User s Manual 5 0 27 May 2011 23 number of jumpers which are used to configure the panel so that it puts various combinations of cells in series and parallel What we want to be fully operational as opposed to doing solar array experiments as part of a separate lab exercise if for the Solar cells to be wired a 3 strings of 2 cells in series This provides the proper voltage for direct energy transfer to the battery more information on Direct Energy Transfer is available though our website EyasSat User s Manual 5 0 27 May 2011 24 20 EPS Compare your EyasSat Solar Array to the one in Figure 4 6 front and Figure 4 7 back to ensure components match Make sure the string configuration is in the 3 by 2 as required see the jumper table printed on the PCB More information on these particular type of solar cells is available on our website Solar Array Cells Four thumb screws for removal Figure 4 6 EyasSat Solar Panel front EyasSat User s Manual 5 0 27 May 2011 25 Figur
64. l Choose File then Open Select Files for the Files of Type at the bottom Search for your file then open it The Text Import Wizard will come up Choose Delimited data type Click Next Text Import Wizard Step 1 of 3 The Text Wizard has determined that your data is Fixed Width Tf this is correct choose Next or choose the data type that best describes your data Original data type Choose the file type that best describes your data Characters such as commas tabs separate each field Fields are aligned in columns with spaces between each field Start import at row 1 zi File origin 437 OEM United States bi Preview of file C Documents and Settings david barnhart USAFA EyasSAT data TXT 1 Eso 140214 I 1 TelemDelay 2 CmdTimeOut 3 Pwr l ADACS 1 Expl s kso 140214 T IHU 26 2 5vR 57 9 Sp 26 2 5 26 2 TcsG 26 2 Bat 0 140214 P BY 8 1 BI 149 8 SPV 0 0 SPI 2 1 5V 4 9 51 105 7 3 Cancel Finish For Step 2 uncheck Tab and check Space and Other Put an in the box to the right of Other Click on Next Text Import Wizard Step 2 of 3 This screen lets you set the delimiters your data contains You can see how your text is affected in the preview below Delimiters Tab Semicolon Comma Space Other I Text qualifier bd Treat consecutive delimiters as one Data preview Cancel Back Finish EyasSat User s
65. ll be integrated during the final session along with the Thermal Subsystem and structure 7 2 EyasSat ADCS Lab Objectives Objective 1 Perform acceptance and verification tests on the EyasSat ADCS Module sensors and actuators Objective 2 Integrate EyasSat ADCS Module with current stack Objective 3 Verify integrated EyasSat operational status EyasSat User s Manual 5 0 27 May 2011 69 7 3 EyasSat ADCS Subsystem Block Diagram Figure 7 1 EyasSat ADCS Block Diagram 7 4 Lab Materials and Equipment EyasSat EPS Module EyasSat C amp DH Module EyasSat Comm Module EyasSat Antenna EyasSat ADCS Module EyasSat Structure EyasSat Data Interface 5V Power Supply 3 3V Power Supply Multimeters Computer w power supply EyasSat RF GSE Latex or cotton gloves Wire jumper kit Red and Black banana to mini hook test leads EyasSat User s Manual 5 0 27 May 2011 7 5 EyasSat ADCS Hardware Acceptance Tests During this section of the lab your team will perform acceptance and verification tests on the various hardware components of the EyasSat ADCS subsystem including the EyasSat ADCS Module EyasSat Torque Rod X EyasSat Torque Rod Y EyasSat Sun Sensor T EyasSat Sun Sensor B and EyasSat Yaw Attitude Sensor All of these parts are on the EyasSat Structure 7 5 1 EyasSat Torque Rod X and EyasSat Torque Rod Y Inspection The purpose of this test is to ensure that your EyasSat Torque Rods magnetorquers were delive
66. ll you are going to estimate by a very simple method but one that could be used on real spacecraft how much mass you have to add to EyasSat to get the center of gravity in the right spot and meet the Launch Vehicle EyasSat User s Manual 5 0 27 May 2011 14 requirements You will learn something about how one has to manage and trade off a bunch of variables to create a design meeting all requirments Let us suppose that our LV requires that the x and y center of mass be within 1cm of the geometric center of the EyasSat There is also going to be a requirement that along the z or vertical axis the center of mass not be greater than 10cm above the baseplate or interface to the launch vehicle Notice that the table has a specific row called ballast This is the weight that has to be added to counter balance the other masses and get the c g within specification olar Panel Assy os O 1 4 Thermal Panel Assy o3 O o To SoS Top Hat Yaw Sensor 1 12 24 Power Board Assembly 05 SSCS SSCS O T DataHandingBoad bo TT amp C board FRBF covers mass ofboth Lifting Fixture hanger Bot pozn o excludngnotittemsy BO O O 1 SCS non flt item Figure 3 2 EyasSat Mass Budget Based on your measured values how much ballast do you have available to meet the Launch vehicle require
67. may be the same or newer than shown If you do not get a startup message verify your COM configuration Send a t command You should then see a line of telemetry from the module as shown in Figure 7 10 35 ADCS Send the 331 command to unlock coefficient setting EyasSat User s Manual 5 0 27 May 2011 79 A Atitude Det Control ADCS Communications Comm Orbit Determination GPS Experiment EXP Text Only Interface I Thermal _ Electrical Power EPS Data Handling DH EyasSAT Stal ADCS EyasSAT 0 ya 0 0 rol 454 2 21 9 yaw 43 1 acIX 7 4 aclY 6 0 aclZ 5 9 ips 0 alg 0 Manual Telemetry Command Window Data Logging idie k Send Command C EyasSat MyEyasSATFile tt Errors Battery Voltage 0 V EyasSAT Response Status EyasSAT Idle Figure 7 10 EyasSat Control Panel Showing ADCS Module Telemetry The fields in the ADCS telemetry line are as follows X and Y X or Y torque rod status 0 1 or 1 sunT Top sun sensor counts no units sunB Bottom sun sensor counts no units pl p2 p3 p4 Yaw sensor counts ya Yaw angle derived from pl 2 3 4 rol pit yaw Gyroscope readings in deg s CCW is aclX Y Z accelerometer reading in sea level g s rps Reaction wheel tachometer reading in rev s alg Indicates which closed loop algorithm is running 36 ADCS Send the 71 command to zeroize the gyroscope a
68. mber 8 high current Turn off 9V battery output number 1 Turn on 9V battery output number 1 Turn off 9V battery output number 2 Turn on 9V battery output number 2 Turn off on high speed telemetry to UMB telemetry scaling on off Switch external port to XBee radio default Switch external port to USARTI Switch USARTI to Experiment radio XBee Send one tlemetry string to UMB O coefficient lockout 331 enable set coefficient for analog input calibration set coefficient b for analog input calibration factory reset of coeffients GPS EXPERIMENT BOARD EyaNav Exp number EyasSat User s Manual 5 0 Reset the GPS receiver 27 May 2011 106 EyasSat User s Manual 5 0 27 May 2011 107 EyasSat User s Manual 5 0 27 May 2011 108
69. ment and still not exceed the 3kg budget 1 Structure First of all to measure the c g in the x and y axis you can hang the EyasSat from its freefall stand By measuring the distance between the table top and each corner of the EyasSat you can figure out how far off center the c g must be See Figure 3 3 2 Structure Measure the overall dimensions of the EyasSat and draw two pictures to scale that show your view looking along the x axis and the y axis Remember that when you hang any object a vertical line drawn from the hanging point will pass through the center of mass of the object 3 Structure Now using the optional kit for center of mass testing hang the EyasSat as depicted in Figure 3 4 Slide the EyasSat back and forth until it is level this means the hanging point is exactly above the center of mass in the z axis and note the distance of the CM above the baseplate 4 Structure Go back to the two pictures you drew is step two and draw a line across the picture at the right distance above the baseplate the distance corresponding to the measurement from the previous step At this line measure how far the x and y center of mass lines are from the center of the satellite Does the EyasSat as built meet the CM requirements Can you determine if and how much of the ballast budget you may have to use to meet the requirement EyasSat User s Manual 5 0 27 May 2011 15 Picture to be supplied Figure 3 3 Measuring for Center
70. nal Test 34 4 6 3 EyasSat EPS Module Software Functional Test esee 38 EyasSat User s Manual 5 0 27 May 2011 3 4 8 4 EyasSat EPS Module Solar Panel Power Input 2 2 42 4 9 ELECTRICAL POWER SUBSYSTEM INTEGRATION AND TEST eese 44 4 9 Electrical Power Subsystem Integration esee eene 44 4 9 2 EyasSat EPS Integrated Functional Test eese 44 5 DATA HANDLING SUBSYSTENL e eco ose pen hann nhe aue Io eoe eU 46 S L JEYASSAT C amp DH LAB OVERVIEW br eva teh e Pra 46 2 2 EYASSAT C amp DH LAB OBJECTIVES 46 5 3 BACKGROUND KNOWLEDGE REQUIREMENTS 4 44400 46 5 4 EYASSAT SUBSYSTEM BLOCK DIAGRAM eee een 47 5 5 LAB MATERIALS AND EQUIPMENT caved sen Stat aces 47 5 6 EYASSAT EPS MODULE CALIBRATION AND CHARACTERIZATION 47 5 6 1 EyasSat EPS Module Calibration Procedure esses 48 5 7 EYASSAT C amp DH MODULE ACCEPTANCE TESTS esee 53 EyasSat C amp DH Module esee 23 did EyasSat C amp DH Module Functional Test ete eerte 54 3 7 3 EyasSat C amp DH Module Software Functional Test sess 55 5 8 EYASSAT C amp DH MODULE INTEGRATION AND TEST 57 5 8
71. nd accelerometers do not touch the module during this step and note that all channels will not completely reset to zero as they are very sensitive 37 ADCS Send the ul command to get continuous telemetry 38 ADCS Verify the tachometer works by rotating the wheel by hand and confirming TACH LED blinks and that the rps field updates 39 ADCS Verify the 3 axis gyroscope works by rotating the module around all three axes and note changes in the roll pitch and yaw telemetry 40 ADCS Verify the accelerometers work by orienting the board on all four edges and top bottom creating 1g acceleration along the corresponding X Y or Z axis and verify acIX aclY and aclZ fields 41 ADCS Send the 00 command to stop telemetry EyasSat User s Manual 5 0 27 May 2011 80 42 ADCS Disconnect the 5V Power Supply 3 3V Power Supply and EyasSat Data Interface from the EyasSat ADCS Module 7 6 EyasSat ADCS Module Integration and Test During this part of the lab we will integrate the EyasSat ADCS Module with the EyasSat Stack Once it is integrated we will perform functional tests to verify proper EyasSat Stack operation 7 6 1 EyasSat ADCS Comm C amp DH and EPS Integration 43 ADCS Place EyasSat ADCS Module on the EyasSat Comm Module assumed configuration is that the stack has been assembled in order from bottom to top 1 power 2 C amp DH 3 Comm 4 add the ADCS module Note that if you have purchased the GPS and or FL
72. o ensure that the wiring to the EyasSat Battery Pack is properly connected The power board has a number of test points on the front of it These allow easy access to test voltages 5 EPS Do not attempt to remove the batteries or disconnect the wiring never charge the batteries with anything other than the charger supplied 6 EPS Using your Test leads for the Multimeter clip the black lead on the circuit board labeled ground and the red lead on the Battery test point as shown in Figure 4 3 mM MAIN AUCC BaIT o 5 2 29 Figure 4 3 EyasSat power board test points EyasSat User s Manual 5 0 27 May 2011 21 GSE 9V Power Pigtail 4 gt S7 Harness gt Charge Figure 4 4 Power Subsystem GSE 7 EPS Set your multimeter to the VDC V mode and hook the banana jack end of the test leads to the multimeter 8 EPS Record the voltage of the battery module in your workbook 9 EPS Disconnect the Test leads from the EPS first then disconnect from the multimeter 4 6 3 EyasSat Battery Pack Characterization Charging Procedures If the initial voltage from the EyasSat Battery Pack Functional Test on page 21 was greater than about 8 volts the module most likely has enough charge If the voltage was less than 8 volts the battery needs to be charged for a period of time In either case we will briefly demonstrate the method of charging 10 EPS Connect the EyasSat GSE Figure 4 4 with it
73. odule Objective 5 Integrate EyasSat EPS Module and EyasSat Solar Array Objective 6 Verify integrated EyasSat EPS operational status 4 3 Background Knowledge Requirements It is assumed that the student has learned the basics of how solar arrays work and how a basic power system on a Spacecraft is designed and operated A number of resources are available to assist the instructor in providing this background EyasSat User s Manual 5 0 27 May 2011 18 4 4 EyasSat EPS Subsystem Block Diagram Power Subsystem Solar Array Connector 9 Circuit Board Block Diagram to Mux N ILSA to Mux to ADC EyasSat Battery Note Fither i Flight or GSE Plugs not both 1 Thermal Connector Temperature Data Bus to Data to ADC Handling Figure 4 1 EyasSat EPS Subsystem Block Diagram 4 5 Lab Materials and Equipment EyasSat EPS Module EyasSat Solar Array EyasSat Electrical Ground Support Equipment EGSE EyasSat Data Interface brainstem with USB cable 9V GSE power supply Li Ion Battery Charger Multimeter 2 Wire Jumper red Computer with EyasSat GUI installed Red and Black banana to mini hook test leads Red and Black banana to banana test leads Halogen lamp or LED lamp Latex or cotton gloves Ceramic load resistors 150 100 51 39 180 or closest values EyasSat User s Manual 5 0 27 May 2011 19 GSE 5 Li Ion Battery pack 4 6 EyasSat Battery Pack Acc
74. odule Acknowledged Delivery Functional Test During this test you are going to verify that the Acknowledged Delivery function works properly Up until this point the radio units have been sending data packets blindly without caring if they are received Acknowledged delivery configures the receiver to verify error free reception of data Upon an error the receiver requests a re transmit up to the number of re tries configurable by the user 41 Connect the EyasSat Data Interface to the UMB port of the EyasSat C amp DH Module 42 DOMM Change COM port in X CTU for umbilical connection 43 COMM Send i 331 command from the terminal window only not Assemble Packet window to enable radio programming 44 DOMM Using the Radio Acknowledged Delivery Command send command where X is the number of retries you would like the radio to use when a bad or missing packet happens the valid range is 0 9 You must receive all 4 bolded messages not bolded on screen to ensure success Repeat this step if you do not ES7 10 32 12 R Acknowledged Delivery On retries 9 ES7 10 32 12 I TelemDelayz1 CmdTimeOut 3 Pwrz1 ADACS 0 1 0 2 0 Exp3 0 ES7 10 32 13 T DH 26 3 5vR 24 8 Sp 4 7 TcW 4 7 4 7 Bat 24 8 4 7 Amb 26 ES7 10 32 13 P 1 BV 8 5 BI 105 0 SPV 0 0 SPI 0 0 5V 4 9 5Iz121 4 3V 3 0 3I 0 0 5 0 ES7 10 32 13 ES7 10 32 13 R Radio Responds with lt CR gt ES7 10 32 13 R Radio Acknowl
75. olar Array GSE Connection 25 EPS Connect the DVM test leads to the thermistor test point on the EGSE Figure 4 8 and record the resistance of the thermistor the lead polarity doesn t matter in this case At room temperature you should see something in the range of TBD to TBD 26 EPS Remove the test leads from the thermistor test point and set your multimeter to the VDC V mode 27 EPS Move the probes to the Solar Panel Power test points Figure 4 8 28 EPS Record the voltage of the EyasSat Solar Array in ambient or room light if you get a negative voltage the polarity is reversed 29 EPS Use either the light source provided or point the array at the sun and record the voltage again note the difference 30 EPS Disconnect all wiring and equipment used in this test 31 EPS If finished with power tests for the day remount the solar panel on EyasSat and plug its harness back into the EPS 4 7 4 EyasSat Solar Array Fundamentals Several previous characterizations of EyasSat solar panels have been performed and representative data is shown in Figure 4 9 The sun results were obtained on a clear day at noon at about 5500ft above sea level The Lamp results were obtained with the LED lamp at a 16 cm 8 distance EyasSat User s Manual 5 0 27 May 2011 28 160 140 120 100 80 Current mA 60 40 20 EyasSat Solar Panel IV Curve Power mW P Halogen Volt
76. onboard microcontroller is able to correctly interpret and execute the call sign time set and telemetry delay commands Refer to Appendix D on page 102 48 C amp DH Connect the EyasSat Data Interface to the UMB port on the EyasSat C amp DH Module 49 C amp DH Open the EyasSat Control Panel 50 C amp DH Reconnect the 5V Power Supply to the power port of the EyasSat C amp DH Module 51 C amp DH You should get a startup message in the Text Only Interface tab similar to the following ESO 10 03 16 EyasSat ESO Startup Firmware Version 4 0 1 7 2008 The version and date may be the same or newer than shown in this manual If you do not get a startup message verify your COM configuration 52 C amp DH Verify that each telemetry line starts with an ES followed by the call sign digit between 0 and 9 followed by a time stamp in 24 hour format Note the time will be 00 00 80 if the clock is not set 53 C amp DH Verify the functionality of the telemetry delay command The tdX command where X is the number of seconds will configure how often in seconds telemetry is reported You may experiment with different values to determine which is optimal for your team 54 C amp DH Verify the functionality of the call sign change command Send an icX command where X is your assigned EyasSat stack number which may match the workbench number Your call sign should update within one frame 55 C amp DH Verify the functionality of t
77. onditions to EyasSat events Note that it could take up to 10 minutes between thermal changes to reach equilibrium Check with your instructor on how long you need to wait between condition changes some courses may use an abbreviated schedule 8 7 1 EyasSat Baseline Thermal Characterization 79 AIT Internal thermal equilibrium should have already been reached by this time in the lab If you are returning to this point in the lab after having EyasSat off for a while you will need to allow the system to reach thermal equilibrium 80 AIT Using the thermal tab of the EyasSat Control Panel note at this time which component s are significantly warmer than the ambient temperature 8 7 2 EyasSat Solar Array Thermal Characterization During this portion of the lab we are going to illuminate the EyasSat Solar Array and observe the thermal and electrical response 81 AIT Iluminate the EyasSat Solar Array with the halogen lamp at your bench at a 6 distance careful not to burn yourself on the halogen lamp gets hot only after few seconds 82 AIT Record the initial temperature of the array as well as the initial voltage V SA and current I SA output see the EPS panel 83 AIT Calculate the initial power output of the EyasSat Solar Array voltage x current a 84 AIT Allow the EyasSat Solar Array to reach thermal equilibrium and record the new temperature 85 AIT Recalculate the output power and compare it to the initi
78. onnected to the battery Examine the power system EGSE and you will see that there are two distinctly different plugs for the charger and the 9V supply Real satellites always use different style plugs when they want to make sure that a technician doesn t make a mistake and plug something in wrong This is the typical operational scenario on the ground Although there are usually special provisions for operating the S C on the battery just to test it end to end most of the time the battery usually has its charge topped off even on the launch pad in some cases and a ground source supply is used to operate the satellite during all testing Before EyasSat is launched we remove the ground red plug and attach the flight green plug This plug connects the solar array to the system and arms the battery that is the battery is now ready to supply current to the satellite When the satellite leaves the launch vehicle a separation or SEP switch is closed and powers up the satellite This allows it to launch dead and not deplete its battery while waiting on the launch pad If you examine the block diagram in Figure 4 1 carefully you will see how these two plugs operate and how the closure of the sep switch activates the electronics If you want to operate EyasSat in it flight mode you can either mount it on the stand available as part of an accessory kit or you can simply set if up between two books so that its SEP switch is activ
79. ow it to run for approximately 100 transmissions During this time observe the number of good packets bad packets and the average RSSI value 20 COMM Click Stop 21 COMM Disconnect the 5V Power Supply from the EyasSat Comm Module 22 COMM Remove the loopback jumper that was installed during step 5 COMM in this test EyasSat User s Manual 5 0 27 May 2011 65 23 COMM Record the number of good and bad packets that were received and calculate the percent error 24 DOMM Close do not minimize the X CTU utility 6 6 EyasSat Comm Module Integration and Test 6 6 1 EyasSat Comm Module C amp DH and EPS Integration During this part of the lab we will integrate the EyasSat Comm Module with the EyasSat Stack Once it is integrated we will perform functional tests to ensure the EyasSat Comm Module and EyasSat Stack continues to perform as designed 25 COMM Place the EyasSat Comm Module on top of the EyasSat C amp DH Module 26 COMM Carefully line up the bus pins and have a lab partner cross check your alignment in both directions 27 COMM you are sure you are properly aligned gently push the EyasSat Comm Module all the way down on the EyasSat C amp DH Module 28 COMM Carefully insert the EyasSat LED Test Module into the EyaBus connector on the EyasSat Comm Module 6 6 2 EyasSat Comm Module C amp DH and EPS Integrated Functional Test 29 COMM Open the EyasSat Control Panel change COM port setting fo
80. ower port of the EyasSat C amp DH Module EyasSat User s Manual 5 0 27 May 2011 56 5 8 EyasSat C amp DH Module Integration and Test 5 8 1 EyasSat C amp DH Module amp EPS Integration During this part of the lab we will integrate the EyasSat C amp DH Module with the EyasSat EPS Once it is integrated we will perform functional tests to ensure the EyasSat C amp DH Module and EyasSat EPS communicate properly Other capabilities of the EyasSat Control Panel will also be demonstrated EyasSat was designed with a distributed master slave computer processing architecture Most subsystems will have their own microcontroller like the EPS we have been using This lab should help you better understand how a aster controller like the one on the C amp DH is able to control slave subsystem controllers such as on the EPS amp ADCS broken Ne careful in the next four steps as the EyaBus pins can easily be bent or 61 C amp DH Place the EyasSat C amp DH Module on top of the EyasSat EPS Module as shown in Figure 5 8 62 C amp DH Carefully line up the bus pins and have a lab partner cross check your alignment in both directions as shown in Please note that the green plastic stack connectors can move around a little it is the PINS that must line up then wiggle the green connectors in position AFTER the pins are engaged in the sockets Picture to be provided Figure 5 8 placing C amp DH on the EPS 63 C amp DH Once you are
81. p DH Verify that you can command the EyasSat EPS Module by repeating step 73 EPS of the EyasSat EPS Module Software Functional Test You must prefix the power commands now with a p For example to turn channel 1 on you must send a pl 1 m 77 C amp DH Use the EyasSat Control Panel pushbutton controls as shown in Figure 5 10 instead of text commands to verify step 73 EPS of the EyasSat EPS Module Software Functional Test on page 41 Test each power line switch by clicking on the red buttons They will turn green on the control panel when switched on EyasSat User s Manual 5 0 27 May 2011 59 EyasSat Control Panel Attitude Det Control ADCS i Communications Comm Orbit Determination GPS Tex Only Interface Thermal Electrical Power EPS 3 3V Pwr mw Solar Array 7 86V V 3 24V N I 18 0 mA Switch Status Batteries Main Bus 7 82V 90 0 mA r 703 8 m 50V Pwr mw v 497V I 1220 mA GSE Power Separation Switch Disconnect ES Status Separated Figure 5 10 EyasSat Control Panel Electrical Power Subsystem Pane 78 C amp DH Remove the red jumper from the EPS 2 pin connector to power down the stack Be careful in the next step to use extreme care while removing these components or the bus pins will bend and possibly break 79 C amp DH GENTLY remove the EyasSat LED Test Module by slowly wiggling it out 80 C amp DH Disconnect the EyasSat Data Interface from the UMB
82. port of the EyasSat C amp DH Module 81 C amp DH Once you have collected and recorded all the data you need for the lab disconnect all cabling and prepare your lab bench for the next users Leave the EyasSat EPS and C amp DH integrated as a stack unless instructed otherwise EyasSat User s Manual 5 0 27 May 2011 60 6 Communications Subsystem 6 1 EyasSat Comm Lab Overview This lab will expose you to a miniaturized spacecraft communications subsystem Comm First acceptance tests will be performed on the EyasSat Comm Module by itself to verify physical compliance and workmanship of the contractor Once this component level testing is complete it will be integrated with the EyasSat stack enabling wireless operation 6 2 EyasSat Communications Lab Objectives Objective 1 Perform acceptance and verification tests on the EyasSat Comm Module Objective 2 Integrate the EyasSat Comm Module with current stack Objective 3 Verify integrated EyasSat operational status 6 3 Background Knowledge Requirements Before undertaking this exercise the student should be familiar with basic principles of the Telemetry system design test and operation The activities here are kept at a fairly simple level For more advanced exercises consult the EyasSat website 6 4 EyasSat Communication Subsystem Block Diagram 5 VDC fixed TTL TX to DH TTL RX from DH TTL TX to EXP TTL RX from EXP 3 3 VDC switched Figure
83. r port for EyasSat RF GSE connection 30 COMM Power up the EyasSat EPS Module by engaging the green flight connector and with the red jumper by connecting it across the 2 pin connector on EyasSat EPS Module 31 COMM Click the Command and Data Handling C amp DH tab on the EyasSat Control Panel 32 DOMM Use the EyasSat Control Panel C amp DH Tab controls instead of text commands to verify steps 53 C amp DH through 55 C amp DH of the EyasSat C amp DH Module Software Functional Test on page 55 Update the clock if necessary and set the Telemetry Delay to 1 second 33 COMM Using the cable extensions plug in the Solar Array Panel and the Thermal panel to the appropriate connectors on the EPS 34 DOMM Click on the Electrical Power Subsystem EPS tab in the EyasSat Control Panel 35 COMM Click on Attach EPS EyasSat User s Manual 5 0 27 May 2011 66 36 COMM Use the EyasSat Control Panel EPS Tab controls instead of text commands to verify step 73 EPS of the EyasSat EPS Module Software Functional Test on page 41 37 COMM Click the Thermal Subsystem tab on the EyasSat Control Panel 38 DOMM Verify that you are getting a thermistor temperature reading from the thermistor board See Figure 8 1 39 COMM Switch to the EPS panel on the GUI 40 COMM Record the Power I Batt V value and note that it has gone up from the Data Handling lab Note that it is now calculated for you on the EPS page 6 6 3 EyasSat Comm M
84. r subsystem Reference back to the block diagram Figure 4 1 This subsystem has been designed to be very similar in architecture to basic direct energy transfer power systems on today s operational spacecraft The solar array voltage has been matched via choosing the number of cells in series and the type of cell to the EyasSat User s Manual 5 0 27 May 2011 34 battery voltage so that it will charge nominally near the peak power point All power subsystems consist of the following components Power generation solar array Power storage in the form of a secondary or rechargeable battery Battery charge manager Power switching and distribution Power monitoring current and voltage at various points in the system EyasSat EPS has all of these components Additionally we must consider how a satellite is operated on the ground how it is launched and how it operates in orbit Your EyasSat kit has two specific plugs that connect to the only externally exposed connector which is located on the front left of the power board Just like real satellites when the ground in this case that means the EyasSat is sitting on a flat table the red plug is used When the red plug this is on the end of a pigtail cable connected to the EGSE is attached the battery can be charged via the power subsystem EGSE and the satellite can be powered by the 9 volt supply BUT the battery is NOT connected to the bus and the solar array is not c
85. re it with mini hook test leads Do not use large alligator type clips 50 EPS Check the voltage across the GND and 5Vcc test points on the EyasSat EPS Module as shown in Figure 4 11 51 EPS Record the voltage of 5Vcc 52 EPS Move the positive test lead to measure the voltage on 3 3Vcc EyasSat User s Manual 5 0 27 May 2011 36 53 EPS Record the voltage on 3 3Vcc the remove the test leads 54 EPS Move the positive test lead to measure the voltage on 55 EPS Record the voltage on AVCC the remove the test leads 56 EPS Move the positive test lead to measure the voltage on 2 5Vref 57 EPS Record the voltage on 2 5Vref the remove the test leads 58 EPS Move the positive test lead to measure the voltage on Battery note the battery is NOT connected in the circuit at this point we are just verifying its voltage 59 EPS Record the voltage and remove the test leads 60 EPS Remove the red plug connector from the EyasSat EPS Module 61 EPS Replace it with the green plug 62 EPS You should now see a single green LED indicating that the bus is armed and ready to go as soon as it leaves the launch vehicle 63 EPS Now lift the back end of the board so that the sep switch is activated you can set it up between two books if you want You should see the two yellow LEDs indicating that the 5V and 3 3V supply is active EyasSat User s Manual 5 0 27 May 2011 37 4 8 3 EyasSat EPS Module Software Functional Test
86. red in the proper configuration c 22 E 5 OE o i o c ed Figure 7 2 EyasSat Torque Rod Mounted to Base PCB 1 ADCS It is recommended that you use cotton or latex gloves before handling the EyasSat structure in order to keep it clean 2 ADCS Compare your EyasSat Torque Rod X and EyasSat Torque Rod Y to the one in Figure 7 2 A torque rod is shown alone in the figure for clarity but two are mounted to the EyasSat Structure The torque rod across the opening of the EyasSat Structure is X the one on the left hand side is Y EyasSat User s Manual 5 0 27 May 2011 71 3 ADCS Visually inspect the EyasSat Torque Rod X and EyasSat Torque Rod Y to ensure that there are no loose wires connectors or solder connections 7 Tarque Rhiastiet dager dd Ko ymulsEgasSelidiogquhb i atiberafttlrization 5 ADCS Using the Probes measure the resistance across JP8 and JP3 the X torque rod and across the two pins for Y at JP 4 See Figure 7 3 6 ADCS Record your value It should be approximately TBD Ohms Figure 7 3 Torque Rod Test Points on Power board 7 5 3 EyasSat Sun Sensor T and EyasSat Sun Sensor B Inspection The purpose of this test is to ensure that your EyasSat Sun Sensors were delivered in the proper configuration and work according to plan EyasSat User s Manual 5 0 27 May 2011 72 Figure 7 4 EyasSat Top Sun Sensor 7 ADCS Compare your
87. rify that there are no loose wire clippings or other material in the EyaBus connectors on the bottom of the module and that the connector pins are not bent 4 COMM Record the hardware version firmware number and serial number of the module hardware version is printed on the board and the serial number is hand written in the bottom corner 6 5 2 EyasSat Comm Module Functional Test The purpose of this test is to ensure that the EyasSat Comm Module meets the basic performance requirements 5 COMM Plug a red jumper onto the loopback jumper port on the EyasSat Comm Module 6 COMM Connect the EyasSat RF GSE shown inFigure 6 3 to the USB cable and to the PC 7 COMM Ensure that there is a red LED on the RF GSE indicating there is power to the unit EyasSat User s Manual 5 0 27 May 2011 63 Assigned Channel Number Port USB cable to computer Figure 6 3 EyasSat RF GSE 8 COMM Close do not minimize the EyasSat Control Panel and open up the X CTU utility This utility will enable us to perform a loopback test on the Comm module to ensure that it is functioning properly 9 COMM When X CTU comes up you will get a setup screen as shown inFigure 6 4 Ensure that the Select Com Port matches your configuration USB Users should select the MaxStream Digi PKG U COM port PC Settings Range Test Terminal Modem Configuration Com Port Setup Select Com Port Communications Port 1 Keyspan High Speed U
88. s optional 9 EPS Remove the red jumper from the BATT ENABLE 2 pin connector to power down the EyasSat EPS Module or set it back on the table to open its sep switch At this point we would like to determine how much power the EyasSat EPS consumes alone By using the formula Power CurrentxVoltage P IV or P BIxBV the power consumption in watts W can be found Record this baseline power draw of EyasSat EyasSat User s Manual 5 0 27 May 2011 43 4 9 Electrical Power Subsystem Integration and Test During this part of the lab we will temporarily integrate the components of the EyasSat EPS which include the solar array and the thermal panel Once integrated we will perform functional tests to ensure the EyasSat EPS performs as designed 4 9 1 Electrical Power Subsystem Integration Configuration the EyasSat is assumed to be disassembled into the following components a Base with EPS subassembly attached as tested in previous section b Solar array and connecting extension cable c The thermal panel which can use the extension cable to connect to the power board and so can still be attached to the structure if desired Both the solar array and thermal panel should be placed next to the power board on the test bench We will not be using the other elements of the electronic stack during this test so they should be placed on an anti static surface or back in the EyasSat case for protection See Figure 4 15 Figur
89. s harness as shown to the GSE port on the Power Board 11 EPS Connect the Battery charger to the port indicated on the GSE note that the charger connector cannot be interchanged with the 9V power connector it is good design practice to assure that technicians cannot plug in a wrong connector by mistake 12 EPS Re attach the voltmeter and test leads as in step 6 and 7 13 EPS Verify the battery pre charge voltage and record 14 EPS Connect the charger to a wall outlet 15 EPS Verify that the battery voltage starts to go up this is slow EyasSat User s Manual 5 0 27 May 2011 22 There are 4 screws that attach each RBF 16 EPS Record the battery voltage and current at 5 TBR minute intervals For more information on these Lithium Ion Cells see our website 17 EPS Stop charging the battery When the green light appears on the charger and record the battery final voltage 4 7 EyasSat Solar Array Acceptance Tests 4 7 1 Removal of Remove Before Flight RBF Covers Before the EyasSat Solar Array can be inspected the RBF cover must be removed from the EyasSat Structure satellites have various protective covers to assure that they are not damaged in shipping and handling When you are finished with EyasSat always re attach the RBFs before storage 18 EPS Remove the 4 thumbscrews as illustrated in Figure 4 6 Be careful to have someone hold on to the cover so that it doesn t fall 19 EPS With the blac
90. ss When you first get your EyasSat you need to look to our video available on the website on getting started This will give you a good overview of the hardware how you assemble it disassemble it and operate it If you do not have a computer with the GUI and other drivers installed available with the accessory kit You will need to get all of that installed on a computer that you can dedicate to the EyasSat laboratory EyasSat User s Manual 5 0 27 May 2011 9 2 EyasSat Overview EyasSat is a fully functional satellite system designed for teaching spacecraft systems engineering electrical controls and general engineering disciplines in the classroom and laboratory but EyasSat is more than the hardware software that provides the hands on part of the experience EyasSat is a set of learning material designed to augment the classroom lectures and experiences provided by the instructor EyasSat is also a user community designed to provide the instructor a resource to help create coursework tailored to the needs of their students EyasSat can be used depending on the exercises performed from high school through post graduate school and also for workforce development activity The name EyasSat has its roots in falconry as eyas means baby falcon or fledgling bird The falcon is the mascot of the U S Air Force Academy where the concept of EyasSat was born Under a Cooperative Research and Developmen
91. sure you are properly aligned gently push the EyasSat C amp DH Module down on the EyasSat EPS Module 64 C amp DH Carefully insert the EyasSat LED Test Module into the EyaBus connector on the EyasSat C amp DH Module again being careful to assure pin alignment 5 8 2 EyasSat C amp DH Module amp EPS Integrated Test 65 C amp DH Power up the EyasSat EPS Module by installing the green flight plug and by installing the red jumper across the 2 pin connector on EyasSat EPS Module 66 C amp DH Verify the Battery light green and the 5Vcc and 3Vcc LEDs yellow are illuminated on the EPS module and the appropriate LEDs are illuminated on the LED test module EyasSat User s Manual 5 0 27 May 2011 57 67 C amp DH Verify the MOSI and TXD LEDs are illuminated on the LED test module The MOSI line is SPI data from the EyasSat C amp DH Module to the subsystems The TXD line is data from the EyasSat C amp DH Module to the radio used later 68 C amp DH Verify the SCK and MISO LEDs flicker at the same time the telemetry updates on the EyasSat Control Panel text only tab This is the response on the SPI bus from the subsystems 69 C amp DH From the Text interface on the GUI attach the power board by sending an command 70 C amp DH Verify that the Pwr field in the I line of telemetry changes to a 1 and that you now start receiving a line of telemetry 71 C amp DH Record the P I_Batt V_Batt value on the power
92. t Agreement USAF CRDA NUMBER 04 239 1 25 August 2004 EyasSat was co developed between the U S Air Force Academy and Colorado Satellite Services EyasSat is now owned by Gerry Murphy and Chuck Allen of EyasSat LLC and that CRADA has been renewed As a result EyasSat is continually evolving improving and providing more and varied capability to is users This manual applies specifically to Rev C completed in April 2011 A number of improvments are planned over the next year which will not require wholesale replacement of EyasSat but allow the users to upgrade single components or add capability through software upgrades Current information on the EyasSat program can be found at http www eyassat com We are always interested in your comments and will soon have a membership site for teachers to share information EyasSat demonstrates six traditional satellite subsystems of a satellite bus Structural Electrical Power EPS Command and Data Handling C amp DH Communications Comm Attitude Determination and Control ADCS and Thermal as shown in Figure 2 1 and Figure 2 2 It also has the capability to integrate additional systems such as a student designed experimental payload or subsystem EyasSat User s Manual 5 0 27 May 2011 10 Figure depicts basic EyasSat Subsystems are stacked from bottom to top as follows ADCS Module Comm Module C amp DH Module EPS Module Figure 2 1 EyasSat Subsystem S
93. tack EyasSat User s Manual 5 0 27 May 2011 11 If the exercises presented herein are done in order from front to back the student looks at each of the subsystems in turn Ideally students should work in teams of two to four to complete these laboratory exercise and over a period of time they will assemble the EyasSat from the ground up Your team can then integrate the subsystem with the existing stack of EyasSat modules and perform integrated system level tests Figure 2 2 Basic EyasSat System rev pictured As stated before it is expected that the instructor will have to pick and choose or modify exercises as required so that they match the needs and capability of their students There is nothing caste in stone about having to follow these exercises in the order presented Each section begins with a suggested configuration of the system as well the needed equipment For those instructors that do not have access to a range of electronic test equipment EyasSat LLC can provide all the laboratory materials that are not readily available The instructor should feel free to contact us at anytime to share your needs concerns or suggestions for improvement and corrections in the learning material EyasSat is not just a piece of hardware it is a learning system built upon a number of years of experience but can always be made better We consider our instructors as partners in this process EyasSat User s Manual 5 0 27 May 2
94. the EyasSat ADCS Module we must verify correct operation 38 AIT Monitor Yaw Sensors 1 through 4 telemetry points 39 AIT Iluminate the elements of EyasSat Yaw Attitude Sensor individually and record the corresponding telemetry 40 AIT Repeat the test using ambient light and record the values 41 AIT Repeat the test but cover each element and record the corresponding value 42 AIT Finally verify that the Yaw Angle telemetry properly reports the direction of the light source 180 normal to Yaw Sensor 1 8 6 4 EyasSat ADCS Test In the Freefall Environment 43 AIT Steady EyasSat with your hand so it is not moving in the free fall stand then let it go 44 AIT Enter a wheel speed of 300 45 AIT Click on Set Wheel Speed EyasSat User s Manual 5 0 27 May 2011 92 46 AIT Observe the movement of EyasSat and yaw gyro reading 47 AIT Enter a wheel speed of 300 48 AIT Click on Set Wheel Speed 49 AIT Observe the movement of EyasSat and yaw gyro reading 50 AIT Experiment with your ability to control EyasSat using this technique This means that the wheel is normally at rest and moves CW or CCW as appropriate to move the spacecraft The previous exercise demonstrated the use of a zero bias momentum wheel 51 AIT Seta wheel speed of 300 52 AIT Use your hand to stabilize EyasSat after the wheel has spun up Release EyasSat 53 AIT Increase the wheel speed to 350 54 AIT Observe the movement of
95. the cells acrylic mounting plate and the circuit board you will see two leads coming from the circuit board that go to the thermistor mounted on the back of the array Solar cells are less efficient when they are hot and real spacecraft go to lengths to help keep their panels cool This is easier with deployed arrays than body mounted panels Our thermistor will give us the temperature of the array when properly calibrated thermistor is simply a resistor that has a temperature dependent resistance We will also make sure that the array generates a voltage when illuminated 22 EPS Remove the Solar Panel from EyasSat by removing the thumb screws from the frame and unplug its cable connector to the EPS at the solar panel Connect the solar panel to the Solar Panel mounting fixture using the same thumb screws that mounted it to EyasSat and connect it to the Solar Panel EGSE using the extension cable provided in the kit see Figure 4 8 23 EPS Adjust the angle to Illuminate solar panel at normal incidence angle in full sun or with the LED lamp or Halogen at a distance of approximately 10 Normal incidence angle is when the light rays are perpendicular to the surface of the panel Don t turn on the light if you are using it just yet 24 EPS Set the multimeter to resistance mode EyasSat User s Manual 5 0 27 May 2011 27 Thermistor test point ee C4 X d EyasSAT Solar Test Set i amp 1 Figure 4 8 EyasSat S
96. tion are complete 13 AIT Configure the EyasSat Control Panel to record all telemetry for this session On the Text Only Interface tab select a location for the data file and check the Enable File Log box If you do not do this properly you will have to repeat this lab 14 AIT Connect the ground system radio to the USB port verify lights are on EyasSat User s Manual 5 0 27 May 2011 89 15 AIT to the comm Panel use the pull down tab to set the comm Channel to the highest number provided as the option note recall that if you are unsure of the port assigned that in the control panel system devices hardware you can see which port the USB connected radio has been assigned Set the port to this number 16 AIT Switch back to the Text only interface panel 17 AIT Connect the GSE power supply to the EyasSat and look for the power up text message 18 AIT Click on the Data Handling C amp DH tab on the EyasSat Control Panel 19 AIT Use the EyasSat Control Panel C amp DH Tab controls instead of text commands to verify steps 53 C amp DH through 55 C amp DH of the EyasSat C amp DH Module Software Functional Test on page 55 Update the clock if necessary and set the Telemetry Delay to 1 second 20 AIT Click on the Thermal Subsystem tab on the EyasSat Control Panel 2 AIT Verify that you are getting a thermistor temperature reading from the all telemetry points as shown in Figure 8 9 EyasSat Control Panel At
97. titude Det Control ADCS Orbit Determination GPS li Electrical Power EPS Flex Experiment EXP Data Handling DH Communications Comm Text Only Interface EyasSat Temperatures Ambient Top of Copper 22 7 Top of Heat Pipe Battery 25 69 RAO DH 23 9 MU Expmt 24 9 Solar Array 19 3 Telemetry in Deg C 4 7 points nof connected Figure 8 9 Thermal control panel expected outputs EyasSat User s Manual 5 0 27 May 2011 90 22 AIT Click on the Electrical Power Subsystem EPS tab in the EyasSat Control Panel 23 AIT Click on Attach EPS 24 AIT Use the EyasSat Control Panel EPS Tab controls instead of text commands to verify step 73 EPS of the EyasSat EPS Module Software Functional Test on page 41 25 AIT Switch back to the text tab 26 AIT Replace the GSE power supply with the Flight plug 27 4IT Note that EyasSat will not restart because the sep switch is open while the EyasSat is not in free flight Figure 8 10 EyasSat Free fall stand 28 AIT Place EyasSat on its free fall stand as shown in the figure note that as soon as lifted off of the bench the system should start up and you will get the standard start up message note if the RF GSE is relatively close by you do not need the antenna on top of EyasSat with the antenna erected you will not be able to spin the EyasSat 29 AIT the Power tab and cl
98. us 34 C amp DH Senda command 35 C amp DH Verify that your newly calibrated telemetry for V 5V and 5V closely matches the metered value If not you have may have made an error entering the coefficients or did not properly record the calibration data 36 C amp DH Record the average V 5 and I 5V telemetry points in the appropriate After column in the spreadsheet or workbook 37 C amp DH Repeat steps 33 C amp DH through 36 C amp DH but use the 100 51 39 and 180 or similar values load resistors and compare to the telemetry to the meter EyasSat User s Manual 5 0 27 May 2011 52 Ambient Thermistor 5V Power Port TTL level Data Port UMB Serial Number amp HW Version 38 C amp DH Remove the load resistor 39 C amp DH Disconnect the red battery enable jumper all test equipment and the EyasSat Data Interface from the EyasSat EPS Module 40 C amp DH Replace the two test jumpers on pins 2 1 and 4 3 5 7 EyasSat C amp DH Module Acceptance Tests SUCC TP a FT j A MN Ai hix THERM 1 TN ES Power LED LY D A iting Real time Clock Software Version Figure 5 6 EyasSat C amp DH Module 5 7 1 EyasSat C amp DH Module Inspection The purpose of this test is to ensure that your EyasSat C amp DH Module was delivered in the proper configuration 4 C amp DH Visually inspect the EyasSat C amp DH Module to ensure that there are no loose
99. y channel In addition we will determine the efficiency of the 5v supply by measuring P and Pout P and then use those values in the following equation 7 x100 5 6 1 EyasSat EPS Module Calibration Procedure 2 C amp DH Set up the EPS module as in the previous procedure in a stand alone mode with out the connection of the Solar array or thermal panel and without the other boards in the stack 3 C amp DH Install the green plug on the external connector Be very careful to make the connections correctly as you can easily damage the module in the following steps DO NOT short out the load resistor leads at any time 4 C amp DH Install the LED test board on the EPS EyasBus connector to use for our variable load 5 C amp DH Using multimeters make the connections illustrated in Figure 5 2 EyasSat EPS Module Characterization Schematic Do not install the load resistor yet Schematic to be provided Figure 5 2 EyasSat EPS Module Characterization Schematic 6 C amp DH Connect the EyasSat Data Interface to the UMB port on the EyasSat EPS Module and to your PC 7 C amp DH Open the EyasSat Control Panel using a shortcut on the desktop is available verify COM port setting for umbilical connection and set to the proper port 8 C amp DH Power up the microcontroller on the EPS by using the red jumper across the test pins of the sep switch and verity that the green light battery power and the two yellow li

User's Manual Version 4.0 To be used with Rev CPlus EyasSat April

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