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1. 71 3 Verification Signal Chain TC The complete control chain from a CERESS Ground Module Control Console Client to the trigger of an event at the CERESS Rocket Module is verified by test in flight Therefore the timestamps of the send command and the event report from the CERESS Rocket Module need to be compared 7 1 4 Verification Signal Chain TM The complete signal chain from the CERESS Rocket Module to a ViTo running on the Internet is verified by test Comparison of the data stored from a ViTo running as a CERESS Ground Module Client and a ViTo running as Internet Client is used for this purpose 7 1 5 Verification COTS Sensors The CERESS Rocket Module uses lower cost COTS Sensors In order to qualify disqualify them for future REXUS Missions the determination of characteristic values is planned Mean Value Standard Deviation Min amp Max Values In Case of the Gyroscope and the Accelerometer the values will be compared to the ones measured from the REXUS Service Module 7 1 5 1 Error calculations Position CERESS gathers position data from two different sources e GPS from the REXUS Telemetry stream e Antenna tracking angles and range from ESRANGE Ground Station Furthermore the Trajectory will be determined by integration of Acceleration and rotation rates provided by the CERESS Rocket Module Due the high frequency measurement 1000HZ it s expected to achieve good results This way
2. A DLR and SSC coopera The CERESS Verification Module receives its power from the CERESS Bus 3 3V and 24V run over the sensor drivers The 3 3V powers the coarse pressure sensor and the heating coils of the melting wire devices while the 24V bus connects to the fine pressure sensor The 5V bus is connected to the GoPro camera via the camera driver board The verification module also contains an arm plug for the melting wire devices This plug consists of a D Sub 15 male connector with two pins separating a power line of the melting wires The arm plug is a female D Sub 15 that will close the electrical circuit once it is in place Therefore the melting wire devices can only be activated with the arm plug plugged in hence no accidental melting of the nylon wire can occur There will also be a so called test plug This plug will also close the electrical circuit but not via the melting wires It will route the power over a resistance and a lamp so the command flow can be verified without actually melting the wires 4 5 3 Command and Control Hardware Fehler Verweisquelle konnte nicht gefunden werden shows the information flow inside the CERESS rocket and verification modules as well as data protocols used HX13 CERESS SEDv3 1 12DEC14 doc Page 83 EuroLAUNCH LR and SSC cooperation 4 Current Feedback Coarse Gyroscope Figure 34 ibd
3. Facebook CERESS Status updates and photographs http facebook de Team Ceress Twitter CERESS Status updates http twitter ceress de YouTube CERESS Videos http www youtube com user CeressR To be Press CERESS General project information released release Feb Press FSMB Article about CERESS and the usage 2012 release of university funding RX13_CERESS_SEDv3 1_12DEC14 doc Page 145 EuroLAUNCH APPENDIX C ADDITIONAL TECHNICAL INFORMATION 1 CERESS System Overview CERESS System CERESS Bus 1 TCP IP HX13 CERESS SEDv3 1 12DEC14 doc Page 146 ADLR and SSC EuroLAUNCH 1 1 CERESS Space Segment Space Segment 28V unregulated 3 3 8 2 5 5 a o 2 m ul ra ul o o o RX13_CERESS_SEDv3 1_12DEC14 doc Page 147 EuroLAUNcCH ADLR and SSC cooperation 1 1 1CERESS Rocket Module p eog gdl 05220 p22y 2 OSLOJ 2227 2 21919u1049 022 051205 2227 2 98205 1227 2 f1919u1049J9022 9014 0014 4 910250140 9520 900250169 4 H J 4 uomejueuinijsuJ ISNI sueg juaun Zsuag
4. until T 1000s Peak power consumption 31W Average power consumption 31W Total power consumption after lift off 8 6 Wh Power ON 1200 s before lift off Power OFF 1000 s after lift off Battery recharging through service module no Experiment signals Signals from service module required Yes No LO Yes SOE Yes SODS Yes RX13_ Table 38 Electrical Interfaces CERESS_SEDv3 1_12DEC14 doc Page 124 A DLR and SSC 6 1 4 Launch Site Requirements 6 1 4 1 Infrastructure ESR POSNET Access Access is needed to the ESR POSNET via the RS232 interface for near realtime GPS position data of the REXUS rocket as well as the tracking angles and ranging information of the ESRANGE ground station tracking antenna SCIENCE NET Access Access is needed to the SCIENCE NET 85232 interface for access to the REXUS TM TC stream Internet Access Access to an one way outgoing internet connection is needed Ethernet TCP IP interface 6 1 4 2 Data Launcher Angles The final launcher angles orientation are needed Timed Flight Events A schedule with timed flight events is needed HX13 CERESS SEDv3 1 12DEC14 doc Page 125 ADLR and SSC cooperation REXUS Ground Segment RS232 CERESS Ground Module RS232 GPS Tracking Server TM TC Ethernet LAN CERESS C amp C CE
5. 100 TEST HARD SAV ED Gunnar 100 NORMAL w o pirani with 100 SHETBDOWNS edid Ga t c deck iret od ir pac inde EP do A OE 100 4 8 3 Functional BIOCKS aset iet tenete 101 1 CERESS SEDVv3 1 12DEC14 doc 4 8 8 1 State and 101 4 8 8 2 Mode Geier 101 4 8 3 3 Information Transfer 101 ECT ER Ier cm 101 4 8 3 5 EVENt LOgger ae ete es en n MEER Rd 101 4 8 8 6 Sensors and O Nodes nens 101 293 7 ecd M LA n D MU 101 4 8 3 8 Receiving ond ooo eps tan hate 102 4 8 4 Additional implemented Blocks nr 103 4 8 4 1 SPI Block EE 103 4 8 4 2 Timestamper s deca to UU EE 103 4843 Timestamp 103 4844 Timestamp clean to bim 103 485 0 103 4 8 5 1 103 4 8 5 2 Data 104 4 8 53 Telemetry Data Frame definition 104 4 8 5 4 Telemetry DBudoet 105 4 8 6 cc ered ee 105 Skier een lasses histone 105 4 8 7 1 B dget eii tat en Sack 106 4 9 Ground Support Equipment Ground Segment
6. 9 53 Figure 14 Camera window cross 54 Figure 15 Venting hole and protection 55 Figure 16 cette ede bas epi 55 Figure 17 Angels of the hull 56 Figure 18 Electrical interface 57 Figure 19 Optocoupler 59 Figure 20 un Ee ioo eei tiep a re xe teo ne edi PE UE 59 Figure 21 Inner Hatch EE 73 Figure 22 Frame structure and 73 Figure 23 The electronic Boards na ape ocu ete etl eec ooi ettet 74 Figure 24 Crossbar with Gyro and Accelerometer 74 Figure 25 boarder conditions of the 76 Figure 26 Von Mises yield 76 Figure 27 Scale von Mun 77 Figure 28 Detail of the cut out Corner iacu ea 77 Figure 29 Displacement i cnt ete Rican he ate 78 Figure 30 Scale EE 78 Figure 31 boarder conditions for cross beam 79 Figure 32 1 mode of the 80 Figure 33 Overview Electrical 81 Figure 34 ibd Rocket Module UE ee 83 RX13_CERESS_SEDv3 1_12DEC14
7. one hole of 10mm diameter is needed for each 15 dm of evacuated air volume Since the complete rocket module has a volume of approximately 5 7dm only one venting hole would be required but since other modules don t have their own venting holes we have to evacuate them as well To protect the inner construction from hot gas flows there is a protection cap on the outside of the venting hole see Figure 15 Venting hole and protection Cap RX13_CERESS_SEDv3 1_12DEC14 doc Page 55 EuroLAUNCH LR and SSC coopera Figure 15 Venting hole and protection cap 4 2 1 4 Hatch For late access possibility to the Main Computation Unit a hatch is designed The hatch is covered by a removable cap which is fixed via 6 bold connections of the size see 16 Outer hatch Figure 16 Outer hatch For better understanding of the positions see Figure 17 Angels of the hull modifications RX13_CERESS_SEDv3 1_12DEC14 doc Page 56 EuroLAuUNcH A DLR and SSC Hatch i Hull E Venting Hol i Hull i4 Camera Vie i Hull E Venting Hol 11 11 Figure 17 Angels of the hull modifications For details see technical drawings at 9 2Appendix C or attachments 4 2 2 Electrical Interfaces Due to its design Ceress has a variety of interfaces both internal and external The following figure gives an overview of these interfaces and the connectors that are used RX13_CERESS_SEDv3 1_12D
8. ACOURE FROM ESRANGE 00 00 00 REXUS Ground Module REXUS Ground Module CERESS Ground Module Power Consumption Acceleration and Gyros DATA FROM ESRANGE CERESS Ground Module CERESS Visualisation DCDCConverter33V 0 Power Consumption x Y z cs CERESS Visualisation Pm DC DC Converter A rj vine w AM Gyros isualisation A o Internet Gyros 2 0 0 0 E Azimut DC DC Cc ter 5 0V meter ee mg Min Accelerometer igh i 5 Elevation DC DC Converter A 0 EAM Accelerometer high 0 ny san REMEE Samm Accelerometer3 high 5 nj 0 IC DC Converter 24 0 0 D GEET 5 iini Accelerometer 4 high 7 s Accelerometer 1 low 2 DC DC Converter A ofr w H UAM Accelerometer low Tg o 0 WE Accelerometer2low 0 2 2 Accelerometer4low2 0 Accelerometer3low 0 o o WII Accelerometer 4 low 0 0 0 co HISTORY Rocket Module HISTORY Ground Module T 400 normal Connection to CERESS RM established 190 7 normal l CERESS GM started T 95 normal BIT started T 95 normal Data Logging activated 7 390 critical CERESS RM is not respondin critical CERESS RM is not responding pe 9 7 30 CERESS RM is responding again T 50 d BIT success T M0 d set to idle mode 115 7 normal d back to ready mode 12 normal start logging Figure 7 CERESS Ground Segment Client RX13_CERESS_SEDv3 1_12DEC14 doc Page 49 4 1
9. Create wiring diagram Design circuit board Software Design Main structure Design procedures CDR Phase D Construction Mechanical Build Mechanical Structures Mechanical testing Electrical breadboard wiring and testing Electrical Assembly Software RX13_CERESS_SEDv3 1_12DEC14 doc 119 days 76 days 73 days 3 days 119 days 64 days 20 days 35 days 82 days 60 days 22 days 0 days 153 days 116 days 80 days 36 days 153 days 110 days 26 days 150 days Mon 05 03 12 Tue 06 03 12 Tue 06 03 12 Fri 15 06 12 Mon 05 03 12 Mon 05 03 12 Fri 01 06 12 Fri 29 06 12 Mon 05 03 12 Mon 05 03 12 Mon 28 05 12 Mon 02 07 12 Fri 25 05 12 Mon 09 07 12 Mon 09 07 12 Mon 29 10 12 Fri 25 05 12 Fri 25 05 12 Tue 20 11 12 Fri 25 05 12 Thu 16 08 12 Tue 19 06 12 Thu 14 06 12 Tue 19 06 12 Thu 16 08 12 Thu 31 05 12 Thu 28 06 12 Thu 16 08 12 Tue 26 06 12 Fri 25 05 12 Tue 26 06 12 Mon 02 07 12 Tue 25 12 12 Mon 17 12 12 Fri 26 10 12 Mon 17 12 12 Tue 25 12 12 Thu 25 10 12 Tue 25 12 12 Thu 20 12 12 Page 30 8 10 Daniel Bugger 10 1 Daniel Bugger 10 1 1 Daniel Bugger 12 10 1 2 Christoph Friedl 10 2 Christoph Friedl Sebastian 10 2 1 Althapp Sebastian Althapp 15 10 2 2 Christoph Friedl 16 10 2 3 10 3 Alexander Schmitt 10 3 1 Alexander Schmitt 19 10 3 2 10
10. The Ground Module shall be able to process stored data of the CSRM in post flight To be done The Ground Module shall condition the data for visualisation R T To be done 3 1 6 1 The Ground Module shall merge all conditioned data into a single file R T To be done 3 1 6 2 The Ground Module shall update the data frequently RorT To be done RX13_CERESS_SEDv3 1_12DEC14 doc Page 118 Eurolauncn ID Requirement text Verification Status 3 1 6 3 The Ground Module shall provide R T To be done access to the conditioned data via the Internet during flight 3 1 7 The Ground Module shall provide R To be done access to the conditioned data post flight 3 1 8 The Ground Module shall provide a interface to send control data to CSRM 3 1 9 The tool shall be capable to handle a TA To be done lost contact to the data stream 3 2 General Req GM 3 2 1 The Ground Module shall be A R To be done operational during all flight phases of the rocket module 3 2 2 The Ground Module shall be A R To be done operational during the countdown phase 3 2 3 The Ground Module shall be capable T A To be done of detecting malfunctions 3 2 4 The Ground Module shall display the R T To be done GM status 3 2 5 The Ground Module shall display the R T To be done CSRM status Table 34 Verification Matrix ID Requirement text Verification S
11. internet and so must be connected with Esranges support Power ON should be at T 600 sec Is Ethernet to be used in a nominal case or emergency RX13_CERESS_SEDv3 1_12DEC14 doc Page 140 A DLR and SSC Experiment PDR ESRANGE Kiruna 28 Feb 2012 Students only emergency Are you thinking about being able to determine attitude Students will attempt but not hopeful Team must elaborate on calibration of sensors as it is a very important Be careful with use of the word calibration it can be misleading 67 please include the module in experiment mass brackets 68 please include timings for SOE and 5005 in the electrical interfaces Planning Org and Outreach Good to see GANTT chart in current level of development Considering to add more team members Students not yet please look at that again Please look at manpower required to fulfil the project Look at backing each other up within the experiment team already planning for this Final Board Call Glass window recommended for the experiment to protect the camera Student questions Do components that were flown before need the logbook No not for such a case Experiment Critical Design Review Flight REXUS 14 Payload Manager Mikael Inga Experiment CERESS Location DLR Oberpfaffenhofen Germany Date 3 July 2012 1 Review B
12. 107 491 CERESS Ground Module 107 492 Trajectory determination principles nenn 108 493 CERESS Ground Module 108 494 Visualization 109 4 9 4 1 109 49 42 JP osbElODEb ele 109 495 Service 109 4 10 Calibration and other Terminology 109 4 10 1 esse 109 OI SOL iani Ava asa ede dec deis 109 4 10 1 2 Factory GallDFallonas 110 4 10 1 3 CERESS calibration 110 4 10 1 4 Data processing noe 110 2 102 Gy o prater bei rite eei 110 4 10 2 1 Zero rate 00 2 110 4 10 2 2 CERESS 110 4 10 2 3 Data plocessing sn esse 111 4 10 3 111 4 10 3 1 Calibration ERES 111 RX13_CERESS_SEDv3 1_12DEC14 doc 4 10 4 Fine pressure 111 4 10 4 1 Factory 111 4 10 4 2 Data processing E 111 4 10 5 Coarse pressure 0 111 4 10 5 1 Factory calibratio
13. 4 1 2 6 Melting Wire Driver The Meltingwire Driver switches the high currents needed to burn the Meltigwires The used voltage for this device is 3 3V Furthermore the Meltingwire Driver provides feedback if current flows through the Meltingwires or not 4 1 2 7 Safety Pin The Safety Pin is implemented as a Insert Before Flight Pin that forms a connection between the 3 3V power source and the melting wires For transport and situations when activation of the melting wires is not permitted HX13 CERESS SEDv3 1 12DEC14 doc Page 47 the plug can be removed therefore disconnecting the power source and the wires For testing there will be a different plug available still isolating power source and melting wires The power will instead flow through LED lights to indicate that the command has been received successfully 4 1 3 The CERESS Ground Module Ground Segment The CERESS Ground Module is divided into Ground Module Servers and Ground Module Clients It is not yet determined on how many computers the servers and clients are running The theoretical minimum is one desktop computer running the server and client software 4 1 3 1 CERESS Ground Module Server The CERESS Ground Module Server provides following tasks e Handle the RS 232 interface of the ESRANGE Ground Station e Handle TM TC from and to the CERESS Rocket Module e Store TM TC data stream Command and Control of CERESS Rocket Module a
14. 50 D GND Feedback melting wire 3 burn wire 3 burn GND Table 19 P5 Digital Connector Pin usage 7 Analogue Connector 1 Al GND Thermistor4 GND 2 AIO Thermistor4 3 Als Thermistor1 4 AI9 Thermistor2 5 Alt Thermistor3 6 AIGND Thermistor5 GND 7 Al2 Thermistor5 8 Al10 Fine Pressure High 9 Al Fine Pressure Low 10 Thermistor6 11 Al GND Thermistor6 GND 12 Al4 No Connection 13 AM2 HSCS1 14 DC DC 1 15 AI5 No Connection 16 AI GND No Connection 17 Al6 HSCS2 18 Al14 DC DC Voltage2 19 Al15 HSCS3 20 Al7 DC DC Voltage3 21 AI GND No Connection 22 Al16 No Connection 23 Al24 No Connection 24 AI25 No Connection 25 Al17 No Connection 26 Al GND No Connection 27 Al18 No Connection 28 Al26 No Connection 29 Al27 No Connection 30 No Connection 31 Al GND No Connection 32 Al20 No Connection 33 Al28 No Connection 34 129 No Connection 35 Al21 No Connection 36 Al GND No Connection 37 Al22 No Connection 38 0 Connection 39 AI31 No Connection 40 AI23 No Connection 41 AL SENSE No Connection 42 AO GND No Connection 43 AO3 No Connection 44 AO GND No Connection HX13 CERESS SEDv3 1 12DEC14 doc Page 70 EuroLauncu 45 2 Connection 46 GND No Connection 47 AO1 No Connection 48 AO GND No Connection 49 AOO No Connection 50 Al GND No Connection Table 20 Analogue Connector Pin
15. EUROLAUNCH A DLR and SSC cooperation SED Student Experiment Documentation Document ID RX14_CERESS_SEDv2 1_31Jul12 doc Mission REXUS 13 14 Team Name CERESS Experiment Title CERESS Compatible and Extendable REXUS Experiment Support Bus Team Name Student Team Leader Daniel Bugger Team Members Sebastian Althapp Christoph Friedl Alexander Schmitt Version Issue Date Document Type 3 0 14 December 2012 SED Issued by D Bugger Approved by Bugger S Althapp C Friedl A Schmitt University TU Munchen TU Munchen TU M nchen TU Munchen Valid from 14 October 2012 RX13_CERESS_SEDv3 1_12DEC14 doc Change Record Version Date Changed chapters Remarks 0 2012 01 12 New Version Blank Book 2010 1 2012 02 13 all PDR 1 01 2012 02 14 Header 6 2 6 3 7 1 02 2012 05 25 1 3 5 4 7 4 10 2 Updated 1 11 5 1 6 2 4 6 4 9 Appendix C 1 12 2012 06 07 All Updated Rearranged 1 13 2012 06 09 8 9 Added Chapter 8 Shifted old Chapter 8 to Chapter 9 2 0 2012 11 06 All Appendix A D CDR 2 01 2012 31 07 All 4 10 Added Chapter 4 10 reduced amount of Abbreviations 2 1 2012 31 07 2 4 21 4 22 4 4 4 5 5 6 14 CDR Comments worked 3 0 2012 10 09 3 1 4 8 1 4 8 3 4 8 4 inserted 4 8 7 4 1 1 8 4 5 4 1 2 7 updated 4 1 1 3 4 1 1 6 removed Added 4 84 shifted following chapters 3 1 2012 12 13 4 2 1 4 4 4
16. Fehler Keine g ltige Verkn pfung Table 31 Data Storage Budget HX13 CERESS SEDv3 1 12DEC14 doc Page 107 EuroLAUNCH 4 9 Ground Support Equipment Ground Segment The Ground Support Equipment GSE of CERESS consists of three major Subsystems For more detailed information see CHAPTER 4 9 1 CERESS Ground Module Server The CERESS Ground Module collects all raw data necessary to compute the data needed for the visualization Therefore the CERESS Ground Module receives the downlink from the CERESS Rocket Module via the REXUS Downlink and decodes the stream into usable information Furthermore it receives data from the telemetry stream of the REXUS Rocket and or the ESRANGE Ground Segment As a third input stream the orientation angle and ranging of the ESRANGE Tracking Antenna is used These data streams are merged to provide the necessary data for the ViTo All data streams are recorded and stored for analysis in case of failure Furthermore the CERESS Ground Module provides status information of the other subsystems Depending on the ground infrastructure Figure 53 the software is distributed on multiple computers Esrange SCIENCE NET Programing Unit Stream Check RS232 CERESS Ground Module Cross TCP IP CERESS Visualization Unit N kr Esrange 4 Internet Qe a Connection Maintenance Flight Visualisation Programing Unit Stream Check Live webcam Figure 53 CE
17. m o nothing 4 lt 2 ___ ir finished gt __2 4 SAVED TEST FINISHED gt 24 Command Procedure OR SODS true Command OR procedure LO signal received E NORMAL w o pirani N Do logging amp sending Nose amp Engine ee separation complete NORMAL with pirani Entry start data acquisition gt 7805 OR Procedure OR SODS false 4 SHUTDOWN gt N 1 ea Entry close files send finish ia Figure 50 State Machine of MAIN 4 8 2 1 POST Power on self test POST is performed by the sbRIO itself and doesn t need any input information The program for FPGA and Real Time Processor is load from a non volatile storage build in RX13_CERESS_SEDv3 1_12DEC14 doc Page 100 Eurolauncn 4 8 2 2 STARTUP STARUP configures the communication channels and all Maintenance data logging 4 8 2 3 IDLE This state is defined for standby and as ready for command state Useful especially for countdown holds because nearly no storage data is generated Furthermore some commands are available like zero offset acquisition and zero offset set The zero offset acquisition command will be used before CERESS Rocket Module integration flat bearing is necessary and delivers the required offset values which are stored in the non volatile storage aboard the sbRIO 4 8 2 4 BIT Build in self test BIT runs a check on defined sensors an
18. 3 2 3 Operational Detecting The Ground Module shall be Malfunctions capable of detecting malfunctions 3 2 4 Operational Display GM The Ground Module shall display status the GM status 3 2 5 Operational Display CSRM The Ground Module shall display status the CSRM status Table 4 CERESS Ground Module Requirements RX13_CERESS_SEDv3 1_12DEC14 doc Page 28 2 4 Requirements Visualization Tool 4 Requirements Visualization Tool 4 1 Display during flight The VT shall display data during flight 4 1 2 Display REXUS Rocket The VT shall display the trajectory of trajectory the REXUS Rocket 4 1 3 Data refresh frequency The data shall be updated once per second 4 1 4 use GM data The VT shall use the data from the GM via the internet 4 2 Display during post flight The VT shall display CERESS data during post flight 4 2 1 Display REXUS Rocket The VT shall display the trjectory of trajectory the REXUS Rocket 4 2 3 Display CSRM data The VT shall display the data collected by the CSRM in post flight Table 5 CERESS Visualization Tool Requirements 2 5 Requirement satisfaction The CERESS system and subsystems are designed to fulfill the Requirements The system components are therefore validated against the above requirements tables RX13_CERESS_SEDv3 1_12DEC14 doc Page 29 EuroLAuNcH A DLR and SSC coopera 3 PROJECT PLANNING The CERESS team consists of four a
19. 4 3 1 1 RX13_CERESS_SEDv3 1_12DEC14 doc Page 64 A DLR and SSC Not every connection is used in the CERESS Mission but is provided for future experiments See 9 2Appendix C for more detailed signal connector and pin definition 4 2 2 7 CERESS Rocket Module internal interfaces CERESS Electric Power System EPS and the CERESS and Data Handling are developed with a top to down approach and are defined in the next and final iteration of the electrical systems based on the definition of the REXUS and CERESS Bus 4 2 2 8 CERESS Verification Module internal interfaces The CERESS Electric Power System EPS and the CERESS and Data Handling are developed with a top to down approach and are defined in the next and final iteration of the electrical systems based on the definition of the REXUS and CERESS Bus 4 2 3 Thermal The operating temperature of the pirani type fine pressure sensor needs to be above 10 C The storage temperature of the pirani sensor shall not be below 20 C These requirements are fulfilled by a heating for the pirani sensor which is implemented as a heating foil The impact of the heating to the rest of the REXUS Rocket is minimised by thermal isolation of the pirani sensor with heating 4 3 Experiment Components In the following section the implementation of the components of the CERESS system are described summary of t
20. Process data The Ground Module shall be able to near real time process down linked data from the CSRM in near real time 3 1 5 Functional Process data The Ground Module shall be able to post flight process stored data of the CSRM in post flight 3 1 6 Functional Condition data The Ground Module shall condition for visualization the data for visualisation 3 1 6 1 Functional Merge The Ground Module shall merge all conditioned data conditioned data into a single file 3 1 6 2 Functional update The Ground Module shall update frequently the data the data frequently 3 1 6 3 Functional Distribute data The Ground Module shall provide near real time access to the conditioned data via the Internet during flight 3 1 7 Functional Distribute data The Ground Module shall provide post flight access to the conditioned data post flight 3 1 8 Operational Interface for The Ground Module shall provide a sending control data interface to send control data to the CSRM 3 1 9 Functional Handle loss of The tool shall be capable to handle HX13 CERESS SEDv3 1 12DEC14 doc Page 27 Eurolauncn 3 Req Ground Module contact a lost contact to the data stream 3 2 General Req GM 3 2 1 Operational Operational The Ground Module shall be during flight operational during all flight phases of the rocket module 3 2 2 Operational Operational The Ground Module shall be during countdown operational during the countdown phase
21. The Camera is implemented as a GoPro HD2 The batteries are removed The power supply is realized by the 5V USB power supply of the camera Control of the camera is implemented by switching the buttons of the camera electronically The GoPro HD2 Camera s predecessor was already flown on the REXUS Project EXPLORE The availability of the configuring know how the high shock resistance and the high resolution video output makes this device very attractive HX13 CERESS SEDv3 1 12DEC14 doc Page 71 A DLR and SSC 4 3 2 2 Pressure Sensors MS5534C 4 TTR 91 The Altitude determination is realised by measuring the ambient pressure Two Sensors are selected to cover the required measurement range MS5534C is a piezoresistive pressure sensor with a measurement range from 10 to 1100 mbar The interface to the sbRIO is a digital three wire interface TTR91 is a Pirani cold cathode transmitter that covers the measurement range from 5e 4 to 1000mBar with an error of 15 below 100mbar The analogue output is proportional to the measured ambient pressure This sensor was selected due to the limited available measurement principles at near vacuum conditions on altitudes of 100km 4 3 2 3 Temperature Sensor KT103J2 The Temperature sensors are implemented as Thermistors due to the simple measurement circuit One Thermistor of the CERESS Verification Module is located at the heating of the Pirani Sensor Two Th
22. The main computing unit provides four 50 connectors for digital input output and one 50pin connecter for analogue input Two of the digital connectors and about half of the analogue connector will remain in the rocket module while the remaining connectors and pins are forwarded to the verification module The digital 50pin connectors of the main computing unit are soldered to a D Sub 50 plug that leads out of the CRM The P4 and P5 digital connectors of the sbRIO are forwarded in this way The pin out can be seen in Chapter 4 3 1 1 RX13_CERESS_SEDv3 1_12DEC14 doc Page 61 EuroLAuNcH A DLR and SSC Not every connection is used in the CERESS Mission but is provided for future experiments See 9 2Appendix C for more detailed signal connector and pin definition 4 2 2 3 CERESS Rocket Module internal interfaces The Rocket module will consist of three PCB One for each DC DC convertor and one housing interface electronics like the RS 422 chip and optocouplers The power boards are using separate power and data outputs Therefore two Samtec IPL1 connectors are used per PCB Due to volume restrictions the interface PCB will not use any connectors cables will be soldered directly to the board and the rocket modules interface connector to the REXUS service module The sbRIO s power supply is implemented using a two wire power connector that supplies 24 and 24 Ret to the sbRIO s power port The rocket modul
23. three Trajectories can be determined and compared 7 1 5 2 Correlations between Accelerometers and Gyroscopes The CERESS Rocket Module is equipped with 4 acceleration sensors in a tetrahedron configuration By using kinematics a correlation between acceleration and rotational rates can be defined A comparison of the calculated data with the measured data of the gyroscope would be interesting to judge the drift and accuracy of both measuring methods 7 1 5 3 Error calculation Altitude The CERESS Verification Module measures the static atmospheric pressure inside a vented REXUS Module This data is used to calculate the altitude of the CERESS Rocket Module This is correlated to the GPS and tracking data RX13_CERESS_SEDv3 1_12DEC14 doc Page 132 EuroLAuUNcH A DLR and SSC to evaluate the measurement error of the height calculated from the static pressure The occurring error will describe the quality of the implemented module venting 7 1 6 Flight Environment Characterisation of a REXUS Experiments flight environment is secondary objective of the CERESS Project Following measurements are taken to accomplish this task 7 1 6 1 Vacuum The fine pressure sensor of the CERESS Verification Module is used to measure the static pressure inside a vented REXUS Module during free flight thus the quality of vacuum is measured 7 1 6 2 Micro Gravity The CERESS Rocket Module is equipped with 4 acceleration sens
24. 4 2 2 4 2 3 4 5 amp 4 7 The electronics schematics must be improved significantly Urgently resolve all errors in the schematics The interface to the REXUS service module is incorrect Connect the correct pins Include filters in the schematics Information is included in the STW presentation and can be found on the teamsite o Do not leave any floating lines o Please send the corrected schematics to Martin Siegl deadlines see below they will be forwarded to Markus Pinzer o The PTC fuses are unlikely to trip before failure of the DC DC converters Lock the sbRIO connectors glue strap power is filtered through a fuse Clarify what is meant with this statement Provide a PCB design Include a grounding concept Beware of noise behaviour sensitivity issues of the sensor lines Thermal SED chapter 4 2 4 8 4 6 The approach to thermal design is fine thermal vacuum test should be performed to verify the thermal design Detailed calculations simulations need to be done Specify what calculations you will perform and carry them out Test or analyse the vacuum thermal conditions of the sbRIO Software SED chapter 4 8 Software development needs to proceed urgently Do not rely too heavily on software engineers who are not part of the team Carefully plan the prioritization of tasks and perform load tests Consider a stop byte on telemetry packets oO Q
25. 5 Updates due to design changes RX13_CERESS_SEDv3 1_12DEC14 doc ABSTRACT The analysis of previous REXUS projects at the Institute for Astronautics at TU Munich has shown that an entire infrastructure had to be designed and built for every new experiment The requirements of these experiment infrastructures are in general very similar Including a regulated power supply onboard data handling command and control of the experiment real time communication as well as interfacing the REXUS systems on the rocket and on ground Besides these basic functions many teams wish to have a real time visualization of the flight The main goal of the CERESS project is the development of a standard platform providing the most important functionalities allowing future teams at TUM to concentrate more on their scientific objectives Once verified on the first flight all used hardware e g Sensors can be directly applied to future experiments After recovery the onboard stored data the telemetry data from CERESS and from REXUS are merged into one data file for distribution analysis and outreach In addition to acceleration angular rate temperature and pressure sensors a camera documents the progression of the experiment Monitoring and control software on the ground enables a thorough surveillance of the experiment during the entire mission Functions like remote control of the experiment sensor or time based actions are provided A v
26. 5 2 1 2 1 Deleted 5 RX13_CERESS_SEDv3 1_12DEC14 doc Page 117 EurolLauncH 0 Requirement text Verification Status 2 1 2 2 Deleted 2 2 The system shall record a video of the T R To be flight resp of VE done 2 2 1 The video camera shall have a frame R To be rate between 25fps and 50fps done 2 2 2 The video camera shall have a resolution R To be of fullHD 1920x1080px done 2 3 The Verification Module shall show that T To be an Action triggered by the rocket module done is performed Table 33 Varification Matrix Requirement text Req Ground module Data Handling GM The Ground Module shall receive telemetry data from the ESRANGE ground networks Status To be done The Ground Module shall receive data from the CSRM via the REXUS downlink To be done 3 1 2 1 The Ground Module shall store the received data stream To be done 3 1 2 2 The Ground Module shall decode the received data streams into the usable data sets To be done The Ground Module shall send data to the CSRM via the REXUS uplink T R To be done 3 1 3 1 The Ground Module shall store the received data stream T R To be done 3 1 3 2 The Ground Module shall code the data that is to be send into the send data stream T R To be done The Ground Module shall be able to process down linked data from the 5 in near real time To be done
27. D E F ms 1 Priorit t Task Nr Task Deadline Kommentare Erledigt Erledigt am 2 3 Christoph 4 CF008 SED Kap 4 7 Power System 06 Jun First Draft Power Board kontrollieren lassen 5 CF009 Test f r jeden eurer Teile berlegen und in SED Kap 5 2 einf gen 20 Mai delayed 6 CF010 SED 6 mit Sebastian Launch Campaign Preparation 06 Jun delayed 5 13 Adapterplatinen festlegen 27 Mai 8 CF014 SED Kap 4 2 Elektical Interfaces 06 Jun 9 CF015 SED 4 5 mit Sebastian 2 El Design 06 Jun CF016 Requirements auf entprechende Systemlevels verteilen 27 Mai x 27 05 2012 11 CF017 Auf HP bei Alex Protokolant einf gen 10 Jun 12 CF018 Rocket Module Schaltpl ne machen 04 Jun 13 CF019 Verification Module Schaltpl ne machen 04 Jun Test f r jeden eurer Teile berlegen und in SED Kap 5 2 einf gen 20 Mai delayed Nochmals bei Jan Kniewasser melden 22 Mai delayed Analyse Software konzipieren 01 Jun erst nach Task 54010 E Software Flowchart erstellen erweitern 06 Jun in progress H hn wegen Vibrationssensor cooperation mit LRT fragen 10 Jun Bei Vektor nach Test Procedure des Rios fragen 13 Jun 23 Sebastian 24 SA002 Sponsoring Conrad Gutscheine f r Ware 16 Mai delayed 25 SA003 SED Kap 4 1 bearbeiten Exp Setup 06 Jun delayed Wir m ssen uns berlegen welche Daten wir brauchen nicht welche interessant sein k
28. E Ajquiassy eor 1 993 8 zu arz 2 6 1 4560 1 60 67 82 120 20 rr 8nvgo T RX13_CERESS_SEDv3 1_12DEC14 doc Page 34 EuROLAUNCH ADLR and SSC cooperation 9020 M 90t0 50 0 062 Gallet EL Dages Sieg EE EN wso 5 99381 27 228072 ZT POSEZ WI ZT das 60 60 zr Aew ver zr 2e er ZT uerez TT AON8Z TT POEO 3 80 iT Jdvger T 18 pueg Figure 3 Gantt Chart HX13 CERESS SEDv3 1 12DEC14 doc Page 35 EuROLAUNCH ADLR and SSC cooperation 3 2 Project plan Short term For short term coordination VBA Excel Sheet is used where every subtask is shown These Tasks have a nominal deadline within the next 2 weeks Each task has priority between 1 and 5 extreme urgent to do it later Done tasks get marked as complete and are tagged with the date The list is cleared of all completed task frequently Completed tasks are saved for records Figure 4 Short Term Action Items shows a part of the list as an example A 8 c
29. NEE 72 2 42 WEE e ET 75 Hull structural analysis EE 75 Cross beam natural vibration analysis 78 Electronics 80 4 5 1 System OVOLVIGW 25 80 Power Systems 81 Command and Control 82 Grounding Austern 84 4 5 4 Interface Board a etae etie aat ace a a ade 84 RS 422 Ri En e 85 Signal Intetpfeler eset e de RN d eters m bM ce 85 86 Interface Board PCB LAVOL ene 86 4 5 5 POWER Boards ciem een ees 87 Powerboard 1 24V o diete abicere 87 Powerboard 1 Iovout 00000 89 Powelboald 218 So V on ian talus eq ea da prato Ate 90 Powerboard 2 PCB 1 2 91 4 5 6 Thermist rss sa et cet 93 45 7 GoPro Hack ien ott 94 Thermal Design cn IP 95 Power System anann 96 Software Design Rocket Module 98 4 8 1 On Board data 98 Ee 98 Real Time Ge 98 48 2 OBDH us oso ave oe cers ME 99 POST Power 99 SPARTE 100 IDEE anne 100 BIT Build in 000
30. ON OFF for Fine Pressure Sensor Heating e Switch Power ON OFF for Coarse Pressure Sensor HX13 CERESS SEDv3 1 12DEC14 doc Page 46 A DLR and SSC The signals to trigger the power switching actions are generated by the MCU of the CERESS Rocket Module 4 1 2 2 Sensors Following Sensors are implemented in the CERESS Verification Module e Fine Pressure Sensor e Coarse Pressure Sensor e Temperature Sensors 4 1 2 3 Camera The Camera is pointing radial outwards of the REXUS Rocket A Camera window is implemented for this purpose The Camera is implemented by the GoPro 2 Hero HD 4 1 2 4 Camera Driver The Camera Driver switches the power of the Camera ON OFF and provides signals and signal feedback from and to the Camera for operations like power up record shut down and delete 4 1 2 5 Melting Wires Three Meltingwires are implemented in the CERESS Verification Module to verify the different control chains of the CERESS System Meltingwire 1 burned by an time triggered command Meltingwire 2 burned by an event triggered command Meltingwire burned by an TC triggered command Each Meltingwire provides a feedback signal if the Meltingwire is burned or not to enable successful verification even in case of no recovery of the CERESS Verification Module The Meltingwires are implemented by a modified melting wire mechanism developed and verified for the TU Munich CubeSat MOVE
31. Reasonable chance to occur D High Quite likely to occur E Maximum Certain to occur maybe more than once Severity S 1 Negligible Minimal or no impact 2 Significant Leads to reduced experiment performance 3 Major Leads to failure of subsystem or loss of flight data 4 Critical Leads to experiment failure or creates minor health hazards 5 Catastrophic Leads to termination of the project damage to the vehicle or injury to personnel Probability Severity 5 Risk index 5 Risk magnitude Unacceptable risk implement new process change baseline seek attention at appropriate high level Unacceptable risk see above Unacceaptable risk must be managed Consider alternative process or baseline Seek attention at appropriate level Acceptable risk control monitor consider options Acceptable risk control monitor RX13_CERESS_SEDv3 1_12DEC14 doc
32. Requirement satsiachon 28 3 PROJECT PLANNING 2 22 iii 29 3 1 c Projectplan Long terms aana a EE 29 3 2 Project plan Short 35 359 cHOSOGOS m 35 Ou geet 35 33 2 IGI 36 3 3 3 External SUDDOL iud Jose dnas np ub teret tei dashed 36 Fac S ash 37 3 4 Outreach ABDIOSETI oit 3T 3 9 Register se EA sd 39 4 EXPERIMENT 42 4 1 Experiment SGLUD teen tc ad ee hse ee ited sth Saleh ded sed 42 411 CERESS Rocket Module Space Segment 42 4 1 1 1 Main Computation IMac eka 43 4 11 27 dco aa incen ties 44 AAAS Sensor Driver Boald aaa ale 44 e NNEN 44 N SNS GUS uices A sees PIER oes oe IO IE vaca eves 44 4 1 16 Storage siia oie dais ng 45 RX13_CERESS_SEDv3 1_12DEC14 doc 4 1 2 1 4 1 2 2 4 1 2 3 4 1 2 4 4 1 2 5 4 1 2 6 4 1 2 7 4 1 3 1 4 1 3 2 4 1 3 3 4 1 3 4 4 1 3 5 4 1 3 6 4 2 4 2 1 1 4 2 1 2 4 2 1 3 4 2 1 4 4 2 2 1 4 2 2 2 4 2 2 3 4 2 2 4 4 2 2 5 4 2 2 6 4 2 2 7 4 2 2 8 4 3 4 3 1 1 4 3 1 2 4 3 1 3 4 3 1 4 4 3 1 5 4 3 2 1 4 3 2 2 4 1 2 The CERESS Verification Module Space S
33. TEN60 2415 is providing 24V In addition to the converters some more components are required for additional functionalities like measurement of current are required The functions of the Power Board are summed up below e Provide regulated 3 3V 5V and 24V e Measure level of output voltage e Measure current usage of rocket and verification module Due to volume restrictions it is not possible to have all power supply hardware on a single board Therefore each DC DC converter has its own circuit and PCB 4 5 5 1 Powerboard 1 24V The DC DC is connected to the 28V and RX GND lines of the Rexus service module To increase electromagnetic compatibility an input filter consisting of a series of capacitors and inductors is implemented In accordance to the converter s application notes a 4 7uF capacitor a TCK 048 common mode choke consisting of two inductors and another 4 7uF capacitor and inserted between 28V and GND Between the Vin and Vout as well as the Vin and Vout lines a 1nF 2kV capacitor is inserted for the same purpose According to the application notes this complies with EN55022 Class B conducted noise The TEN60 2415 has the capability to adjust the output voltage within a specified range by connecting the Trim Pin with either Vout or Vout through HX13 CERESS SEDv3 1 12DEC14 doc Page 88 A DLR and SSC coopera a resistor Connecting Trim to Vout results in a reduction of o
34. collector to GND storing or high impedance 4 SOE Start Stop of experiment Startup Shut down the open collector to GND CSRM and CSVM or high impedance 5 LO Lift off Synchronization of open collector to GND CSRM and ViTo data or high impedance timestamp RX13_CERESS_SEDv3 1_12DEC14 doc Page 58 EurolLauncH Pin Name Specification Usage 6 EXP out Non inverted experiment Transmit data from data from CSRM to RXSM CSRM to RXSM RS 422 7 EXP out Inverted experiment data Transmit data from to from CSRM to RXSM CSRM to RXSM RS 422 8 28V GND Power GND Ground connection of CSRM and CSVM 9 28V Battery Power Power the CSRM and 24 36 V unregulated CSVM via a DC DC peak lt converter 10 28 V Charging Experiment battery Not used Power charging power 11 spare 12 UTE not available Not used 13 EXP in Non inverted data from Receive CSRM control RXSM to CSRM RS 422 data 14 EXP in Inverted data from RXSM Receive CSRM control to CSRM RS 422 data 15 28V GND Power GND Ground connection of Table 11 RXSM Electrical Interface CSRM and CSVM The SOE SODS and LO signals are transferred by optocouplers as recommended as in the RX User Manual V7 3 The electrical layout of this interface can be seen below RX13_CERESS_SEDv3 1_12DEC14 doc Page 59 EuroLraunch ADLR and SSC c 50052 Port0 DIOC 4N28 D GND Figure 19 Optocoupler schemat
35. juan 75055 Lesues juaun 2 7108 06 zduio posuas e1nje1eduuo Po Addnawod HMd WYS X84 WYS eed ZAS 2120 LAS 2120 Las eed 05 NOW xogesn4 WASI X84 WASO 19420 5533329 WHSD RX13_CERESS_SEDv3 1_12DEC14 doc Page 148 DLR and SSC cooperati 1 1 2CERESS Verification Module uomejusuinijsu ISNI ____ _ 9e9jnpojy SS3332 WASI o eds HX13 CERESS SEDv3 1 12DEC14 doc Page 149 Lem a I 2 EuroLAUNCH 1 2 CERESS Ground Segment s 2 E 5 E 3 5 a 5 u RX13_CERESS_SEDv3 1_12DEC14 doc Page 150 EuroLAUNCH ADLR and SSC cooperation 2 CERESS Components Overview gt 53 uoneijs 39NV3S3 OVA MS ION OVA SNXIY 9S1njonujsejju 3ONVHS3 f19 0ui019 022V 05205 2 4190 9U1019 022 051205 2227 2 95205 2227 2 95205 22 2 p
36. mode Only needed telemetry for each mode is shown All other are Priority eleven no telemetry Fehler Keine g ltige Verkn pfung Table 30 Telemetry Budget As it can be seen there s no problem for too low data rate to ground In Normal Mode all Sensor Data is updated five times per second 4 8 6 Telecommand No continuous uplink for data transmission is planned Some commands are for additional BIT or configuration downlink The Telecommand Data Frame is similar to the Telemetry 4 8 7 Data Storage The data storage is done with a NI 9802 SD Card Module It allows acces on file level Following Files are used e One for each sensor e Telemetry Telecommand The file format is bin to save space Postprocessing will convert files to readable format Additional the onboard non volatile storage of the sbRIO is used for e Timeline including all relevant Mode Changes Powerups etc RX13_CERESS_SEDv3 1_12DEC14 doc Page 106 EuroLAuUNcH A DLR and SSC coopera The file format is txt with information organized in columns and Ongoing timestamps in lines 4 8 7 1 Budget Table 31 Data Storage Budget shows the calculation of the data volume due to Telemetry amp Measurement The duration is defined by flight time 800s and spare 200s for possible test runs The data will be stored in two different SD Cards parallel to ensure a recovery of the data The Data Volume is no problem due today s storage devices
37. the test run the experiment module is submitted to integration on the REXUS rocket HX13 CERESS SEDv3 1 12DEC14 doc Page 127 EuROLAUNCH A DLR and SSC cooperation 6 3 Launch Campaign Timeline CERESS Launch Campaign Timeline based on Presentation at Student Training Week fd BIT Day 2 Data Data availability check Launch angles Launch angles GPS etc heck Communication Laptop lt gt Internet heck Communication WebCam lt gt Internet ERESS assembly Day 3 ICERESS assembly Visualization Check data GM gt Visualisation Visualization Check data RM hard saved gt Visualisation Visualization Check data RM sensors gt Visualisation Day 4 ERESS flight simulation light Readiness Review preparation Se gees Table 39 Launch Campaign Timeline RX13_CERESS_SEDv3 1_12DEC14 doc Page 128 EuroLauncu 6 4 Timeline for countdown and flight CERESS CERESS TIME s ESRANGE Ground Module Rocket Module Initialize 3600 Plug In before Flight insertion STATE to POST 1000 Power On gt STARTUP gt IDLE Check Check Communication Communication STATE to and 660 back Display BIT 600 Acq VALUES 480 Provide VALUES Switch to Flight 120 Visualization STATE to NORMAL 60 SODS act w o PIRANI Internal Timer Reset Internal Timer Reset 0 LO act STATE to NORMAL 80 to be SOE act with PI
38. usage 4 3 1 2 Gyroscope L3G4200D The Gyroscope provides the possibility to be run on different ranges It is only necessary to switch the configuration and this gyro can be used for high rotatory velocities around 5 5Hz or slow ones around 0 72 Both configurations are flown for best results For communication the SPI is used 4 3 1 3 Accelerometer LIS331HH Similar to the Gyroscope this sensor can be used During engine powered ascending of the rocket the 24g mode is used wider range lower accuracy using four sensors during free flight further four sensor provide measurements within the range of 6g lower range higher accuracy For communication the SPI is used 4 3 1 4 Power Supply TEN 40 2420 amp TEN60 2415WI As a regulated power source the products of TRACO POWER are well known and already flown on other REXUS Projects 4 3 1 5 Structure Structure is everything needed to keep the components in place In this case it includes also the structure of the CERESS Verification Module for easier budgeting 4 3 2 CERESS Verification Module The CERESS Verification Module houses the sensors that aren t relevant for the trajectory but useful for event detection or demonstration of the CERESS Rocket Module s functionality To verify the control of the CERESS Verification Module by the CERESS Rocket Module CERESS Verification Module Interface three melting wires are blown during flight 4 3 2 1 Camera GoPro HD2
39. values are stored on the non volatile storage on the sbRIO due the fact they only change values if the assembly is modified or corrupted 4 10 1 4 Data processing 1 Zero G offset interpretation 2 Attitude correction through CERESS calibration values 3 Calculation of acceleration by linear correlation to native 16bit values 4 Filter 5 Possible Mean Value generation from all devices 6 Possible Integration to Position 4 10 2 Gyroscope 4 10 2 1 Zero rate level Zero rate level describes the actual output signal if there is no angular rate present L3G4200D pdf p 14 This implies that values below the Zero rate level has to be interpreted as no rate 4 10 2 2 CERESS calibration The zero rate level of precise MEMS sensors is to some extent a result of stress to the sensor and therefore the zero rate level can slightly change after mounting the sensor onto a printed circuit board or after exposing it to extensive mechanical stress This value changes very little over temperature and time L3G4200D pdf p 14 HX13 CERESS SEDv3 1 12DEC14 doc Page 111 EuroLraunch ADLR and SSC c Furthermore the imperfect horizontal alignment of the devices within the RM the attitudes have to be defined by measurements on a horizontal reference plane with a rotatory degree of freedom The calibration values are stored on the non volatile storage on the sbRIO due the fact they only change values if the assembly is modifi
40. 0 0 Verification and testing SED chapter 5 HX13 CERESS SEDv3 1 12DEC14 doc 143 EuROLAUNCH A DLR and SSC cooperation The test plan is well developed and could be expanded with tests for subsystem testing and different failure modes dropout of data power etc Internal Panel Discussion Summary of main actions for the experiment team Rework the camera mounting to make it stiffer and stronger Add arm plug design The electronics schematics must be improved significantly Provide a PCB design Detailed calculations simulations need to be done Specify what calculations you will perform and carry them out Software development needs to proceed urgently CDR Result Pass under the following conditions Complete electronics schematics and PCB design are submitted no later than 25 July 2012 An iteration of the SED is submitted as specified below Next SED version due Version 2 1 is due on 31 July three weeks after receipt of this document and shall address all open items Provided that Version 2 1 addresses all open items Version 3 0 will only need an update of the project management part RX13_CERESS_SEDv3 1_12DEC14 doc Page 144 APPENDIX B OUTREACH MEDIA COVERAGE Print amp Online Releases Media Publisher Content Homepage CERESS Detailed project information http ceress de
41. 0 and 200 C 1 2 5 2 The internal temperature sensor shall be R To be able to measure temperatures with an done accuracy of 1 C 1 2 5 3 The internal temperature sensor shall R To be make 1 temperature measurement every done second The rocket module shall retrieve data A R 1 3 Req Software 3 To be from internal sensors done 1 3 10 The rocket module shall be capable to A R T To be perform operations on the verification done experiment 1 3 11 The rocket module shall be capable to A R T To be execute received commands done 1 3 2 The rocket module shall retrieve data A R T To be from verification module sensors done 1 3 3 The rocket module shall safe retrieved A R T To be data from sensors done 1 3 3 1 The rocket module shall safe the H To be retrieved data from the sensors with done 1000Hz 1 3 4 The rocket module shall be capable to A R T To be interpret the received data done HX13 CERESS SEDv3 1 12DEC14 doc Page 115 Eurolauncn 0 Requirement text Verification Status 1 3 8 The rocket module shall be capable to R T To be be self tested done 1 3 8 1 The rocket module shall be capable to R T To be detect malfunctions done 1 3 8 2 The rocket module shall be capable to R T To be perform counteractive measures if an done malfunction is detected 1 3 9 The CSRM shall accept a request for R To be radio silence at any time while on the done lau
42. 1 6 5V sbRIO No Connection SPI DOUT 7 Port0 DIO2 Accelerometer1 8 DGND Accelerometer1 SPI Enable GND 9 Port0 DIO3 Accelerometer2 10 5V sbRIO No Connection SPI SPC 11 Port0 DIO4 Accelerometer2 12 D GND Accelerometer2 SPI DIN GND 13 Port0 DIO5 Accelerometer2 14 D GND No Connection SPI DOUT 15 Port0 DIO6 Accelerometer2 16 DGND No Connection SPI Enable 17 PortO DIO7 Accelerometer3 18 D GND Accelerometer3 SPI SPC GND 19 Port0 DIO8 Accelerometer3 20 D GND No Connection SPI DIN 21 Port1 DIO9 Accelerometer3 22 Port1 DIOCTL Relay2 SPI DOUT 23 Port1 DIOO Accelerometer3 24 D GND Relay2 GND SPI Enable 25 Port1 DIO1 Accelerometer4 26 D GND Accelerometer4 SPI SPC GND 27 Port1 DIO2 Accelerometer4 28 D GND No Connection SPI DIN 29 Port1 DIOS Accelerometer4 30 D GND No Connection SPI DOUT 31 Port1 DIO4 Accelerometer4 32 D GND No Connection SPI Enable 33 Port1 DIO5 Gyro1 SPI SPC 34 D GND Gyro1 GND 35 Port1 DIO6 Gyro1 SPI DIN 36 D GND No Connection 37 Port1 DIO7 Gyro1 SPI DOUT 38 D GND No Connection RX13_CERESS_SEDv3 1_12DEC14 doc Page 66 Eurolaunch 39 Port1 DIO8 Gyro1 SPI Enable 40 D GND Relay3 GND 41 Port2 DIO9 Data Storage1 SPI 42 Port2 DIOCTL Relay3 CLK 43 Port2 DIOO Data Storage1 SPI 44 D GND Data Storage 1 DIN GND 45 Port2 D
43. 109 A DLR and SSC CERESS Rocket Module It will be implanted with LabView due the possibility to display data in real time in graphical diagrams 4 9 4 Visualization Tool ViTo Tool is implemented as a Google Earth plugin which consists of two kml files The Client file is run by Google Earth It tells the Plugin how data is visualized and the address of the required server file on the internet The server file contains the data that is to visualize and is updated by the GM frequently Since there are two possibilities show the trajectory in realtime and afterwards there has to be different modes 4 9 4 1 Flight Mode The Data is supplied via the Internet when ViTo is in Flight Mode Only the position and the trajectory will be displayed 4 9 4 2 Post Flight Mode The data is supplied via a file generated by the CERESS Ground Module Visualization Server In addition to the trajectory the sensor data detected events like nose cone ejection or engine stop are available in the post flight visualisation 4 9 5 Service Computer The service computer is used for configuring programming and testing the rocket module after integration of the Processing Unit and during launch preparations Therefore the service computer may be considered as Ground Support Equipment It is the same through the whole project A team member s laptop is used for this purpose 4 10 Calibration and other Terminolog
44. 13 11 10FS 60 12 days Daniel Bugger 12 1 Daniel Bugger 12 1 1 Daniel Bugger 24 12 1 2 12 2 Christoph Friedl 12 2 1 Christoph Friedl Sebastian 12 2 2 Althapp Y 12 3 Implement pups 120 days Software Testing STEE IPR 0 days EAR 0 days Integration Week 5 days System Testing 5 days Launch Campaign 10 days Experiment Results Symposium sani 8 462 days Proj 462 51 462 days Documentation 462 days Outreach 462 days Table 7 Project Plan RX13_CERESS_SEDv3 1_12DEC14 doc Fri 25 05 12 Fri 09 11 12 Tue 16 10 12 Sat 01 12 12 Mon 14 01 13 Mon 18 02 13 Mon 29 04 13 Mon 03 06 13 Thu 01 09 11 Thu 01 09 11 Thu 01 09 11 Thu 01 09 11 Thu 01 09 11 Thu 08 11 12 Thu 20 12 12 Tue 16 10 12 Sat 01 12 12 Fri 18 01 13 Fri 22 02 13 Fri 10 05 13 Fri 07 06 13 Fri 07 06 13 Fri 07 06 13 Fri 07 06 13 Fri 07 06 13 Fri 07 06 13 Page 31 Alexander Schmitt 12 3 1 Alexander Schmitt Daniel 30 12 3 2 Bugger 24 27 12 4 13 14 15 16 17 Daniel Bugger 18 Daniel Bugger 18 1 Daniel Bugger 18 2 Alexander Schmitt 18 3 Christoph Friedl Sebastian 18 4 Althapp Page 32 EuroLAUNCH Ster 1 590 21 90 62 zr dsseo men zt Aewet Come zr uerez rr oNsc 22060 rr 8nvso ue HX13 CERESS SEDv3 1 12DEC14 doc Page 33 EuroLAUNCH SSC cooperation D erroz
45. 13_CERESS_SEDv3 1_12DEC14 doc Page 74 EuroLAUNCH ADLR and SSC cooperation Figure 23 The electronic Boards To be able to calculate the rotation axis just with accelerometers they have to be placed as a triangle And to be redundant there is a tetrahedron configuration with 4 sensors 3 of the 4 sensors are mounted on the rear side of the bulkhead The fourth is with the gyro placed on a crossbar at the centre of the main rotation axis X axis of the rocket see Figure 24 Crossbar with Gyro and Accelerometer Figure 24 Crossbar with Gyro and Accelerometer All structural components shielding sensor mounts etc are made from aluminium RX13_CERESS_SEDv3 1_12DEC14 doc Page 75 EuroLAuUNcH A DLR and SSC Part WESSELS Bulkhead Hull 4 5 Shielding 0 625 Sensor mounts 0 34 EPS 0 25 Sensors 0 3 Camera 0 2 sbRio 0 3 Wiring 0 3 Summed 2 315 44 5 Margin 30 96 0 665 Total Bulkhead amp Hull 2 98 44 5 Table 22 Mass Budget 4 4 2 FE Analysis 4 4 2 1 Hull structural analysis A static stability analysis was carried out for the hull with special attention on the cut out for the outer hatch The boarder conditions were a rigid clamping at the bottom an overall acceleration of 20 g 196 2 m s and the static force of the other modules 55kg and the nosecone section 13 kg with the acceleration of 20g times a safety factor of 1 5 20012 4N at t
46. 14 doc Page 63 e 3 3V Digital I O 2 e 3 3V Digital I O 3 e 3 3V Digital I O 4 e 24V Digital In e 24V Digital Out Analogue I O e PWR providing 3 3V 5V 24V 28V unregulated REXUS power The power connector must be able to accommodate the four input voltages For each voltage there should be three pins for voltage and three pins for ground This adds up to a total of 24 pins the connector used will therefore be a D Sub 25 connector 1 3 3V PWR 2 3 3V GND 3 3 3V PWR 4 3 3V GND 5 3 3V PWR 6 3 3V GND 7 5V PWR 8 5V GND 9 5V PWR 10 5V GND 11 5V PWR 12 5V GND 13 24V PWR 14 24V GND 15 24V PWR 16 24V GND 17 24V PWR 18 24V GND 19 Spare 20 28V unregulated PWR 21 28V unregulated GND 22 28V unregulated PWR 23 28V unregulated GND 24 28V unregulated PWR 25 28V unregulated GND Table 14 Power Connector Layout The main computing unit provides four 50pin connectors for digital input output and one 50 connecter for analogue input Two of the digital connectors and about half of the analogue connector will remain in the rocket module while the remaining connectors and pins are forwarded to the verification module The digital 50pin connectors of the main computing unit are soldered to a D Sub 50 plug that leads out of the CRM The and 5 digital connectors of the sbRIO are forwarded in this way The pin out can be seen in Chapter
47. 14 doc Page 81 EuroLAuUNcH ADLR and SSC Space Segment CSVM CERESS Verification Module 28V unregulated Figure 33 Overview Electrical System 4 5 2 Power System The electrical power for the CERESS Rocket Module as well as the CERESS Verification Module is supplied by the REXUS service module in the form of unregulated electrical power with typical voltage of 28VDC This unregulated power source is converted in the CERESS Rocket Module to provide regulated power for itself and the verification module as shown below In the CERESS Rocket Module is protected by a PTC self resetting fuse to prevent overvoltage from the service module to the DC DC convertors and vice versa Incoming power is then converted to 3 3VDC 5VDC and 24VDC in two DC DC convertors Directly after the DC DCs the voltages are split in to two lines each One line goes together with its respective GND line to the power interface to the verification module The other line stays in the board for powering components of the rocket module In each of these lines there is a shunt resistance connected to a high side current sense chip to allow measurement of output current The 3 3V are used to power the accelerometers and gyros of the rocket The 3 3V are also connected to the optocouplers in order to allow the experiment to use the 28V signal lines 24V output is used to power the sbRIO RX13_CERESS_SEDv3 1_12DEC14 doc Page 82
48. 1919u1019 022 4 4 1 6 951209 2 4 LSNI xogesn4 WHS X84 WUSI O LIA MS OLIA 5 1952 US WOSD 19 SS3332 WOSD 5 eeg LOS 9 ej191u 5005 5005 305 305 1025 eeg 05 01 07 uonejnduio NOW gdl Z osuag o1nje1eduuo zdweL o1nje1oduio A ddns 1932034 654445 WUSI 10suog o1nje1oduuo Ziosuae ounje1oduuo zdweL J0SUOS 0188014 9891200 7804 2 o nyesodwe pwal 1 OINSSAlg 4 Lead 4 uonejuownasu ISNI YAA 9jnpojy 6544425 WASI uawas aoeds 5 SS3332 HX13 CERESS SEDv3 1 12DEC14 doc Page 151 EuroLAuNcH A DLR and SSC coopera Additional information can be found in the files attached to this SED RX13_CERESS_SEDv3 1_12DEC14 doc Page 152 A DLR and SSC coopera APPENDIX D EXPLANATION OF RISK REGISTER Risk ID TC technical implementation MS mission operational performance SF safety VE vehicle PE personnel Probability P A Minimum Almost impossible to occur B Low Small chance to occur C Medium
49. 3 6 Visualisation Tool e Displays 3D Flight Visualization A local instance of the ViTo can run as a CERESS Ground Module Client without the need of the ESRANGE Internet connection if Internet connection is applicable 4 2 External Experiment Interfaces The main Interfaces of the CERESS system are shown in Figure 8 CERESS Interfaces bdd Package Blocks Overview J _ F M __ A external external RSM RGM R REXUS Service Module EC e TET ent e RSM RGM E 1 M REXUS Bus A RcM cm RGM GM subsystem subsystem RM GM Ground Module E gt 3 Da Service interface Bern ea Service Computer i pere C2 Service Interface BEL ens CERESS Bus Verification Module Visualization Tool Figure 8 CERESS Interfaces 4 2 4 Mechanical Interfaces REXUS Bus 4 2 1 1 On Bulkhead On top of the bulkhead the rocket module and the fine air pressure sensor are mounted seeFigure 9 Top view of the bulkhead The carrier structure is fixated with 14 screws of the size M4 The fine air pressure sensor is mounted with 4 screws of size M4 The sbRio is mounted directly on the Bulkhead with 12 screws of size M3 see Figure 10 sbRio on Bulkhead Below the bulkhead the 6 accelerometers two times the bottom triangle of the tetrahedron are mounted to protect the sensors and the wiring a prote
50. Can be difficult for system level verification Considering this experiment requirements become so much more important What s missing is a market survey of what could be accommodated Sensors that could be connected to this should be included that CERESS would still function if these were connected Mechanical Camera viewport be made to fit to the camera to reduce its size Piranis can actually survive Cable feedthrough extended to wall and positioned at 1800 Consider ports on top on top rather than on the side for accessibility Mass budget nice and clear Electrical wire electronics students will be same as focus used power schematic for soRIO should be included in SED Interface lines to RXSM should also be included Must be careful with reliability with using modules and other software with using LabView Who will manufacture PCBs Students to be done outside Sensitivity analysis would be a good thing to do Need to careful of behaviour of sensors when packaged together for a flight Careful of I O connectors and sensitivity to EMI Sub Ds normally used consider lockable mil c connectors or RX13_CERESS_SEDv3 1_12DEC14 doc Page 139 A DLR and SSC coopera Experiment PDR ESRANGE Kiruna 28 Feb 2012 other consider expensive sub Ds Thermocouples can be connected through the connectors but will require the
51. Capcitators Various suppliers components resistors SD Card 9802 National Board Instruments Camera GoPro HD2 camforpro com Melting wires TUM LRT workshop Structure TUM LRT workshop Table 21 Part Availability 4 4 Mechanical Design 4 4 1 Setting Current status of supplier The Ceress Rocket Module is located inside the shielding The Ceress Verification Module is mounted directly to the hull and bulkhead see chapter 4 2 1 for details As well as the hull the shielding box has a hatch The hatch is located directly behind the outer hatch The two hatches injure the late access possibility of the sbRIO there i e the RJ 45 connector the reset button and the status LEDs see Figure 21 Inner Hatch HX13 CERESS SEDv3 1 12DEC14 doc Page 73 EuroLAUNCH ADLR and SSC Figure 21 Inner Hatch uc E I The shielding is designed with a frame structure to carry the loads and shielding plates The front and back plate are secured against lateral oscillation with groove in the bulkhead All other connections are done with Screws Figure 22 Frame structure and shielding Frame Inside the shielding are the sbRIO two Accelerometers two Gyros located the SD Card Board the two Power Boards and the interface Board See Figure 23 The electronic Boards RX
52. Design Plug on Hatch The hatch shall provide a plug for programming and Checking 1 7 Req Processing Unit 1 7 1 Deleted 1 7 2 Design Connection to Gyros 1 7 3 Design Connection to Verification Module 1 7 4 Functional Processing The Processing Unit shall be capable to speed perform the logging actions within near real time 1 8 Req Structural 1 8 1 Design Position of Maximum X 20 mm Y 20 mm Z 20 CoG mm 1 8 2 Design Moment of Maximum Ix 0 1 kg m2 ly 0 1 kg m2 Inertia Iz 0 1 kg m2 1 8 3 Design Total Mass Shall not deviate more than 0 5kg 1 8 4 Design Mass Around 0 25kg per 100mm distribution Table 2 CERESS Rocket Module Requirements HX13 CERESS SEDv3 1 12DEC14 doc Page 25 A DLR and SSC 2 2 Requirements CERESS Verification Module 2 1 Functional Sensors 2 1 1 Functional Temperature The system shall measure the temperatures inside the VE 2 1 1 1 Performance Temp range The temperature sensor shall be able to measure temperatures between 40 and 200 C 2 1 1 2 Performance Temp The internal temperature sensor accuracy shall be able to measure temperatures with an accuracy of 1 C 2 1 1 3 Performance Temp The internal temperature sensor measurement frequency shall make 1 temperature measurement every 2 1 2 Deleted E 2 1 2 1 Deleted 2 1 2 2 Dele
53. EC14 doc Page 57 A DLR and SSC cooperation 5 S RM Sensors 8 ar 3 4 bRIO f 5 VM Board D Sub 9 D Sub 9 D D GND 5 A 2 9 gt SR 2 AIGND gt 2 PWR GND SS e Coi Cable 50pin DIO 4 50 Ce DSub25 3 a a ei a 18 D Sub 9 1 E 1515 gt 5 y gt 15 gt m ki E PWR PWR gan E D Sub 25 Power Con Power Interface Board D Sub 15 3527 lifi Figure 18 Electrical interface overview The following subchapters will further detail these interfaces See 9 2Appendix C for even more detailed signal connector and pin definitions 4 2 2 1 REXUS Bus The CSRM uses the Power and Control Interface of the RXSM The control interface uses the RS 422 EXP in out Both interfaces are implemented as D SUB Connector Pin Name Specification Usage 1 28V RXSM Power Power the CSRM and 24 36 V unregulated CSVM via DC DC l peak lt converters on the power board 2 spare 3 SODS Start Stop of data storage Trigger CSRM data open
54. IO6 Data Storage1 SPI 46 D GND No Connection DOUT 47 Port2 DIO7 Data Storage1 SPI 48 D GND No Connection Enable 49 Port2 DIO8 No Connection 50 DGND No Connection Table 16 P2 Digital Connector Pin usage P3 Digital Connector 1 DGND SODS GND 2 Port0 DIOCTL SODS Signal 3 PortO DIOO Accelerometer5 4 Port0 DIO9 Accelerometer5 SPI SPC GND 5 PortO DIO1 Accelerometer5 6 5V sbRIO No Connection SPI DIN 7 Port0 DIO2 Accelerometer5 8 DGND No Connection SPI DOUT 9 Port0 DIO3 Accelerometer5 10 5V sbRIO No Connection SPI Enable 11 Port0 DIO4 Accelerometer6 12 D GND Accelerometer6 SPI SPC GND 13 Port0 DIO5 Accelerometer6 14 D GND No Connection SPI DIN 15 Port0 DIO6 Accelerometer6 16 D GND No Connection SPI DOUT 17 Port0 DIO7 Accelerometer7 18 D GND Accelerometer7 SPI Enable GND 19 Port0 DIO8 Accelerometer7 20 D GND LO GND SPI SPC 21 Port1 DIO9 Accelerometer7 22 Port1 DIOCTL LO Signal SPI DIN 23 Port1 DIOO Accelerometer7 24 D GND No Connection SPI DOUT 25 Port1 DIO1 Accelerometer7 26 D GND No Connection SPI Enable 27 Port1 DIO2 Accelerometer8 28 D GND Accelerometer8 SPI SPC GND 29 Port1 DIO3 Accelerometer8 30 D GND No Connection SPI DIN 31 Porti DIO4 Accelerometer8 32 D GND No Connection SPI DOUT HX13 CERESS SEDv3 1 12DEC14 doc Page 67 EuroLauncu 33 Port1 DIO5 Accelero
55. P GND 17 Port3 DIO2 Feedback 18 D GND Feedback Camera Camera P S GND 19 Port3 DIO3 Feedback 20 D GND Activate Camera P Camera S GND 21 Port3 DIO4 Activate Camera 22 D GND Activate Camera S P GND 23 Port3 DIO5 Activate Camera 24 D GND Activate Camera GND 25 Port3 DIO6 Activate Camera 26 D GND Feedback Safety Pin GND 27 Port3 DIO7 Feedback Safety 28 D GND Activate Melting Pin Wire 3 GND 29 Port3 DIO8 Activate Melting 30 D GND Activate Melting Wire 3 Wire 2 GND 31 Port4 DIO9 Activate Melting 32 Port4 DIOCTL No Connection Wire 2 33 Port4 DIOO No Connection 34 D GND Activate Melting Wire 1 GND 35 Port4 DIO1 Activate Melting 36 D GND Feedback Melting Wire 1 Wire 3 enable GND HX13 CERESS SEDv3 1 12DEC14 doc Page 69 37 Port4 DIO2 Feedback Melting 38 D GND Feedback Melting Wire enable 3 Wire 2 enable GND 39 Port4 DIO3 Feedback Melting 40 D GND Feedback Melting Wire 2 enable Wire 1 enable GND 41 Port4 DIO4 Feedback Melting 42 D GND Feedback melting Wire 1 enable wire 1 burn GND 43 Port4 DIO5 Feedback melting 44 5V No Connection wire 1 burn 45 Port4 DIO6 46 D GND Feedback melting wire 2 burn GND 47 Port4 DIO7 Feedback melting 48 5V No Connection wire 2 burn 49 Port4 DIO8 Feedback melting
56. RANI checked Burn Meltingwire 100 time triggered Send Meltingwire Il 300 signal Meltingwire II 300 offset from ground triggered Meltingwire IIl Possible event triggered time range tbd Switch Visualisation STATE to Shutdown 1000 SODS deact to Interpolation 1010 Power Off estimated by CDR Gremium RX13_CERESS_SEDV3 1_12DEC14 doc Page 129 A DLR and SSC Note Like in the CDR discussed the meltingwires will get time slots in which they can be activated The timeslots have to defined in agreement with the other teams to prevent peak currents 6 5 Post Flight Activities Recover storage device from CERESS Rocket Module if CERESS is recovered e Transfer storage device to GM e Check Meltingwires document status e Backup the data e Process the data for post flight visualization e Thank Sponsors RX13_CERESS_SEDv3 1_12DEC14 doc Page 130 7 DATA ANALYSIS PLAN 7 1 Data analysis plan Verification of the CERESS System is one primary objective of the CERESS Project Therefore the collected data is mainly used to evaluate different verification aspects 711 Verification Triggered Events Command and Control of Experiment time triggered event Command and Control of Experiment event triggered event Command and Control of Experiment TC triggered event CERESS is designed to provide the data needed
57. RESS Ground CERESS Ground Module Client CERESS Ground Module Module Client2 Client3 ViTo Server TCP IP 3D KML File ESRANGE INTERNET 2 CONNECTION Internet CERESS Visualisation Tool Internet Server 1 Figure 55 Connections at ground segment 6 2 Preparation and test activities at ESRANGE Since the CERESS Experiment does not contain any hazardous decomposing or overly fragile objects it arrives at ESRANGE fully assembled meaning all components are already mounted in flight configuration Flight software is preinstalled and only changed if necessary To ensure launch readiness the experiment is inspected on arrival by the team including visual inspections and functional tests 1 Visual inspections e Check for damage inflicted during transport e Check for any loose screws bolts or connectors e Check solder joints 2 Functional tests e Turn on ground support equipment and run software e Connect experiment to power source HX13 CERESS SEDv3 1 12DEC14 doc Page 126 Experiment Status Checkout Turn on power supply and check correct output voltages of DC DC convertors Turn on sbRIO and check for nominal sensor data of all sensors Run experiment timeline according to flight plan wire melting simulated Check data storage of experiment and camera for correctly stored data and GSE for downlinked data Test debriefing of the Team Plan further steps if necessary After completion of
58. RESS Ground Segment RX13_CERESS_SEDv3 1_12DEC14 doc Page 108 The CERESS Ground Module has several screens They can be categorized in Controls and Displays The Flight Visualization Display presents connections processing time and a preview of the Visualization as well the captured webcam stream For insurance of proper functional behavior both live streams are used for checking on the programing Unit The upper right shows the development and preflight situation for programming with the CERESS Module 4 9 2 Trajectory determination principles Three possibilities are considered for trajectory determination 1 The easiest way is to use GPS signal that is sent from the RXSM and fed to the data stream that is provided at the ESRANGE Ground Station Filtering of the received data will be necessary to fit it to the required refresh rate of the visualization tool The ESRANGE Link Antenna provides the range between the rocket and ground station and two angles The Azimuth and Elevation Angle These together define a vector on which the REXUS rocket probably is located The principle is also shown in Figure 54 B Elevation Altitude 4 lt Azimuth 4 9 3 CERESS Ground Module Clients The CERESS Ground Module provides a software interface to display all downlinked information and a possibility to communicate with the Figure 54 Trajectory determination RX13_CERESS_SEDv3 1_12DEC14 doc Page
59. Rocket Module The REXUS Bus is connected to the CERESS Rocket Module by the Interface Board containing optocouplers as galvanic isolation of the three command signals SOE SODS and LO and a RS 422 conversion chip to allow RX13_CERESS_SEDv3 1_12DEC14 doc Page 84 A DLR and SSC EuroLAuNcH communication with the experiment And both ensure the floating ground of the Ceress rocket module due to the galvanic isolation All sensors of the rocket and service module deliver their signals to the soRIO via digital interfaces or the analogue inputs The data is stored in raw form by the Data Storage 1 and 2 and sent to the ground module The sbRIO is used to control various relays and circuits that switch sensors heating foil camera melting wires ON OFF The data flow within the sbRIO resp the software is explained in Chapter4 8 4 5 3 1 Grounding Concept The Ceress space segment has several electrical grounds 28V GND from the Rexus SM 3 3V Ret and 5V Ret from DC DC1 e 24V Ret from DC DC2 Al GND and D GND from the sbRIO The Rexus GND is used together with the 28V to power the two DC DCs and is not connected to any other component of the experiment Ceress has a variety of devices both analogue and digital The signal lines of these devices require a stable ground for representative measurements They are therefore connected to the sbRIO s analogue Al GND or digital ground D GND respectively The connect
60. SEDv3 1_12DEC14 doc Page 40 A DLR and SSC Action Select suitable sensor to withstand the external environment Select suitable camera to withstand the external environment Write software to be able to handle temporary and continuous loss of connection Redundancy due to onboard data storage Downlink data test functionality Select screw able connectors where possible or glue tight Use several mounting points check every component before flight For every critical system a back up person has to be qualified to fill in good time management for enough buffer Order early Page 41 ADLR and SSC coopera Risk amp Consequence Experiment funding not sufficient PR30 Have different sources of capital e g tuition fees sponsorings Table 10 Risk Register RX13_CERESS_SEDv3 1_12DEC14 doc Page 42 EuroLAuNcH 4 EXPERIMENT DESCRIPTION 41 Experiment Setup In the following sections the different subsystems and components of the CERESS System are described multiple times from different views e g Mechanical Electrical Software etc The CERESS System consists of a space and a ground segment each containing several subsystems which themself contain several components The connections and interactions between the REXUS Rocket and the CERESS Rocket Module are de
61. SEDv3 1_12DEC14 doc 12 List of tables Table 1 CERESS Team Members enn 20 Table 2 CERESS Rocket Module Requirements nn 24 Table 3 CERESS Verification Module Requirements nn 25 Table 4 CERESS Ground Module 27 Table 5 CERESS Visualization Tool Requirements sess 28 Table 6 Working field mappimg nn 29 ibable in ade a und 31 Table 8 Budget Overview 2 36 Table 9 Outreach 0 2 00 40 38 Mable TOP RISK 41 Table 11 RXSM Electrical 1 58 Table 12 Power Connector LayOoll e RR IRR ute dias 60 Table 13 RXSM Electrical Interface 62 Table 14 Power Connector Layout 63 Table 15 Experiment Summary ass 64 Table 16 P2 Digital Connector Pin usage 66 Table 17 P3 Digital Connector Pin usage ee 67 Table 18 P4 Digital Connector Pin usage 68 Table 19 Digital Connector Pin usage 69 Table 20 Analogue Connector Pin usage EEN 70 Table 21 Part Avallability oreet unen to ie pore ptr pecu bano e pour prex bar petra 72 Table 22 Mass eto haa deed d dnte ted cud heut dud erg 75 Table 237 lee e dco ie ciini pee ue pe
62. Therefore they are explained here 4 8 3 1 State and Value Collector All collected data has to be available for downlink or interpretation e g time trigger event Therefore these functional blocks make the data available to downlink preparation as well as regular data storage Some additional information like sample counts of sensors or running time is prepared The blocks buffer the data in appropriate Frequencies 4 8 3 2 Mode Setter This block receives the modes set by the Sequencer located on the RT Processor through the Information Transfer blocks It just sets for every functional block the new desired mode 4 8 3 3 Information Transfer The four blocks shown in Figure 49 buffer all state information and transfer them to the Target resp buffer and transfer all mode information to the target Due the handshake principal its processor blocking behaviour no sensor values are transferred 4 8 3 4 File Control The File Control block checks the SD Cards for existing Files and defines new ones if necessary Especially after a power loss the block is responsible for File Handling 4 8 3 5 Event Logger The Event Logger stores all Mode Changes and File Information for a successful recovery after power losses and prevents unwanted data loss due file overwriting or comparable occurrences The Event Logger uses the internal non volatile storage of the sbRIO 4 8 3 6 Sensors and I O Nodes These threads communicate with th
63. a and print media Currently the focus is on online outreach to raise public interest towards CERESS and the REXUS programme in general This includes our homepage http ceress de which is updated continuous with the work in progress giving detailed information on the goals project definition and project progress To reach an even broader community of interested people our outreach programme relies heavily on social networks including Facebook http facebook de Team Ceress Twitter http twitter ceress de and YouTube http www youtube com user CeressRexus Facebook is used to provide status updates on the project s progress as well as sharing pictures of our team at work and at REXUS related events e g selection workshop or training week Twitter is used to distribute news of the project and promote changes of the homepage in a fast way YouTube is used for uploading videos of work and project related events The print media outreach is intended to start later on in the project It involves distribution of press releases to various newsletters local newspapers and even local TV stations about our participation in the REXUS programme Posters and flyers distributed at TU Munich are also planned mainly in the engineering faculty but also in other faculties as well The CERESS Team is going to join Dr Ing Andreas Stamminger from MORABA on his presentation about MORABA at the TU Munich In addition to these commonly used ou
64. a transmission specs of the Service Module for receiving data 1 4 2 Functional Sent data to The rocket module shall send ground information to the ground module through the whole flight of the rocket 1 4 2 1 Design Specs send The rocket module shall meet the data transmission specs of the Service Module for sending data 1 5 1 Design Withstand The mechanical and electrical vibrations components shall withstand the vibration loads during nominal operation of the rocket 1 52 Design Withstand The mechanical and electrical shock components shall withstand the shock loads during launch of the rocket 1 5 3 Design Withstand The mechanical and electrical acceleration components shall withstand the acceleration loads during nominal operation of the rocket 1 5 4 Design Withstand The mechanical and electrical HX13 CERESS SEDv3 1 12DEC14 doc Page 24 EuroLAuNcH A DLR and SSC 1 Req Rocket Module pressure components shall withstand the pressure loads during nominal operation of the rocket 1 5 5 Design Withstand The mechanical and electrical temperature components shall withstand the thermal loads during nominal operation of the rocket 1 5 7 Design Temperature The temperature of the experiment box durability shall be kept between 40 C and 30 C 1 6 Req Topology 1 6 2 Design Fit in Box The Rocket Module shall fit in standard REXUS Module max height 85mm 1 6 3
65. alization een 134 8 2 Requirements for future 02 22422 2 134 8 2 1 Floating GhOUN uio oun en ini na 134 Bae D OP tic accedant E dac 134 8 235 SPRO tte oa ER Dr 134 8 2 4 Maximal Power 134 ABBREVIATIONS AND REFERENCES sees 135 9 1 Abbreviations inno seiten uade Ee EA eg 135 9 2 Heterences AAA 137 Appendix A Experiment Reviews 4 2 138 Appendix B Outreach and Media Coverage nenn 144 Appendix C Additional Technical 145 Appendix D Explanation of Risk Register 152 HX13 CERESS SEDVv3 1 12DEC14 doc 10 List of illustrations Figure 1 CERESS Mission sa hee 3 Figure 2 CERESS System 15 Figure 3 Gantt EE 34 Figure 4 Short Term Action NC 35 Figure 5 bdd Rocket Module 43 Figure 6 bdd Verification 0 45 Figure 7 CERESS Ground Segment Client 48 Figure 8 CEHESS InterfacBs ee 49 Figure 9 Top view of the 2 50 Figure 10 sbRio on 51 Figure 11 Bottom view bulkhead n u 220 Besen ee 52 Figure 12 Gamera elatripss sido o uote o p MD siat erui 53 Figure 13 Camera
66. ally a infinite number of Clients for mission specific needs can be connected to the CERESS Ground Module Server Furthermore the CERESS Ground Module Server can be set up to back up the experiment data via TM on ground in case the REXUS Rocket is not recovered 8 1 7 3D flight Visualization The Visualization Tool can be used to display REXUS flight data and CERESS Rocket Module data The kml files used for the 3D flight data visualization are an open source standard and can be easily modified 8 2 Requirements for future Teams To be able to use the CERESS System successfully the following Requirements need to be obtained 8 2 1 Floating Ground The CERESS Rocket Module has a floating ground different to the REXUS Ground CERESS is completely galvanic isolated Future Experiments need to maintain the galvanic isolation 8 2 2 CGP To not build ground loops the CERESS Provides a common Ground Point located at the sbRIO Future teams shall use the provided ground connection to the CERESS Rocket Module Common Ground Point 8 2 3 sbRIO I Os The CERESS Bus 1 are directly forwarded from the sbRIO Therefore the maximal current loads on the CERESS Bus shall be the same than in the sbRIO specifications 8 2 4 Maximal Power Consumption The maximal provided by the CERESS Rocket module needs to be determined RX13_CERESS_SEDv3 1_12DEC14 doc Page 135 9 ABBREVIATIONS AND REFERENCES 91 Abbre
67. and SSC coopera Test Number 13 Test type Functional Test Test facility LRT student laboratory Test item sbRIO Software Test level The software shall be tested for correct state recovery procedure and after reboot of the sbRIO duration Test campaign Tbd duration Table 36 Test Plan 5 3 Test Results Physical testing starts after the delivery of the hardware HX13 CERESS SEDv3 1 12DEC14 doc 6 LAUNCH CAMPAIGN PREPARATION 6 1 611 Dimensions and mass Page 123 Input for the Campaign Flight Requirement Plans Experiment mass in kg 2 98 4 5 Experiment dimensions in m 20 356 x 0 12 Experiment footprint area in m2 0 3982 Experiment volume in m3 0 04778 Experiment expected COG centre of Gx 2 8mm gravity position Gy 0 9mm Gz 47 9mm from lowest surface of the hull Table 37 Experiment dimensions and mass summary 6 1 2 Safety risks 6 1 3 Electrical interfaces Table 9 Electrical interfaces applicable to REXUS REXUS Electrical Interfaces Service module interface required Yes No usually yes Number of service module interfaces 1 TV channel required If yes when is it required Yes you asked for it Up D ownlink RS 422 required Yes No Data rate downlink 2594 bytes s Data rate uplink 800 bit s Power system Service module power required Yes No usually yes
68. ary Testing in vacuum conditions consider Heat sinks Imply bearing points closely to each other Adapt design of components to requirements and loads Implementation of robust cable routing ID Risk amp Consequence S TC10 Critical component is 3 destroyed in testing TC20 Short circuit in electrical 3 system TC30 Experiment fails thermal 2 vacuum or vibration testing 40 Experiment is damaged in 2 transport TC 50 Test Infrastructure fails 2 MS10 Software programme in 3 microcontroller fails during flight MS20 Overheating of 3 microcontroller electronics 530 Vibration shocks destroy 4 electronic boards 540 Structure failure 4 550 Vibration causes damage to 4 cable harness 560 Acceleration Sensor fails 1 570 Gyro fails 2 HX13 CERESS SEDv3 1 12DEC14 doc Acceptable due to tetrahedron configuration Select suitable gyro to withstand the external environment ID Risk amp Consequence MS80 Pressure sensor fails MS90 Camera fails MS100 removed MS110 Loss of up downlink MS120 System fails to store data on sd card MS130 Electrical connectors unplug due to vibration or acceleration MS140 Components detach from mounting and damage other subsystems PR10 Team member has less time for project than expected PR20 Component is not delivered in time RX13_CERESS_
69. board and communicates with the CERESS Ground Module by which it is can be controlled Furthermore it provides regulated power to the CERESS Verification Module and is capable to invoke actions on the CERESS Verification Module The CERESS Rocket Module is designed for reusability in future experiments and is the key component of the CERESS Space Segment 1 3 2 CERESS Verification Module The CERESS Verification Module contains melting wires as simple actuators which are used to verify the different control chain provided by CERESS A HX13 CERESS SEDv3 1 12DEC14 doc Page 16 variety of sensors is used to characterize the experiment s flight environment The sensors include temperature pressure and a camera The arrangement of the sensors and their purposes are explained in chapter 4 The CERESS Verification Module is replaced by the actual experiment in future REXUS missions from TU Munich 1 3 3 CERESS Ground Module The CERESS Ground Module consists of desktop computers running custom software It interacts with the space segment via Telemetry and Telecommand in order to communicate with the CERESS Rocket Module Furthermore it merges the data from the CERESS Rocket Module and the REXUS telemetry stream Position and measurement data is processed at the CSGM and forwarded via Internet to multiple end user clients running the 3D flight visualization tool ViTo The Internet connection from the CERESS Ground Mo
70. card Preliminary Design Review Payload System Test REXUS ground module Rocket Module REXUS Service Module Software Student Experiment Documentation Swedish National Space Board Start Of Data Storage Start Of Experiment Swedish Space Corporation Student Training Week Systems Modeling Language Time before and after launch noted with or To be confirmed To be determined Technische Universit t M nchen Visualization Tool Verification Module Work Breakdown Structure RX13_CERESS_SEDV3 1_12DEC14 doc 9 2 1 2 3 4 5 6 7 8 9 10 11 12 Page 137 References EuroLaunch BEXUS User Manual 2010 REXUS User Manual 2010 European Cooperation for Space Standardization ECSS Space Project Management Project Planning and Implementation ECSS M ST 10C Rev 1 6 March 2009 SSC Esrange Esrange Safety Manual EU A00 E538 20 March 2006 European Cooperation for Space Standardization ECSS Space Engineering Technical Requirements Specification ECSS E ST 10 06C 6 March 2009 European Cooperation for Space Standardization ECSS Space Project Management Risk Management ECSS M ST 80C 31 July 2008 European Cooperation for Space Standardization ECSS Space Engineering Verification ECSS E ST 10 02C 6 March 2009 Project Management Institute Practice Standard for Work Breakdown Structures second Edition Project Management Ins
71. ction sheet plate is attached see Figure 11 Bottom view bulkhead For details see technical drawings at attachments HX13 CERESS SEDv3 1 12DEC14 doc Page 50 EuroLAUNCH A DLR and SSC cooperation Melting Wires Fine air pressure sensor Figure 9 Top view of the bulkhead HX13 CERESS SEDv3 1 12DEC14 doc Page 51 A DLR and SSC cooperation sbRio mounting screws Figure 10 sbRio on Bulkhead HX13 CERESS SEDv3 1 12DEC14 doc Page 52 EuroLAUNCH A DLR and SSC cooperation Screws for rocket module carrier structure Protection sheet plate transparent Figure 11 Bottom view bulkhead HX13 CERESS SEDv3 1 12DEC14 doc Page 53 EuroLAUNCH ADLR and SSC cooperation 4 2 1 2 At hull The Camera is mounted directly at the hull structure with 4 screws of size M4 see Figure 12 Camera clamp Furthermore in front of the camera lens there is a glass window including fixation structure see Figure 13 Camera window and Figure 14 Camera window cross section Figure 12 Camera clamp Figure 13 Camera window RX13_CERESS_SEDv3 1_12DEC14 doc Page 54 A DLR and SSC coopera Figure 14 Camera window cross section 4 2 1 3 Venting Hole In order to get better measurements of the ambient air pressure two venting holes at the outer structure are required As described in the RX User Manual v7 3
72. d generates a report Digital sensors provide some relevant check values which declare the functionality of the device Analogue device however don t provide such values and as a result another interpretation of the sample data is needed 1000 values are acquired and processed to a Mean Value the standard deviation as well as min and max values A comparison with typical values enables an interpretation of the functionality of the device For each sensor a test report is generated and downlinked 4 8 2 5 TEST HARD SAVED TEST HARD SAVED is part of the tests The sbRIO doesn t configure any sensors and sends an emulated ideal Stream of data to the ground module The stream therefore is stored on the storage unit for checking purposes 4 8 2 6 NORMAL w o pirani with pirani This state is defined to be the normal operating mode of the CERESS Rocket Module Data will be collected processed saved and send The LO Signal resets the Internal Timer The fine pressure sensor PIRANI will be activated after Burn Out of the engine because of a higher shock resistance of the sensor in off mode 4 8 2 7 SHUTDOWN SHUTDOWN closes files and prepares the CERESS Rocket Module for Power shutdown and landing impact RX13_CERESS_SEDv3 1_12DEC14 doc Page 101 EuroLAuNcH A DLR and SSC coopera 4 8 3 Functional Blocks Functional Blocks formerly named Threads are all program parts which are not covered in the OBDH state description
73. d to be reused 3 The used components and electric circuits can be adopted in the new mission If you can wrap the services up in this few words we have done our job right It s plug n play for REXUS experiments 8 1 1 Regulated Power Supply The CERESS Rocket Module supplies switchable 3 3V 5V and 24V regulated and fused power lines as well as the not switchable but fused 28V unregulated REXUS Power 8 1 2 Command amp Control The CERESS Rocket module offers more than 100 DIO channels and 20 Analogue I Os which can be used for 10 differential measurements Command and Control actions can be e time triggered by the on board sequencer e event triggered by an on board event e Telecommand triggered by the CERESS Ground Module 8 1 3 On Board Data Storage The CERESS Rocket Module is able to store experiment data on two redundant SD Cards 8 1 4 TM TC The CERESS System offers a complete TM TC interface derived from the ECSS Telemetry and Telecomand packet utilization RX13_CERESS_SEDv3 1_12DEC14 doc Page 134 8 1 5 LabView integration LabView SubVI is provided by the CERESS Ground Module which ports provide the values at the sbRIO I O Pins in near realtime during flight and during replay of the data in post flight 8 1 6 CERESS Ground Module Server The CERESS Ground Module Server handles the TC TM streams provides TM data and receives TC data from multiple clients Theoretic
74. de Button pin is tied to ground for a few seconds This is equivalent to physically pressing the power button This is RX13_CERESS_SEDv3 1_12DEC14 doc Page 95 EuroLAUNCH ADLR and SSC achieved by connecting Pwr Mode and ground via optocouplers which is then triggered by a sbRIO digital output To check if the camera is recording Data Interface is connected to a digital I O of the sbRIO This pin is low if the camera is not recording and high as soon as the recording starts 4 6 Thermal Design As mentioned in chapters before the fine pressure sensor pirani type needs a heating The Sensor and Heating are thermal isolated against the rest of the CERESS Verification Module Detailed calculations simulations need to be done Figure 48 Components Temperature Ranges shows the temperature ranges of the components 60 5 20 20 40 60 80 100 120 140 Figure 48 Components Temperature Ranges RX13_CERESS_SEDv3 1_12DEC14 doc Page 96 A DLR and SSC 4 7 Power System The power system is made up of two DC DC convertors one providing 3 3V and 5V and the other providing 24V four fuses to protect the experiment from to high currents one solid state relay to turn the 24V DC DC on once the SOE signal comes in and three shunts and high side current sense chips to measure the output current
75. dido lod oe deo oinnes 79 Table 24 GoPro Connector Pinout Eo ren ert as 94 Table 25 Power Budget of electrical components 96 Table 26 Power Budget Heating Mode 97 Table 27 Power Budget Wire Melting 97 Table 28 Data Packet Header tec DR d rt us 104 Table 29 Data KEEN 104 Table 30 Telemetry m Ue 105 Table 31 Data Storage BUdOel ii pe pa wed iiu 106 Table 32 Verification Malbec 116 Table 33 Varification Matrix re 117 Table 34 Venfication Matrix suo toL oe aa cb p US 118 HX13 CERESS SEDVv3 1 12DEC14 doc 13 Table 35 Verification Mall sarah 118 TTable 36 KE e VE 122 Table 37 Experiment dimensions and mass 123 Table 38 Electrical Interfaces uu een 123 Table 39 Launch Campaign Tmelme 127 1 CERESS SEDVv3 1 12DEC14 doc Page 14 1 INTRODUCTION 1 1 Scientific Technical Background Teams participating in the REXUS program are facing similar challenges in order to perform their experiment Power supply on board data handling and telemetry are examples for tasks to be taken care of to perform the actual experiment Talking to former REXUS team members at LRT name
76. doc 241 Figure 35 RS 422 Convertor 85 Figure 36 Signal Interpreter 86 Figure 37 Interface Board PCB Component 87 Figure 38 TENDO 2415 Cell s ci oit betta D RE TL ER ORE 88 Figure 39 High side current sense 88 Figure 40 24V level 89 Figure 41 24V Board Bottom Top View ENEE 89 Figure 42 24V Board Top 2 nnn 90 Figure 43 TEN40 2420 ee D 91 Figure 44 High side current sense 91 Figure 45 3 3 5V Board Bottom Top 92 Figure 46 3 3 5V Board Top Top cesis edic eter sinite oin etnia erano 93 Figure 47 Thermistor 93 Figure 48 Components Temperature 95 Figure 49 On Board data flow cc nennen cte in Ga ede 98 Figure 50 State Machine 99 Figure 51 Telemetry Data Frame building scheme ss 102 Figure 52 Telemetry Data 104 Figure 53 GERESS Ground Segment ret Delete 107 Figure 54 Trajectory determination 0 108 Figure 55 Connections at ground segment 125 RX13_CERESS_
77. dule to the Internet is governed by the ESRANGE Internet access 1 3 4 Visualization Tool ViTo The ViTo displays the position and orientation of the CERESS Rocket Module and therefore the altitude and attitude of the REXUS rocket in near real time during flight and as replay in post flight Furthermore data from the CERESS Rocket Module and CERESS Verification Module sensors can be displayed During the flight the ViTo receives data from the CERESS Ground Module via Internet In post flight the needed data is obtained by processed data of the on board data storage 1 3 5 Service Computer The Service Computer is needed for programming and maintaining the CERESS Rocket Modules Main Computation Unit MCU during development testing after integration and launch preparation 1 4 Team Details 1 4 1 Contact Point Address CERESS Rexus Claas Olthoff Technische Universitat M nchen Lehrstuhl Raumfahrttechnik BoltzmannstraBe 15 85748 Garching Germany Email team ceress googlemail com Phone 49 176 23585826 Team Leader RX13_CERESS_SEDv3 1_12DEC14 doc 1 4 2 Team Members The team consists of students from the TU M nchen studying aerospace engineering The project is not part of any university course e T Page 17 A DLR and SSC Daniel Bugger 12th Semester Aerospace Engineering Dipl Ing at TU Munich Functions e Project Leader e Project Coordination e M
78. e Handshake Handshake gt 3x Meltingwire Mode Clonee Heating on off a Seins Burn signals gt 2208 Information Digital Out Node Scheuer Information ode Information Transfer to Power on off for sensors Sensor Power Transfer to And downlink target File Control Du receive File information init and re gt buffered 7 up Front End 95 09 Storage NI 9802 Handshake Handshake to all Functional Store dod 5 Blocks Real Time Processor RT Host l FPGA Target Page 99 EuROLAUNCH A DLR and SSC cooperation 4 8 2 OBDH states The OBDH has to be capable to perform appropriate tasks in different phases of the launch campaign and the flight itself Therefore a state machine as shown in Figure 50 is used The state changes are performed either by command procedure or the mode has reached its predefined end checked by the Sequencer The Procedure is a predefined state change in order to enable an automatic full test or the mission itself State machine MAIN EN SOE e POST finished v pv A STARTUP N Entry configure files and N Communication P u m STARTUP finished pn d E GE DES E BIT Eommand Procedure e dee TESTHARDSAVED N Entry 5 IDLE N Entry send SD CARD saved N Exit send report Do i
79. echanical Design e Data Processing e Outreach Experience e Internship at Amir Kabir University Tehran Iran e Microsat Engineering at TU Delft Netherlands Working with a Thermal vacuum test chamber at LRT HX13 CERESS SEDv3 1 12DEC14 doc Page 18 EuroLAUNCH Sebastian Althapp 5rd Semester Aerospace Engineering B Sc at TU Munich Functions e Ground Segment e Visualization e Outreach Experience e Former tutor for microcontroller programming at the Begabtenforderung Physik GE Hennef scholarship for gifted in physics e Member of the WARR Scientific Workgroup for Rocketry and Spaceflight 2 place at the national competition Jugend Forscht Youth Researches with the paper Entwicklung und Erforschung eines Hybridraketentriebwerks Development and study of a Hybrid Rocket Engine e Fraunhofer Talent School for Micro Mecha tronics e Internship at DLR Cologne RX13_CERESS_SEDv3 1_12DEC14 doc Page 19 EuroLAUNCH Christoph Friedl 11th Semester Aerospace Engineering Ing at TU Munich Functions e Electrical Design e Data Processing e Outreach Experience e CubeSat Workshop at LRT e Internship at EADS Division Cassidian Air Systems RX13_CERESS_SEDv3 1_12DEC14 doc Page 20 EuroLAUNCH Alexander Schmitt 11th Semester Aerospace Engineering Dipl Ing at TU Munich Functions e On Board Data Handling e Outreach e Minu
80. ecification Usage or high impedance and CERESS Verification Module 5 LO Lift off Synchronization of open collector to GND CERESS Rocket Module or high impedance and ViTo data timestamp 6 EXP out Non inverted experiment Transmit data from data from CERESS Rocket CERESS Rocket Module Module to RXSM RS 422 to RXSM 7 Inverted experiment data Transmit data from to from CERESS Rocket CERESS Rocket Module Module to RXSM RS 422 to RXSM 8 28V GND Power GND Ground connection of CERESS Rocket Module and CERESS Verification Module 9 28V Battery Power Power the CERESS 24 36 V unregulated Rocket Module and peak lt CERESS Verification Module via a DC DC converter 10 128 V Charging Experiment battery Not used Power charging power 11 spare 12 UTE not available Not used 13 EXP in Non inverted data from Receive CERESS RXSM to CERESS Rocket Rocket Module control Module RS 422 data 14 EXP in Inverted data from RXSM Receive CERESS to CERESS Rocket Rocket Module control Module RS 422 data 15 28V GND Power GND Ground connection of CERESS Rocket Module and CERESS Verification Module Table 13 RXSM Electrical Interface 4 2 2 6 CERESS Bus The connection for power and command amp control between the CERESS Rocket Module and the CERESS Verification Module is divided into several connections e CGP the common ground point CERESS is floating ground e 3 3V Digital I O 1 RX13_CERESS_SEDv3 1_12DEC
81. ed or corrupted 4 10 2 3 Data processing 1 Zero rate level interpretation 2 Attitude correction through CERESS calibration values Calculation of rate by linear correlation to native 16bit value Filter 3 4 5 Possible Integration to Altitude 4 10 3 Thermistors 4 10 3 1 Calibration The Calibration of Thermistors is a correlation to defined temperatures The Thermistors will be applied to ice water temperature 0 C and afterwards to heating water temperature depending on day s static ambient air pressure 4 10 4 Fine pressure sensor 4 10 4 1 Factory calibration The device is factory calibrated and isn t supposed to be recalibrated until pollution or long time usage distorts the measurements 09222 0201_TTR91 pdf p 2 4 10 4 2 Data processing 1 Calculation of pressure by linear correlation to Voltage 16bit ADC value 2 Calculation of height by correlation to pressure 0 4 10 5 Coarse pressure sensor 4 10 5 1 Factory calibration The device has calibration data stored in the interface IC which make typical characteristics achievable The average of 2 to 4 subsequent pressure values is required due to noise of the ADC MS5534C pdf p 5 p 9 p 15 4 10 5 2 Data processing 1 Pressure and temperature measurement RX13_CERESS_SEDv3 1_12DEC14 doc Page 112 EuroLAuUNcH A DLR and SSC coopera 2 Temperature compensating 3 Possible second order temperature compensation 4 Calcu
82. egment 45 Sensor Driver Board etes tt etes haare 45 SUIS OS pouce t 46 Camera MNT 46 Camera Driver ita d it odit tertie e 46 Malla WE 46 Melting Wire coh ee to iud 46 Safety PIN et ata he iia ta IR 46 413 CERESS Ground Module Ground Segment 47 CERESS Ground Module Server 47 Visualization bb 47 CERESS Internet 47 CERESS Flight Simulation Clients nennen 48 CERESS Ground Module 48 VisHsalisSdtioH EE 49 External Experiment Interfaces 49 4 2 1 Mechanical Interfaces REXUS 49 CI BOITE cie 49 IP O 53 Venting FONG RE fre seed dea ede 54 mlt HOO ER HP EE 55 4 2 2 Electrical Interfaces nen 56 REXUS o 57 BERESS BUS ccd btn tod Laval Aer be 59 CERESS Rocket Module internal interfaces 61 CERESS Verification Module internal interfaces 61 BUS ro
83. eir devices and provide data packets to the Store and publish data thread If necessary they generate higher priority packets Their Modes can be set from the Main thread 4 8 3 7 Sending This block creates a full Telemetry Data Package including Header Data Frame and Trailer RX13_CERESS_SEDv3 1_12DEC14 doc Page 102 EuROLAUNCH A DLR and SSC cooperation First the data frame is filled with packets owning the highest priorities until the frame can t take the next packet If the first packet exceeds the Data Frame a sequence of Data Frames will be generated Afterwards the remaining data frame is filled with packets owning lower priorities but have smaller packet sizes Filling aborts when the remaining free space is smaller than the lowest packet size The Trailer at the end of the package and the Header at the beginning are generated and attached like described in Section 4 8 5 3 Telemetry Data Frame definition Then the package is released for transmitting Untaken packets remain in the buffer and were processed in the next loop Some Priorities cause an update of their remaining data packet see Section 4 8 5 1 Priority This procedure enables a very high load factor for Telemetry and guarantees a quick transmitting of high priority packets like error reports or comparative events Furthermore additional packets are easy to integrate into the telemetry stream Start Take current data packages and flag the
84. ermistors of the CERESS Rocket Module are located at the DC DC converters and one is located at the sbRIO 4 3 2 4 Meltingwires The melting wires demonstrate the possibility to perform action on the verification module resp the future TUM experiment The three wires will be blown using one of the following triggers e Time pre defined e Event special values of a sensor achieved e Command from CERESS Ground Module uplinked 4 3 2 5 Meltingwire Driver The Melting Board is supposed to forward the required Amps to the melting wires if the input from the sbRIO occurs 4 3 3 Part Availability Exact Name Manufacturer Current status of Supplier supplier Temperature KT103J2 US Sensors high TTR 91 Oerlikon Leybold Pressure Vacuum low MS5534C AMSYS Pressure Acceleration LIS331HH sparkfun com launch Acceleration LIS331HH sparkfun com freefly RX13_CERESS_SEDv3 1_12DEC14 doc Page 72 Type Exact Name Manufacturer Supplier Gyro launch L8G4200D sparkfun com Gyro freefly L8G4200D sparkfun com Processing National Instruments National Unit sbRIO_9642 Instruments Power Supply TRACO POWER Farnell com TEN 40 2420 TRACO POWER TEN Farnell com 60 2415 TRACO POWER Farnell com TEP 75 481 5WI Solid State Crycom CN024D05 Farnell com Relais High side MAX4172ESA Farnell com current sensors RS 422 Chip MAX488EESA Farnell com Small
85. erospace engineering students from the Technical University of Munich TUM The organization is divided into five different groups Project Coordination Mechanical Design Electrical Design Software Development and Ground Support The responsible person of each part is shown in Table 6 Working field mapping Because of the small team size the hierarchy is flat with strong interactions between all fields of activities Task Responsible person Project coordination Daniel Bugger Software Design Alexander Schmitt Electrical Design Christoph Friedl Mechanical Design Daniel Bugger Ground Segment Sebastian Althapp Table 6 Working field mapping 3 1 Project plan Long term The long term planning is done with the MS Project software In Table 7 Project Plan the main phases and development steps are shown For better time understanding the same data is shown in Figure 3 Gantt Chart in a Gantt chart Task Name Duration Start Finish Resource Names Predecessors WBS Call for Proposal 0 days TUR 1 Write Proposal 38 days dT Ns 1 2 Deadline Proposal 0 days x See 3 dc cd Aldays Tom er a 44 pies m E AN SE Training Week 5 days 7 8 PDR Grae ZER Mon 7 9 27 02 12 27 02 12 HX13 CERESS SEDv3 1 12DEC14 doc Phase C Design Phase Mechanical Develop Mechanical Structures Create technical drawings Electrical Design electrical layout
86. es all I O tasks and emulation of data transfer protocols High frequency data condition is possible All processing on this device is deterministic Unfortunately for every change a re compilation which needs time is needed 4 8 1 2 Real Time Processor The device is splitable into the several normal priority loop time critical loop First contains the main program with different states which are explained in the following section For secure data exchange between loops and FPGA a buffer principle with handshake principal is used Normal priority does not imply that there wouldn t be in time checks The data is logged to the Storage through the FPGA An Event logger with storing cabability on the internal storage will guarantee that the last state can be recovered after an power loss HX13 CERESS SEDv3 1 12DEC14 doc Signals Int 4 SODS SOE etc E Uplink uplink Sending r 1 0 Node Receiving Downlink gt 5422 RXSM Event uplink Logger for decoding Downlink possible data Sample 1 0 Node Recovery Se preparation Conditioning data Sensors Status Main 4 Ge Information Digital Out Node Transfer io formation State Collector Value Collector Heating Foil Host receive uk From all Functional From all Sensor Information buffered Bus de Blocks FIFO eso Digital In Out Interpre Interface dois buffered buffered tation and Ee Front End Nod
87. es instrumentation will be placed externally Therefore a power and data interface is needed Power is provided by the mainboard via two 9 pin power connectors that in in a D Sub 9 connector allowing easy cable replacement Since the sensors are already soldered to breakout boards with connected power and digital grounds the ground connection will be soldered directly to breakout boards and connects together with the data lines to the sbRIO s DIO connectors 4 2 2 4 CERESS Verification Module internal interfaces The verification module will use a main power and data distribution board The specific interfaces will have to be defined as soon as all components interfaces especially the GoPro s are defined 4 2 2 5 REXUS Bus The CERESS Rocket Module uses the Power and Control Interface of the RXSM The control interface uses the RS 422 EXP in out Both interfaces are implemented as D SUB Connector Pin Name Specification Usage 1 28V RXSM Power Power the CERESS 24 36 V unregulated Rocket Module and peak lt CERESS Verification Module via DC DC converters on the power board 2 spare 3 SODS Start Stop of data storage Trigger CERESS Rocket open collector to GND Module data storing or high impedance 4 SOE Start Stop of experiment Startup Shut down the open collector to GND CERESS Rocket Module RX13_CERESS_SEDv3 1_12DEC14 doc Page 62 EuroLauncH Pin Name Sp
88. etween Req 1 1 3 1 and 1 1 3 2 Req 1 3 The term pulsing should be clarified to mean frequency Req 1 7 4 The term logging actions within real time is imprecise Req 1 8 3 Remove the term exact about Req 3 1 1 is not phrased clearly Since SysML is used for requirement definition tracing of requirements could be considered Mechanics SED chapter 4 2 1 amp 4 4 The mechanical design is generally very clear RX13_CERESS_SEDv3 1_12DEC14 doc Page 142 EuROLAUNCH A DLR and 556 cooperation Add overall dimensions and basic dimensions in the text o Include manufacturing drawings in the appendices as the construction appears to be sufficiently advanced Perform structural analysis to verify structural integrity consider static and dynamic load cases give boundary conditions Note that the 0 line launcher rail is along the hatch Venting hole sheets may be provided by SSC Rework the camera mounting to make it stiffer and stronger Include further detail on the camera window as the mounting was not clear Also clarify the mounting of the sbRIO 11 screws in the document Please cover the accelerometers both on top and at the bottom of the module to prevent accidental damage o Add the experiment footprint to the document including the angles of module modifications hatches venting holes o Add arm plug design Electronics and data management SED chapter
89. flight RX13_CERESS_SEDv3 1_12DEC14 doc Page 15 Secondary objectives of CERESS e Intuitive data visualization for situational awareness universal outreach purposes e Characterization of the experiments flight environment e Distribution of collected data to interested parties e Flight verification of often used key components which are not part of the in flight functional verification 1 3 Experiment Overview The CERESS System consists of the following major subsystems The space segment is defined as the CERESS Rocket Module which performs the typical infrastructure tasks and the CERESS Verification Module which is used to verify the functionality of CERESS The CERESS Verification Module is replaced by the scientific experiment in later missions The ground segment consists of the CERESS Ground Module the Visualization Tool ViTo and the Service Computer block CERESS bdd Modell Data Project Overview1 y block Ground Segegment block Space Segment block block block block Verification Module Rocket Module Ground Module Service Computer Figure 2 CERESS System Overview block Visualisation Tool 1 3 1 CERESS Rocket Module The CERESS Rocket Module retrieves data from included sensors and those of the attached CERESS Verification Module The CERESS Rocket Module stores and processes the data on
90. he mechanical properties is given in the table below Experiment mass in kg 2 98 4 5 Experiment dimensions in m 00 356 x 0 12 Experiment footprint area in m2 0 3982 Experiment volume in m3 0 04778 Experiment expected COG center of Gx 2 8mm gravity position Gy 0 9mm Gz 47 9mm from lowest surface of the hull Table 15 Experiment Summary 4 3 1 CERESS Rocket Module 4 3 1 1 Main Computation Unit sbRIO 9642 The heart of the Command and Control OBDH system is the National Instruments sbRIO 9642 It is responsible for all experiment control on board data handling and data exchange with the REXUS service module RX13_CERESS_SEDv3 1_12DEC14 doc Page 65 This single board Reconfigurable Input Output sbRIO provides FPGA with 2 Million Gates a real time processor 4 analogue outputs 32 analogue inputs 110 digital I O at 3 3 V 32 Digital Inputs at 24 V and 32 Digital outputs at 24V The sbRIO will be configured using LabView The usage of blocks within the language will provide the possibility to develop a configurable system for future teams The used pin connectors of the sbRIO are shown in the tables below P2 Digital Connector 1 D GND Relay1 GND 2 Port0 DIOCTL Relay1 3 PortO DIOO Accelerometer1 4 Port0 DIO9 Accelerometer1 SPI SPC SPI DIN 5 Port0 DIO1 Accelerometer
91. he shunt and output resistors vary The circuit below is implemented four times twice for 3 3V and twice for 5V Figure 44 High side current sense circuit Since the voltage levels are within sbRIO s analogue input range no voltage divider is required 4 5 5 4 Powerboard 2 PCB Layout The circuits above result in a printed circuit board with the following parameter e Dimensions 120x105mm e Double layer 70um copper RX13_CERESS_SEDv3 1_12DEC14 doc Page 92 A DLR and SSC cooperation sa se ek asss ms O Figure 45 3 3 5V Board Bottom Top View RX13_CERESS_SEDv3 1_12DEC14 doc Page 93 EuroLauncu ADLR and SSC 9092009200 I Figure 46 3 3 5V Board Top Top View 4 5 6 Thermistors To measure temperature temperature dependent resistors thermistors are used The following circuit is used for each thermistor Figure 47 Thermistor circuit This circuit is basically a voltage divider Supply voltage goes through a 10kQ resistor and then via the thermistor to ground The voltage is measured RX13_CERESS_SEDv3 1_12DEC14 doc Page 94 A DLR and SSC between resistor and thermistor Knowing the input voltage value of R1 and the measured voltage the value of the thermistors resistance can be calculated and the temperature of the sensor In this case the supply voltage is channelled
92. he upper contact surface see Figure 25 boarder conditions of the hull HX13 CERESS SEDv3 1 12DEC14 doc Page 76 EuroLAUNCH ADLR and SSC cooperation Figure 25 boarder conditions of the hull Figure 26 Von Mises yield criterionshows the Von Mises yield criterion The maximum occurs at the top corners of the cut out see Figure 28 Detail of the cut out corner The maximum is 3 47 E 008 N m2 Figure 26 Von Mises yield criterion RX13_CERESS_SEDv3 1_12DEC14 doc Page 77 EuROLAUNCH ADLR and SSC cooperation von Mises Spannungen Knotenwerte 1 N m2 2 47e 003 Auf der Begrenzung Figure 27 Scale von mises Figure 28 Detail of the cut out corner Figure 29 Displacement As you can see the maximum is at the centre of the cut out The maximum displacement is 0 2 mm RX13_CERESS_SEDv3 1_12DEC14 doc Page 78 EuUROLAUNCH ADLR and SSC cooperation Figure 29 Displacement Translationsverschiebungsvektor 1 mm 0 162 0 141 0 121 Auf der Begrenzung Figure 30 Scale displacement 4 4 2 2 Cross beam natural vibration analysis A natural vibration analysis was done The boarder condition was rigid clamping where the position of the screws see Figure 31 boarder conditions for cross beam RX13_CERESS_SEDV3 1_12DEC14 doc Page 79 A DLR and SSC Figure 31 boarder conditions for cross beam The result of the analysis is
93. ic Experiment data is exchanged using the RS 422 protocol Therefore a RS 422 converter chip is used as shown below D GND MAX488EESA Ceramic13 EXP 1 5 Out c rono Doo B 500101 Exp in gt 5 91 Figure 20 RS 422 implementation 4 2 2 2 CERESS Bus The connection for power and command amp control between the CSRM and the CSVM is divided into several connections e SGP the single ground point CERESS is floating ground e 3 3V Digital I O 1 RX13_CERESS_SEDv3 1_12DEC14 doc Page 60 A DLR and SSC e 3 3V Digital I O 2 e 3 3V Digital VO e 3 3V Digital VO 4 e 24V Digital In e 24V Digital Out Analogue I O e PWR providing 3 3V 5V 24V The power connector must be able to accommodate the three input voltages For each voltage there should be three pins for voltage and three pins for ground This adds up to a total of 18 pins the connectors used will therefore be a 25 pin power connector on rocket module side and a D Sub 25 connector on verification module side Pin Signal Pin Signal 1 3 3V PWR 2 3 3V Ret 3 3 3V PWR 4 3 3V Ret 5 3 3V PWR 6 3 3V Ret 7 Spare 8 Spare 9 5V PWR 10 5V Ret 11 5V PWR 12 5V Ret 13 5V PWR 14 5V Ret 15 Spare 16 Spare 17 24V PWR 18 24V Ret 19 24V PWR 20 24V Ret 21 24V PWR 22 24V Ret 23 Spare 24 spare 25 Spare Table 12 Power Connector Layout
94. ion is achieved by wiring the devices GND pins to the sbRIO s ground pins that are located in the 50pin connectors of the board Internally the Al GND and D GND as well as the ground lug are connected cf sbRIO User Manual Therefore the sbRIO will contain the single ground point SGP for the rocket module components The 3 3V Ret 5V Ret and 24V Ret are forwarded to the verification module together with the corresponding voltage By twisting these cables together EMI should be reduced 4 5 4 Interface Board As the name implies this board acts as an interface between the Rexus service module and the Ceress rocket module for data signals and power Its main function can be broken down the three sub functions e Conversion from and to RS 422 communication standard e Interpretation and galvanic isolation of the three Rexus signals e Distribution of 28V power lines and protection from continuous overvoltage Derived from these sub functions are three independent circuits that are detailed in the following chapters HX13 CERESS SEDv3 1 12DEC14 doc Page 85 A DLR and SSC coopera 4 5 4 1 RS 422 Convertor The function of this circuit is to convert telemetry data of the main computation unit and telecommands coming in via the Rexus service module using the RS 422 standard Outgoing data is converted from a single bit stream to a non inverted Exp out and an inverted signal Exp out Incoming data is
95. isualization tool illustrates the rocket s trajectory in a 3D simulation in near real time and as post flight replay This complements the CERESS project with a widely requested feature that allows the general public to access the fascination of REXUS experiments Keywords REXUS SED Student Experiment Documentation CERESS Compatible and Extendable REXUS Experiment Support Bus Technische Universit t M nchen Figure 1 CERESS Mission Patch HX13 CERESS 1 12DEC14 doc CONTENTS EE 3 1 INTRODUCTION BEE 14 1 1 Scientfic Technical Background nase 14 1 2 Experiment ge tron ec ta e xe pego qe xe DH etx ER pce 14 1 3 Experiment Overview dened fant den aan 15 1 3 1 GERESS Rocket Module an ae 15 1 3 2 gt CERESS Verification Module 15 1 3 3 CERES S Ground nenne 16 1 3 4 Visualization Tool VET EE 16 1 35 Serice Comp te 22 2 ret a 16 14 Team Detail S ans ae 16 TAE T Contact POIDS nennen 16 14 2 Team Members asien kei 17 2 EXPERIMENT REOUIDREMENTG sss 21 2 1 Requirements CERESS Rocket Module 21 2 2 Requirements CERESS Verification 25 2 3 Requirements CERESS Ground 26 2 4 Requirements Visualization 28 2 5
96. item Sensors Test level The sensors shall be tested on correct functionality procedure and duration Test campaign duration Test Number 4 Test type Vibration Test Test facility DLR Bremen Test item Mechanical components Test level The mechanical components of the experiment shall be procedure and tested under vibrations that occur during nominal duration launcher operations Test campaign duration RX13_CERESS_SEDv3 1_12DEC14 doc Page 120 ADLR and SSC coopera Test Number 5 Test type Vibration Test Test facility DLR Bremen Test item Entire system Test level The entire experiment shall be tested under vibrations procedure and that occur during nominal launcher operations duration Test campaign duration Test Number 6 Test type Electromechanical interferences Test facility LRT Laboratory Test item Electrical components Test level The influence of electrical components on each other procedure and shall be tested duration Test campaign duration Test Number 7 Test type Functional Test Test facility LRT Laboratory Test item Whole RM Test level RM shall recover to the last state in every phase of procedure and countdown and flight when a power drop occurs duration Test campaign 2 days duration Test Number 8 Test type Functional Test Test facility LRT Labo
97. l up resistor 4 5 4 3 PTC Fuse The third circuit is solely to turn one 28V line into two lines in order to supply both power boards In addition a self resetting PTC fuse is integrated to prevent the experiment from continuously drawing too much power from the Rexus service module 4 5 4 4 Interface Board PCB Layout The circuits above result in a printed circuit board with the following parameter e Dimensions 140x36mm e Single layer 35um copper The relatively large dimensions are result of the boards physical location within the rocket module RX13_CERESS_SEDv3 1_12DEC14 doc Page 87 A DLR and SSC coopera ss 2 PSS A Sv Figure 37 Interface Board PCB Component side 4 5 5 Power Boards The REXUS service module provides a 28V power source This source however is unregulated meaning the voltage is not a constant 28V Furthermore most experiment components cannot be operated with 28V supply voltage It is therefore necessary to convert the incoming voltage to correct and regulated voltages In case of the Ceress experiment these voltages are 3 3V 5V and 24V To achieve this two DC DC converters are used Tracopower TEN40 2420 provides both 3 3V and 5V while the Tracopower
98. lation of height by correlation to pressure tbd HX13 CERESS SEDv3 1 12DEC14 doc Page 113 A DLR and SSC 5 EXPERIMENT VERIFICATION AND TESTING 51 Verification Matrix ID Requirement text Verification Status 1 Req Rocket Module 1 Reg Electrical 1 1 1 The system shall provide regulated R To be electrical power done 1 1 1 1 The Power Supply shall provide the R T To be power to melt the wires done 1 1 1 5 The electrical power system shall accept R T To be unregulated power from the REXUS SM done 1 1 1 6 The electrical power system shall be R T To be able to provide 30W of power done 1 1 3 The Rocket Module shall use the power R T To be provided by the RXSM done 1 1 3 1 The electrical power supply shall accept R T To be input currents of 28V DC done 1 1 3 2 The power supply shall accept Peak R T To be currents of 3 Amps done 1 1 4 1 The experiment must make provisions to R To be limit voltage ripple feed back to the done RXSM over the power line to a maximum of 500 mV p 37 The system shall measure acceleration R T 1 2 Req Sensors 2 To be in all 3 axes done 1 2 1 1 The acceleration sensor shall cover the R To be range from 10mg pg flight state to 25g done launch state 1 2 1 2 The acceleration sensor shall have an R To be accuracy of 10mg ug flight state done 1 2 1 3 The accelerati
99. lients These CERESS Ground Module Clients are running on local CERESS desktop computers located at ESRANGE They include e Control Console for the CERESS Rocket Module e Control Console for Payload CERESS Verification Module e Display of the CERESS Mission Events amp time e Display of the CERESS Rocket Module Status e Display of the CERESS Verification Module Status e Display of the CERESS Ground Segment Status e Display of Scientific Data Each CERESS Ground Module Client caches the data provided by the CERESS Ground Module Server in order to display it or in order to send a TC request to the CERESS Rocket Module Server Multiple Clients can be running on a single desktop computer An impression of a joined display and control panel is given in Figure 7 CERESS Ground Segment Client CERESS MAINTENANCE Temperature intern CONTROL CERESS Package INFO OVERVIEW Temp 1 intern 5 ES e nnum WEM Gyros 3 Temp 1 intern 2 en II Temp 2 intern n STATUS EAM Gyros 4 Temp 2intern 2 ar System HOLD Temp 3 intern dec IM Accelerometer high2 Temp 3 intern 2 RESTART CERESS m DCDC Converter 330 sme ackages receive Estimated Temperature 9 Heg DCDC Converter 5 0V aci 00 Critical Temperature 0 00 00 00 m dee Converter 24V Mission Time ACQUIRE VALUES REXUS
100. ll accept Peak Peak Input currents of 3 Amps 1 1 3 3 Performance 14 DC The power supply shall accept 1A current Input continuous current 1 1 4 Deleted Deleted 1 1 4 1 Performance max feed The experiment must make provisions back to limit voltage ripple fed back to the RXSM over the power line to a maximum of 500 mV p 37 1 2 Req Sensors 1 2 1 Functional The system shall measure acceleration Acceleration in all 3 axes 1 2 1 1 Performance The acceleration sensor shall cover the Acc Range range from 10mg ug flight state to 25g 1 2 1 2 Performance Acc The acceleration sensor shall have an Accuracy accuracy of 10mg ug flight state 1 2 1 3 Performance Acc The acceleration sensor shall take 1000 measurement frequency measurements every second 1 2 2 Design withstand All Sensors shall withstand the rocket environment environment condition within a REXUS launch campaign 1 2 2 1 Design withstand The sensors shall withstand the thermal RX13_CERESS_SEDv3 1_12DEC14 doc Thermal loads load cases Page 22 EuroLAuNcH A DLR and SSC 1 Req Rocket Module 1 2 2 2 Design withstand The sensors shall withstand the acceleration loads acceleration load cases 1 2 2 3 Design withstand The sensor shall withstand the pressure pressure loads load cases 1 2 3 Functional Angular The system shall measure angular rate Rate in all 3 axi
101. ll be capable to Operations perform operations on the verification experiment 1 3 11 Operational Execute The rocket module shall be capable to commands execute received commands 1 3 2 Functional Data from The rocket module shall retrieve data HX13 CERESS SEDv3 1 12DEC14 doc CSVM Sensors from verification module sensors Page 23 A DLR and SSC 1 Req Rocket Module 1 3 3 Functional Store The rocket module shall store retrieved sensor data data from sensors 1 3 3 1 Performance Data The rocket module shall store the save rate retrieved data from the sensors with 1000Hz 1 3 4 Functional Interpret The rocket module shall be capable to received data interpret the received data 1 3 8 Design Self test The rocket module shall be capable to be self tested 1 3 8 1 Design Malfunction The rocket module shall be capable to detection detect malfunctions 1 3 8 2 Design Counteractive The rocket module shall be capable to measures perform counteractive measures if an malfunction is detected 1 3 9 Operational Radio The CSRM shall accept a request for Silence radio silence at any time while on the launch pad 1 4 COMS 1 4 1 Functional Receive The rocket module shall be capable to ground data receive information from the ground module through the whole flight of the rocket 1 4 1 1 Performance Specs The rocket module shall meet the receive dat
102. ly T REX RX03 VERTICAL RX04 VECTOR RX08 and FOCUS RX10 identified a profound interest in a platform providing the tasks mentioned This allows teams to focus more on the scientific experiment itself The lack of data concerning the experiment flight environment and the documentation of disturbing influences on milli gravity was mentioned as well by previous Teams Providing these values allows a more detailed design of the experiment and a more profound analysis of the experiments data The CERESS project aims to provide both A support infrastructure including a power supply hard and software for OBDH and Command and Control as well as flight environment characterisation tasks using a variety of sensors e g accelerometers gyroscopes vibration temperature and pressure sensors Another goal is to enhance the teams situational awareness during the mission by providing a near real time visualisation of the rocket s flight The acronym CERESS is meant to catch the universal design approach of the CERESS Project as Compatible and Extendable REXUS Experiment Support Bus 1 2 Experiment Objectives The primary objectives have to be archived in order to consider the experiment Any additional objectives are secondary objectives Primary objectives of CERESS e Develop an REXUS Experiment Support Bus for future TUM REXUS teams consisting of a space and a ground module e Functional verification of the system at its first
103. m as untaken Sort current data packets by priority Sort current data packets by size within priorities Attach highest untaken priority packet into data frame and flag it as taken has BE enough capacity for next highest untaken lt SN packet 7 be no yes 4 8 3 8 Receiving _ Data Frame has _ enough capacity for current untaken minimal packet size 7 yes Nextuntaken 2 packet fits in remaining gt Look at next untaken packet no frame space Attach highest untaken priority packet into Data Frame and flag it as taken current Trailer Y Generate and attach current Header Generate and attach Y Release Delete taken packets and keep untaken ones Po Figure 51 Telemetry Data Frame building scheme Data is received and decoded for use in the main program RX13_CERESS_SEDv3 1_12DEC14 doc Page 103 A DLR and SSC coopera 4 8 4 Additional implemented Blocks There are some Blocks which are used and implemented but not described yet 4 8 4 1 SPI Block The SPI Communication to the digital Sensors is implemented in single cycle loop with a clock rate of 10MHz resulting to a clock tick of 0 1us The block accepts an array of clusters containing all necessary information for a successful communication and deli
104. meter8 34 D GND No Connection SPI Enable 35 Port1 DIO6 Gyro2 SPI SPC 36 D GND Gyro2 GND 37 Port1 DIO7 Gyro2 SPI DIN 38 D GND No Connection 39 Port1 DIO8 Gyro2 SPI DOUT 140 D GND No Connection 41 Port2 DIO9 Gyro2 SPI Enable 42 Port2 DIOCTL No Connection 43 Port2 DIOO Data Storage2 SPI 44 D GND Data Storage2 CLK GND 45 Port9 DIO6 Data Storage2 SPI 46 D GND No Connection DIN 47 Port9 DIO7 Data Storage2 SPI 48 5V sbRIO No Connection DOUT 49 Port9 DIO8 Data Storage2 SPI 50 D GND No Connection Enable Table 17 P3 Digital Connector Pin usage P4 Digital Connector 1 DGND No Connection 2 PortO DIOCTL No Connection 3 Port0 DIOO No Connection 4 Port0 DIO9 No Connection 5 Port0 DIO1 No Connection 6 5V No Connection 7 Port0 DIO2 No Connection 8 DGND No Connection 9 Port0 DIO3 No Connection 10 5V No Connection 11 Port0 DIO4 No Connection 12 D GND No Connection 13 Port0 DIO5 No Connection 14 DGND No Connection 15 Port0 DIO6 No Connection 16 DGND No Connection 17 Port0 DIO7 No Connection 18 D GND No Connection 19 Port0 DIO8 No Connection 20 DGND No Connection 21 Port1 DIO9 No Connection 22 Port1 DIOCTL No Connection 23 Port1 DIOO No Connection 24 DGND No Connection 25 Port1 DIO1 No Connection 26 D GND No Connection 27 Port1 DIO2 No Connec
105. n 2 times 4 HX13 CERESS SEDv3 1 12DEC14 doc Page 45 EuroLauncu ADLRai e Rotation Rate Sensors 2 times 1 e Temperature Sensors 3 4 1 1 6 Data Storage The Data Storage of the CERESS Rocket Module is implemented with a NI 9802 SD Card Module It provides a full file system access on file level The two slots are capable of 2GB each For Event Logging the non volatile onboard storage of the sbRIO is used 4 1 2 The CERESS Verification Module Space Segment The CERESS Verification Module is replaced by the actual experiment in future missions For the CERESS Mission the CERESS Verification Module is used for verification of the CERESS System and is used for flight environment characterisation with several sensors It is fully controlled and supplied by the CERESS Rocket Module over the CERESS Bus bdd Modell Data CSVM y system CSVM x N EE subsystem subsystem 3 E 5 Structure E LN N block blocks Safety SNSR DVR 1 x block A y 1 Jo 1 block block DVR Heating _ SNSR S Figure 6 bdd Verification Module 4 1 2 1 Sensor Driver Board Task of the CERESS Verification Module Sensor Driver Board is to switch the power for the CERESS Verification Module sensors ON OFF e Switch Power ON OFF for Fine Pressure Sensor e Switch Power
106. n stdin cp 111 4 10 5 2 Data processing EE 111 5 EXPERIMENT VERIFICATION AND 113 5 1 Verification Lec e UE LUUD Le LUE LUE E LU 113 5i2 lest PIA oce coo cbe cei ciae cc die cd 119 deele 122 6 lt LAUNCH CAMPAIGN PREPARATION nenn 123 6 1 Input for the Campaign Flight Requirement Plans 123 6 1 1 Dimensions and mass 123 6 1 2 Safety TISKS en ce o edt SURE mM 123 6 1 3 Electrical interfaces 123 6 1 4 Launch Site Requirements 04 222044441121 124 6 1 4 1 c meu 124 ACCESS 124 SCIENCE NET Access 124 Interne 124 Bele Dalai al al al 124 Kalinehek ERA 124 Timed Flight Events AEN 124 6 2 Preparation and test activities at 125 6 3 Launch Campaign Timeline sea aaa 127 6 4 Timeline for countdown and 128 6 5 Post Flight ACHVIIIBS nee ee ee 129 7 DATAVANALY SIS RUANDA Dre P een 130 7 1 Data analysis nein eonun ud 130 7 1 1 Verification Triggered 130 7 1 2 Verificati
107. nch pad 1 4 Req COMS 1 4 1 The rocket module shall be capable to R To be receive information from the ground done module through the whole flight of the rocket 1 4 1 1 The rocket module shall meet the R To be transmission specs of the Service done Module for receiving data 1 4 2 The rocket module shall send To be information to the ground module done through the whole flight of the rocket 1 4 2 1 The rocket module shall meet the R To be transmission specs of the Service done Module for sending data 1 5 1 The mechanical and electrical T A To be components shall withstand the vibration done loads during nominal operation of the rocket 1 5 2 The mechanical and electrical T A To be components shall withstand the shock done loads during launch of the rocket 1 5 3 The mechanical and electrical A R To be components shall withstand the done acceleration loads during nominal operation of the rocket 1 5 4 The mechanical and electrical T R To be components shall withstand the pressure done loads during nominal operation of the rocket 1 5 5 The mechanical and electrical T R To be components shall withstand the thermal done loads during nominal operation of the rocket RX13_CERESS_SEDv3 1_12DEC14 doc Page 116 Eurolauncn ID Requirement text Verification Status 1 5 7 The temperature of the experiment box A T To be shall be ke
108. nd payload the CERESS Verification Module e Merge Data from ESRANGE Ground Station Antenna tracking angles and ranges e Merge Data from REXUS Telemetry GPS The CERESS Ground Module Server utilizes the CERESS TM TC protocol The received data is checked for limits and validity depending on the mission phase and flagged in case of limit violations or errors The different data sources are merged into a unified data structure backed up at the local data storage and forwarded to the CERESS Ground Module Clients in near real time 4 1 3 2 Visualization Tool Server The REXUS Telemetry is used by the Visualization Tool Server to generate the 3D flight visualization data The ESGANGE Internet Connection forwards this data to the CERESS Internet Server located in the Internet For post flight the Visualization Tool Server generates a flight visualization data file for replay with additional scientific data 4 1 3 3 CERESS Internet Server The CERESS Internet Server distributes the 3D flight simulation data to the CERESS Flight Simulation Clients located worldwide over the internet RX13_CERESS_SEDv3 1_12DEC14 doc Page 48 A DLR and SSC cooperation 4 1 3 4 CERESS Flight Simulation Clients The CERESS Flight Visualization Client is implemented as a Google Earth plugin Using free and extendable software enables the broad public to get involved with the REXUS programme 4 1 3 5 CERESS Ground Module C
109. nnten Wir brauchen z B ein Kriterium wann wir den Meltingwire Command schicken Au erdem brauchen wir den Status unseres Experiementes nicht die r 90452012 Zahlenwerte der Sensoren Ein ganzer Bildschirm voller Zahlen ist sinnlos Ein Bildschirm mit gr nen L mpchen schon 26 54005 Bei Markus Wilde Andi Fleischner sich Infos ber das GM Front End einholen 19 Mai besser KISS So einfach wie m glich 27 54007 SED Kap 4 6 4 6 Thermal Design 06 Jun Heaters igendwie nachrechnen erst nach reorganisation der requirements 28 54008 Test f r jeden eurer Teile berlegen und in SED Kap 5 2 einf gen 20 Mai m glich E M gt Tabelle1 Tabelle2 Tabelle3 2 Wal m SC Figure 4 Short Term Action Items 3 3 Resources 3 31 Manpower The CERESS team consists of four members with about 8 hours per week available for the project In normal case that creates 32h week manpower in total If the need arises additional time on weekends can be allocated HX13 CERESS SEDv3 1 12DEC14 doc Page 36 EuroLAUNcCH 3 3 2 Budget Type Cost OBDH 3100 EPS 300 Structure 1800 Sensors 1000 Test equipment 1000 Overall costs 7200 Studienbeitrage from University 5200 DLR Hardware 2000 Overall funding 7200 Total 0 Table 8 Budget Overview Additional funding in form of hardware is intended 3 3 3 External Support The Institute of Astronautics LRT
110. nual Major tasks are e Forward LO SOE SODS Signals e Provide galvanic isolation 4 1 1 3 Sensor Driver Board The tasks of the Sensor Driver Board are e Switch Power ON OFF for CERESS Rocket Module Sensors e Switch Power ON OFF for CERESS Rocket Module Data Storage The electrical components of the CERESS Rocket Module are powered by the CERESS Rocket Module Power Supply To prevent high inrush currents and to protect the CERESS Rocket Module Data Storage against power fluctuations at startup and shutdown the electrical power of these components can be switched ON OFF Power switching is critical for mission success so every switch is implemented as two Solid State Relays in parallel 4 1 1 4 Power Supply The CERESS Rocket Module Power Supply provides following regulated voltages e 3 3V e 5V e 24V The Power Supply is implemented with two DC DC converters one for 3 3V and 5V and one for 24V The 28V unregulated REXUS Power is directly forwarded to the CERESS Verification Module The CERESS Rocket Module is floating ground The common ground point is located at the ground connection of the Main Computation Unit 4 1 1 5 Sensors If necessary the sensor of the CERESS Rocket Module is implemented two times one for course measurements during liftoff and reentry and one for fine measurements during free flight and vacuum Implemented Sensors are e Acceleration Sensors mounted in an tetrahedron configuratio
111. o o eoe OOo ee Carles dr s 61 GERESOS BUS nl ecd bnc Ule ds 62 CERESS Rocket Module internal interfaces 64 CERESS Verification Module internal interfaces 64 423 Thermal a bc at b 64 Experiment 0 0 64 4 3 1 CERESS Rocket Module eto eit e be bet ent 64 Main Computation Unit 5080 9642 64 Gyroscope eet qub o e Uus 70 Accelerometer LIS331HH EE 70 Power Supply 40 2420 2415 70 get 70 4 3 2 CERESS Verification Module s ices t geseent ne 70 Camera GoPro H2 me tnc ad ape asia 70 Pressure Sensors MS5534C amp TTR 91 71 1 CERESS SEDVv3 1 12DEC14 doc 4 3 2 3 4 3 2 4 4 3 2 5 4 4 4 4 2 1 4 4 2 2 4 5 4 5 2 4 5 3 4 5 3 1 4 5 4 1 4 5 4 2 4 5 4 3 4 5 4 4 4 5 5 1 4 5 5 2 4 5 5 3 4 5 5 4 4 6 4 7 4 8 4 8 1 1 4 8 1 2 4 8 2 1 4 8 2 2 4 8 2 3 4 8 2 4 4 8 2 5 4 8 2 6 4 8 2 7 Temperature Sensor 10342 71 71 Meltingwire 71 4 3 3 Parr Availability cnc ae ois 71 Mechanical Design 2 2 72 Ne
112. oard members DLR Bremen Martin Siegl chair editor Mark Fittock minutes DLR Bremen Marcus H rschgen DLR MORABA Tobias Ruhe DLR MORABA Nils H ger DLR MORABA Frank Hassenflug DLR MORABA Markus Pinzer DLR MORABA Natacha Callens ESA Education Alex Kinnaird ESA Education Mikael Inga SSC Solna Jianning Li SSC Solna RX13_CERESS_SEDv3 1_12DEC14 doc Page 141 EuROLAUNCH A DLR and SSC cooperation 2 Experiment Team members Daniel Bugger Technische Universitat Munchen Alexander Schmitt Technische Universitat M nchen Sebastian Althapp Technische Universitat M nchen Christoph Friedl Technische Universitat M nchen 3 General Comments Presentation It was 19 min long make sure to keep the time It was delivered confidently and answered many open questions The system overview was very good but might have had too many details in the slides SED The document is very good from a formal perspective The correct EuroLaunch logos are used throughout the document All presented information is very clear The graphics used to present the system overview in the presentation should also be part of the SED In some sections relevant information is missing The extensive use of abbreviations three letter acronyms makes the document hard to read Panel Comments and Recommendations Requirements and constraints SED chapter 2 Clarify currents b
113. of the DC DCs The schematic is included in the electrical design chapter The power requirement of all electrical components is listed in the table below Component Voltage Current Power W Quantity Total V mA Power IW sbRIO 24 333 8 00 1 8 00 3 3 5V DC DC 24 100 2 40 1 2 40 24V DC DC 24 85 2 04 1 2 04 Accelerometers 3 3 0 25 0 01 8 0 08 Gyros 3 3 6 1 0 01 2 0 05 Coarse Pressure 3 3 1 0 01 1 0 01 Sensor Fine Pressure 24 42 1 01 1 1 01 Sensor Heating Foil 24 0 14 3 43 1 3 43 Thermistors 3 3 60 0 2 6 1 2 GoPro HD Hero2 5 gt 500 2 5 1 2 5 High Side Current 3 3 0 42 0 001 6 0 006 Sensors Meltingwire mw 3 3 1 3 3 1 3 33 for 5 secs Table 25 Power Budget of electrical components Since not all components are powered at the same time two different operating modes can be defined In Normal Mode all nominal components sbRIO DC DCs various sensors and the heating are active Normal Mode Component Quantity Power W Total Power W sbRIO 1 8 00 8 00 3 3 5V DC DC 1 2 40 2 40 24V DC DC 1 2 04 2 04 Accelerometers 8 0 01 0 08 HX13 CERESS SEDv3 1 12DEC14 doc Page 97 A DLR and SSC Normal Mode Gyros 2 0 01 0 02 Coarse Pressure Sensor 1 0 01 0 01 Fine Pressure Sensor 1 1 01 1 01 Heating Foil 1 3 43 3 43 Thermistors 6 0 2 1 2 GoPro HD Hero2 1 25 2 5 High Side Curren
114. on Datahanding ses 130 7 1 3 Verification Signal Chain TE 131 7 1 4 Verification Signal Chain 131 7 1 5 Verification COTS Gensors e 131 7 1 5 1 Error calculations vio 131 7 1 5 2 Correlations between Accelerometers and Gyroscopes 131 7 1 5 3 Error calculation Altitude sr ae ect calc a o E P ac d 131 7 1 6 Flight Environment nee een 132 7 1 6 1 A A EA 132 eh EST MM ere CIERTO T m T 132 1 CERESS SEDVv3 1 12DEC14 doc 7 2 Launch Campaign EE 132 TEES 132 7 4 Discussion and Conclusions eren nein tn ENEE 132 1 9 e EE e WEE 132 7 5 1 Project Planning gt ay 132 7 5 2 System 132 GERESS USER MANUAL SE SS ee ae terme 133 8 1 Services provided by 133 811 Regulated Power Supply 133 8 1 2 amp COMUOL seu Mdb 133 8 1 3 Board Data 133 8 14 STIMME a pti ate inst ants 133 8 1 5 LabView 134 8 1 6 55 Ground Module 134 8 1 7 3D flight Visu
115. on sensor shall take 1000 R To be measurements every second done 1 2 2 All Sensors shall withstand the T R To be environment condition within a REXUS done launch campaign 1 2 2 1 The sensors shall withstand the thermal T R To be load cases done 1 2 2 2 The sensors shall withstand the R To be acceleration load cases done 1 2 2 3 The sensor shall withstand the pressure T R To be load cases done 1 2 3 The system shall measure angular rate R T To be RX13_CERESS_SEDv3 1_12DEC14 doc Page 114 Eurolauncn 0 Requirement text Verification Status in all 3 axis done 1 2 3 1 The angular rate sensor shall be able to R To be measure up to 5Hz done 1 2 3 2 The angular rate sensor shall have an R To be accuracy of 10mHz done 1 2 3 3 The angular rate sensor shall take 1000 R To be measurements every second done 1 2 4 The system shall measure the ambient R T To be pressure done 1 2 4 1 The ambient pressure sensor shall cover R To be the range from Ombar to 1013mbar done 1 2 4 2 The ambient pressure sensor shall be R To be able to measure pressure with an done accuracy of 1mbar 1 2 4 3 The ambient pressure sensor shall make R To be 1 pressure measurement every second done 1 2 5 system shall measure the R T To be temperature inside the inside the CSRM done 1 2 5 1 The internal temperature sensor shall be R T To be able to measure temperatures between done 4
116. onnecting one output line the the sbRIO s analogue inputs For 24V a voltage divider has to be used since the sbRIO can only handle input voltages of up to 10V Figure 40 24V level measurement 4 5 5 2 Powerboard 1 PCB layout The circuits above result in a printed circuit board with the following parameter e Dimensions 120x60mm e Double layer Oum copper 4 Iv bread Vas Figure 41 24V Board Bottom Top View RX13_CERESS_SEDv3 1_12DEC14 doc Page 90 EuroLAuNcH A DLR and SSC coopera o 4V Board v1 Figure 42 24V Board Top Top View The PCB s top layer is basically a ground plane for the entire board This is due to the fact that space is very limited on the board 4 5 5 3 Powerboard 2 3 3 5V For 3 3V and 5V output a single DC DC converter is used The Tracopower TEN40 2420 is able to provide both voltages with sufficient current The input filer is equivalent to the one of the 24V converter the difference being that not two but four 1nF 2kV capacitors are necessary since it has two different Vout and Vout This converter does not have the capability to trim the output voltage The circuit for 3 3V and 5V output are shown below HX13 CERESS SEDv3 1 12DEC14 doc Page 91 A DLR and SSC coopera Figure 43 TEN40 2420 Circuit The circuit to measure current is the same as for the 24V Powerboard only the values of t
117. ors and 1 gyroscope Each number times two for coarse and fine measurement These are used to judge the quality of micro gravity during free flight 7 2 Launch Campaign T 3 Results 7 4 Discussion and Conclusions 7 5 Lessons Learned 7 5 1 Project Planning Working in a small Team without a clear work distribution may work when the Team has not keep up with deadlines and no external standards are applied As soon as deadlines and external standards e g REXUS SED apply the work distribution is critical for keeping up with the deadlines 7 5 2 System Definition The system definition needs to be done in an iterative process All systems on a specific system level need to be defined before going deeper in the system hierarchy in the next iteration A system level hierarchy deeper than 4 levels is not applicable due to complexity HX13 CERESS SEDv3 1 12DEC14 doc Page 133 EuroLAuUNcH 8 CERESS USER MANUAL This section aims to provide future Teams the information needed to use CERESS on their mission It is continuously updated after CDR 8 1 Services provided by CERESS CERESS is a Compatible and Extendable REXUS Experiment Support Bus aiming to simplify the REXUS interfaces and experiment development Therefore CERESS offers several services for future Missions 1 The Software is fully reusable and designed with expandability in mind 2 The CERESS Rocket Module may need to be modified but is also intende
118. pins of connectors and sockets to be the same materials Need to be careful of ground loops as they could affect your readings Need to also be careful of where the sbRIO is grounded to Grounding concept needs to be investigated especially considering the experiments Thermocouples may well need to be isolated Thermal Graph was a very neat way to show component ranges Consider a heatsink on the processor Test processor on ground first and then in a thermo vac chamber Software Software has been covered very well see that the team realises that software is a major component of their experiment It s not clear what the signals from RXSM used for within the exp software Themal cutter would be activated by command from ground desired Calibration of sensors when the rocket is lifted ready for launch Testing Some verification methodologies were missed e g REQ 151 test and review currently should be analysis and test Make sure to be careful with tests not inspection when something is being set up for a test Other issues to be discussed with Mr DeBeule Look at high accelerated live testing Safety and risks Take the risk description out of the SED Risks such as team losing members covered Covered well after revisions Operations Slantrange is also provided by Esrange and DLR TM Problem with being connected to Esranges system and
119. pt between 40 C and 30 C done 1 6 Req Topology 1 6 2 The Rocket Module shall fit in standard A R T To be REXUS Module max_height 85mm done 1 6 3 The hatch shall provide a plug for To be programming and Checking done 1 6 4 Design Plug to RXSM R To be done Proce 1 7 1 deleted 1 7 2 Design Connection to Gyros R To be done 1 7 3 Design Connection to Verification R To be Module done 1 7 4 The Processing Unit shall be capable to A R T To be perform the logging actions near real done time 1 8 Req Structural 1 8 1 Position of CoG Maximum X 20 mm R To be 20 mm 2 20 mm 1 8 2 Moment of Inertia Maximum Ix 0 1 A R To be kg m2 ly 0 1 kg m2 12 0 1 kg m2 done 1 8 3 Total mass Shall not deviate more than A R To be 0 5kg done 1 8 4 Mass distribution Around 0 25kg per A R To be 100mm done Table 32 Verification Matrix ID Requirement text Verification Status 2 Requirements Verification module 2 1 Functional Sensors 2 1 1 The system shall measure the R To be temperatures inside the VE done 2 1 1 1 The temperature sensor shall be able to R T To be measure temperatures between 40 and done 200 C 2 1 1 2 The internal temperature sensor shall be R T To be able to measure temperatures with an done accuracy of 1 C 2 1 1 3 The internal temperature sensor shall R To be make 1 temperature measurement every done 2 1 2 Deleted
120. ratory Test item Whole RM Test level Data on SD Cards has to be readable after a power drop procedure and and no data is overwritten duration Test campaign 2 days duration RX13_CERESS_SEDv3 1_12DEC14 doc Test Number Page 121 EuroLAuNcH A DLR and SSC Test type Functional Test Test facility LRT Laboratory Test item Whole RM Test level Full test in full length including countdown and flight procedure and duration Test campaign 2 days duration Test Number 10 Test type Thermal Vacuum Test Test facility LRT laboratory Test item sbRIO Test level sbRIOs performance an environment resembling procedure and the flight environment shall be tested duration Test campaign duration Test Number 11 Test type Thermal Vacuum Test Test facility LRT laboratory Test item All electrical components Test level All electrical components shall be tested for survivability procedure and under vacuum conditions duration Test campaign duration Test Number 12 Test type Thermal Vacuum Test Test facility LRT laboratory Test item Fine Pressure sensor heating cycle Test level All components of the heating cycle shall be tested under procedure and flight conditions temperature and vacuum duration Test campaign duration RX13_CERESS_SEDv3 1_12DEC14 doc Page 122 EuroLAuNcH A DLR
121. s 1 2 3 1 Performance AR The angular rate sensor shall be able to Range measure up to 5Hz 1 2 3 2 Performance AR The angular rate sensor shall have an Accuracy accuracy of 10mHz 1 2 3 3 Performance AR The angular rate sensor shall take 1000 measurement frequency measurements every second 1 2 4 Functional Ambient The system shall measure the ambient pressure pressure 1 2 4 1 Performance Amb The ambient pressure sensor shall pres range cover the range from Ombar to 1013mbar 1 2 4 2 Performance Amb The ambient pressure sensor shall be pres accuracy able to measure pressure with an accuracy of 1mbar 1 2 4 3 Performance Amb The ambient pressure sensor shall pres measurement make 1 pressure measurement every frequency second 1 2 5 Functional Internal The system shall measure the Temperature temperature inside the inside the CSRM 1 2 5 1 Performance Int Temp The internal temperature sensor shall Range be able to measure temperatures between 40 and 200 C 1 2 5 2 Performance Int Temp The internal temperature sensor shall Accuracy be able to measure temperatures with an accuracy of 1 C 1 2 5 3 Performance Int Temp The internal temperature sensor shall measurement frequency make 1 temperature measurement every second 1 3 Reg Software 1 3 1 Functional Data from The rocket module shall retrieve data int Sensors from intern sensors 1 3 10 Functional Perform The rocket module sha
122. s shown in Figure 52 and explained afterwards Fehler Keine g ltige Verkn pfung Figure 52 Telemetry Data Frame e SYNC These Bytes are for detecting the next CERESS Telemetry Data Frame on ground e MSGINF Message Info The Message Info contains the highest included priority within the Message four bit a sequence control two bit and the sequence message count two bit e MONT Message Count HX13 CERESS SEDv3 1 12DEC14 doc Page 105 A DLR and SSC This Counter is increased with every Message Therefore it is easy to find out which Telemetry Data Frames were missing by detecting the absence of the MCNT number The Counter is modulo 255 8 bit e Data Frame The data packets are stored within Byte four to nineteen CRC Cyclic Redundancy Check The CRC is an error detecting code It represents a check value calculated out of the transmission data The CRC two Bytes will be calculated with the provided C Code from MORABA CSM BSD Checksum The CSM is calculated by adding all 16bit words while after each step the accumulator is rotated to the right by one bit This prevents an overflow of the CSM two Bytes 4 8 5 4 Telemetry Budget The downlink is used in different cases for different information Considering only the Telemetry Data Frame without Header and Trailer a usage for every mode is computable The following Table shows the usage relating to one second and
123. scribed as the REXUS Bus The Connections and interactions between the CERESS Rocket Module and the CERESS Verification Module are described as the CERESS Bus The communications interface between the CERESS Rocket Module and the CERESS Ground Module is referred to as Telemetry TM and Telecommand TC 411 CERESS Rocket Module Space Segment The CERESS Rocket Module is the key component of the CERESS Space Segment It provides the CERESS Bus by extending the functionality of the REXUS Bus forwarded to the CERESS Verification Module RX13_CERESS_SEDv3 1_12DEC14 doc Page 43 EuroLAUNCH bdd Modell Data CSRM subsystems Instrumentation subsystem PWR SPY 1 block SNSR DVR 5 block SD Cards Figure 5 bdd Rocket Module 4 1 1 1 Main Computation Unit The Main Computation Unit MCU is the key component of the CERESS Rocket Module and provides following operations e Data acquisition e Data storage e Command amp Control of the CERESS Rocket Module and CERESS Verification Module e TM TC handling The MCU is implemented by a sbRIO see Appendix for Datasheet The tasks of the MCU are often wrapped up as On Board Data Handling OBDH RX13_CERESS_SEDv3 1_12DEC14 doc Page 44 4 1 1 2 Interface Board The Interface Board implements the signal connections of the REXUS Bus as proposed in the RX User Ma
124. shown in Table 23 Natural vibrations of the crossbar The most relevant mode is the first one it is a pure translatory motion in z direction of the rocket coordinate system see Figure 32 1 mode of the crossbar Frequenz Tz Rx Ry Rz Hz 1 2015 5 0 00 0 00 59 33 0 00 0 00 0 00 2 2884 4 0 00 58 47 0 00 0 01 0 00 0 00 3 5003 1 0 56 0 00 0 00 0 00 32 63 0 00 4 5131 0 0 00 0 02 0 00 31 66 0 00 0 00 5 7841 0 0 00 0 00 0 00 0 00 0 00 37 32 6 8946 9 0 00 0 00 15 62 0 00 0 00 0 00 7 11303 0 00 0 00 0 00 0 00 0 00 0 05 8 11433 0 01 18 75 0 00 0 00 0 00 0 00 9 11639 67 73 0 00 0 00 0 00 1 26 0 00 10 13829 5 61 0 00 0 00 0 00 15 55 0 00 Table 23 Natural vibrations RX13_CERESS_SEDv3 1_12DEC14 doc Page 80 EuroLAUNCH A DLR and SSC cooperat Figure 32 1 mode of the crossbar 45 Electronics Design This chapter details the electronic design ranging from circuit schematics to printed circuit boards 4 5 1 System Overview The electrical system includes the sbRIO two DC DC converters one camera pressure sensors temperature sensors accelerometers gyros and melting wires as well as additional components like cabling connectors and other electrical components It can be subdivided into two segments e Power system EPS Command and control OBDH C amp DH An overview of the electrical system can be found below HX13 CERESS SEDv3 1 12DEC
125. supports CERESS e The employees contribute know how to the project Experts are at hand for sensor selection system engineering programming project management and industry contacts e The Institute allocates resources like the Clean Room the Workshop Student Laboratory IT Infrastructure and a thermal vacuum chamber e Software licenses are provided for LabView MatLab CATIA STK and MagicDraw REXUS Alumni at our Univerity Fellow students at our institution who have already participated in the REXUS program help us in critical situations and design decisions Oerlikon Leybold Vacuum GmbH We managed to get sponsoring by Oerlikon Leybold Vacuum GmbH They provide us with Pirani sensors for low air pressure measurements National Instruments e National Instruments already supported us with an ask the expert session and additional sponsoring is in the pipe RX13_CERESS_SEDv3 1_12DEC14 doc Page 37 A DLR and SSC coopera 3 3 1 Facilities At the department Institute of Astronautics access to different laboratories a thermal vacuum chamber and an integration room clean room is provided Material resources at the laboratories and workshops such as simple raw materials like bolts and electronics can be used Smaller hardware components can directly be manufactured there 3 4 Outreach Approach CERESS project s outreach focuses on two main pillars Online medi
126. t 6 0 001 0 006 Sensors Total 20 7 With 50 margin 31 05 Table 26 Power Budget Heating Mode The second mode is Wire Melting Mode In this mode the heating is turned off while the melting wires are powered for a five second interval Component Quantity Power W Total Power W sbRIO 1 8 00 8 00 3 3 5V DC DC 1 2 40 2 40 24V DC DC 1 2 04 2 04 Accelerometers 8 0 01 0 08 Gyros 2 0 01 0 02 Coarse Pressure Sensor 1 0 01 0 01 Fine Pressure Sensor 1 1 01 1 01 Thermistors 6 0 2 1 2 GoPro HD Hero2 1 2 5 2 5 High Side Current 6 0 001 0 006 Sensors Melting Wire 1 3 3 3 3 Total 20 6 With 50 margin 30 9 Table 27 Power Budget Wire Melting Mode RX13_CERESS_SEDv3 1_12DEC14 doc Page 98 EuROLAUNCH A DLR and SSC cooperation 4 8 Software Design Rocket Module 4 8 1 On Board data flow The Main Computation Unit of CERESS is a single board Reconfigurable Input Output sbRIO produced by National Instrument Figure 49 shows the data flow between function blocks according to their allocation onto the sbRIO In Node Signals Figure 49 On Board data flow 4 8 1 1 FPGA The Field Programmable Gate Array provid
127. tatus 4 Requirements Visualization Tool 4 0 The VT shall display the flight of the R T To be done REXUS Rocket 4 1 The VT shall display data during flight R T To be done 4 1 2 The VT shall display the trajectory of the R T To be done REXUS Rocket 4 1 3 The data shall be updated once per R To be done second 4 1 4 The VT shall use the data from the GM R To be done via the internet 4 2 The VT shall display CERESS data R T To be done during post flight 4 2 1 The VT shall display the trajectory of the R T To be done REXUS Rocket 4 2 3 The VT shall display the data collected R T To be done by the CSRM in post flight Table 35 Verification Matrix RX13_CERESS_SEDv3 1_12DEC14 doc 5 2 Test Plan Test Number Page 119 A DLR and SSC coopera Test type Functional test Test facility LRT student laboratory Test item Melting wires EPS Test level The ability of the power supply to melt the melting wires procedure and shall be tested duration Test campaign duration Test Number 2 Test type Functional Test Test facility LRT student laboratory Test item DC DC Converters Test level The DC DC converters shall be tested on correct output procedure and voltages and ability to handle peak currents duration Test campaign duration Test Number 2 1 Test type Functional Test Test facility LRT student laboratory Test
128. te Taker Experience e Tutor for practical courses the programming languages C C institute for information technologies of TU Munich e Seminar Team formation and group leading Teambildung und Gruppenleitung at ITQ e TUTOR soft skill program at TU Munich e Second Place in the engineering competition CAR toffel at TU Munich e Internship at EADS Division Cassidian Air Systems Table 1 CERESS Team Members RX13_CERESS_SEDv3 1_12DEC14 doc 2 2 1 1 1 Functional Provide Power Page 21 A DLR and SSC EXPERIMENT REQUIREMENTS Requirements CERESS Rocket Module Req Rocket Module 4 Req Electrical 1 The system shall provide regulated electrical power Performance Power to The Power Supply shall provide the Meltingwires power to melt the wires 1 1 1 2 Deleted Deleted 1 1 1 3 Deleted Deleted 1 1 1 4 Deleted Deleted 1 1 1 5 Design SM to EPS The electrical power system shall accept unregulated power from the REXUS SM 1 1 1 6 Performance Perf The electrical power system shall be provided power able to provide 30W of power 1 1 3 Design Receive Power The Rocket Module shall use the power from RXSM provided by the RXSM 1 1 3 1 Performance 28V DC The electrical power supply shall accept Input input voltages of 28V DC 1 1 3 2 Performance 3A DC The power supply sha
129. ted 2 2 Functional Video The system shall record a video of the flight resp of VE 2 2 1 Performance Video frame The video camera shall have a rate frame rate between 25fps and 50fps 2 2 2 Performance Video The video camera shall have a resolution resolution of fullHD 1920x1080px 2 3 Operational Actions The Verification Module shall show that an Action triggered by the rocket module is performed Table 3 CERESS Verification Module Requirements RX13_CERESS_SEDv3 1_12DEC14 doc Page 26 EuroLAuUNcH 2 3 Requirements CERESS Ground Module 3 Req Ground Module 3 1 Data Handling GM 3 1 1 Functional Data from live The Ground Module shall receive link telemetry data from the ESRANGE ground networks 3 1 2 Functional Data from The Ground Module shall receive CSRM data from the CSRM via the REXUS downlink 3 1 2 1 Functional Save received The Ground Module shall store the data received data stream 3 1 2 2 Functional Decode The Ground Module shall decode received data the received data streams into the usable data sets 3 1 3 Functional Data to CSRM The Ground Module shall send data to the CSRM via the REXUS uplink 3 1 3 1 Functional Store send data The Ground Module shall store the received data stream 3 1 3 2 Functional Code data for The Ground Module shall code the sending data that is to be sent into the send data stream 3 1 4 Functional
130. through a voltage reference therefore eliminating the need to measure the voltage 4 5 7 GoPro Hack To use the GoPro camera it is necessary to provide it with power and remotely turn recording on and off For this purpose knowledge of the 30pin connector on the back of the camera is required Table 24 GoPro Connector Pinout Reference http chargeconverter com blog pz71 Video out 2 1 GND B Video out 4 3 G Video Out USB 5V power 6 5 USB 5V power USB Data 8 7 USB Data Audio Out Right 10 9 GND Pwr Mode Button 12 11 Audio Out Left Audio In Right 14 13 Playback Mode Button IR Input 16 15 Audio In Left GND 18 17 Trigger digital output ID2 digital input 20 19 ID1 digital input ID4 digital input 22 21 ID3 digital input Aux Adapter Output 24 23 Adapter Output VBat 26 25 VBat Data Interface 28 27 GND GND 30 29 CLK Interface 2 Since it is not advisable to use the camera s lithium ion battery on a sounding rocket external power has to be applied This is achieved by connecting both USB 5V power pins of the GoPro connector to the 5V supply of the rocket module To start recording the camera is first set to one button mode by hand This mode means that the camera starts recording a video as soon as it is turned on To turn it on the Pwr Mo
131. tion 28 D GND No Connection 29 Port1 DIO3 No Connection 30 D GND No Connection 31 Port1 DIO4 No Connection 32 D GND No Connection 33 Port1 DIO5 No Connection 34 D GND No Connection 35 Port1 DIO6 No Connection 36 D GND No Connection 37 Port1 DIO7 No Connection 38 D GND No Connection 39 Port1 DIO8 No Connection 40 D GND No Connection 41 Port2 DIO9 No Connection 42 Port2 DIOCTL No Connection 43 Port2 DIOO No Connection 44 D GND No Connection 45 Port2 DIO1 Corse Pressure 46 D GND Coarse Pressure HX13 CERESS SEDv3 1 12DEC14 doc Page 68 EuroLaunch DIN DIN GND 47 Port2 DIO2 Coarse Pressure 48 DGND Coarse Pressure DOUT DOUT GND 49 Port2 DIO3 Coarse Pressure 50 D GND Coarse Pressure SCLK SCLK GND Table 18 P4 Digital Connector Pin usage P5 Digital Connector 1 D GND No Connection 2 Port7 DIOCTL No Connection 3 Port7 DIOO No Connection 4 Port7 DIO9 No Connection 5 Port7 DIO1 No Connection 6 D GND Connection 7 Port7 DIO2 No Connection 8 DGND Heating GND 9 Port7 DIO3 Heating 10 DGND Activate Coarse Pressure Sensor GND 11 Port3 DIO9 Activate Coarse 12 Port3 DIOCTL No Connection Pressure Sensor 13 Port3 DIOO No Connection 14 D GND Activate Fine Pressure Sensor GND 15 Port3 DIO1 Activate Fine 16 D GND Feedback Camera Pressure Sensor
132. titute Pennsylvania USA 2006 European Cooperation for Space Standardization ECSS Space Engineering Ground systems and operations Monitoring and control data definition ECSS E ST 70 31C 31 July 2008 European Cooperation for Space Standardization ECSS Space Engineering Ground systems and operations ECSS E ST 70C 31 July 2008 European Cooperation for Space Standardization ECSS Space Engineering Ground systems and operations Telemetry and Telecommand packet utilization ECSS E 70 41A 30 January 2003 European Cooperation for Space Standardization ECSS Space Engineering SpaceWire Links nodes routers and networks ECSS E 50 12C 31 July 2008 Wilfried Ley Klaus Wittmann Willi Hallmann Handbook of Space technology John Wiley amp Sons Ltd 2009 RX13_CERESS_SEDv3 1_12DEC14 doc Page 138 A DLR and SSC APPENDIX A EXPERIMENT REVIEWS Experiment PDR ESRANGE Kiruna 28 Feb 2012 Presentation Was 41 seconds too long Presented well and confidently Writing on slides often too small General SED Comments Many missing sections followed in presentation References need to be updated for literature and component references Front page very good Chapter 7 Data Analysis needs to be considered so that it is reflected in the design Requirements and constraints Although not by the standard format appears to be effective
133. to generate the information needed for the verification even if the REXUS Rocket is not recovered See Chapter Experiment Setup Meltingwires The CERESS Rocket Module provides the following data e Feedback of each Meltingwire if current is flowing through the coils e Feedback of each Meltingwire device by a switch Each of the feedback signals is stored with a timestamp on board and also via TM on the CERESS Ground Segment By this the order of events can be correlated and judged for plausibility 7 1 2 Verification Data handling Although each single part of the data handling chain is verified before flight the complete interaction of every component involved in data handling can only be verified in flight The complete process of data acquisition to data storing data protection and data readout can be verified by inspection of the data stored on the SD Cards Therefore two procedures are planed 1 Correlate expected and actual data format on both SD Cards 2 Bitwise comparison of the two different SD Cards Furthermore CERESS stores data at the CERESS Rocket Module and at the CERESS Ground Module via TM These two elements are not part of the same signal chain Therefore a correlation of the on board and the on ground stored data is used to judge the quality of the data redundancy The amount of downlinked data is expected to be only a fractional part of the on board stored HX13 CERESS SEDv3 1 12DEC14 doc Page 131
134. treach approaches the CERESS project has one that is unique The visualization tool allows people around the globe to experience the rocket flight in near real time as well as replay it afterwards with additional information Combined with the on board camera s recordings we intend to get people more interested in spaceflight in general and the REXUS programme in particular HX13 CERESS SEDv3 1 12DEC14 doc Page 38 EuroLaunch Media Publisher Content Homepag CERESS _ Detailed project information e http ceress de Faceboo CERESS Status updates and photographs http facebook ceress de Twitter CERESS Status updates http twitter ceress de YouTube CERESS Videos http www youtube com user CeressRex us To be Press CERESS General project information released release Feb Press FSMB Article about CERESS and the use of 2012 release university funding Table 9 Outreach media RX13_CERESS_SEDv3 1_12DEC14 doc 3 5 Risk Register The following table shows all identified risks to the project and the experiment For Explanation of Risk Register see Appendix D Page 39 A DLR and SSC Action Order spare components and keep them available Use resistors and redundancies Test early and thoroughly Handle with care package softly Repair Heartbeat checks for crashes and resets if necess
135. utput voltage connecting to Vout with an increase of output voltage Since the output voltage should not be considerably lower than 24V only the trim up resistor is implemented The possibility to use remote sensing is not used therefore 4Sense is connected to Vout and Sense to Vout The resulting circuit can be seen below Figure 38 TEN60 2415 Circuit To measure the current usage of rocket and service module a shunt resistor is placed on the respective output line By measuring the voltage drop on this shunt the current can be calculated using Ohm s Law A more comfortable way than measuring voltage before and after the shunt is to use a high side current sense HSCS chip like Maxim s MAX4172ESA This chip is amplifying the voltage drop and outputting a single voltage that can be measured in comparison to ground Therefore only one analogue input of the sbRIO is used Figure 39 High side current sense circuit RX13_CERESS_SEDv3 1_12DEC14 doc Page 89 A DLR and SSC coopera The circuit above is implemented twice once for RM and once for VM voltage output Between the HSCS V and GND a 0 1uF capacitor is implemented to reduce ripple By connecting the measurement signal Out via a resistor to ground and measuring between Out and resistor the scale of the output can be set In principle this is a voltage divider The level of output voltage can be measured directly by c
136. vers the received values A detailed description will be available handbook for future teams 4 8 4 2 Timestamper Due the high frequency of data acquisition it s necessary to get a timestamp of the gained values Unfortunately a true timestamp with date and time is only available on the Real Time Hast and there only with an accuracy of ms Therefore an single cycle loop with 10MHz is utilized to give an timestamp with an us accuracy and a capacity up to six an half hour which should cover the maximum power up time including Countdown and flight The Timestamps are available to all functional block through global variables There are two different types of timestamps One is the clean version which is readable as us ms s min and h The other is a combined array of Booleans with a size of 35bit 4 8 4 3 Timestamp clean to bin Converts the readable timestamp to 35bit representation For example used in the RS422 or store block 4 8 4 4 Timestamp clean to bin Converts the 35bit timestamp to readable representation For example used in the RS422 or store block 4 8 5 Telemetry Several data is necessary for surveillance of the CERESS Rocket Module and CERESS Verification Module The following section explains the packets theirs size as well as the Telemetry Data Frame definition and the priority scheme 4 8 5 1 Priority Due the fact that some information is more important than other it s a need to have a short time delay bet
137. viations AIT asap bdd BO BR CDR CERESS COG CRP DLR EAR EAT ECTS EIT EPM EPS ESA Esrange ESTEC ESW FAR FPGA FRP FRR FST Mbps Assembly Integration and Test as soon as possible block definition diagram SysML Bonn DLR German Space Agency Bremen DLR Institute of Space Systems Critical Design Review Compatible and Extendable REXUS Experiment Support buS Centre of gravity Campaign Requirement Plan Deutsches Zentrum f r Luft und Raumfahrt Experiment Acceptance Review Experiment Acceptance Test European Credit Transfer System Electrical Interface Test Esrange Project Manager Electric power system European Space Agency Esrange Space Center European Space Research and Technology Centre ESA NL Experiment Selection Workshop Flight Acceptance Review Field Programmable Gate Array Flight Requirement Plan Flight Readiness Review Flight Simulation Test Ground Module Ground Support Equipment Hardware House Keeping High side current sense Interface internal block diagram SysML Interface Control Document Interim Progress Review Lift Off Line of sight Lehrstuhl f r Raumfahrttechnik Institute of Astronautics Local Time Mega Bits per second HX13 CERESS SEDv3 1 12DEC14 doc Page 136 EuroLruncH Main Computation Unit Mission Flight Handbook Mobile Raketen Basis DLR EuroLaunch On Board Data Handling Oberpfaffenhofen DLR Center Printed Circuit Board electronic
138. vice versa converted from a non inverted Exp In and an inverted signal Exp out to a single bit stream To achieve this goal Maxim s RS 422 transceiver MAX488EESA is used The circuit is displayed below mWh5 O O s Figure 35 RS 422 Convertor Circuit In accordance to the Rexus service module a 1kQ resistor is implemented between the incoming data lines Furthermore a capacitor is inserted between the 5V supply and the ground line to compensate for jitter in the supply voltage 4 5 4 2 Signal Interpreter The function of the signal interpreter circuit is to detect changes in the three supplied control lines while at the same time galvanically isolating the signals in order to prevent the experiment from accidentally switching the LO signal on This is achieved by using three optocouplers consisting of a light source and a phototransistor Since only the light source can trigger the phototransistor and not the other way around switching can only occur in one direction Furthermore the 28V source of the service module cannot damage any experiment components that are sensitive to overvoltage The circuit used is shown below HX13 CERESS SEDv3 1 12DEC14 doc Page 86 EuroLAuNcH A DLR and SSC coopera Figure 36 Signal Interpreter Circuit The circuit is in accordance to Rexus user manual s chapter 7 6 7 with a 3kQ resistor between the 28V and the optocouplers and a 1kQ pul
139. ween event happening and report on ground A Solution is to prioritize the information There are eleven HX13 CERESS SEDv3 1 12DEC14 doc Page 104 A DLR and SSC priority levels within CERESS Level one is the highest and eleven the lowest It s needful to understand that priority eight to ten update their packets after each sending loop in order to downlink the latest measurement data Fehler Keine g ltige Verkn pfung 4 8 5 2 Data Packets Every Thread and Function within the OBDH has its unique SourcelD Each of them has different Data Packets which are processed stored downlinked etc For identification of them the sources have packetlDs The IDs bound together represent a Header for data packets with fixed size throughout the whole OBDH see Table 28 This is also the reason why the GM can interpret the Data Frame with chained packets See Appendix C for details of the data packets Fehler Keine g ltige Verkn pfung Table 28 Data Packet Header Some representative Data packets are listed in the following Table More packets will arise during implementation Fehler Keine g ltige Verkn pfung Table 29 Data Packets 4 8 5 3 Telemetry Data Frame definition The usable Telemetry Data Frame consists of 24 Bytes according to the REXUS Manual which includes Header Data Frame and Trailer It is generated by the sending thread like described in Section 4 8 3 7 Sending The whole Frame i
140. y To prevent confusions it s necessary to describe the terminology for each sensor 4 10 1 Accelerometer 4 10 1 1 Zero G offset Zero g level offset TyOff describes the deviation of an actual output signal from the ideal output signal if no acceleration is present A sensor in a steady state on a horizontal surface will measure 0 g in X axis and 0 g in Y axis whereas the Z axis will measure 1 g A deviation from ideal value in this case is called Zero g offset LIS331HH pdf p 14 This implies that all values below the explained offset have to be interpreted as no acceleration HX13 CERESS SEDv3 1 12DEC14 doc Page 110 A DLR and SSC coopera 4 10 1 2 Factory calibration The IC interface is factory calibrated for sensitivity So and Zero g level TyOff The trimming values are stored inside the device in a non volatile memory Any time the device is turned on the trimming parameters are downloaded into the registers to be used during the active operation This allows using the device without further calibration LIS331HH pdf p 15 4 10 1 3 CERESS calibration Due the imperfect horizontal alignment of the devices within the RM the attitudes have to be defined by measurements on a horizontal reference plane available at the workshop The devices are configured to a common acceleration vector with same direction normal to the reference plane and length The calibration

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