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1. 59 4 4 5 Structural analysis 5g horizontal 60 EIGGIFONIES IDESIGA e 63 4 5 1 Devices connected to Micro controller 63 4 5 2 ee Be e 66 4 5 3 Stacked Sensor Board 2 SB2 71 EE te El Cl si au sva dee degtk s adsis 75 4 5 5 Heaters Board H Board ccccsccceecceeeeseeeseeeeeeeensees 76 4 5 6 Power control unit POU ennn 79 4 5 7 Motion Mind Motor Controller sss 83 4258 GPS AGA IU s LUOGO 84 Thermal Te AE 85 4 6 1 Thermal model archtecthure 85 46 2 Boundary eelef de AE 87 4 0 0 Se Ie Nara 87 40A E EE 88 4 0 9 GONCIUSIONS iactis nis tiat is sem tuin ti p 91 moli i E 92 4 7 1 Power Line One overview PL1 92 4 2 Power lines two and three overview PL2 PL3 94 4 7 9 Power Control Unit PO 98 4 7 4 Safety issues and SOIUtIONS eeeceeeeseeeeneeeeeeneaees 99 sollware DESIghi 100 4 8 1 Requirement Analysis 100 48 2 Operating lee 100 4 8 3 Software System Architecture n 101 4 84 MissioristaleS a ela 102 499 RE e e Lu Dee 109 490 Totaldata talee 112 Ground Support Equipment ii 114 4 9 1 Ground Station Software 114 4 9 2 GSS Communication Protocols 116 4 9 3 On
2. Uplink Downlink Figure 4 8 7 Bandwidth requirement related to altitude and mission time Note that in figure 4 9 2 bandwidth is shown without any safety factor and assuming the ideal case in which GS command is requested only during Pre Launch phase The peaks in bandwidth correspond to altitude variation when there is a request for change of SW state Page 114 EUROLAUNCH RUN end 80 ec Student Experiment Documentation 4 9 Ground Support Equipment 4 9 4 Ground Station Software All data collected by the on board unit has to be sent to the Ground Station and displayed via HID through a graphical interface These data should include sensory data i e ambient data internal sensory etc and they have to be eventually correlated with some flags reporting the status of the different components of the system The interface in which these data are shown also allows the user to manually set some of the system parameters such as heaters valves pumps and specific instruments on and off GSS will be developed using LabVIEW Figure 4 9 1 GSS interface preliminary design Student Experiment Documentation GS message receive behaviour request active Request timeout counter is reset when new SetValue message is sent Send SetValues Request timeout Yes read Message ConfirmRequest Page 115 EUROLAUNCH A DLR and SSC cooperation StatusUpdate
3. A5 Unibo 1 Project Management Encarnaci n Nani 3 Subsystems 3 1 Power 3 2 Electronics Abramo 3 3 Mechanical 3 4 Ground Station Paolo Igor 3 6 Instruments and Sensors ES Alberto Nani 3 5 Thermal Marco 3 7 Software 3 8 Testing Alice Luca Mattia Svetlozar Figure 3 1 1WBS 2 Documentation 4 Outreach i Nani Alberto Igor 5 Scientific backgroundand Analysis Elisa Erika Page 28 gt E UROLAUNCH and SSC cooperation 3 1 1 Subsystem Tasks 1 1 Project planning 1 2 Review project planning 3 Companies contact for purchasing and technical support feedback Su Preliminary circuits 3 1 2 Power budget 33 Components Selection ordering AIT Figure 3 1 2 Tasks Selection AIT programming 3 2 2 Sensors interface H W 3 2 3 PCB design Student Experiment Documentation 2 1 Receiving documentation from subsystems 2 2 Giving format to the document 2 3 Preparing slides for presentation 3 3 1 Planning structure 3 3 2 CAD 3 3 4 AIT Student Experiment Documentation 3 7 Software Tals a pe X A Sy 7 f Lin i I LY I PA a Fa VT 101 AICE LUCAd IVI all a IIC ALG IVIGLLIOI 3 7 1 Planning S W structure 3 7 2 Program ming sensors interface S W 3 7 3 Testing
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5. Table 4 8 2 Idle state YES YES v set CLIMB tate Figure 4 8 2 Idle state Page 105 Student Experiment Documentation EuroLAUNcH Climb Enter condition GS submits a request for launch or the altitude starts increasing Exit condition Experiment nominal altitude is reached Operating Mode Autonomous GS ACK Description All parameters are monitored sent to GS and logged on the internal SD Once a pre set altitude is reached about 25 km a confirmation is requested to GS and the operating mode is switched to GS ACK If acknowledgment is obtained or a timeout occurs this stage is concluded and the system advances to the following step entering back in Autonomous Mode Ep Communication links ON data Acquire sensory Data loggers ON o veve o i ON OFF On ON ON Write to SD Air lon Counters Particle Counter ON o J C C nication NO communicatio Table 4 8 3 Climb state YES v Set SAMPLING SETUP State Figure 4 8 3 Climb state Page 106 E UROLAUNCH cooperati Sampling setup Student Experiment Documentation Enter condition Experiment nominal altitude is reached Exit condition Valves are open Operating Mode Autonomous Description Before performing the sampling we have to open valves In this stage a loop is used to open valves and check the flow inside the SU pipelines All parameters are monitored sent
6. 4 Outreach 4 1 Website and Twitter Igor 4 2 Facebook Nani 4 3 Journals and other media contacts Nani Figure 3 1 3 Tasks Il 3 2 Schedule Page 29 E UROLAUNCH 3 8 1 Test supervisor e all components needed e performance e results 5 Scientific background and Analysis 5 1 Research and State of Art 5 2 Theoretical concepts Experiment design 5 3 Data Analysis Page 30 EUROLAUNCcH Student Experiment Documentation Once A5 Unibo was selected the tasks were defined in depth Every task is managed by a responsible assigned in order to cover all the parts of the project The Gantt chart see appendix C gives a general estimation of the overall project duration The chart is updated weekly with the project progresses In the meetings every team member explains the work done during the week Every single member is also part of a working sub team where all the information is shared deeply In this way we would like to avoid possible vacancies in the subsystems If any member has to leave the team other two or three members could take care of his her work in order to not stop the progress of the project Sub team 1 Electronics and Power Nani Danilo and Abramo Sub team 2 System Test and Mechanics Nani Paolo and Riccardo Sub Team 3 Software and ground station Alice Luca Mattia Svetlozar and Igor Sub Team 4 Outreach Igor Nani and Riccardo Sub Team 5 Scienti
7. BC337 AQY211EH used for driving the relay load The paralleled output pins of the relays will be connected to the tips of the pinch valves cable GPS level 5V A voltage divider TXB0101 is used in 4 5 16 translator order to change voltage from 3 3V to 5V for power and UART Page 72 EUROLAUNCH Student Experiment Documentation E A Es E E EI E E ESSE E Tx Figure 4 5 11 SB2 schematics pt 1 Page 73 a Student Experiment Documentation EURroLAUNCH 0 Ve D alle x n C P jt I Ei m CH AC i 5 LI Fe g7 Pa A e RH KEE o ND I de d M Figure 4 5 12 SB2 schematics pt 2 Page 74 E UROLAUNCH Student Experiment Documentation Figure 4 5 13 Data Logger schematics Figure 4 5 14 ADC schematic and signal conditioning circuit Page 75 Student Experiment Documentation wssess cooperation Figure 4 5 15 Paralleled solid state relays schematics Il Figure 4 5 16 GPS level translator 4 5 4 Ethernet Shield The Arduino Ethernet Shield allows an Arduino board to connect to E Link It is based on the Wiznet W5100 Ethernet chip that provides a network IP stack capable of both TCP and UDP The Ethernet shield connects to an Arduino board using long wire wrap headers which extend through the shield This keeps the pin layout intact and allows other shields to be
8. Risk analysis i es Albero Assembly and Imegration l ee Alberta Hani loor Danilo PaHaRi Testing i i Rictardo Power i Designing pawer system prebminary circuits REA Danili gus Nani Seleding components power corarel board relays baten KSE Danila Preliminary power budget ERN Danilo Batteries Selection i i E Danilo Batteries ordering i d 3 24 Batteries change of the design selection and ordering i l ua a a ee Barreries delivering ER AIT power i SE Danilo gt Mechanical i Planning design and structure Mass budget CADI Seleding Ordering stmutcture E a a a a a a a a a a NES Paolo Delivering Structure i Assembling Testing Vibration and FEA li i eE Paolo Testing Drop Testi i i i J Electronics Electronic design electing ME Ordermng MC Deliverirg MIC Programming MC Sensor Interface erc Data logging PCA Design i EEE Abramo PCB Order i i 277 Abramo Testing xS Abramo z5oftware l Planning Software design and Structure SN a 2 AliceigerloraMania Definiban of HAL interface and Messages specification I AlicelgerLeca Mania Programming i Peete m m mW Ce Ce gor Lura Matia OCBH control fiw design and Implementation 1 DE Bice igor Luca Mattia Mesion Simulator for testing Experiment i bk AlkcelgorLuca Mania Development and testing of me driver for the Experiment i i ee Albregor Lucx Mattia Whole system Testing i amp i25 Ground Station i Planring EE igor Developing Progra
9. Student Experiment Documentation EuroLAUNCH 16 Project Management Institute Practice Standard for Work 17 Breakdown Structures second Edition Project Management Institute Pennsylvania USA 2006 Misra et al 2002 Page 154 EUROLAUNCH i I Student Experiment Documentation APPENDIX A EXPERIMENT REVIEWS Preliminary Design Review PDR REXUS BEXUS Experiment Preliminary Design Review Flight BX18 Payload Manager tbd Experiment A5 Unibo Location SSC Esrange Space Center Sweden Date 04 Mar 2014 1 Review Board members Andreas Stamminger MORABA Peter Turner MORABA Olle Persson SSC Alex Kinnaird SSC Simon Mawn ZARM Dieter Bischoff ZARM Koen deBeule ESA Lucio Scomaliero ESA Natacha Callens ESA Nora Newie ESA 2 Experiment Team members Encarnacion Serrano Castillo Alberto Sodi Riccardo Lasagni Manghi Igor Gai 3 General Comments Presentation Don t read slides Some text too small Focus on design earlier in presentation Try to get more contact with the audience SED Some content technical data missing it s version 1 0 also for change record put name under issued by include bookmarks keep to SED numbering as in guidelines ch 4 caption your figures and tables Preface missing If information missing or unclear at the moment say tbd All chapters should be filled out Keep the document in English Do not change the format of the cover page Too many blank p
10. 2011 Role of sulphuric acid ammonia and galactic cosmic rays in atmospheric aerosol nucleation Nature 476 7361 429 433 P Palumbo V Della Corte A Rotundi A Ciucci A Aronica J H Brucato L Colangeli F Esposito E Mazzotta Epifani V Mennella H Battaglia G Ferrini F J M Rietmeijer G J Flynn J B Renard J R Stephens E Zona and S Inarta 2008 DUSTER Aerosol collection in the stratosphere Memorie della Societa Astronomica Italiana 79 p 853 Census BEXUS 7 http www stratospheric census org blog test Deshler T M E Hervig C Kr ger D J Hofmann J M Rosen J B Liley 2002 Thirty years of in situ stratospheric aerosol size distribution measurements from Laramie Wyoming 41 N using balloonborne instruments J Geophys Res Atmospheres 108 D5 EuroLaunch BEXUS User Manual 2014 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 REA00 E60 23 June 2010 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 Page 153
11. Figure 4 4 2 Experiment side view The experiment is housed in a frame structure built up of Rexroth 20mm x 20mm grade 6061 aluminium extrusions as shown in Fig 4 4 2 The choice of this frame has been made due to its flexibility for future changes To connect these frames aluminium Cubic connectors model 20 3 by Bosh are being used Figure 4 4 3 Aluminium Extrusion 4 4 1 Instruments Housing assembly IHA The instruments housing is still made by Rexroth aluminium 20x20 profiles covered by aluminium sheet and an insulating layer as shown in Figure 4 4 5 It contains all the main scientific instruments the two AICs the OPC the Pump and the SU with its valves and Sioutas sampler The AICs OPC and SU must have access to the external air in order to gather valuable data therefore they must be placed near the surface wall where holes are created to host the inlets that guarantee the airflow Since the airflow for the OPC is quite low up to a maximum of 3 I m at ground level no exhaust pipe is needed and the incoming air will be directly injected Page 56 d EuroLAUNCH and SSC coopera Student Experiment Documentation inside the IHA where only a small venting hole will be inserted for pressure regulation On the contrary Pump and AIC s will generate significant airflows around 9 l min and 24 l min respectively so in order to avoid internal pressure rise due to small diameter of venting holes and forced conve
12. Test date 30 06 14 completed MEB Results An active control of the airflow is successfully achieved using the MMmc and both the methods have proven to be reliable for flow determination In the first part bag inflation the 9 l min flow was estimated to occur at approximately 2 5 V corresponding to a duty cycle value of 250 while in the second hot wire anemometer at 2 6 V Test type Pump performance at stratospheric conditions Test facility Flight Mechanics laboratory University of Bologna Tested item Pump Test Pump is put inside a vacuum chamber and ambient pressure procedure reduced down to 10 mbar Pump performance is evaluated using a Pitot tube and voltage level is set in so that the flow is exactly 9 l m as requested to optimise samples collection The experiment is repeated at several ambient pressures ranging from 10 to 200 mbar and in the end a performance external pressure voltage for required flow curve is obtained by fitting the results Test date 21 07 14 Completed Test type Pump vibration micro vibration Test facility Alma Space facilities Tested item Pump Test The Pump is turned on and the voltage is set to the expected procedure value that will be used at stratospheric conditions depending on PT2 results Vibrations at several operating voltages close to the selected value are evaluated using a vibration generating plate Page 129 EUROLAUNCH Student Experiment Doc
13. 5 la I ei Figure 4 5 23 PCU Board Grounding strategy The grounding strategy that will be implemented employs a star topology in which each different category of instruments has its own line and all the separate lines gather into a single point junction In fact 4 different kinds of ground are used Power ground e Analogic ground Digital ground Page 83 fe E UROLAUNCH Student Experiment Documentation H Board ground This strategy is used in order to control the reference grounding levels for each instrument and avoid ground loops and reference fluctuations that could degrade output signals from the most precise instruments Figure 4 5 24 Ground scheme 4 5 7 Motion Mind Motor Controller In order to control the voltage given to the brushed DC motor of the 7502 BOXER Pump a motor controller has been selected The variation of flow and voltage of the PUMP is linear Thus some test will be performed in order to know the precise flow at a certain pressure and the input voltage needed in order to obtain that flow Figure 4 5 25 M M Motor Controller Page 84 P EuroLaAuncH i 9 Student Experiment Documentation Table 4 5 4 Motor Controller features Voltage 6 24VDC brushed motors Interface Binary or ASCII control interface RS232 or TTL signal levels 19 2KBPS or 9 6KBPS Control Serial PID based closed loop velocity 16 bit requires Up to 9A continuous current 25A pe
14. GA A EuroLAUNcH Student Experiment Documentation A DLR nd SSC cooperation Show subsystem and component tests in document PT2 is very important test do soon For full verification of operation under flight conditions temperatures tests should be done in a low pressure environment team still looking for institute with thermal vacuum chamber Shock is hard to verify by analysis Drop Test think about ground preparation you don t want hard impact Safety and risk analysis SED chapter 3 5 O O O Add numbers to risks risks of missing fundings budget missing risks of shipping delay of experiment to Esrange missing Launch and operations SED chapter 6 O O O OOo U UGU O Kr 9 e o O Chapter 4 and 6 experiment summary tables must be same team already changed it Team shall be supplied with laser operation guidelines by SSC and be aware of the requirements for handling and shipping Team doesn t want to open laser then considered class 1 this wouldn t need approval of Swedish authorities When how experiment will be turned off not considered yet by team recommendation is to switch off by telecommand before descent If you need advance notice before cut down tell how much Cleaned room but no clean room available ca 1km away from balloon preparation area Specify what kind of clean room you need Discuss with SSC about ultra sonic bath SSC probably doesn t have it Bring your own cleaning sol
15. In this way we can be sure that the Ethernet receive buffer will never become full because it will be regularly flushed by the OBDH Moreover the Arduino platform and libraries we are using have been designed to work in a polling fashion so using interrupts would require us to do a lot of difficult modifications in these already stable and well tested libraries Code Base A Git repository a5system has been deployed at https bitbucket org a5unibo a5system Page 123 EUROLAUNCH Student Experiment Documentation ADR and SSC cooperation 5 EXPERIMENT VERIFICATION AND TESTING Verification and Testing is a fundamental part of the experiment s development and has the objective of assuring that every requirement functional performance design and operational is indeed fulfilled Every person is responsible for testing the subsystem and instruments they have been assigned to but the whole team is responsible for the testing of the system during the integration process The following categories of verification processes have been used T Verification by test Verification by inspection A Verification by analysis or similarity R Verification by review of design o Similarity Test has yet to be performed Test has been performed with positive results Test has been performed but will be repeated Test has been performed with negative results Requirement has been verified through the selected procedure
16. Table 4 9 1 Legend 5 1 Verification Matrix Table 5 1 1 Verification matrix FR1 The experiment shall measure particle size distribution outside the gondola during the whole flight The experiment shall measure particle ion densities outside the gondola during the whole flight R T FR4 The experiment shall measure outside ambient pressure during the whole flight FR5 The experiment should measure outside ambient relative humidity during the whole flight FR3 The experiment should measure outside ambient 4 temperature during the whole flight Page 124 EUROLAUNCcH Student Experiment Documentation FR6 The experiment shall collect aerosol samples drawing R T air from outside the gondola during the floating phase in the stratosphere and make them available for post flight analysis FH The experiment shall keep track of its absolute position T8 R T throughout the flight in order to relate the collected data to a particular height and coordinate FR8 The experiment shall measure the temperature inside 13 14 R T the gondola in order to ensure the operational range of the instruments is not exceeded FR9 The experiment should measure the rate of air flow ii through the pump for the whole duration of sampling design phase FR10 The experiment shall record all the measured quantities T8 into an internal SD FH11 The experiment shall relay to ground all the measured 13 quantiti
17. Team clarified that no hole in gondola floor required nsulation foam should survive low pressure Optical particle counter might be sensitive to vibrations Think about how you can define and verify level of micro vibrations introduced by instruments Electronics and data management SED chapter 4 2 2 4 2 3 4 5 4 7 4 9 Needs more detail for CDR A All subsystems should be identified where they are in the box Justify power consumption do power budget Clarify GPS system that team wants to use some are limited in altitude and speed make sure it can do what you need GPS needs to be open some systems stop at 18km eg Novatel Re think and refine the power system design Thermal SED chapter 4 2 4 amp 4 6 Well identified and complete Much of the analysis should rather be in appendix than main document Often some kind of valve needed for aerosol collection valves have problems with exposure to cold temperatures Software SED chapter 4 8 Make sure software doesn t stop in case no GPS signal is received stopped Well designed but implementation missing so far Overall modes automatic manual ground station are very good Make a decision after a state a real state machine would be good for your experiment then you could switch between states now mainly sequencing Approach with sequence programme might have a lot of delays since you only have sequencing machin
18. To allow synchronous data transmission the SPI bus uses four wires They are called e MOSI Master out Slave in This line carries data from our Arduino to the SPI controlled device s e MISO Master in Slave out This line carries data from the SPI controlled device s back to the Arduino e SS Slave select This line tells the device on the bus we wish to communicate with it Each SPI device needs a unique SS line back to the Arduino e SCK Serial clock Ves Vss SCK MOSI PRESSURE MISO SENSOR SS GND GND In Arduino Mega 2560 the pins dedicated to these four wires are 50 for MISO 51 for MOSI 52 for the SCK and SS is usually choose any other pin for SS When the SS line is activated LOW we have communication between Master Arduino and Slave sensor The data are transmitted one byte each time through the line MOSI and line MISO SCK synchronizes the operations Page 174 EUROLAUNCH A DLR and SEC cooperation Student Experiment Documentation Each byte contains 8 bits that representing a binary number with a value of between zero and 255 So 2 bytes are enough to represent the sensor output In the data transmission we need to know how byte is send at first MSB most significant bit or LSB least significant bit The way to send data is specific for each sensor and datasheet shows how it happens SPI ARDUINO LIBRARY Arduino provides a library for SPI connections The library is lt
19. 1 33 Expernment OD ecllVGS x95 39 m 2 4 i eats e siste ae ian 15 UE eam REEL 15 LAT CONTACT EE 15 142 Tean Members EE 16 2 EXPERIMENT REQUIREMENTS AND CONSTRAINTS 22 2 1 Euncldonaltedgulr moells eege ee EE 22 2 2 Performance Requirements sie edo omes S mapa mec mare cu mes ud 23 2 9 DESIGN Tegultermiellls ege eegene 24 2 4 Operational Requirements enr 25 9 EST EN NUES eege eege 27 3 1 Work Breakdown Structure WBS 27 94 1 SUDSysiemilasks ea 28 9 2 SCI 29 Sd JTACSOUICCS eer tee siete Viste letus uates eu urs o scu eg 31 So Manpower E 31 0 9 BUOOGOL one R E E deste 32 333 EQUGATIONAl SUPHO EE 35 3 34 D le Eer IR ee E 37 3 3 5 Analysis and testing support facilities 38 9 Outreach Approach aos 39 S D RISK REJIS lO snai 39 4 EXPERIMENT DESCRIPTION ME 44 dl e Ten OCD EE 44 22 INCA Saab 46 A Ne Uer inibita 46 4 22 EECC UE 47 43 EXDeFIMENTEOMPONEnssicallalia iaia 48 4 3 1 Optical Particle Counter OPC 48 4 5 2 DISDUOFSGEITI T UMD E 49 4 4 4 5 4 6 4 4 8 4 9 4 3 9 AIFIONGOUNIEIS AICS rn 50 4 34 Samping Wait SW EE 51 Mechanical RTL iii alia 54 4 4 1 Instruments Housing assembly IHA 55 4 4 2 Battery Housing Assembly 58 4 4 3 Electronics housing assembly EHA 58 4 4 4 Structural analysis 10 g vertical
20. 152 Appendix A Experiment REVvieWSs nnne 154 Appendix B Outreach and Media Coverage 161 APPERCXG gna 167 Appendix D Thermal design details sees 170 Appendix E Communication protocols 173 LIST OF TABLES Table 2 1 1 Functional requirements 22 Table 2 2 1 Performance requirements A 23 Table 2 3 1 Design regure ments i 24 Table 2 4 1 Operational requirements 25 Table 3 3 1 Manpower Der WEEK cootra i poetae oo e dee eee eaaet ee ac esee eues 31 Ee ManpoWOer V COM EE 31 RE Tee meer E m Monee nc enn Te 32 Table 3 3 4 ESA as SDOlSOL cssc bl 34 Ee UE ee Ee ege Be d te OrI DEIN DroEUPINDEDiUP EO PEU UPDPL EE De DpLeDrtOS 34 Table 3 5 1 BISK HeglS Ie aaacasa 40 Table 4 3 1 Experiment summary table annaannannannnannnnnannnnnnnnnnnnnnnnnnnnnnnnnnnne 48 Table 43 2 LOAG specilicatio iS incarica 48 Table Eer lee 50 Table 4 4 1 Mechanical Components 54 Table 4 4 2 Structural analysis summary 59 Table 4 5 1 Sensors communications protocol 65 Table 4 5 2 Other devices communications protocol 65 Table 4 5 3 SB1 Sensors and Instruments connected 66 Table 4 5 4 Motor Controller features 84 Table4 5 5 GPS Tealul65 s csdtistevrebe etx n rase Ste vmi vo nma rasis 84 Table 4 6 1 Critical c
21. 4 11 Z axis displacement 4 4 5 Structural analysis 5g horizontal The structure was analysed separately for two types of loads An acceleration load of 5g in the horizontal X axis and horizontal Y axis direction The boundary conditions were the same as the ones considered in the previous section for the 10g vertical analysis except for the direction and magnitude of the load Page 61 EUROLAUNCH Student Experiment Documentation EIN Node WM PE Rats runi etui 2ecc e Pet type Static nodu stus Tress erst zou 347 TOS vor Meses uro 3 452m D 34424 1012 D 255 706 D Me 1078 25008 578 b 2 1369740 1873 smo 15553765T D 12534 1630 ba n 6 265 954 3 320 05 wrest o gt Vini stet 27 000300 9 Figure 4 4 12 Von Mises 5 g x axis Noid urne Sly rene Pool type Dero di URES unm 17030201 13276002 1 0006 29 Figure 4 4 13 X axis displacement Page 62 EUROLAUNCH i RUN end 80 ec Student Experiment Documentation Mode are deuctur bret 2 40 3304 Tee bert Phot true Stat tended sess Spes s Deor conte 2102 von Mos NK 20 444 3220 37307 pecu Jr 20 PAn 2 0 20 297 pez 0 17 761 3780 15 234 200 0 12557 40 161451 1480 75144720 sort 796 d 250 120 3 34462 gt Vids vrengtn 275000 0003 Figure 4 4 14 Von Mises 5g y axis URES mm 22346001 20486001 1 8620 001 1 Eier 1 4866 001 1 302e 001 1 1176 001 5 308e 062 7 4476 0 2 5556 062
22. A5 Unibo Website Et O oh Fi ma wa tetea con x oj o AS Usbo Biegrafia 7 Seen 7 Acwaligar la fer z ng de la p gina D mm frei A8 Gebe is a bk empertront teem selected do tate port at the Ben 15 19 core er e Cesate r 00148 Chur Ve der E 3 uv352 i te eussito RS EM Me jaita We te amuncio agus mode TR fete m A Oferta ente re pert cw d has estado ng wsdr SE015 80019 Rocket Balloo aperi werte for Lover EM Doe sii gt iine a Peano A baian tranalatian of the sta nc rmniaral Conn fra rba udi 8 2 5 A5 Unibo Facebook Ah ks bm hig Tw Die dl ia Page 164 EUROoLAUNCH ae Student Experiment Documentation La 14 Ef M feme ates com c jio SEI D A D n dits mm M ee ee eS EN A A SSS A fg le 4 de T ee 4 bocce et GEOX n o Fota Wi Wor Aldi D Airis em ir 7 Foto AS Unibo Masan Lrastisation of t e she Complete Soon me sino wi 250 De ia abe i Sea Monee Spanish f mo 5g ned L erc a Pre 1 Fotoe 27 cue aart Pagid A5 Uribo halan eration of t e she compu 390 ve sito wi ao De ia abe ie Sparesr to reit CNmTA sto venta AS Unibo una Ho pubbscaro 14 into su Facceboce of aun VACUUM CHAMBER TEST A arie OPCU e me S PE ote wre a 8 2 6 A5 Unibo Twitter la Repubblicat Archivio
23. DESCENT state Figure 4 8 5 Sampling state Page 108 EUROLAUNCH i SOIN Student Experiment Documentation Descent Enter condition GS request or experiment starts descent Exit condition Experiment is turned off Operating Mode Manual Autonomous Description Descent is the last stage of the mission The SU line is closed and all the power lines are manually turned off one at a time using the current limiting switches If no request is received from GS after a certain timeout the experiment switches to autonomous mode and turns off the power lines 4 Start e Communication links Data loggers data Pump OK Write to SD Air lon Counters Particle Counter l BE Table 4 8 6 Descent state communication Stationary ER Figure 4 8 6 Descent state Page 109 EUROLAUNCH Student Experiment Documentation EIN 4 8 5 Datagram structure First of all we need to consider the header of the UDP itself that is 32 byte long A specific data protocol has been developed for A5 Unibo Data packaging is different for the two sides of communication In the following the general datagram structure is shown mer TSN ERO mm Table 4 8 7 Datagram structure CMD ID Command ID Serial 2 byte Unique progressive serial Number number for CMD ID packet counter 2 byte Check for data integrity DATA Data depends on Data bytes CMD ID Command CMD
24. Engineering Science at Bologna University with a project called Non linear control for under actuated systems atmospheric and space applications for attitude control She is the team leader of A5 Unibo selected due to the fact that she has experience in coordinating groups as logistics coordinator and Educational assistant in ESEO European Students Earth Orbiter programme Encarnaci n in responsible for the project management the project planning the communication with sponsors and economical management and part of the outreach of this project She is also system engineer and due to her background she will give support to the electric and electronic subsystems and sensor interfaces and testing Page 17 EUROLAUNCH Student Experiment Documentation ADR and SSC cooperation Alberto Sodi System Engineer He has completed his BSc in Aerospace Engineering at Bologna University with a Thesis in Control Theory entitled Modelling and Control of an Extended Formation with Behavioural Approach He is now earning his MSc in Aerospace Engineering at Bologna University Alberto is responsible for the supervision of the project and the analysis and prevention of each possible risk Igor Gai Ground Station Igor was born in Borgo Maggiore SMR in 1991 He lives in Torraccia in the small Republic of San Marino He graduated in 2013 at University of Bologna in Aerospace Engineering Bachelor s with the thesis Design an
25. Experiment Documentation Tested item Integrated system Test The whole experiment will be integrated and put into a procedure vacuum chamber pressure at 0 01 mbar Pre flight checks and flight sequence will be performed during the lowering of the pressure and once reached vacuum Experiment temperature will be constantly monitored and recorded using several sensors Completed Test type Test facility University of Bologna Tested item Integrated system Test Pump and instruments are turned on to evaluate functionality procedure of electronics and sensors and structural integrity under vibrational environment Completed Test type Thermal pre launch phase simulation Tested item Integrated system Test The whole experiment will be integrated and put into a thermal procedure chamber or refrigerator for at least 2 hours Temperature will be set to 15 C expected temperature during pre launch phase Pre flight checks and sequences are going to be performed while temperature will be constantly monitored and recorded using several sensors Completed Page 135 UROLA Student Experiment Documentation EuroLAuNcn Test type Thermal Tested item Integrated system Test The integrated experiment will be put into a thermal chamber procedure with its temperature set to 40 C or even to a lower one depending on the performance of the facility ideally 80 C The experiment will then be turned on and flight
26. In addition external nodes are subjected to solar flux sky flux albedo flux and planetary flux Page 86 cooperation Student Experiment Documentation Nodes which face with the internal control volume are conductively coupled with internal air The conductivity of the internal air has been computed as follows according to the atmospheric model 3 a 2 64638 x 10 T2 12 T 245 4x10 T In addition internal nodes are mutually coupled by radiation The following figure is a schematic view of the overall architecture with the relevant heat exchange mechanisms convection conduction radiation The following 13 nodes are here represented External surface 1 Inner surface 2 3 4 Internal air up 5 Inner plate up 6 Inner plate down 7 Internal air down 8 Lower plate up 9 Lower plate down 10 Gondola plate 1 1 Batteries 12 Other instruments masses electronics 13 Batteries External Environment Sy Conductive flux Comescli lux Radiative flux External Environment Figure 4 6 1 Thermal Node structure Temperature C Page 87 EUROoLAUNCH Student Experiment Documentation ADR and SSC cooperation 4 6 2 Boundary conditions The temperature of some nodes of the thermal model are known e The temperature of the Planet has been supposed equal to 283 15 K e The temperature of the Sky is about 4 K e The external air temperature is known as a function of the time The following graph
27. Personnel unavailable B 4 PE unexpectedly R19 Components not A A PE available steadily Critical component PE destroyed during testing R20 R21 Not enough funds for the PE experiment R22 Not enough funds for PE travelling and accommodation R23 Conflicts within the group PE R24 Overload of work for a PE team member R25 Lack of expertise C 2 Detailed thermal simulation and testing Include external heaters Detailed thermal testing in vacuum chamber Ensure redundancy and choose priority so that the main mission gains priority Control battery output tension in order to foresee discharge and avoid over exploitation Choose homologate sensors and test them Several sensors put in key positions Ensure all sub systems are covered Recruit back up resources Order components in time Order multiple pieces of low cost components and test critical components early Detailed investigation in case of test failure and possible changes in design Outreach and early fund raising Acceptable risk Fundraising Try mediation Lot of effort in building team spirit Detailed WBS Each system should be assigned to at least two team members Use of BEXUS mentorship Page 43 Student Experiment Documentation Rotana 8 cooperation R26 Schedule is not followed IC 3 PE R27 Delay du
28. a combination of scattering and absorption of radiation The interaction of aerosol particles with the solar radiation depends on their size shape and chemical composition Some components of the aerosol can scatter solar radiation reducing its flux to the Earth s surface and are thus capable of reducing the heating caused by greenhouse gases for example sulphate Other components such as elemental carbon have a continuous absorbing effect that extends to the IR and can contribute to the heating effect The global Radiative forcing caused by this effect the change in solar Irradiance with respect to 1750 results from the balance of positive forcing mainly due to black carbon absorption of solar radiation and a negative forcing of reflecting aerosols and is estimated to be 0 5 Wm 0 40 which means an overall cooling effect 1 The indirect Effect is the role that aerosols exert on radiative balance due to their interaction with clouds In fact cloud formation itself relies on the presence of aerosols that act as nuclei for condensation of water vapour Moreover the abundance of aerosols influences some key features of clouds such as their Albedo and lifetime In a cloud of constant liquid water content a greater number concentration of aerosol particles leads to a greater number of smaller cloud droplets which leads to an enhanced reflection of solar radiation due to increased surface area of the droplets and hence an increased
29. and low dissipation at stratospheric conditions Detailed testing will show whether cooling has to be done Pump is turned off before descent to keep the working time as low as possible and to avoid the suction of debris or water after the landing that could cause damage to the pump itself Page 139 Student Experiment Documentation Routan 85 cooperation External Piping material inlet and outlet ports of the SU and TSP inlet elements of the OPC are coming out of the Gondola and could be accidentally hit while moving the experiment A clearly visible HBF cover is added to identify these two elements 6 1 3 Electrical Interfaces Table 6 1 1 Electrical interfaces applicable to BEXUS BEXUS Electrical Interfaces E Link Interface E Link required Yes Power system Gondola power required Yes Peak power or current consumption 29 41W uu Average power or current consumption 29 41 W Power system Experiment includes batteries Yes Eum BR Capacity 1 battery 6 8 Ah Voltage 1 battery 3 75 V A safety factor of 1 5 has been applied Average and peak power are the same cause we estimated power on for 7 hours flight duration without descending phase 6 2 Preparation and Test Activities at Esrange 6 2 1 Launch site requirements At Esrange Space Centre we will need the following e Mechanical tools e Electrical tools e Regulated DC power supply with output up to 28V and 6A Two separate
30. as Arduino is used implementation of the software will be developed in C C The ground segment software is developed using LabVIEW 4 8 3 Software System Architecture Subjects expected in the system e OBDH the A5 experiment deployed on gondola e GS the Ground station Messages exchanged between subjects SetValues cmd 1 Ack cmd 2 ConfirmRequest cmd 3 ConfirmResponse cmd 4 StatusUpdate cmd 5 Interactions between subjects of the systems are better expressed using particular keyword to describe them e SendUpdate OBDH dispatches StatusUpdate to GS e SendCmd GS asks SetValues to OBDH OBDH confirms Ack message e AskForConfirm OBDH requires ConfirmRequest to GS GS replies with ConfirmResponse Where the semantic of the highlighted keyword is e Dispatch refers to a one to one asynchronous communication where the sender expects the message to be received by recipient Page 102 EUROLAUNCcH Student Experiment Documentation e Ask refers to a one to one asynchronous communication where the sender expects to receive a message received confirmation by the application layer of the recipient e Require refers to a one to one asynchronous communication where the sender expects a reply message from the recipient 4 8 4 Mission States The mission is performed in a series of following steps To correctly perform them the software itself is divided into a certain number of states Each state r
31. calling the function the address device of 7 bit has to be setted The library is Wire h and the functions that we use are Wire begin activate I C bus Page 176 EUROLAUNCcH Student Experiment Documentation Wire requestFrom address num_bytes used by the master to request a certain number of bytes from a slave device Wire available returns the number of bytes for retrieval with Wire read Wire read reads a byte that was transmitted from a slave device to a master after a call to requestFrom ONE WIRE One Wire is a digital serial communication that uses only one line to transfer data One Wire sensor uses any din digital pin of Arduino DIGITAL PIN EIN sss ONE WIRE LIBRARY OneWire myWire pin create the OneWire object using a specific pin myWire search addrArray Search for the next device The addrArray is an 8 byte array If a device is found addrArray is filled with the device s address and true is returned If no more devices are found false is returned myWire reset search begin a new search The next use of search will begin at the first device myWire reset reset the 1 wire bus Usually this is needed before communicating with any device myWire select addrArray select a device based on its address After a reset this is needed to choose which device you will use and then all communication will be with that device until another reset myWire w
32. cloud albedo This effect is called Cloud Albedo effect or Twomey effect The second indirect effect relates to the lifetime of clouds An increase in the number concentration of aerosol particles leads to a greater number of smaller cloud droplets and hence reduces the precipitation efficiency of the cloud as smaller droplets take longer to grow to a size needed to precipitate out This increases the lifetime of the cloud and hence also its reflectivity over time 2 These indirect effects are difficult to evaluate since the microphysical processes involved in cloud formation are not completely understood Page 13 l EuroLAUNcH Student Experiment Documentation ees However a net radiative forcing is estimated to be around 0 70 Wm 1 1 0 4 and from this result it is clear that there is still a big uncertainty in the estimation of this effect Another factor that is believed to affect cloud formation is the ionization of atmospheric particles caused by Cosmic Rays This proposal stems from an observed correlation between cosmic ray intensity and Earth s average cloud cover over the course of one solar cycle that was first reported by Svensmark and Friis Christensen in 1997 3 The observed variation of low clouds by about 1 7 absolute corresponds to a change in Earth s radiation budget of about 1 Wm between solar maximum and minimum which is highly significant when compared for example with the estimated radiativ
33. cogrira per dew pesas dw org Lg 8 2 7 A5 Unibo La Repubblica Page 165 Student Experiment Documentation EuroLAUNcH her woe zer incontri e imizialive Spod ri Agenda event imm wider hae gat ben Pre y Adma Rubriche T RAI Leti LOW TA Ot Malin va sais te howe lerici wu ricerca AS hoce mento somiiku selezionato del ESA ud amp aM bd WW ing rime pias AS l esperimento scientifico selezionato dall ESA l team di Ingegneria serospaziale cel Campus di Forl stato selezionato da l Agenzia Sparale Luropes per far volare I propno esperimento su un pallone serostetico in Svena Mdeo st Yearbook ly vrenare in mostra s Gana Cr sting Act on docente Lindbo ta ures honor 5 caus tied Lob x rh Tecnica d ty hase le Rologna Business School per formare manager interrarional age rola Spariade Furapea FSA ha asiszianano allnnerma de pragramma Rewis ewur Mesperimiesto dion pruppo d Dderi de Pmwern di Dolegna cos Base al Campes di Fer CI sidente marti de Corso di lares magistrate in Ingegneria Aecspadiale si stanno darato da fare per attinaro d pragetto e se mor o sarareto fires ottobre putranto far volare us pal oe aerostabon cor uti volume nar a 7000 mem cuti rufficie didattico dell ESA che promuove H progetto yg Jos arc lae i avide Learn sonno prsssrcare un empero m een c imbarcare la strurmertarione di mimurarione e anaba c a borio a an rag26 son do Rees 6 un moneda un plane sorda B
34. electrons Secondary electrons can be formed by collisions with the nucleus where substantial energy loss occurs or by the ejection of loosely bound electrons from the sample atoms The energy of secondary electrons is typically 50 eV or less To create an SEM image the incident electron beam is scanned in a raster pattern across the sample s surface The emitted electrons are detected for each position in the scanned area by an electron detector The intensity of the emitted electron signal is displayed as Page 146 EUROLAUNCH i SOIN Student Experiment Documentation brightness on a cathode ray tube CRT By synchronizing the CRT scan to that of the scan of the incident electron beam the CRT display represents the morphology of the sample surface area scanned by the beam Magnification of the CRT image is the ratio of the image display size to the sample area scanned by the electron beam The SEM uses a focused beam of high energy electrons to generate a variety of signals at the surface of solid specimens The signals that derive from electron sample interactions reveal information about the sample including external morphology texture chemical composition and crystalline structure and orientation of materials making up the sample The SEM is also capable of performing analyses of selected point locations on the sample this approach is especially useful in qualitatively or semi quantitative determining chemical composition using Energy
35. flight time The experiment control volume is filled with air at pressure and temperature variable with the altitude it is a 0 36 0 45 0 40 mm cube thermally insulated with respect to the external environment by means of 20 mm thickness polyurethane foam characterized by a conductivity of 0 023 W mK and by the following thermal optical properties on both sides a 0 12 0 035 on the external surface a multi layer aluminized film is applied Physical properties of air have been deduced by the standard model of air The experiment is placed on a 1 5 mm thickness Aluminum plate with a conductivity of 175 W mK and conductively coupled with the gondola deck which is approximated as a 20 mm thickness Aluminum plate One internal node represent the air inside the box in order to evaluate the temperatures that each component can reach during the flight and so helping us to decide what kind of heating to use for the critical instruments The plates and the insulating wall have been simulated as couples of diffusive nodes in order to take into account the conduction through the material Nodes which are exposed to the external environment are thermally coupled with the sky background by radiation and external air by convection sky background and external air have been simulated as boundary nodes oince the convection coefficient is unknown a sensitivity analysis has been performed varying the convection coefficient value from 1 up to 9 W m K
36. for the negative ions These operate in the following way oustide air is pulled inside the instrument by a fan at a rate of 24 l min and as it passes through the meter negative or positive ions are taken from the flowing air and deposited onto an internal collector Figure 4 3 3 AIC plate by a 10V voltage difference between the plate and the external walls The number of elementary charges per second that hit the collector is found by measuring the voltage of the collector plate which is connected to ground through a 10 G ohm resistor In table 4 3 3 some of the key features of the AIC s are listed Table 4 3 3 AIC specifications 0 to 200K ions cm 0 to 2 V output 1 to 100 mV Moise 10 ions cc 2s averaging Operating Range 50 to 50 C 10 to 14 VDC Fan On 45 MA typical Fan Off 4 mA typical Weight 305 g Size 160x100x55 mm As mentioned in section 3 5 there are some effects that can interfere with the ion readings and should be avoided e he presence of static charges near the AIC s should be avoided since an excess of charges near the top slot would cause a lower reading since ions would be deflected away same charge or attracted towards the inlet instead of the collector plate opposite charge In order to avoid this effect the AIC case which is coated by a conductive material has to be Page 51 EUROoLAUNCH Student Experiment Documentation ADR and SSC cooperation connected
37. in case of failure of ST1 R T some devices JJ J to the sample holder to monitor the environment during SR2 SW shall not crash in case of error Handle failure a SR4 SW shall restart in case of failure not be compromised ST1 in case of power loss SR7 SW shall correctly store all collected data SR8 SW shall not overwrite or corrupt stored data NEN SW shall be redundant in the determination of ST2 R T descending phase start meanly rely both on GPS and pressure data to determine descending rate but also CD JJ co request GS ACK JJ SR10 SW shall comply with E Link and TCP IP specification SR11 SW shall not fail in case of GS connection failure and ST1 manage to reconnect SI SH12 SW shall not to be crashed by GS commands error R T JJ Page 127 E UROLAUNCH Student Experiment Documentation Rotana 85 cooperation SR13 GSS shall receive display and log data i CORTO SH14 GSS shall allow user to set commands to on board R T software OR1 The experiment shall be able to function autonomously 18 R T in the event that contact with Ground is lost Piping materials and parts of the instruments coming out of the experiment shall be protected with a remove before flight cover Remove before flight cover shall be removed before IT flight The experiment shall autonomously open the pinch T8 R T valves and unseal the sampling filter once reached the nominal altitude in the
38. is procedure performed giving false GPS signals in order to switch between the different states Data is collected onto the internal SD and sent to ground station through e link to allow for an evaluation of the instruments performance The experiment is run for the whole time duration to verify batteries performance Completed Page 137 EUROLAUNCH Student Experiment Documentation ADR and SSC cooperation Test type Pressure sensor test Test facility University of Bologna Tested item Pressure sensor and ECU Test The pressure sensor is mounted on the ECU and put into a procedure vacuum chamber ECU is turned on and barometric measurements are recorded while the ambient pressure is reduced down to 5 mbar Desired operational range has to be reached Test date 07 07 14 Completed Results Pressure sensor s desired operational range is reached Testtype Sensors acquisition Test facility Flight Mechanics laboratory Tested item All the sensors Temperature Humidity Pressure GPS OPC and AIC s Test After the correct working of each single sensor has been procedure tested the sensors are connected all together to Arduino to check for any incompatibility in the communication protocols SPI I2C UART and Serial Hardware failure is simulated by physically disconnecting one device at a time without changing the operating software Completed 5 3 Test Results Detailed procedures and results for eac
39. reliability Table 4 7 4 PL1 overview Current Energy Pi ASIA 5612W 2389 Wh A5 LN pack 21 A max C NN for tci MN max 306 m the three series in parallel Table 4 7 5 PL2 PL3 overview Current Energy PL2 PL2 PL3 1 1295A 00 A 29 41 W 41 W 20585 Wh 85 Wh liso NN supply 2 nn 56 e 364 bereien two batteries Page 98 E UROLAUNCH Student Experiment Documentation 4 7 3 Power Control Unit PCU Figure 4 7 4 shows a logical scheme of the PCU Black arrows represent the power lines while blue arrow represents the serial communication used to regulate ESC Motion Moreover the Pinch Valves supply passes through the electronics where it is controlled by a relay Speed pump regulator Pinch Valves BE Switch Air lon Counter Air lon Counter Particle Counter VR12 VR12 CL amp Switch 28V gondola 28V gondola CL amp Switch VR 7 2 Heaters Board Supply Figure 4 7 4 Logical scheme of the PCU board e Ad battery pack provides 15 V and needs to be regulated down to 12V for the pinch valves while ESC Motion Mind motor controller will regulate the voltage supply for the pump The gondola batteries which supply the instruments and electronics provide 28 V and need to be regulated down to 12V for both AICs 7 2V for OPC 5V for electronic components and 3 3V for GPS and pressure sensor Voltage Regulators P
40. sequence will be performed for the whole duration of flight plus an extra of 15 minutes Temperatures will be monitored and recorded in different critical points of the experiment Also functionality of the instruments will be checked by analysing the gathered data Completed Test type Water Landing Test facility University of Bologna Tested item Tubing with sealing valves Test sealed tube containing an absorbing material is submerged procedure in water for 1 day The material is inspected to see if the sealing valves have worked properly Completed Test type Random Vibration Test facility Alma Space facilities Tested item Mechanical structure Test otructure is filled with a dummy load and put on a plate at the procedure Alma Space facilities that is able to generate random vibrations Structure integrity is checked afterwards by visual inspection Page 136 EUROLAUNCH i A DLR end SEC cooperation Student Experiment Documentation Completed Test type Drop Test Test facility University of Bologna Tested item Mechanical structure Test otructure is filled with a dummy load and dropped from 3 procedure metres height Structural integrity is checked by visual inspection while the load factor is measured using an accelerometer Completed Test type Flight simulation Test facility University of Bologna Tested item Integrated system Test A complete flight sequence including pre launch checks
41. shows the temperature profile versus time obtained during BEXUS10 flight which has been taken as reference 10 i H 0 2000 4000 6000 8000 10000 12000 14000 16000 18000 20000 D e eT n ___6 wuo ele N e LA eo b 50 4 dl cx e le 70 80 Time s 4 6 3 Solution The temperature of the nodes results from a balance between thermal inputs which cause an increase of the temperature and thermal outputs which cause a drop of the temperature The thermal balance in steady state condition is given by the following relation which contains the terms described above taking into account the only contribution due to the radiation wo weno paa wr V In fact the thermal regime is determined also by the conductive link between adjacent nodes and T T i dq cond i dA A Where 4 is the thermal conductivity of the material s is the distance between the element s centre of mass T and T are the temperatures of the adjacent nodes and dA is the contact area between elements Page 88 EUROLAUNCcH Student Experiment Documentation The thermal balance in steady state condition which takes into account both radiative and conductive contribution is Qsuw Anno Apraner T Isky 2 Aa cond 0 l Finally transient analysis is performed considering an additional term which represents the internal energy variation in time Th
42. stage of project SSC makes balloon GPS data available to all teams post flight 5 Internal Panel Discussion Summary of main actions for the experiment team o O O O Power system needs a different design capacity problems Redundancy drives design not good reconsider More system level concept redundancy and power concept to be shown Mechanical some information lackinc CDR Result conditional pass SEDv2 1 due on May 28 2014 Page 160 EUROLAUNCcH Student Experiment Documentation Integration Progress Review IPR Experiment Acceptance Review EAR Page 161 EUROLAUNCH Student Experiment Documentation EIN APPENDIX B OUTREACH AND MEDIA COVERAGE Choice of Logo A5 Unibo Logo is the signature of the experiment and one of the most valuable assets because it is a single element that symbolizes the whole project We tried to design it simple and unique A5 Unibo decided to choose the circular geometry as REXUS BEXUS Logo and as most of previous experiments of the program We decided to choose a single icon or image to represent the whole experiment a cloud This regards our primary objective that is to study the correlation between different atmospheric parameters in order to better understand the clouds formation and its relation with climate change We chose blue and grey to model a real sky and then we choose red for the frame and yellow for the name because they are very bright colours th
43. system to stop is then disabled Communication with GS E Link communication is constantly monitored especially when the OBDH in set in Manual Mode When A5 Unibo is set in Manual Mode it acts according to Page 122 EUROLAUNCcH Student Experiment Documentation the instructions from GS so in case of connection loss the OBDH can stall while waiting from a GS reply Manual Mode Override function is necessary to automatically switch OBDH to Autonomous Mode when E Link connection is lost In order to detect this communication loss the GS periodically sends heartbeat packets when in Manual Mode If the OBDH does not see a heartbeat packet for a long time it switches back to Automatic Mode Critical Data transmission A Time Stamp field is inserted at the end of critical data packet in order to associate data with the correct time For the OBDH we decided not to use hardware interrupts The various tasks are scheduled to be executed in a single execution flow This choice has been done on the following reasons e Our system can work well and respect all timing constraints also without using interrupts e By not using interrupts we avoid the risk of failures caused by coding errors arising from the complexity of managing concurrency e All the tasks that are scheduled to run in the single execution flow will be written in a way so that they are bound to end in a fixed maximum amount of time so they cannot halt the system
44. to GS and logged on the internal SD Communication links Somos ON Data loggers ial Valves Pump Pine o ton Couns N Perle Courier N Table 4 8 4 Sampling setup state a Start T Open valves Y Acquire sensory data Write to SD EMEN GS communication NO YES v Set SAMPLING State Figure 4 8 4 Sampling setup state Page 107 Student Experiment Documentation EuroLAUNCH Sampling Enter condition Valves are open Exit condition GS request for experiment termination or experiment starts descending Operating Mode Autonomous GS ACK Description Once the expected altitude is reached the sampling shall begin Valves are now open and air is flowing through SIOUTAS sampler All parameters are monitored sent to GS and logged on the internal SD Some minutes before the cut off a command is given by GS Nonetheless also an autonomous function is implemented to close valves Using GPS the descending rate is calculated When it dramatically increases descending speed higher than 5 m s an alert appears on GS interface and the operating mode is switched to GS ACK If acknowledgment is obtained or timeout occurs this stage is concluded and the system advances to the following step entering again in Autonomous Mode a Start D Y SCH i N Table 4 8 5 Sampling state Descent Close valves Y se
45. to ground with the supplied long cord Moreover any plastic material used in the structure will be selected also considering its charging properties e The inside of the meter can become dusty In that case the dust can create a slightly electrically conducting bridge between the internal collector plate and the metal chamber which surrounds the collector plate causing an increase in the offset value for output voltage In order to mitigate these effects some pre flight checks have to be performed to verify the correct grounding and cleaning has to be done on a regular basis and especially before mounting the instruments in the gondola See chapter 6 for pre flight procedures 4 3 4 Sampling Unit SU For the sample collection we chose to use a SIOUTAS Impactor It is a device that efficiently samples ultrafine fine and coarse gt 2 5 um particles simultaneously When aerosol impinges on or flows around a surface the air is diverted by the surface but if the particles are sufficiently large or dense the inertia can cause them to impact on the surface where they may then be retained The SIOUTAS sampler is optimized for a flow rate of 9 l min perfectly achievable with the BOXER pump through an active control of the magnet brushed motor Figure 4 3 4 Sioutas Impactor Choice of device To get a meaningful detection the mass of the caught particles needs to make up at least 1 ppb of the mass of the filter The relative ma
46. will be connected to the E Link unit using a cable provided by EuroLaunch During testing the Ground station will be directly connected with a normal RJ45 Ethernet jack Figure 4 2 4 RJF21B socket Figure 4 2 3 RJF21B mounting Page 48 EUROLAUNCH I Student Experiment Documentation 4 3 Experiment components Table 4 3 1 Experiment summary table Experiment mass in kg Experiment dimensions in m 450mm 445mm 412mm Experiment footprint area in m Experiment volume in m Experiment expected COG centre 300mm x axis of gravity position 2 0mm y axis 210mm z axis 4 3 1 Optical Particle Counter OPC Overview Our initial choice for the particles size measurements was to use the 212 profiler OPC from Met one Instruments but after the vacuum chamber test OPCT2 it was shown that this instrument gives a reliable output only for pressures down to 500 mbar and since we already have it it will be considered only as a backup solution in case of any trouble with the new model Our choice is now to use the LOAC instrument from Meteo Modem which is already involved in several research programs of atmospheric studies and has proved to work in high altitude balloons This instrument is capable of measuring aerosols distributions in 20 size classes between 0 3 and 50 um and thanks to measurements of light scattering at two different angles one sensitive and one insensitive to particles shape is c
47. 0 84 21 9 153 59 2 A 4W Wh Table 4 7 3 Power line three PL3 Total Total Total ong e oes ee poner V TGR 0 48 0 04 0 48 3 36 Page 95 EuROLAUNCH Student Experiment Documentation Rta s amp t cooperation Ethernet Shield 0 5W 0 1A o 5 3 5 Wh 574 Le irene x RIA UR Air lon Counter 0 045 A 0 Sg 0 i 1 a 1 56 Wh P sensor 336 E OEREJEJ m T sensor Lj 20 140 H sensor 0 E 84 HIH9120 Ka mWh Valves 75 22 5 12V DE 112 SWAD fee me AE iiam HERD E EIE EE Communication 0 3 E HE w pem SIE MIC2S49A 49A 90 uA CIEN v e e SE L 7 5 5 mA 7 5 52 5 KCN mW mW mWh uM S Not NE valued on 10 ms every 10 s Figure 4 7 2 shows the power consumption profile over time for PL2 and PL3 The total power consumption has an almost constant value of 29 41 W while the total energy spent is approximately 205 85 Wh Since these values exceed the performance of a single battery pack of the Gondola supply we asked for two battery packs which will be put in parallel through the PCU Page 96 EUROLAUNCH A DLR and SEC cooperation Student Experiment Documentation PL PL3 3 Total i Power W o 1 2 3 4 5 6 T e Timeline hours Figure 4 7 2 Consumption profile for PL2 and PL3 1 1 4 A5 Battery Pack A5 battery pack consists of three series of four MP 176065 Integration SAFT capable of providing 15 V 306 Wh nominal energy and 20 4 Ah of capacity Thi
48. 1 1 Electrical interfaces applicable to BEXUS 139 Table 6 3 1 Pre flight operations 141 Table 6 3 2 Flight sequence nnn 141 LIST OF FIGURES FOUG SFIN B ET iii 27 FOUG Te TASKS em cm 28 FOUG S To TASKS Mosor E 29 Figure 4 1 1 Experiment overview nnns 44 Figure 4 1 2 Main scientific msirumente ne 45 Figure 4 2 1 Experiment mounting in M EGON gondola 46 Figure 4 2 2 Mounting detail sc ieri 47 Figure 4d 2 5 RJE2TB MOUNINO DEE 47 Figure 4 2 4 ee ER 47 FONE SR EE 48 Foure 43 2 BOXerF ENEE EIERE 49 FOULA E AO 50 EIgure 4 3 4 Sloutas IMPACTO uvuiesas uid cus d ud eed tb dava Ed uva Sed usas Ed ved Ud rutas 51 POUCA S TONOVE aaa 53 Figure 4 4 1 Experiment front view 54 Figure 4 4 2 Experiment side VIEW 55 Figure 4 4 3 Aluminium Extrusion i 55 Figure 4 4 4 Instruments Housing Assembly top VIEW 56 Figure 4 4 5 Rubber thickness detail 56 Figure 4 4 6 SU mounting detail esens n 57 Figure 4 4 7 AIC exhaust Slit 57 Figure 4 4 8 Battery and Electronic housing assemblies 58 Figure 4 4 9 Von Mises 10 g vertical 60 Figure 4 4 10 Z axis dsplacement 60 Figure 4 4 11 Von Mises 5 g x axis enne 61 Figure 4 4 12 X axis deplacement i 61 Figure 4 4 13 Von Mises 5g y AXIS c ccccccsececeseecece
49. 37238 002 9520 002 1 06e 60 Figure 4 4 15 Y axis displacement Page 63 a Student Experiment Documentation EURroLAUNCH 4 5 Electronics Design A5 Unibo will use an Arduino MEGA 2560 microcontroller for data acquisition from sensors and instruments and to control the electro valves that will open the flow stream needed for taking the aerosol samples Fig 4 5 1 shows the Arduino MEGA 2560 microcontroller 4 5 1 Devices connected to Micro controller ARDUINO Mega Figure 4 5 1 Devices connected to Arduino Page 64 EuroLAuNcH Student Experiment Documentation EM Faq INA em E dex da eoa e LEE 9 oo L la Lil IL E C oU dii bi Riti I MINNI Ka GND C Figure 4 5 2 Arduino Mega and Pinning scheme Fig 4 5 1 shows a diagram of the whole electronics interfaces with the power supply red lines the communications between the different sensors and instruments with the microcontroller blue arrows and switches for heater boards and relays green lines The sensors and instruments used to achieve the goals of the experiment use different ways to send data at the microcontroller The communication protocols see APPENDIX F that Arduino Mega 2560 uses are e SPI e C Page 65 Student Experiment Documentation wsssess cooperation e ONE WIRE e UART Table 4 5 1 Sensors communications protocol Sensors Protocol Pressur
50. 543 3 4 424 sal 390543 83245 Ey 390543 374 477 From the scientific point of view Professor Laura Tositti from Department of Environmental Chemistry of the University of Bologna will offer theoretical support and support for the post flight analysis Page 36 EuroLAuncH gt TS Student Experiment Documentation Laura Tositti Associate Professor CHIM 12 CHIMICA DELL AMBIENTE E DEI BENI CULTURALI CHIM 12 http www unibo it faculty laura tositti 39 051 20 9 9488 Dipartimento di Chimica Giacomo Ciamician Via Selmi 2 Bologna Goto map Other Contacts e my 390512099456 E E a 39 051 20 9 9531 A5 Unibo would like to thank all the experts that offer their kind help in order to support the team From ESTEC Figure 3 3 4 Nickolaos Panagiotopoulos Page 37 Student Experiment Documentation EUROLAUNCH From Forl Figure 3 3 5 Support from Forl 3 3 4 Financial support Supervisors Fabrizio Giulietti Research Group funds will cover the experiment costs in case of no external sponsorship ESA is A5 Unibo s Sponsor for Travel and Accommodation for four team members At the moment we have these sponsors for the project Air lon Counter ALPHALAB Inc American manufacturer of electronic measuring devices They offer Gauss meters electromagnetic field meters measured by the strength and polarity of the electromagnetic field air ion counters number of ions per cu
51. A taking advantage of the simplicity of their structure Two holes will be cut in the front aluminium panel to host the inlet slots of the two AlCs To facilitate the expulsion of drawn air two metal slits are inserted at the exhaust hole Figure 4 4 7 AIC exhaust slit Page 58 P E UROLAUNCH A DLR and SSC coope Student Experiment Documentation 4 4 2 Battery Housing Assembly The battery housing is made by Rexroth aluminium 20x20 profiles covered by aluminium sheet and an insulating layer as shown in figure 4 4 10 The BHA shares the same support frame with the EHA but the two are separated by a sliding aluminium plate that A vertical plate installed on one side to facilitate the mounting of the power line and e link connectors p Figure 4 4 8 Battery and Electronic housing assemblies 4 4 3 Electronics housing assembly EHA It contains the Arduino micro controller with its stacked boards the PCU board the Heater s board and the Motion Mind motor controller As already stated it shares the support frame with the BHA from which it is divided by a sliding aluminium plate A central hole connects the EHA with the IHA and allows for the passage of cables and connections Figure 4 4 9 EHA detail Page 59 EUROLAUNCH Student Experiment Documentation A DLR and SSC cooperation 4 4 4 Structural analysis 10 g vertical A static structural analysis was performed for the A5 assembly considering a dow
52. Analysis Elisa was born in Chiaravalle Ancona in 1989 she took her bachelor degree in Environmental Science at the University of Bologna in 2012 During a stage in the INGV National Institute of Geophysics and Volcanology in Bologna she wrote her thesis titled Interaction between hurricanes and phytoplankton blooms in the Atlantic Ocean Now she s earning her Master Degree in Science and nature management at the University of Bologna In A5 she will be responsible for the post flight data analysis of the collected sample Riccardo Lasagni Manghi Verification and Testing Riccardo was born in Reggio Emilia in 1990 He took his Bachelor degree in Astronomy at the University of Bologna with his final thesis on Virial Theorem and its Astrophysics applications During summer of 2013 he attended the Alpbach Summer School organized by ESA where he took active part in the development of the Pacman mission After this experience he decided to apply for the Master degree in Aerospace Engineering in Bologna where he is currently studying In A5 he will be responsible for the writing of the SED documentation and for the Testing and Verification process Page 20 UROLAUNCH Eurok mi Student Experiment Documentation Erika Brattich Data Analysis Erika was born in Genova Italy in 1984 Nowadays she lives in a small town called Ravenna in the North East of Italy 80 km far away from Bo
53. Board Data Handling OBDH 117 49 4 Failure detecllon xui eibi deeg deg deeg dee 121 EXPERIMENT VERIFICATION AND TESTING ossssieseneeeeeeneenennennnn 123 ee Oe de in ft E 123 92 AES PIIN sea 127 321 sPUImpD TOSIS PT R 127 5 2 2 OPC performance testS 129 5 2 3 Air lon Counter tests ACTA 130 5 24 Sotware E E EE 131 52 09 General Tesis A DE REN 133 0 9 Jee Egger eegene 137 6 LAUNCH CAMPAIGN PREPARAT TION eee 138 6 1 Input for the Campaign Flight Requirement Plans 138 6 1 1 Dimensions and Mass annoannennannennnennnnnnnnnnnonnnnrnnnnnne 138 Sm ME CAE E I DOT 138 Biles JEle clrical MICH AGES ausis afi lira 139 6 2 Preparation and Test Activities at Esrange 139 6 2 1 Launch site requirements s ssnesseeneeneereeerrerrrsrrenr ree 139 0 2 2 e ul e El 140 6 23 Preparato no t Sissa 140 6 3 Timeline for Countdown and Flight 141 60 4 Post Fllght e cete Re e asta 143 6S SVSIEM e 143 7 DATA ANALYSIS AND RESULTS 145 1 1 Data ANALYSIS FAN ees 145 7 1 1 X Atmospheric data analySiS rnn 145 Vla ample analysis tee ett eet eebe ee Cat 145 7 2 EIERE ege 149 22 0 149 fL MESSONS d 25025cdpoohcxi AE 149 8 ABBREVIATIONS AND REFEERENGES iii 150 E Hiel e alla 150 Ou EE
54. Dispersive detectors crystalline structure and crystal orientations using Electron Backscatter Diffraction detectors The SEM EDS laboratory at Biological Environmental and Geological Sciences at the Bologna University is equipped with a SEM Philips 515 with a BS detector with high efficiency It has a video card for digital acquisition of images IMAGESLAVE The instrument is an EDAX DX 4 for energy dispersive microanalysis and the apparatus for the preparation of samples is formed by a carbon coater and sputter coater Figure 7 1 1 SEM setup at BIGEA laboratory PIXE Particle Induced X ray Emission or Proton Induced X ray Emission PIXE is a powerful yet not destructive elemental analysis technique used in the determination of the elemental make up of a material or sample This technique involves the excitation of the atoms in the sample to produce characteristic X ray and a means of detection The X ray spectrum is initiated by irradiating the Page 147 Student Experiment Documentation EuroLAuNcH sample with a proton beam produced from pure Hydrogen by a Van der Graaf accelerator When a sample is irradiated with the proton beam the protons interact with the electrons to create inner shell vacancies in the atoms present in the sample material The energies of the X rays which are emitted when these vacancies are filled again are characteristic of the elements from which they originate The number of X rays of a cert
55. EUROLAUNCH A DLR and SSC cooperation SED Student Experiment Documentation Document ID BX18_A5Unibo_SEDv3 0_07July14 Mission BEXUS 18 Team Name A5 Unibo Experiment Title Advanced Atmospheric Aerosol Acquisition and Analysis Team Leader Encarnaci n Serrano Castillo Team members Alberto Sodi Igor Gai Riccardo Lasagni Manghi Paolo Lombardi Danilo Boccadamo Alice Zaccone Erika Brattich Elisa Luconi Marco Didon Abramo Ditaranto Mattia Baldani Luca Mella Version Issue Date Document Type 3 0 07 July 2014 IPR Valid from 07 July 2014 Issued by Riccardo Lasagni Manghi Approved by Fabrizio Giulietti CHANGE RECORD Version _ Date Changed chapter 2013 12 11 New Version Blank Book 2013 2014 02 17 all PDR Sections PDR corrected Preface List of Tables List of Figures 1 3 2 1 2 2 2 3 2 4 J 1 3 2 3 9 9 9 4 1 4 2 4 3 By ls Ore 6 all 2014 04 11 1 4 2 d e d 9 d 4 1 4 2 4 3 4 4 4 5 4 6 4 4 8 4 9 2 8 0 9 6 1 6 2 6 3 2014 05 28 CDR corrected 2 minor changes 3 3 3 5 4 2 434 4 4 minor changes 4 5 4 7 4 8 4 9 5 minor changes 6 2014 07 07 142 4 3 4 4 4 4 5 PCB s 5 2 CONTENTS CHANGE REGO RE 3 LS OR re ences m 7 LSFOFFIGURES aaa 8 PREFACE M LL LIA LIL SARAS aaa 10 11545 GE 11 1 INTRODUC TION m 12 1 1 Scientific Technical Background 12 1 2 Experiment CONCEP EE 14
56. EUROLAUNCcH Student Experiment Documentation 4 7 Power System The system is divided into three different power lines e PL1 provides pump and pinch valves which have the highest power consumption e PL2 feeds heaters and OPC e PL3 feeds all the other instruments and the electronics The power is provided by two different sources e BEXUS batteries that provide power to PL2 and PL3 In particular two batteries will be put in parallel through the power board e Ab battery pack which provides power to PL 1 and is designed to match the high power request for this line We estimated the power budget for each one of the lines separately and consequently chose the best solution for the batteries taking into account performance costs and reliability 4 7 1 Power Line One overview PL1 The power budget for this line was estimated considering the following assumption that represent a worst case scenario e The pump is turned on at ground and kept at 6V for pre launch and climbing phase for a total of 3 hours and at 12 V maximum for the sampling phase PL1 is then turned off before the descending phase 12 V is in fact the voltage required to obtain the maximum airflow of 32 l min which is much higher than the target flow of 9 l min that we have to achieve during sampling phase Vacuum chamber tests will determine what is the real voltage required to obtain this value in a low pressure environment and therefore allow a b
57. ID Define the structure of DATA field CMD ID assume value between 0 and 3 Serial Number This is a unique progressive number Data DATA This field contains data bytes The interpretation of all data bytes is message specific i e depending on the CMD ID value the meaning of bytes and the length of the field is different The description of the specific message is in the following tables Checksum CRC Checksum is obtained with a 2 byte cyclic redundancy check 16 bit CRC CCITT to verify data integrity Structure of DATA Table 4 8 8 UPLINK COMMAND datagram UPLINK MODIFY Require 1 byte Require changing m changing STATE STATE value 1 byte New value for STATE 1 1t0 6 iecore e e o 1 to 3 mm mec threshold 0 to 255 Page 110 oLAunc EuroLa Student Experiment Documentation VALVES VALVES 1 byte New value for value VALVES B00001111 open B11110000 close CRC CCITT with polynomial x x x 1 0x8408 and initial value Oxffff Arduino library lt util crc16 h gt This field is filled with new values to set in OBDH The MODIFY field ts a bit that request modification of one or more of the values of STATE MODE PUMP or VALVES In particular its encoding is shown in the following We should underline that this CMD ID datagram is used also to acknowledge the request raised by OBDH In fact bit 4 of MODIFY field is used as ACK For instance if GS requires th
58. IOCK 81 Figure 45 235 T CU BOSE oznazesesecu setas esessuD eener 82 FigUre 4 5 24 Ee Leen EE 83 Figure 4 5 25 MM Motor Controller 83 Wielt 5 26 GPSJAdalltlze sori 84 Figure 4 6 1 Thermal Node structure e 86 Figure 4 6 2 Worse lege 90 FOUE NICA Pu Mom 90 Figure 4 6 4 WHC cooling due to airflow 91 Figure 4 7 1 PL1 consumption Grofe 93 Figure 4 7 2 Consumption profile for PL2 and PL3 96 Figure 4 7 3 Ad battery pack 97 Figure 4 7 4 Logical scheme of the PCU board ansennnaennnannnnnnennnnnnennnnnnnnnne 98 Figure 4 7 5 Logical scheme Heaters board 99 FOUre 4 8 1 Eine E EP 103 Foure Ne Slate a ario ia 104 Figure 4 9 3 CMD EE 105 Figure 4 8 4 Sampling setup State i 106 FigUre 4 3 5 SamplihG Stale aac 107 Figure 4 8 6 Descent State E 108 Figure 4 8 7 Bandwidth requirement related to altitude and mission time 113 Figure 4 9 1 GSS interface preliminary design 114 Figure 4 9 2 GS message receive bEehNAaViOUur i 115 Figure 4 9 3 GS message transmission behaviour 116 Figure 7 1 1 SEM setup at BIGEA laboratory eee 146 Figure 7 1 2 PIXE setup at INFN Legnaro eese 147 Figure 7 1 3 Germanium detectors at ERL ccccecccccsseeeeeeeeeeeseeeeeesaaees 148 9 2 Et le A D ne DEE 161 S 2 2 FINALOgG0 iaia 162 aC Giai CUO aC Io 162 E E Ee He Le WV CO
59. Kirune Svena cum magg gers coorta 10000 metri ewm ara scegiie non la mmi mertamone acieguate per deeg tQuel Scientific La revisione de progetto ce hanno ne d recenne HESA ardita bene d hanno Lato icormginenil Ora si devsn o trovare gi asossor per aczu stare contatore d part cele dice arena il docente 1 gruppo di ricerca intarti ha ricevuto parte della sirumentarione sia da n asianda cie che ca onmelfe na di orenanenm meccaniche ma Part re Coustir da eerste decine miglia di euro non ancora stato acguatato Nonostante tutto Fabrizio Guidetti Sdocosx us esperimento armati spero vedeno in honda Lidvcetion Office delbhpenala Spade Burogoa propono altre al Maui Berus 3 0 orogr rendi eg studet urme tar Uno d quests ESEO Tha Europea Student Eacth Crear n network di un verts piropas che ha chieermeo Ti rea irzere it meme un cates da utherere per emenmert scene d progezo promossa a PESA con la collaborazione di A MASSace urrad endo des Tore kais off dal Uriiversit di Baicgna con sede a fer Corso Lauren logs era meccanica di fori pewter per attiuanmerne A progetto e OEA in eece eradeng di ale urrmmenit europe per atv du Fe e roon f Hasse sampe Altro riviste Unibo Redannme Lifter gare E oops ght At BIN MATER ERC A Losse La cd Blogs a Zongen 3 4126 Bonagia Porta MA Dram TAM 8 2 8 A5 Unibo Unibo Magazine Page 166 EuRoOLAUNCH xmv s 7 Student Experiment Documenta
60. N gondola e The experimental setup will be bolted to the gondola using the standard screws specified in the BEXUS user manual that will be fixed with Loctite glue once definitive mounting is performed e The experiment is mounted on four Enidine Compact wire rope springs CR6 100 to reduce the forces experienced during landing The CR6 100 spring has the highest load rating in the entire series and is capable of supporting a maximum static load of 133N Also these mounting devices are very versatile due to the possibility of sliding along the aluminium extrusions and so allowing late adjustments in design Fig 4 2 2 e No hole in the gondola floor is required while the external fabric cover should be removed on one side to facilitate the external air suction by OPC and piping of the SU Page 47 EUROLAUNCH Student Experiment Documentation ADR and SSC cooperation Figure 4 2 2 Mounting detail 4 2 2 Electrical The electrical interface will enable the connection between the experiment and Ground via the E link As the experiment outputs data serially through the microcontroller an RS232 to Ethernet module will be used to convert the serial signal to transmit it over the E link This signal will then be converted back to the serial protocol when it arrives to Ground The experiment s Ethernet cable will be mated to the E link connector an RJF21B with an RJ45 Ethernet jack During flight the outside interface of the RJF21B
61. SA provide technical support to the student teams throughout the project And BEXUS are launched from SSC Esrange Space Centre in northern Sweden e EuroLnauricn e Z RYMDSTYREI Qi Page 11 l EUROLAUNCH Student Experiment Documentation ees ABSTRACT A5 is a scientific experiment whose aim is to study the microphysical processes involved in cloud formation It will fly on the 18th BEXUS balloon that will be launched from Kiruna SWE at the end of October 2014 The experiment consists mainly in two different phases The first one is the in situ measurement of key parameters involved in cloud formation such as particles size distributions humidity temperature and pressure In addition to these parameters also ion densities will be measured in order to assess if a link between ionization rates and cloud formation can be found All these data will be associated to a specific height and location in order to create detailed vertical profiles The second is the collection of Stratospheric Aerosols that will be performed with the use of sampling filters These samples will then be recollected and analysed in laboratory to gather information about aerosol s composition and properties Some of the above mentioned measurements will require the development of brand new instruments and designs seen the incapacity of commercial ones to work properly in the harsh stratospheric environment In particular a great effort will b
62. SPI h gt and the functions that we use are SPI begin activate SPI bus SPIl setBitOrder MSBFIRTS or SPI setBitOrder LSBFIRTS says which byte is send at first MSB or LSB SPI transfer value send one byte data SS line for the specific device has to activate at the moment of data transfer so SS line has to be activated at the first digitalWrite SS LOW an deactivated digitalWrite SS HIGH at the end lC IC Inter Integrated Circuit is a master serial single ended computer bus lC uses only two bidirectional lines e Serial Data Line SDA e Serial Clock Line SCL SDA is the unique line used for data transfer in both directions Page 175 Student Experiment Documentation EuroLAUNcH Vss Vss SCL SLAVE IC SDA SENSORS GND GND The Arduino Mega 2560 uses PIN 20 for SDA and 21 for SCL The sensor is designed to work as a Slave and it will respond to request from the Master device Arduino The communication starts with the Master that sends a byte containing the specific address sensor 7 bits plus a bit for the request read 1 or write 0 Consequently the Slave sends an ACK and executes the command The SCL synchronizes the operations The sensor sends a byte each time and 2 bytes are enough for sensor output The datasheets tell if it is send at first MLB or LSB AIC I AIC I analogic gt ADC Humidity Sensor IPC ARDUINO LIBRARY Arduino provides a library for IC connections Before
63. Wait for User No No user decided decision Yes Send Confirm Response Show and Store Figure 4 9 2 GS message receive behaviour Page 116 EUROLAUNCH A DLR and SEC cooperation Student Experiment Documentation GS message transmission behaviour User action Initialize timeout SN reset Ack Recvd Ack Recvd Request timeout Send SetValues Figure 4 9 3 GS message transmission behaviour 4 9 2 GSS Communication Protocols All data picked up by Arduino are correlated with some status flags and properly packaged Finally data packs are sent to GS using Ethernet shield to connect to E Link RJ 45 connector A UDP connection is preferable for real time applications where a simple and fast communication is requested UDP provides no handshake so it admits some data loss This is not a real problem since critical data are stored inside an on board memory card Moreover we are not really interested to have any data that is not the most recent one and above all we do not want to have long handshake time that could generate some problem involving timeout To ensure a command has been received we provide datagrams with two specific fields to identify a command and to acknowledge if the command has been executed A checksum provides the integrity of data datagram Page 117 EUROLAUNCH Student Experiment Documentation EIN The UDP transmission is binary coded Little End
64. age 99 Student Experiment Documentation EuroLAuNcH Switching regulators are more efficient if compared to linear voltage regulators although they create more noise therefore they are used to regulate 28V down to 12V and 7 2V Switching regulators are used to regulate 12V down to 5V To regulate 15V down to 12V for pinch valves we use two linear regulators in parallel while to regulate 5V down to 3 3V for the Pressure Sensor and the GPS we use a low dropout regulator Therefore our PCU uses a combination of switching and linear voltage regulators Regulators are used in cascade to allow minimum power dissipation Figure 4 7 5 shows a logical scheme of the heaters board where black arrows represent power lines and blue arrows represent the data transmitted from temperature sensors Heaters Bag temere Control 3 T Sensor 3 Sensor 3 G Figure 4 7 5 Logical scheme Heaters board 4 7 4 Safety issues and solutions Each power line is equipped with a current limiter CL to prevent overconsumption in case of failure of some instruments and to ensure the possibility of recovery for the system in opposition to fuses We can control the current and turn off the instrument or the whole line in an attempt to reset the instrument itself or the Arduino MEGA buffer As current limiters we use MIC25 45A for all power lines In particular the high current consumption of PL1 needs to be regulated with two parall
65. ages Do not copy scientific text verbatim for your scientific introduction reference all sources Foundings vs funding Ensure requirements updates in chapter 2 are copied to chapter 5 Include data sheets of the COTS instruments to be used Page 155 SP EUrRoLAUNCH Student Experiment Documentation A DLR nd SSC cooperation 4 Panel Comments and Recommendations Requirements and constraints SED chapter 2 Some requirements to be split up eh FR3 Should and shall to be used correctly Some are in wrong category OR2 is mix up between ops and design req Don t use survive in requirements 10m in altitude is hardly to achieve maybe less precise measurement Objectives are good Functional requirements may be a little wordy especially FR1 and FR2 A Avoid lumping requirements FR3 it makes requirement management and verification more difficult Functional requirements are good and all cover all the important aspects of the experiment PR8is an incomplete requirement DR8 include the correct pinning of the Amphenol connector in the requirement Mechanics SED chapter 4 2 1 amp 4 4 Experiment components list is missing Use metallic connectors not plastic ones for profiles Fix with glue esp for recovery in truck Need verification test analysis or similar that it can withstand 5g mention here Might be possible to improve mass and volume
66. agmented into different parts depending on the function Page 69 EUROLAUNCH Student Experiment Documentation EIN Figure 4 5 6 Humidity sensor schematics el DAT 1 IN 1 1 F O t t I Figure 4 5 7 Pressure sensor schematics Page 70 EUROLAUNCcH Student Experiment Documentation Figure 4 5 8 Temperature sensor schematics Figure 4 5 9 AIC offset closer Page 71 E UROLAUNCH and SSC cooperation Student Experiment Documentation 4 5 3 Stacked Sensor Board 2 SB2 LI S r Digits ele cO stal 14 zi AME FILATI LS A REES Er ADC I2C PPPS C ia wr bb co Loy DATALOGGER TXBBLBA Li i ru D Ab Seba e r7 mer ger T wer t mer men wen gero eno epi a E AC UCC VE AEE AE JE cia GA I 1 x I n 22 m 4 E E F F E E E E z er fg Af Af er SC ASTA SI n T CK y e TR Figure 4 5 10 Stacked Sensor Board 2 SB2 Table 4 5 4 Stacked board 2 Data logger 5V UART Voltage level shifting for the TXO from 4 5 13 open log 3 3V to 5V using level translator IC TXB0101 ADC 5V C 5KOhm pull up resistors inserted 4 5 14 MCP3422 between the VCC and the SCL SDA for AlCs lines CH1 and CH2 lines are connected with two separated pins of the terminal where will be attached the analogic output of the ion counters Solid state digital Average 5mA each A NPN BJT 4 5 15 Relays high low bipolar junction transistor
67. ags EuroLaunch Page 143 EUROLAUNCH Student Experiment Documentation EIN T 0H45 Access to gondola pad ends e T 0H35 Starts balloon inflation T 0H30 Final pre flight operation Igor Nani T reason se dont E e 1 T 0H10 Lift gondola EuroLaunch ur NN T2HOO Balloon reaches sampling altitude MEN GS ACK for sampling altitude GS operator EE Set SW SAMPLING INIT valves open EE mE Set SW SAMPLING REQUIREMENT Need few minutes 5 10 GS operator minutes re warning from EuroLaunch of balloon cut down Checklist ECU SW manually set to DESCENT Turn OFF pump CLOSE valves Close PL1 Close PL2 Turn off the experiment T5HOO Balloon cut down T5H45 Balloon lands EN 6 4 Post Flight Activities Post Flight activities include detailed data and sample analysis that will be further described in section 7 as well as an evaluation of the flight sequence and of the integrity of instruments and experiment structure 65 System Success Optical Particle Counter ge Page 144 EUROLAUNCcH Student Experiment Documentation The OPC should measure particles size 20 distributions at a rate of one measurement every 20 s up to an altitude of at least 10 Km The OPC should measure particles size 50 distributions at a rate of one measurement every 10 s up to the maximum altitude reached during the flight Air lon Counters The AIC s should measure the ion densities 10 at a rate of one
68. ain energy is proportional to the mass of the corresponding element found in the sample A Lithium drifted Silicon detector is used for data acquisition allowing for the simultaneous analysis of the elements from Sodium through Uranium Data reduction is then accomplished using computer software which normalizes the detected X ray intensities against those measured from pure standards for each element Thus elements are easily identified and quantified University of Bologna has a long term collaboration with the INFN National Laboratories of Legnaro Padova The PIXE set up at INFN Legnaro is the following one Amplifier ORTEC 672 ADC Silena Multichannel Ortec Match Maker Software Lab View Chamber with a steel cylinder 20 cm 5 10 automatic samples holder turbo molecular pump vacuum 10 6 the detector is a Ge lper pure Canberra with a surface area 100 mm crystal thickness 1 cm polymer window 0 4 um resolution 160 eV 137 eV measured distance from the target 3 cm detector target angle 45 beam target angle 0 funny filter Mylar 60 um hole 10 Figure 7 1 2 PIXE setup at INFN Legnaro Spectrometry Germanium detectors are semiconductor diodes having a PIN structure in which the intrinsic Il region is sensitive to ionizing radiation particularly x rays and gamma rays Under reverse bias an electric field extends across the intrinsic or depleted region When protons interact with the material within the depleted volum
69. ak Modes encoder Serial PID based closed loop velocity 32 bit requires encoder Analogic PID based closed loop position 10 bit resolution analogic feedback Built in over temperature over current over voltage under voltage protection 4 5 8 GPS Adafruit After a wide research Novatel u blox etc and due to budget reasons A5 Unibo has selected this GPS Receiver because of its reliability and low cost It has been tested in a HAB High Altitude Balloon up to 27 km high although Adafruit guaranteed up to 40 km altitude for some models Figure 4 5 26 GPS Adafruit Table 4 5 5 GPS features Sensitivity 165 dBm 10 Hz updates 66 channels 5V 20mA current draw Maximum Altitude gt 25Km altitude firmware up to 40km tested at 27 Km Page 85 l EUROLAUNCH Student Experiment Documentation ees 4 6 Thermal Design Table 4 6 1 shows the allowable temperature range for each sensor of the experiment Table 4 6 1 Critical components range Batenes III This section reports the description of the thermal model of A5 Unibo and the assumptions on which the thermal modelling is based Two thermal cases cold case and hot case have been simulated Boundary conditions for what concerns external temperature of air have been deduced by BEXUS10 flight 4 6 1 Thermal model architecture We performed transient analysis in order to evaluate the temperature inside the experiment as a function of the
70. al amplifier it is used as a buffer for voltage tracking Its inputs are represented by the voltages coming from voltage dividers where each first resistor is made by a 4 KOhm resistor and each second one is made by the thermistor NTCLE100E3 See figure 4 5 19 e LM139 quad comparator it compares the voltage coming from the output of OPA 4180 with a reference voltage for O C If the measured temperature gets below 0 C the signal goes up and becomes higher than the reference voltage Thus the output of LM139 goes up to VCC and the control block fig 4 5 20 is activated The parallel resistors in the right high corner are pull up resistors for the output of LM139 The pair of diodes in the left low corner are used to have a positive voltage not only for positive temperatures but also for temperatures below 0 C E T Y Hd Figure 4 5 19 Logical block of H Board Regarding the control block Fig 4 5 120 shows how the signal coming from the LM139 output Ox O1 O2 O3 is powered For this purpose a BUT BC337 is used When the signal Ox goes up the three BJTs activate other three BJTs and in the meanwhile charge three 147uF polarized capacitors Their function is to maintain the control block activated for about 75 seconds after 0 C is reached that is after Ox is grounded from LM139 Page 78 EURoLAUNCH A DLR and SSC cooperation Student Experiment Documentation The three solid state relays AQY211EH
71. apable of accurately determining the size and estimating the main nature of aerosols This feature is particularly interesting when combining this instrument to the collections of samples that could be used as a check for these estimations Table 4 3 2 LOAC specifications 0 3 to 50 um 19 channel bins Figure 4 3 1 LOAC 0 to 2000 particles cm Page 49 Student Experiment Documentation EuroLAuNcH 450 mA 30 mA 4 3 2 Diaphragm Pump Performance Flow rate up to 32 l min Type Diaphragm pump magnet brushed DC motor Operating Range 50 to 50 C Figure 4 3 2 Boxer 7000 Pump 12V DC Max current 3 A Our current design employs the use of a 7500 BOXER pump capable of generating an airflow up to 32 l min This will be used to generate the flow inside the SU and in particular inside the SIOUTAS sampler Since this device requires a specific flow rate of 9 l min to correctly sort the particles by their size an active control of the supplied voltage and hence the flow has to be performed To achieve this we will employ a Motion Mind DC Motor Controller board Detailed testing will be performed in vacuum chamber to determine the amount of voltage required to achieve the correct flow See PT1 and PT2 Page 50 Sere Student Experiment Documentation 4 3 3 Airlon Counters AICS We chose to use two AIC s from Alphalab Inc for the ion density measurements One will be used for positive ions and one
72. are used to switch on the heaters that need about 0 18A each ted E o H Be a dej T 37 KE dh EB D oh J L T9 Za EN L ui TS me ZS l L i Ha a fa XL DK Ge Figure 4 5 20 Control block of H Board Page 79 E UROLAUNCH Student Experiment Documentation 4 5 6 Power control unit PCU T Figure 4 5 21 PCU voltage converting block Page 80 EUROLAUNCcH Student Experiment Documentation Fig 4 5 21 shows a schematic of the PCU board Three categories of ICs are shown The first one is the variable switching voltage regulator DE SWAD J that can give an output up to 25Watt The second one is represented by fixed 5Volts switching regulator DE SW005 that gives an output of 5V with a ripple lower than 2 which is perfect for the electronic powering The third one is represented by the variable linear voltage regulator L T3080 that has the potential to be paralleled Due to the different requirements for performing of the different instruments the PCU has different power outputs Air ion counters 12V and 45mA provided by a switching voltage regulator DE SWADJ Electronic boards 5V and 500mA For this purpose we have used the switching voltage regulator DE SWO05 Pinch Valves 12 V needed and 0 33A of current each Thus two linear variable voltage regulators have been placed in parallel LT3080 and three diodes in parallel in order to provide high
73. arri 163 9 2 5 Ab Unibo FacebOOl sini inant ico 163 8 2 6 A5 Unibo TWitter RR Immer 164 PREFACE A group of students from the department of Aerospace Engineering Environmental Science an Informatics Engineering of the University of Bologna has been selected to carry out an experiment to monitor the stratosphere In particular the proposed experiment A5 Unibo Advanced Atmospheric Aerosol Acquisition and Analysis aims to deepen the knowledge of stratospheric aerosols and reveal some aspects which are not clear in the process of cloud formation This experiment was proposed in the framework of the BEXUS programme that allows students from universities and higher education colleges across Europe to carry out scientific and technological experiments on stratospheric research balloons Each year two balloons are launched carrying up to 12 experiments designed and built by student teams The REXUS BEXUS programme is realised under a bilateral Agency Agreement between the German Aerospace Centre DLR and the Swedish National Space Board SNSB The Swedish share of the payload has been made available to students from other European countries through a collaboration with the European Space Agency ESA EuroLaunch a cooperation between the Esrange Space Centre of SSC and the Mobile Rocket Base MORABA of DLR is responsible for the campaign management and operations of the launch vehicles Experts from DLR SSC ZARM and E
74. at would contrast with the base design in order to highlight tte name of the team in yellow the program that we belong to and institution where we come from in white over red frame We chose a lightening for the letters because it is an element very linked to the clouds that also shall represent the strength and determination to face the difficulties during the project Te 8 2 1 Preliminary Logo Page 162 EuroLAuncH xmv s 7 Student Experiment Documentation 8 2 2 Final Logo e La Repubblica Newspaper 22 01 14 e http ricerca repubblica it repubblica archivio repubblica 2014 01 22 ingegneri in svezia per studiare la vita html e Other Regional and National Newspapers are interested in us e Universit di Bologna Magazine is also interested in us e http www magazine unibo it archivio 2014 05 23 a5 12019esperimento scientifico selezionato dall2019esa e Aerospace Engineering Faculty Open Days 03 04 2014 e http corsi unibo it Laurea IngegneriaAerospaziale Eventi 2014 02 open day sede di forl htm e Elementary School Activities 60 children in Flight Mechanics Laboratory 14 04 14 Presentation to the Advance Science Institute of the University of Bologna July 2014 e Presentation to CNA Confederazione Nazionale del Artegianato in order to show the companies in Emilia Romagna Region what A5 Unibo is performing e Contact other companies and institutions that could be possibly interested as ambiental foundatio
75. ay the particular characteristics of one instrument Sioutas that require an specific air flow from Page 31 EUROoLAUNCH Student Experiment Documentation re the pump that must be controlled by a motorcontroller This tests are taking more time than initially foreseen The purchasing and delivering of components are the leading causes of delay during this phase of the project 3 3 Resources 3 3 1 Manpower Depending on the availability of each team member we define the table 3 3 1 Table 3 3 1 Manpower per week Alberto Paolo Elisa Name of Team Member Page 32 EUROLAUNCH A DLR and SEC cooperation Student Experiment Documentation a Svetozar dede nien Table 3 3 2 shows the availability of each team member during the year The colours code is Green more than 70 of the time Yellow between 30 and 70 and red Less than 30 where 100 is defined as 16 hours per week In grey the months of no participation in BEXUS programme Months of the project are shown in orange for 2013 in blue for 2014 and in pink for 2015 3 3 2 Budget Table 3 3 3 Budget Arduino Ethernet Shield 33 17 1_ 39 17 EML Present Controller MicroSDcad 8 J e 2 Batteries Li Po SAFT 530 125 1185 Air lon Counters 550 2 1 550 free Particle Counter 2500 2500 Pump BOXER Electro valves and related materials 175 2 350 Temperature sensors 4 94 3 DS18B20 Page 33 Student Exp
76. bic centimetre of air surface DC voltmeters electrostatic meters voltage touch monitors etc Page 38 EUROLAUNCH A DLR and SEC cooperation Student Experiment Documentation Pump Boxer amp Pumps Boxer Pumps are used in portable and fixed gas analysers pipette controllers and many other pressure and vacuum applications otructure Manufacturing C 0 S s r l I C O S s r l has found in the product and process differentiation its success factor by the fusion of artisan tradition and technological innovation The production is diversified perforating tubes prickers and punches for press knives for footwear leather and paper industries precision mechanical parts by sub contracted operations turning milling EDM metal heels special horseshoes and precision metal fittings in general C 0 S has skills and professionalism innovative machineries flexible and complementary production processes to offer the customer a quality service Camera Dogcam dogcam is the leading UK based design and development company of innovative and rugged bullet video cameras for action sports recreation and motorsport use We are still looking for other institutions and companies that could appreciate our project A5 Unibo will be fully cover by FML funds in case of no external sponsorship for all the components needed for the experiment The International Relationship Department of the Forli City Hall is currently studying a p
77. bjectives 1 4 1 4 1 Toretrieve aerosol samples and make them available for laboratory post flight analysis in particular PIXE SEM y spectrometry To analyze the samples determining aerosols chemical composition and morphology To create a reliable yet simple concept for future atmospheric measurements Team Details Contact Point Facilities address Flight Mechanics Laboratory Engineering and Architecture School Via Fontanelle 55 47121 Forli Italy Supervisor Prof Fabrizio Giulietti 39 0543 374 424 fabrizio giulietti unibo it Page 16 EUROLAUNCcH i A Student Experiment Documentation Team Leader Nani Serrano Castillo 393270863294 nani serrano unibo it Team Website and e mail www the5f com bexus a5unibo gmail com 1 4 2 Team Members Encarnaci n Serrano Castillo Team Leader and System Engineer Encarnaci n was born in Madrid in 1988 She took her bachelor and master degree in Aerospace Engineering in the Polytechnic University of Madrid In 2011 she went to Italy with a Students Exchange program called ERASMUS She was interested in the work that Flight Mechanics Laboratory was developing so she stayed in Italy for her Master Thesis project Quadrotor modelling and data fusion complementary filter she had the opportunity to study the dynamics to integrate sensors and acquire the data for the attitude determination system of a Quadrotor Now she is a PhD student in Advanced
78. ceeseceueeceeseceusessueeseues 62 Figure 4 4 14 Y axis deplacement 62 Figure 4 5 1 Devices connected to Arduino 63 Figure 4 5 2 Arduino Mega and Pinning scheme aannannnannannannnnnnnnnennnnnn 64 Figure 4 5 3 Stacked Board 1 SB1 i 66 Figure 4 5 4 Stacked board SB1 schematics part 1 67 Figure d 5 5 SB Dart a schelmal6S usce cen diste d ir e E onu iem 68 Figure 4 5 6 Humidity sensor schematics n snnennsenneennenenrnesrrerresrrerneennee 69 Figure 4 5 7 Pressure sensor ScheMAatics ie 69 Figure 4 5 8 Temperature sensor schematics 70 Figure 4 5 9 AlC ONSel ee E 70 Figure 4 5 10 Stacked Sensor Board 2 GR 71 Figure 4 5 11 SB2 schematics pt 1 i 72 Figure 4 5 12 5B2 schematics pt EE 73 Figure 4 5 13 Data Logger schemaice i 74 Figure 4 5 14 ADC schematic and signal conditioning circuit 74 Figure 4 5 15 Paralleled solid state relays schematics 75 Figure 4 5 16 GPS level translator 75 Figure 4 5 17 Arduino Ethernet Shield sees 76 Figure 4 5 18 Heaters Board H PBoardl 76 Figure 4 5 19 Logical block of H Board esee 717 Figure 4 5 20 Control block of H Board 78 Figure 4 5 21 PCU voltage converting DIOCK 79 Figure 4 5 22 PCU Switch and Current limiting D
79. cles that stick to a surface between the valve and the ambient atmosphere is minimized e The optimal direction to prevent contamination especially from the balloon is straight down so the inlet pipe will point downwards e A blank filter identical to the collection substrate but not exposed directly to the airflow is used to monitor the contamination inside the SU and in particular the one occurring during assembly and flight sequence e All mechanical parts with surfaces exposed to the sampling air are assembled in a class 100 clean room where they will be cleaned with ultrasonic cleaner before being assembled Assembling and cleaning procedures for the SU are explained in more detail in chapter 6 Figure 4 3 5 SU overview Page 54 Sere Student Experiment Documentation 4 4 Mechanical Design Table 4 4 1 Mechanical Components Components Product number Cubic connector 20 3 Bosh 3842524478 20 40 Angular Bosh 3 842 538 517 20x 20 Beam Bosh 3842993231 The mechanical structure of the experiment is subdivided into three different sections Electronics Housing Assembly EHA Instruments Housing Assembly IHA and Battery Housing Assembly BHA This choice has been taken in order to realize a modular structure that could be modified as easily as possible and assembled easily and quickly Figure 4 4 1 Experiment front view Page 55 e d T Student Experiment Documentation EURroLAUNCH
80. creation of vertical profiles In this way we hope to be able to create a link between ionization rates and CCN s density Moreover once reached the nominal altitude in the stratosphere we will perform an in situ collection of aerosols with the use of a diaphragm pump This pump will create an airflow through a special collector called Sioutas Impactor that owns the big advantage of sorting the sampled particles by their mass and size making post flight analysis much easier with respect to normal filters This experiment design therefore combines the collection of aerosols following the footsteps of previous experiments such as DUSTER 7 or Stratospheric Census 8 to the direct in situ analysis of particle distributions as the ones performed by other balloon borne experiments studying both the direct effects of aerosols by analysing their chemical composition and the indirect effects related to cloud formation Page 15 EUROLAUNCH Student Experiment Documentation ADR and SSC cooperation 1 3 Experiment Objectives Primary Objectives 1 To create detailed vertical profiles for Particle size distributions and lon densities throughout Troposphere and Stratosphere To study the microphysical processes behind cloud formation combining these data with key atmospheric parameters such as temperature humidity and pressure Investigate the correlation between cosmic rays ionization and nucleation rates Secondary O
81. ction All instruments and ECU are turned on and correct acquisition of data is checked both on SD and through data logging to GS Page 133 E UROLAUNCH Student Student Experiment Documentation e Documentation A series of operations is then performed to verify that main SR are fulfilled 1 Power is manually switched off and of by unplugging and re inserting the power cable SR4 Request for manual mode is sent and then connection is removed SR5 All the instruments are turned off one at a time and then turned on again while experiment is running SR6 Connection to GS is interrupted by unplugging the e link cable and reconnected later on SR11 Unknown or wrong commands are sent from GS J Completed Test type Operating Simulation flight sequence Test facility University of Bologna Tested item ECU Instruments GS Test A complete flight sequence is performed giving false GPS procedure signals in order to switch between the different software modes Moreover GS commands are going to be sent in order to evaluate manual override A second flight sequence is performed where loss of contact with GS is simulated by unplugging the e link cable to evaluate the capability of the system to autonomously perform the flight sequence Completed 5 2 5 General Tests T Test ype Test facility Flight Mechanics Lab University of Bologna Page 134 E UROLAUNCH A DLR and SSC coope Student
82. ctive effects that can affect thermal regulation exhaust pipes will be needed for all these instruments Figure 4 4 4 Instruments Housing Assembly top view A series of particular design are being implemented for safety reasons e he pump will be mounted on the bottom plate using a rubber thickness to reduce vibrations The experiment is mounted on four Enidine Figure 4 4 5 Rubber thickness detail Student Experiment Documentation Page 57 E UROLAUNCH Compact wire rope springs CR6 100 that will also help in reducing vibrations generated by the pump and the external environment Since the optics of OPC require fine alignment and are very sensible a dedicated mounting provision will protect this instrument both by random vibrations and shocks especially during landing Since the aerosols sampling requires a deep level of cleanliness and insulation the SU will be mounted inside a separate box fixed to the bottom of the IHA through four corner bolts In this way the SU mounting will be performed inside a clean room and only once this is done and SU is completely insulated it will be mounted inside the IHA Also during post flight this design will facilitate the removal of the SU and its safe transport to the clean room where the filters will be taken out A preliminary sketch of the SU can be seen in chapter 4 3 4 Figure 4 4 6 SU mounting detail The two AIC will be bolted directly to the bottom plate of the IH
83. cuum Cha Solare performante Operating Simulation Sensars OCBH contro flow design and Implementation lesting Experiment with Mission Simulator Development and testing of he driver for the Experiment Vacuum and thermal of the Integrated System Battenes Voltage Release Rate VRE until complete dach Bameries VRE until complere discharge in operating temp Bamerles release at the pump system ln ceder to charact Vibration of the integrated System Thermal and Cricgeric Water Landing Random Vibration Drop Tes G55 Manup Test UDP Transmision Working Test Sofware GR Software Control Test Fligha Simulation of Integrated System Scientific Analysis and Results Page 169 E p e s P D EUROLAUNCH ADLR and SSC cooperation Danila Nanl Riccardo Alice por Lucx Mattia cos na Nani Panto Ric aria anie RiccardaErikaNani EE Erika Manj Riccardo Hani 1 De Nani iccardo 3 i zm xx mx Hom E Alice lger Luca Mattia DEBEMUS luca Matta 5xetiozar Cc LueipMamaseerlazar ee ee Luca Mattia svetlazar kass sMarco Riccardo i DU A omo Danila DI EE Danilo Re Danilo Bu a aa a d a a n Nani Paala Riccardo i i REA Marco Rlccardo ENER FaolaRiccardo BEE SEEN fani Paala Riccarda pode NanbPaale Riccarde i RES uor Soo Lane ees LaMar ivea i o 1 16 T TII Flisa 5t Gantt Chart has been updated according to the needs of the project and the delays due to the purchasing and delivering
84. d implementation of a control and remote management device for a satellite tracking system ALMA Tracker He also did a previous internship using LabVIEW on a Compact RIO system for data acquisition and processing He is now attending Aerospace Engineering Master Degree at University of Bologna Concerning A5 Igor is developing Ground Station SW and he is mostly involved in the software design Danilo Boccadamo Power Danilo was born in Rimini in 1991 He lives in San Clemente a small town near Rimini He is a bachelor student in Aerospace Engineering At the moment he s writing his bachelor thesis on Dual Fuel Application in Diesel Motors For this thesis he was responsible of setting the test bench and the acquisition systems Furthermore he has as a hobby static and dynamic modelling In A5 Unibo he is responsible for the Power Subsystem Page 18 E UROLAUNCH A DLR and SSC coope Student Experiment Documentation Paolo Lombardi Mechanics Paolo has completed his BSc in Aerospace Engineering at Bologna University and he is currently studying for the Master Degree in Aerospace Engineering at Bologna University Paolo is responsible for the Mechanical design of AS Alice Zaccone Software Alice was born in Rimini in 1991 a small city in the centre of Italy Alice studied Aerospace Engineering as an undergraduate at the University of Bologna and is now studying to take the Master d
85. e maybe you rather use interrupt programming of Arduino Mega Ensure manual mode has a timeout to take it back to autonomous mode You will experience a gradual descent during float this should be accounted for in your tolerances for detection of descent descent rate and confirmation of float Define data rates Verification and testing SED chapter 5 Maybe you want to test some of the requirements you only review so far like water test T3 T4 thermal test should show how good your calculations are test in August is too late do asap Page 156 ss EuROLAUNCH A DLR end SEC cooperation Student Experiment Documentation pumps starting at low pressure is often a problem gt test early PT3 is good test call it differently pump vibration or microvibration test Add column in verification matrix where you correlate to test number a Safety and risk analysis SED chapter 3 5 5 risks with a severity of 5 classification is wrong e g components missing no 5 Lots of risks missing more detail needed for CDR Forgot schedule budget conflict in team lack of expertise risks Flight batteries are a risk for recovery battery fire Launch and operations SED chapter 6 A lot is missing timeline BX interface You need to make sure that the particles are actually from atmosphere and not ground Need very clean pumps needs a lot of work Team wants to use spare filters Have a look at Cass E SED for t
86. e Counter ON e GPS ON e Read all sensors Read all enabled instruments e Prepare status save status to Data Log e do SendUpdate sense status and sen d poll for message IS S m ppe a open all valves eege d all valves A A i interaction Head UDP packet if available Parse Message In case of SetValues set values and send Ack SendCmd interaction In case of Ack permit pending state change transitions AskForConfirm interaction by setting a Ack Received Flag start pump e Stop pump N e check_systems oet Manual Mode S S S e Set Manual Mode S e Set Automatic Mode ask confirm climb If Increasing Altitude Flag is marked do Active ALL sensors and Instruments AskForConfirm interaction set Page 119 Student Student Experiment Documentation Re Documentation EUROLAUN cH WaitingConfirm flag and initialize WaitingConfirm time If Increasing Altitude Flag is marked and WaitingConfirm is set update Waiting Confirm Time If Waiting Confirm Time is greater than WaitLimit change state autonomously and reset flags ask confirm float If StationaryAltitudeFlag is marked do AskForConfirm interaction set WaitingConfirm flag and initialize WaitingConfirm Time If StationaryAltitudeFlag is marked and WaitingConfirm is set update WaitingConfirm T ime If WaitingConfirm Time is greater than WaitLimit change state autonomously and reset flags as
87. e Sensor AIC I analogic gt ADC AIC I analogic gt ADC Humidity Sensor Temperature Sensor LOAC Table 4 5 2 Other devices communications protocol Other Devices Protocol fin 36 Electro valves gt Relay SD TX3 RX3 Pump motor controller Motion Mind TX2 RX2 GPS TX0 RX0 Ethernet Shield MOSI MISO SS All of the sensors and instruments give a digital output except for the two AIC s whose analogic output needs to be converted into digital thanks to a 18 Bit Multi Channel A2 Analogic to Digital Converter with 12C Interface and On Board Reference see fig 4 5 1 and 4 5 2 A5 Unibo team has decided to design different printed circuit boards PCB in order to simplify and make more reliable the physical interfaces and connections between the different components The entire electronics interfaces with sensors and instruments will be designed in order to exactly fit with Arduino MEGA 2560 Board The PCU Power Control Unit instead does not have very strict geometry requirements All of them are placed together in the electronics box as shown in the mechanical design Page 66 EUROLAUNCcH Student Experiment Documentation 4 5 2 Stacked board 1 Figure 4 5 3 Stacked Board 1 SB1 Fig 4 5 3 shows the stacked board SB1 the sensors and instruments connected are shown in table 4 5 3 Regarding the geometry the board exactly fits with Arduino MEGA 2560 pin schematics in order to overlap the microcon
88. e change of both STATE and VALVES status the resulting MODIFY byte will be 10010000 CMD ID 1 could be sent more than once until the proper datagram of confirmation is received Table 4 8 9 DOWNLINK ACK E SN ACK EE 2 byte ANTI TOTAL 2 SN ACK byte is used confirm the receiving of a CMD by replying the SN of the CMD received CMD ID 2 Page 111 EUROLAUNCH Student Experiment Documentation A DLR and SSC cooperation Table 4 8 10 DOWNLINK REQUEST CONFIRM datagram N S next STATE 1 byte TOTAL IL N S is used to request confirm for changing to next STATE e g CLIMB request when altitude starts increasing Table 4 8 11 Sa RESPONSE datagram reply serial number of 2 byte a req TOTAL _ TOTAL This field is used to reply to a request for changing to next state CMD ID 4 Table 4 8 12 DOWNLINK datagram D LS Timestamp ms 1ums2t 4 STATE STATE ife 0 1 MODE MOPE __ I GES lat in32t Li GES lon GPS data in32t 4 GPSat MNA Cd 1 Inte 1 NEM NNNM 1 uintt6 t Le Pressure measure measure LOAC measure 19 uint16_t NO dl Page 112 E UROLAUNCH i Student Experiment Documentation Temperature rung BH Relative humidity 1 uint16 t Valves open 1 byte Others bit TBD TOTAL 66 In this case DATA is filled with all values measured by on board software pl
89. e descending rate but also request GS ACK SR10 SW shall comply with E Link and TCP IP specification SR11 SW shall not fail in case of GS connection failure and manage to reconnect SR12 SW shall not to be crashed by GS command errors SR13 GSS shall receive display and log data SR14 GSS shall allow user to set commands to on board software 2 4 Operational Requirements Table 2 4 1 Operational requirements Pet Requirement OR1 The experiment shall be able to function autonomously in the event that contact with Ground is lost OR2 Piping materials and parts of the instruments coming out of the experiment shall be protected with a remove before flight cover OR3 Remove before flight cover shall be removed before flight ORA The experiment shall autonomously open the pinch valves and unseal Page 26 EUROLAUNCcH Student Experiment Documentation mM the sampling filter once reached the nominal altitude in the stratosphere OR5 The experiment shall autonomously close the pinch valves and re seal the sampling filter prior to the descent ORT The experiment shall be turned off prior to entering the descending phase Pump AIC s and OPC should be disabled OR8 The amount of Offset for the AIC s shall be measured prior to the flight and it shall not be higher than 100 mV Student Experiment Documentation 3 PROJECT PLANNING EuroLaAuncH A DLR and SSC coope 3 1 Work Breakdown Structure WBS
90. e forcing of 1 4 Wm from anthropogenic CO2 emissions The main mechanism that is believed to link ionization and cloud formation is the so called lon aerosol clear air mechanism 4 aerosols responsible for Cloud Droplets CD formation can be directly injected into the atmosphere e g volcanic eruptions or pollution or created from trace condensable vapours in the atmosphere itself In the latter case ionization of gases can lower the nucleation barrier and hence increase the formation rate of UCN Ultrafine condensation nuclei that can eventually grow into CCN Cloud condensation nuclei which are aerosols with sufficient diameter typically 20 1 um to act as nuclei for CD formation Besides enhancing nucleation charged aerosol particles resulting from CR ionization can also grow more quickly than uncharged particles owning to the enhanced condensation rate of polar molecules These two effects combined together suggest that this mechanism has an outcome quite similar to the Aerosol indirect effect in the sense that it helps the formation of more smaller particles increasing cloud reflectivity and lifetime but has two major differences it acts on a global scale is not spatially limited to polluted regions and can act on different time scales since CR fluxes vary not only through a solar cycle but on centennial and millennial time scales Recent measurements by an airborne ion mass spectrometer in the upper troposphere showed la
91. e of a detector charge carriers holes and electrons are produced and are swept by the electric field to the P and N electrodes This Page 148 EUROLAUNCH i I Student Experiment Documentation charge which is proportional to the energy deposited in the detector by the incoming photon is converted into a voltage pulse by an integral charge sensitive preamplifier The germanium detector is cooled with liquid Nitrogen in order to reduce the thermal generation of charge carriers thus reverse leakage current and mounted in a vacuum chamber The sensitive detector surfaces are thus protected from moisture and condensable contaminants Germanium detectors allow non destructive measurements i e no radiochemical separations are necessary and provide information about both the energy and rate of photons reaching the detector i e they provide a spectrum where photons with different energy can be recorded simultaneously The resolution of Germanium detectors is much better than other photon detectors such as scintillators and this allows differentiating photons with quite similar energies In the Laboratory of Environmental Radiochemistry LER gamma spectrometry measurements are carried out using two low background Hyper Pure Germanium crystal detectors a p type coaxial and a planar respectively for higher and lower energy ranges 50 2000 keV and 0 900 keV The first one has a relative efficiency of 38 and FWHM of 1 8 keV at 1332 keV
92. e put into the development of a tailored Optical Particle Counter capable of working in micro pressure conditions and of detecting particles down to 0 3 um Our hope is to be able to create detailed vertical profiles for Particle size distributions and the other key parameters that could be used as a reference for future experiments We are aware of the fact that to follow the whole nucleation process other bigger and more expensive instruments such as Aitkin Nuclei Counters would be needed in order to detect particles with sizes lower than 0 3 um Nonetheless we believe that the development of this new balloon borne design could provide the basis for future applications since it employs a multi instrument acquisition approach that could be duplicated even in higher budget missions Page 12 EUROLAUNCcH Student Experiment Documentation 1 INTRODUCTION 1 1 Scientific Technical Background Aerosols are solid or liquid particles suspended in the air They can come from a wide range of sources both natural such as volcanoes sea foam or dust as well as from anthropogenic sources such as combustion e g transportation heating energy production industry etc particles have a size range from few nm to hundreds of um The effects of their presence in the atmosphere can be divided into direct and indirect effects The direct effect is the effect that aerosols themselves exert on the radiative balance of the Earth through
93. e size distribution of particles n cm for each selected size interval and finally exits from an exhaust pipe The OPC will be kept on for the whole flight allowing for the creation of a continuous vertical profile e Air lon Counters AICs these devices use a fan to create an airflow and draw air from outside the gondola lons present in the air are diverted from the flow and collected on a plate which gives a voltage output proportional to the number of ions collected n cm The air is then expelled downwards through the bottom plate Also AICs will stay on for the whole flight allowing the creation of a vertical profile e Pump and Sampling Unit SU Once reached a nominal altitude in the stratosphere the pump is used to create an airflow through the Sioutas sampler in order to collect aerosol samples Valves posed both before and after the SS are opened only during sampling phase and remain closed for the rest of the flight to avoid contamination from non stratospheric particles Figure 4 1 2 Main scientific instruments Page 46 4 E UROLAUNCH A DLR and SSC coope Student Experiment Documentation 4 2 Interfaces 4 2 4 Mechanical The experiment housing has been designed to suit all mounting requirements specified in the BEXUS user manual The spacing of the feet and the slot sizes have been incorporated in the mechanical design such that it fits on the M EGON gondola Figure 4 2 1 Experiment mounting in M EGO
94. e thermal balance equation in transient condition is dT sun Varsevo Apraner d sky 2 das m c dt The term on the right represents the variation of the internal energy due to the thermal evolution m is the mass of the system c is the specific heat dr is the time lapse and dT the temperature variation in the elapsed time 4 6 4 Results In order to achieve the numerical solution for the problem a Matlab script has been implemented Here we only display the final results but more details about the equations used in the thermal calculations can be found in appendix E After the CDR we added in our calculations the airflow of pump and OPC as a possible source of heat loss In particular a constant 10 W of heat loss through these instruments have been considered We computed the temperature for each of the air nodes and the batteries that are the most demanding components in term of thermal design We also computed the analysis for 4 different scenarios e Worst Cold Case 1 WCC1 launch at night with only 5W heating on batteries e Worst Cold Case 2 WCC2 launch at night with no heating on batteries and instruments e Worst Hot Case 1 WHC1 launch during the day only SW heating for the batteries e Worst Hot Case 2 WHC2 launch during the day with 5W heating for the batteries and 10W heating for the other instruments Page 89 Student Experiment Documentation EURPOLAUNCH Temperature trend during fl
95. egree in Aerospace Engineering For her bachelor thesis she worked on a project for the analysis of the atmospheric gasses The system was composed of an array of gas sensors controlled with a microprocessor and she developed a software for data acquisition and transmission to ground Alice is responsible for the configuration and control of the ambient sensors Abramo Ditaranto Electronics Abramo was born in Matera in the south of Italy in 1988 He studied Aerospace Engineering at the University of Bologna and took his bachelor degree in 2010 working on a project which consisted on the creation and the construction of a device for infrared transmission developed for on board satellite applications V In A5 Abramo is responsible for the Electronic Subsystem Page 19 Student Experiment Documentation EuroLAuNcH Marco Didone Thermal Marco was born in Castelfranco Veneto in 1990 He lives in a small town called Albaredo in the North East of Italy He was graduate at the University of Padua in 2013 with the thesis on Environmental flux modelling and thermal analysis for MISSUS experiment on stratospheric balloon BEXUS and now he is a Master student in Aerospace Engineering at the University of Bologna He played basketball for ten years and at present he plays the bass guitar for a rock band Concerning A5 Unibo experiment Marco is responsible for the Thermal design Elisa Luconi Sample
96. el CLs In total we employ four CLs on the PCU board Moreover we need to consider that a hard impact or water landing could cause damage to the pump and possibly an explosion if still on and subsequently a contamination of the samples or a loss of stored data To avoid this we Page 100 EUROLAUNCcH Student Experiment Documentation decided to turn off the whole experiment prior to the descending phase This done employing a solid state relay for PL2 amp PL3 and a GBLA relay for PL1 4 8 Software Design 4 8 1 Requirement Analysis The software overall design should keep all the tasks requested by the software requirements in consideration Error handling is necessary to have a reliable on board software All processes should be monitored to prevent unpredictable behaviour by handling errors exceptions or bad data Furthermore they have to be supervised regarding the execution time using a timeout to end a task without creating long delays in the life cycle Regarding inputs acquisition it is important to underline that altitude detection is performed twice the most reliable and accurate measurement is provided by a GPS but in case of failure of this device the altitude is obtained from pressure measurement Failure Detection Isolation and Recovery approach is being considered to reach that The main parts of the control software are divided into functional groups one for each of these specific tasks 1 Moni
97. ell as by means of some freely available R packages and MATLAB codes 7 1 2 Sample analysis After recollection of the experiment the samples will be extracted in a safe way and transported to our facilities at the University of Bologna where the following analyses are going to be performed SEM The Scanning Electron Microscopy SEM is a method for high resolution imaging of surfaces The SEM uses electrons for imaging as well as light microscope uses visible light The SEM generates a beam of incident electrons in an electron column above the sample chamber The electrons are produced by a thermal emission source such as heated tungsten filament or by a field emission cathode The energy of the incident electrons can be as low as 100 eV or as high as 30 keV depending on the evaluation objectives The electrons are focused into a small beam by a series of electromagnetic lenses in the SEM column and directed towards the sample Ihe incident electrons cause electrons to be emitted from the sample due to elastic and inelastic scattering events within the sample s surface and near surface material High energy electrons that are ejected by an elastic collision of an incident electron typically with a sample atom s nucleus are referred to as backscattered electrons The energy of backscattered electrons will be comparable to that of the incident electrons Emitted lower energy electrons resulting from inelastic scattering are called secondary
98. epresents a specific step of the mission and requests its own specific routine to be correctly performed The mission will be successful if no state will fail The successful completion of one state is the essential requirement to pass to the following one This kind of behaviour is the most likely and desired Nevertheless some shortcuts are necessary to make the system to be a real state machine Therefore the software should manage to switch from a state to another one not necessary the following one In Manual Mode this is simply requested by user using a dedicated button that activate on board software changing in status phase In principle this command is available also for the Autonomous Mode since a shortcut exists Balloon landed Vclimb 0 successfully power on Pro checklist not decreasing altitude PRE LAUNCH completed Vclimb 0 DESCENT B 1 OR error in test decreasing altitude checklist successfully Vclimb lt 0 completed KC constant C SAMPLING A5 Unibo wie constant altitude MISSION CH altitude 0 open valves increasing altitude Vclimb gt 0 closed valves SAMPLING CLIMB increasing altitude INITIALIZATION p Vclimb gt 0 steady altitude Vclimb 0 Page 103 Student Experiment Documentation Pre Launch Enter condition Main power on Exit condition All tests successfully passed Operating Mode Manual EUROLAUNCH A DLR and SSC cooperatio Descripti
99. eriment Documentation Routan 85 cooperation Temperature sensors 1 11 10 11 1 LM35DZ HIH9120 021 BUCK BOOST 12V 0 4A 2 8 Pressure Sensor 1 01 Beams and plates 75 1 75 75 mM ke GPS Adafruit 40 497 7285 1 ND IC REG 0 4 5 2 LDO 3 3V 0 1A LT3080EST TRPBFCT 14 24 ND omre Ian 70 Consumables cables 1 9 wire etc Modular Plastic Storage Boxes Printed circuit boards SB1 SB2 200 3 Power Control Unit 200 1 200 Launch campaign 1500 4 6000 Travel and accommodation C Page 34 EUROLAUNCH A DLR and SSC NUN Student Experiment Documentation Travel and 350 accommodation CDR Taxes Robot ltaly 48 65 1 4865 rn pe FML Flight Mechanics Laboratory funds DEC Department of Environmental Chemistry BOXER Boxer Pumps In table 3 3 3 all the components needed for the project are mentioned The instruments ordered are shown and yellow while the ones already present in the laboratory are shown in green The LOAC Optical Particle Counter will be purchased by FML and DEC jointly As shown in table 3 3 4 ESA is our biggest sponsor regarding Travel and Accommodation since it pays for the participation of four team members at every project related event The estimated amount sponsored is of 11400 Table 3 3 4 ESA as Sponsor Travel and 1000 4000 oponsored accommodation PDR Travel and om Pe mem accommodation CDR La
100. es PRI Measurements for particles size distribution shall be made at a rate of at least 1 measurement every 20 s corresponding to a vertical resolution of 80 100 m given the average ascending speed of 4 5 m s R JJ JJ PR2 Measurements for ion densities shall be made at a rate of at least 1 measurement every 20 s corresponding to a vertical resolution of 80 100 m given the average ascending speed of 4 5 m s PR3 The temperature measurements outside the balloon 14 should be possible in a range between 90 and 30 C PR4 The temperature measurements outside the balloon data sheet should be made with an accuracy of 0 2 C T R T T R PR5 The pressure measurements shall be possible in a R T range between 10 and 1100 mbar The pressure measurements shall be made with an accuracy of 1 mbar appendix PR7 The humidity measurements should be possible in a M range from 0 to 100 RH data sheet PR8 The humidity measurements should be made with an accuracy of 2 data sheet The pump shall suck a nominal flow rate of 9 l min at stratospheric conditions in order to maximize the JJ efficiency of the collecting filter Page 125 Student Experiment Documentation Rotana 85 cooperation PR10 The altitude shall be measured with an accuracy of 40 TM m PR11 The coordinates shall be measured with an accuracy of data sheet 40 m PR12 Ihe temperature measurements i
101. est Zen insieme A tee owe putre Enio gl klamm ci Ford propongono us wuger rip Bees cfumato AL Advanced Abram parta Aeros hog t on and Aon s Steam suparvizionato da Laura Tositzi doceece di Valutazione ambiente e Mimi Ze V quisa d Operatic di Cirata G Liaricen del Alma Water dalla ade dal toam d ncerca War Serrano Cantils dal Sacente di Meccarica de volo Petrino Gol etti T zrogetto spiega Guleni rest student e 3979 oe che lo stanno perra da sort Noc siamo y um suppnea LESA trito che amp ia arramo un docente di ofer resto roi garantiamo pet le Suttore e ordt una soria di gentoridt Nel lempa ii gruppo 3 4 progmeceamente alargata ome al mee abew d ingegneria Aercaparile s sor agguinti studenti d Sjenre chela Tera e hegre Elettracca OF ebievitei principali delfespenirmente sone due diste is Wacoal cogli Manner lee ccc sirewea in contatore ci tore kurs dinamiche del meccanarme di formazione dele muti che nelle rantagunnze prasirte petrehbeeo mig org le previsioni meeerecoing ehe Vn il pogano per me va sive corri maa Ciubetti in futuro S gor ache Imbarcare ko strumento di misurazione sa GON e aw azane Prammer simane co pi a tans custa Inctre uriaperianaa moto ormativa per APR Po d Z re r n Con un properme ESA oo dew oe retkgere spense onde dsmarnde des wore npettere le ecacterye r Leenrare in inan F lancio det palone sonda previsto per ottobre nell Ler enge Spece Conter a
102. etter estimation of the power consumption Table 4 7 1 Power line one PL1 Selz e N Page 93 EuROLAUNCH Student Experiment Documentation Rta 85 cooperation 100PDxNC12 1 32 48 B MUERE sal pe fee E en ESC motion 0 024 A 0 0 0 T 2 52 Wh 450 180 900 6 3 nam DEAC IENE relay 56 12 238 9 ENER E Figure 4 7 1 shows the power consumption profile over time for PL1 As shown the peak power consumption during sampling phase is approximately 56 12 W while the total energy consumed is 238 9 Wh Since both these values exceed the performance of the Gondola supply an external battery pack has to be used Electronics Pump Finch Valves Total PL 1 Power Y Timeline hours Figure 4 7 1 PL1 consumption profile Page 94 EUROLAUNCH soprat Student Experiment Documentation 4 7 2 Power lines two and three overview PL2 PL3 The power budget for these lines was estimated considering the following assumption e All the instruments are kept on for the whole duration of the flight with the exception of the descent phase 7 hours in total Table 4 7 2 Power line two PL2 Componen Curren Voltag Total Total Mosfet 0 06 Optical Particle 1 7 045A 72V 344 049 3 24 55 6g wh W A W Counter Temp Sensor 60 uA cl 7 mWh LM35DZ H Heaters 7 9 15 22 5 Switch 7 5 7 5 1 7 5 mA 1 5V 5 mA 52 5 mWh AQY211EH mW mW 7 2V DS 60 0 8 uA uW Trans 0 62 66 1 87 Total
103. fic Riccardo Elisa and Erika Sub Team 6 Sensor Interfaces Nani Alice and Abramo Sub Team 7 Project Management Documentation Nani and Riccardo At the moment most of the tasks are being developed on time although some new tests have been added and the dates of some others have been modified because shipping delays of key components for tests In Gantt chart it is also highlighted the current progress with a vertical red line As it can be seen we have some delays in the power subsystem due to the selection of a different model of batteries after CDR recommendations The mechanics subsystem has some delays in the acquisition of the components and consequently in testing due to the change of the design because of the change of OPC that is now substituted by LOAC But the structure beams and connectors are already in laboratory and the structure is being manufactured Regarding the electronics the design of the PCB and PCU has been finished and is ready to be sent for manufacturing The software team has one new member Svetlozar that has been selected in order to complete and support the Software amp GS subsystem team The software subsystem has improved a lot and they are ahead of schedule The thermal subsystem has finished the software modelling and is waiting for heaters acquisition for testing Regarding the secondary objective thus taking samples of aerosol A5unibo has performed many tests in order to interface in a correct w
104. g amp amp GroundAltitudeRang e NOTE Pre launch does not have a specific next state The only way to exit this dead state is to manually specify the next state via proper command message interaction SendCmd Manual Mode override OBDH can also switch to manual mode if GS requires it In this case all actuators are commanded exclusively via GS commands and for this reason monitoring the E Link connection becomes important Hardware Abstraction layer HAL Following interfaces have been adopted in order to better separate HW dependent parts from the control logic of OBDH This will meaningfully increase the testing capabilities of the software team Further details at absystem src obdh common hal h interface at code base 4 9 4 Failure detection A5 Unibo SW can detect and try to solve some possible errors Possible failures that we can control are related to OBDH sensors failure A5 UNIBO uses several sensors with different communication protocols 12C SPI UART and One Wire so it is important to monitor the correct working of each process so that it does not compromise the whole system A Watchdog timer is used to detect if the execution flow is blocked in a certain task for an excessive amount of time thus preventing the whole system to work The execution could be blocked by a code error or a fault in hardware e g an I2C sensor that never replies to a send data request The task that has caused the whole
105. ght R4 The experiment shall measure outside ambient pressure during the whole flight R5 The experiment should measure outside ambient relative humidity during the whole flight The experiment shall collect aerosol samples drawing air from outside the gondola during the floating phase in the stratosphere and make them available for post flight analysis The experiment shall keep track of its absolute position throughout the flight in order to relate the collected data to a particular height and coordinate FR8 The experiment shall measure the temperature inside the gondola in order to ensure the operational range of the instruments is not exceeded FR9 The experiment should measure the rate of air flow through the pump for the whole duration of the sampling phase FR10 The experiment shall save all the measured quantities on an internal SD R11 The experiment shall relay all the measured quantities to ground Page 23 Student Experiment Documentation EuroLAUNCH 2 2 Performance Requirements Table 2 2 1 Performance requirements Ref Requirement From PR1 Measurements for particles size distribution shall be made at a FR rate of at least 1 measurement every 20 s corresponding to a vertical resolution of 80 100 m given the average ascending speed of 4 5 m s PR2 Measurements for ion densities shall be made at a rate of at least FR2 1 measurement every 20 s corresponding to a
106. h test can be found at the REXUS BEXUS repository at https rexusbexus zarm uni bremen de share page repository in the TEST folder for our experiment Page 138 EUROLAUNCH A DLR and SEC cooperation Student Experiment Documentation 6 LAUNCH CAMPAIGN PREPARATION 6 1 Input for the Campaign Flight Requirement Plans 6 1 1 Dimensions and Mass Experiment mass in kg Experiment dimensions in m 450mm 445mm 412mm Experiment footprint area in m Experiment volume in m Experiment expected COG centre 300mm x axis of gravity position 2 0mm y axis 210mm z axis 6 1 2 Safety Risks Risk Mitigation precaution measures OPC s laser OPC contains a class 3B laser diode 635 nm 25 mW whose light beam is totally confined under normal operation If this is the case it is graded as a Class 1 Laser product and is of no hazard to the user Anyway it will be marked with the following warning sign Batteries MP 176065 Integration SAFT batteries are reliable but risks related to common batteries still exist and in particular explosion due to over exploitation The following mitigating solutions are implemented e Detailed power budget calculations and tests are performed Current limiting switches are inserted to avoid pulse discharges and overconsumption Battery packs are kept in a separate closed box BHA covered with aluminium plates and labelled with a warning sign Pump Pump may overheat due to friction
107. he properties of the planet s surface since different materials can lead to absorption in certain wavelength bands The fraction of the solar radiation which is reflected is Ja BEDO A AN um 5 Where p or a is the bond albedo coefficient at 0 5 um Thermal input due to the planetary radiation which depends on the temperature of the planets surface and the mutual position of the spacecraft and the planet QPLANET A T PLANET T P j i PLANET Is the absorption coefficient of the surface for a 4um wavelength Page 171 l EUROLAUNCH Student Experiment Documentation ees aaner S the emissivity coefficient of the planet s surface at the same wavelength e Thermal output towards the sky background at 3 4 K temperature which is assumed to behave like a black body The heat flux qsky emitted by the node towards the sky background is given by the following relation Qacy AT Een i By the knowledge of all other view factors previously calculated the view factor F sgy is computed as follow e Heat exchanges between internal nodes n qi AiGi 1 Fi i H A Fi G j 1 j i Where Gis the radiance and has been calculated solving the following linear system n AjGi AiJ li AF j l Where J ejoT and r 1 Conduction The conductive heat exchange between adjacent nodes is given by the following equation TT dg oond i A dA A Convection Heat exchange by convection bet
108. ian data representation is used according to Arduino since LabVIEW uses Big Endian bytes are switched on GSS The design of the OBDH control logic is based on an architecture inspired by IEC 60848 SFC The design team decided to adopt a simplified model due to the low complexity of the mission flow determined in problem analysis phase 4 9 3 On Board Data Handling OBDH Types of task e Sporadic S executes once when activated Sporadic tasks are pulsed after a state transition e Periodic P executes several times according to a specified period Periodic tasks can be stored which means they keep on running even after the deactivation of their launching state or non stored which means they keep running until their launching state remains active and reset when a state decides to shut them down enable for idle Communication links ON Sensors OFF Data loggers OFF Valves OFF Pump ON Air lon Counters OFF Particle Counter OFF GPS ON enable for climb Communication links ON Sensors ON Data loggers ON Valves OFF Pump ON Air lon Counters ON Particle Counter ON GPS ON enable for float e Communication links ON e Sensors ON Data loggers ON e Valves ON e Pump ON Air lon Counters ON Page 118 DUR and SSE cooperation Student Experiment Documentation e Particle Counter ON e GPS ON enable for descent S NA e Communication links ON e Sensors ON Data loggers ON e Valves OFF e Pump ON Air lon Counters ON e Particl
109. icle Counter Printed Circuit Board electronic card Preliminary Design Review Proton induced X ray Emission Payload System Test Remove Before Flight Storage Device Student Experiment Documentation Scanning Electron Microscope Support Frame Assembly Swedish National Space Board Start Of Data Storage Student Training Week Sampling Unit Software To be confirmed To be determined Unsigned long Work Breakdown Structure Zentrum f r angewandte Mikrogravitation Raumfahrttechnologie und Page 152 8 2 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 ROLAUNCH Eu oL Student Experiment Documentation References Climate Change 2007 The Scientific Basis Contribution of working group to the Fourth Assessment Report of the Intergovernmental Panel on Climate Change Cambridge University Press Cambridge UK Albrecht B A 1989 Aerosols cloud microphysics and fractional cloudiness Science 245 4923 1227 1230 Svensmark H Friis Christensen E 1997 Variation of cosmic ray flux and global cloud coverage a missing link in solar climate relationship J Atmos Solar Terr Phys 59 11 1225 1232 Carlslaw K S Harrison R G Kirby J 2002 Cosmic Rays Clouds and Climate Science 298 5599 1732 1737 Lee et al 2003 Lower Stratosphere Particle Formation by lon Nucleation in the Upper Troposphere and Lower Stratosphere Science 301 1886 1889 Kirby J et al
110. ight WCC1 S Temperature Celsius External wal temperature ie Supeno air temperature 70 Intenor air tamperature Gondola temperature Baltenes temperature External temperature Temperature Celsius Estamal wall temperature Spenn air temperature Inferior ar temperature Gondola tempersture Battenes temperature Estemal tamparature Time s Figure 4 6 3 WCC 2 Temperature Celsius Temperature Celsius Page 90 EUROLAUNCH Student Experiment Documentation Temperature trend during flight WHC1 D 10 20 30 40 60 SI Extemal wall temperature Supenor air tampersture 7D Wfenor air Temperature i Gondola ternperaturs Battenes temperature 80 Extemal temperature a 2000 4000 6000 ani 10000 12000 14000 16000 18000 Time 5 Figure 4 6 3 WHC1 Temperature trend during flight WHC2 20 o FRIES PREPA RE SIRES d OTN NTE EE E DEE Re RC TRI S 0 d n geen icai per KREE EES e TT d 1 ri 10 i EI A ae I U an V W wl _ gena wil temperature KH upang sir Termperatura a LL Ta C Se NE NI 9 Gondola temperature ke run dol wv a e Bsttenes temperature a Extemal temperature E NN V D 2000 4000 000 68000 10000 12000 14000 16000 13000 Time s Figure 4 6 2 Worse Hot case 2 Page 91 EUROLAUNCH Student Experiment Documentation ADR and SSC cooperation Temperature Celsius Temperature tre
111. impossible to occur B Low Small chance to occur C Medium 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 Table 3 1 Example of risk index and magnitude scheme Probability F Severity 5 Table 3 5 1 Risk Register y o ID Risk and consequence PxS Action R1 Valves fail to open C 3 Execute tests to ensure that Student Experiment Documentation MS preventing samples collection R2 MS Valves fail to close causing the risk of samples contamination R3 MS GPS fails leading to unexpected opening or closing of valves R4 MS GPS fails to determine experiment s position R5 MS Communication fails R6 Landing in water soaks MS Instruments and samples R7 Required level of B EN cleanliness is not achieved R8 Static charges D EN accumulate interfering with AIC reading R9 Vibrations affect B EN instruments performance and SD R10 Electromagne
112. ips and ideas on how to keep pumps clean Environment during Launch will be dirty Hercules balloon pad Ascent cleans balloon of dust with goes to gondola measurements during ascent are from ground Team clarified that Optical Particle Counter is not a real laser more a light put in SED Team will not sample during descent No flight requirements Organisation project planning amp outreach SED chapters 3 1 3 2 3 3 amp 3 4 Pictures for team members would be nice Include a contact phone number for the student team WBS is clear White is hard to read Testing what in subsystems in unclear team clarified it means for assembled experiment add also progress how far along you are here we only see what you intend to do when Colours in Gantt chart unclear Map the availability of the team over the year to the workload shown in the Gannt chart to be sure you have sufficient resources at the right times Update budget in document Budget for traveling delivery cost of components spare components missing Add column of who is paying so we know what budget you have and what is missing include everything even if you get it for free from sponsors Use tdb instead of Nothing about outreach in appendix more information needed copied or articles screenshots of websites Put logo in outreach section description Facebook website additionally also in Italian Website ZARM logo missing more pictures add RXBX section link t
113. k_confirm_descent If DecreasingAltitudeFlag is marked do AskForConfirm interaction set WaitingConfirm flag and initialize WaitingConfirm Time If IncreasingAltitudeFlag is marked and WaitingConfirm is set update WaitingConfirm Time If WaitingConfirm Time is greater than WaitLimit change state Page 120 Sere Student Experiment Documentation autonomously and reset flags monitor_altitude 0 5 s e Read pressure sensor e Determine when altitude is increasing and set IncreasingAltitudeFlag StationaryAltitudeFlag Or DecreasingAltitudeFlag e Setaflag ExperimentAltitudeRan ge when stabilized around 25000 30000 m e Also set GroundAltitudeRange when stabilized around 0 2000 m eee States and transition initial NA pulse check_systems store poll for message sense status and send Climb pulse go auto enable for idle store monitor altitude no store ask confirm climb Climb IncreasingAltitudeFla Sampling pulse enable for climb g AckReceivedFlag Init Sampling StationaryAltitudeFla Sampling no store open valves g amp amp pulse enable for sample ExperimentAltitudeR no store ask confirm float ange amp amp AckReceivedFlag valves are open Descent no store ask confirm descent DecreasingAltitudeFl On no store close valves ag amp amp Ground AckReceivedFlag Page 121 l EUROLAUNCH Student Experiment Documentation ees StationaryAltitudeFla turn off
114. logna She got her bachelor in Atmospheric Physics and Meteorology at the University of Bologna in 2003 with the thesis Techniques of data analysis and measurements in the Bologna area She graduated in Physics at the University of Bologna in 2010 with the thesis Composition of atmospheric particulate matter in Bologna Application of receptor modelling Now she obtained her PhD degree in Environmental and Geological at the University of Bologna dissertation thesis to be discussed in April 2014 with the thesis Origin and variability of PM10 and atmospheric radiotracers at the WMO GAW station of Mt Cimone 1998 2011 and in the central Po Valley Meanwhile since February 2014 she is assistant research fellow at the University of Bologna Concerning A5 Unibo experiment Erika is responsible of the scientific and theoretical analysis of the experiment Luca Mella Luca was born in Cesena in 1988 He worked a few years in the ICT industry before starting his studies in Computer Engineer at University of Bologna in 2008 He actively participated in several off lecture initiatives and began to coordinate the CeSeNA Security group in 2010 a Unibo study group which takes part in security competitions around the world aka Capture the flag Luca took his bachelor degree in fall 2011 with the thesis Rilevamento di attacchi di rete attraverso protocolli di monitoraggio per router IP and continued his studies with a Master on Com
115. mbly Integration and Test BD Back scatter Diffraction detector BHA Battery Housing Assembly BJT Bipolar Junction Transistor CCN Cloud Condensation Nucleus CD Cloud Droplet CDR Critical Design Review CR Cosmic Ray CRP Campaign Requirement Plan CRT Cathode Ray Tube DLR Deutsches Zentrum f r Luft und Raumfahrt EAT Experiment Acceptance Test EAR Experiment Acceptance Review ECU Electronic Control Unit EHA Electronics Housing Assembly EIT Electrical Interface Test EPM Esrange Project Manager ESA European Space Agency Esrange Esrange Space Center ESTEC European Space Research and Technology Centre ESA NL ESW Experiment Selection Workshop FAR Flight Acceptance Review FST Flight Simulation Test FRP Flight Requirement Plan FRR Flight Readiness Review GS Ground Station GSS Ground Station Software GS ACK Ground Station Acknowledgment GSE Ground Support Equipment HW Hardware HK House Keeping HID Human Interface Device ICD Interface Control Document IHA Instruments Housing Assembly IN lon Induced Nucleation IPR Integration Progress Review Student Experiment Documentation IR LT LOS Mbps MFH MORABA OP OPC PCB PDR PIXE PST HBF SD SED SEM SFA SNSB SODS STW SU SW TBC TBD UL WBS ZARM Page 151 DLR and SSC cooperation Infra Red Local Time Line of sight Mega Bits per second Mission Flight Handbook Mobile Raketen Basis DLR EuroLaunch Oberpfaffenhofen DLR Center Optical Part
116. measurement every 20s up to an altitude of at least 10 Km The AIC s should measure the ion densities 3096 at a rate of one measurement every 10s up to the maximum altitude reached during the flight Aerosols Sampling The SU should collect enough particles to 10 96 alow for SEM analysis and it should guarantee that particles are stratospheric rather than tropospheric The SU should collect enough particles to 2096 allow for SEM and PIXE analysis and y Ray spectrometry Moreover it should guarantee that particles are stratospheric rather than tropospheric and sort the samples by their size between the different filters Page 145 l EuroLAUNcH Student Experiment Documentation ees D DATA ANALYSIS AND RESULTS 7 1 Data Analysis Plan 7 1 1 Atmospheric data analysis What we expect to gather during the flight is a continuous set of values for ambient parameters such as Temperature Pressure and RH and for lon and Particulate densities each one of them related to a specific height and time Acquired data will be processed for obtaining mono variant and multi variant statistical analysis descriptive statistics correlation analysis time series analysis and other multivariate statistical techniques such as cluster and factor analysis for instance will be performed on the acquired data matrix The results will be obtained by means of some commercial software such as Microsoft Excel Statistica OriginLab as w
117. mming with Labview Alicelgn cacM MA COL BH simulator far tesbrig GS under boundary conditions i ie a ae Communications and interlace with the HE Tle cel gor Lea Mattia S Thermal i Study the system propierties and temperature ranges xcci Marca Develope thermal strategy i nn Soana modellarion Selecting Heaters Ordenng heaters Delivering H amp arers AIT heaters sensors and Instruments EE Ven Bet SS5ysltem components El5ensors and Instruments Selecting hoo Abrama Nani Ordering fee Nani Acquisition i EEE Man Delivering i EEN Nani Al i i nnne aee Abrama ManiPaolo Riccardo OTesting Particle Counter Acquismon Test i i BancBaccardia Particle Counter Arduino Acquisition and Data Logging Te i NanbPaale Pump performance ar ground conditions i eee Nani ficcardo Pump performance at stramospherie cond ions i REEERE WaniRiccardo Pump Motion kp Control Ground Conditions i i E icRiccarda Pump Motion Mind Air Hoos Test GC i Alice Mani Pump Maion Mind Air Flow Test Bag NanicRiccardo Pump Ar Foos Tube Piit GL Vacuum Chamber i Nani Pump Ar Fica Tube Pitot GC Hangar I L Nani Student Experiment Documentation Pump Air Flaw Tube Pitat vacuum Chamber with Batte Pressure temperature humidiry sensor Test Pump Vibration OPC performance at ground conditions OPC performance in near vacuum Conditions AC Analog Signal to ADC AUC performance at strataspheric conditions Va
118. nd batteries shall be marked with a specific danger sign more details given in chapter 6 DR15 DR16 All components used for the collection of aerosol samples shall be clean to ensure that particles collected are stratospheric rather than contamination DR1 The pore size of the aerosols collecting filters shall be 0 5 um to ensure collection of small particles Page 25 Student Experiment Documentation Rotana 85 cooperation A sealing barrier shall be used to ensure that the components used for the collection of aerosol samples remains clean during assembly testing and integration A blank control sampling filter shall be added identical to the sample holder to monitor the environment during pre launch launch and flight and assess any possible contamination Software requirements SW shall be compatible with HW SW shall not crash in case of error Handle failure SW shall monitor running time of each loop and eventually interrupt it avoid delays in running time SW shall restart in case of failure not be compromised in case of power loss SW shall not be locked in manual mode in case of data link loss SW shall continue to work correctly in case of failure of some devices SW shall store all collected data without any losses SW shall not overwrite or corrupt stored data SW shall use redundant data in the determination of descending phase start meaning rely both on GPS and pressure data to determin
119. nd during flight WHC cold due to external air 7 E lemal wal temeerals Duperor ae temperatum irferior sir Ier persturt cedola lemperature Hattanas temparatune Extemal temperature SULL JERE 6000 SUCC ILL AG 14000 16000 12223 Time s Figure 4 6 4 WHC cooling due to airflow 4 6 5 Conclusions From the previous simulations what we can conclude is that Flight during the day is preferable and will be assumed from now on Heating is needed for the batteries and a 5W amount is sufficient to keep the temperature within the desired temperature of 0 C Electronics superior air in graphics never get below 10 C in WHC2 simulation so heating will probably be unnecessary for ECU Comparing WHC2 with WHC cooling which assume respectively a 10 W heating and a 10 W cooling for the instrument housing assembly inferior air in graphics we see that lowest temperatures vary between approximately 25 C and 48 C respectively While the former is an acceptable value for almost all components the latter is unacceptable and hence depending from the real cooling effect of the airflow a total amount of heating required is between 10 W and 20 W However even in the worst case scenario the big safety margin in power budget allows us to increase the amount of heating to critical components PT2 tests will help determine the heat generation by pump and hence the amount of external heat required Page 92
120. nd this facility is currently unavailable at Esrange e Preparation and mounting procedures take a long time The total preparation time is estimated to be around 10 hours 1 hour for demounting 6 hours for cleaning 2 hours of filter weighing and 1 hour of mounting and other 24 hours are required for filters conditioning e Instrumentation needed for conditioning and weighing of the filters is fragile and expensive and therefore shipping could be dangerous More details about filter preparation can be found in appendix In the following table a list of the activities to be performed at Esrange is provided Note that some timing should be adjusted later on during the project development since these are just estimations Page 141 Student Experiment Documentation Routan 85 cooperation per We me dei o 1 hour Cleaning of critical components tubes Erika Elisa pipes and inlets using ultrasonic bath 1 hour Cleaning of non critical components box Erika Elisa valves and mounting provisions with cleaning solution 2 hours Mounting of the Sampling Unit Riccardo Erika Elisa aye 1 hour Instalment of the SU in the experiment Riccardo Paolo Placement of the RBF seal Riccardo Paolo 6 3 Timeline for Countdown and Flight ho A5 Unibo will take part of BEXUS 18 launch in October 2014 Table 6 3 1 Pre flight operations Visual check of accessible electronics battery and probes Check battery cha
121. ng shall be supplied with a sufficient number of brackets or a bottom rail plate to facilitate safe mounting of the experiment DR12 The experiment housing shall have mounting provision to interface on to M EGON gondola Page 126 DLR and SSE cooperation Student Experiment Documentation DR13 A panel mounted connector for the E Link of the type Amphenol RJF21B must be used DR15 Components that can represent a possible hazard for the recovery team OPC s laser and batteries shall be marked with a specific danger sign more details given in chapter 6 DR16 All components used for the collection of aerosol samples shall be clean to ensure that particles collected are stratospheric rather than contamination ae DR17 The pore size of the aerosols collecting filters shall be 0 5 um to ensure collection of small particles A sealing barrier shall be used to ensure that the components used for the collection of aerosol samples remains clean during assembly testing and integration DR19 A blank control sampling filter shall be added identical i Co pre launch launch and flight and assess any possible contamination SH3 SW shall monitor running time of each loop and SR5 SW shall not be locked in manual mode in case of data link loss SR1 SW shall be compatible with HW ST1 eventually interrupt it avoid delays in running time SI R T STI R T SH6 SW shall continue to work correctly
122. ns that has as main goals the prevention in the environmental field to protect the health of the population and promote sustainability Website in three languages English Italian and Spanish 8 2 3 Other Outreach Page 163 Student Experiment Documentation EuroLAuNcH ERIN IONIA e wew The 5f com m m _ _ __l p nm _ _____n __ _ ___ What is A5 Unibo experiment AS is a scientific experiment whose aim is to study the mycrophisical processes involved in cloud formation It will fy on the 18t Bexus baloon that will be launched from Kiruna SWE on the of October 2014 The experiment consists mainly im two different phases The first one is the in stu measurement of key parameters involved in cloud formation such as humidity temperature pressure and particles size distributions In addition to these parameters also on densities wil be measured in order to assess if a ink between ionization rates and cloud formation can be found The second is the collection of Stratospheric Aerosols that will be performed with the use of samping fiters These samples wil then be recolected and analysed in laboratory to gather information about aerosol s composition and properties Some of the above mentioned messuremetns will require the development of brand new intnimente arri deen seen the inramarite nf commernal eee Ion werk cenmeriy in the harsh 8 2 4
123. nside the gondola 13 14 R T shall be possible in a range from 20 to 50 PR13 The temperature measurements inside the gondola data sheet shall have an accuracy of 1 C DR1 The experiment shall withstand static vertical loads of A 10 g and horizontal loads of 5 g DR2 The experiment should withstand landing shocks of up to 35g DR3 The experiment shall be able to operate while exposed 13 R T to outside temperatures down to 15 C for the whole duration of pre flight phase DR4 The experiment shall be able to operate while exposed 14 R T to outside temperatures down to 80 C for the duration of the flight DR5 The experiment and in particular the SD shall T3 R T withstand storage temperatures down to 15 C for the duration of the recovery procedures up to 48 hours R8 Integrity of samples shall be guaranteed in case of water T5 R T landing DR7 On the outside of the experiment housing two 4 pin connector type MIL C 26482P series 1 connectors shall be installed in order to access the gondola s power bus D The experiment batteries shall be qualified for use ona T1 T BEXUS balloon The experiment batteries shall either be rechargeable or 18 A T shall have sufficient capacity to run the experiment Analysis during pre flight tests flight preparation and flight DR10 Ihe batteries in the gondola mounted experiment 18 R T should be accessible from the outside within 1 minute The experiment housi
124. nward negative Z axis acceleration force of 10g Components such as the filter holders pumps batteries and electronics were simulated as point masses coupled to their respective mounting plates The plates which are mounted on the Enidine wire rope springs have instead been considered directly linked to the frame and hence constrained in all degrees of freedom The Enidine wire rope springs were not simulated considering a conservative approach The model was meshed in SolidWorks Simulation Input data e Material 6061 T6 Aluminium alloy e Young s modulus 71 GPa e Density 2 77 x 10 6 Kg mm e Poisson s ratio 0 33 e Yield stress 276 MPa The following table summarizes the performed analyses and the safety factors identified for the structure Table 4 4 2 Structural analysis summary Page 60 EUROLAUNCcH Student Experiment Documentation Mood reme uire Din 2 40 Study rare Shay Pol hype Sd room chess Sent Deran cw 24 170 von Mees Mer 51 N ECO 32 01120 00 0 41208 2460 958 478 2722 331472 206 0 2 865 X0 d M 058 AM 0 19 255 468 0 14 4445435 IER STG 4539551 2 Z3NA0 b yeu obey 275008 0003 Figure 4 4 10 Von Mises 10 g vertical Mods reme tuire Stm 2 40 Study rare Shoyi Pot hype Gaio dese edet Deng emet Deren cw 24 178 USES inei 1 339000 17 2500 155 4990C 1 s 1 1290 0C See LX Ae vs 6106 7 48378 Er 2222 D n 1 tte gi 1900 209 Figure 4
125. o our website ZARM SSC etc include links for the Institutional partners 5 Internal Panel Discussion Summary of main actions for the experiment team Detail electronics Need information in chapter 6 PDR Result conditional pass Next SED version due SEDv1 2 on March 24 Page 157 EUROLAUNCH Student Experiment Documentation Saree Critical Design Review CDR BEXUS Experiment Critical Design Review Flight BX18 Payload Manager Simon Mawn Experiment AS Unibo Location ESTEC Noordwijk the Netherlands May 8 2014 1 Review Board Members Kristine Dannenberg SNSB Nick Panagiotopoulos ESA Alex Kinnaird SSC Piero Galeone ESA Gunnar Andersson SSC Natacha Callens ESA Maria Roth DLR Nora Newie ESA Simon Mawn ZARM Document Review only Dieter Bischoff ZARM Lucio Scolamiero ESA Julia Gr nhage ZARM 2 Experiment Team Members Nani Serrano Danilo Boccadamo Abramo Ditaranto Alice Zaccone Riccardo Lasagni 3 General Comments Presentation o Reading of the slides a lot o Very technical details good but overall concept was missing to understand the detail Avoid blank pages Introduce acronyms first time you use them Include bookmarks Reduce size of file Some information is in wrong chapters Internal references are not working maybe problem with pdf ing as they are blue coloured Footer is missing Sometimes you start a new line in the middle of a sentence Ver
126. of the components and instruments Red line current Status Green line progress line Page 170 EUROLAUNCcH Student Experiment Documentation APPENDIX D THERMAL DESIGN DETAILS Thermal exchanges In this section the exchanged thermal fluxes used for the Thermal Analysis of section 4 6 are listed and described Radiation Thermal input due to the solar radiation The direct solar flux also called solar irradiance is inversely proportional to the square of the distance to the Sun The assumed value for the solar constant is J 1367 Wwn The solar input gsun for each node can be calculated with the following equation sun 3 AF ant s is the absorption coefficient of the spacecraft surfaces at 0 5 um wavelength The view factors have to be determined with the following relation F sun TA l COS COS x e Sem dAsuy i AB Thermal input due to the albedo radiation which is the fraction of the solar radiation that is reflected by the planets surface is highly dependent on the surface s optical properties To a first approximation the planet can be considered a Lambertian body therefore the radiation is uniformly reflected back into space in all directions The albedo radiation can be assumed to have the same spectrum as the solar radiation therefore the maximum of the spectrum corresponds to 0 5 um visible wavelengths the actual albedo radiation spectrum can change depending on t
127. omponents range 85 Table 4 6 2 Node numbering and archtechure cccccceccceeceeeeeeeeeeeeeeeeees 171 Table 4 6 3 Node PropertieS ii 172 Table 4 6 4 List of materialS ri 172 Table 7 I eg e el CR E NEE 92 Table 4 7 2 Power line two PL2 94 Table 4 7 3 Power line three PL3 eeeceeesseeseeeeeeeeeeteeeteeeeeeeseteeeeeeees 94 Taber 4 PLA OV CIVICW aa 97 Table 4 7 5 PL2 4 PLES Re TEE 97 able 4 8 1 Preslaunen stfale erat 103 Wable 4 9 2 el 104 Table 4 8 3 Gib Stale sio due deri uode due 92 093 0 2 Decide ede eo det Dexia deu duode 105 Table 4 8 4 Sampling Setup State ccccccccccsseeccssecceececseseeseeeesseeeessaeees 106 Table4 5 5 Samplih g SESTO iate tratarse etn talia 107 Table 4 8 6 Descent EE 108 Table 4 8 Datagram SIr clUte o ei lisina 109 Table 4 8 8 UPLINK COMMAND datagram eese 109 Table 4 8 9 DOWNLINK ACK datagram ccccccesceeseeeeeseeeesaeeeesseneesseees 110 Table 4 8 10 DOWNLINK REQUEST CONFIRM datagram 111 Table 4 8 11 UPLINK RESPONSE datagram c ccccccecseeeeseeeeaeeeeeeeeens 111 Table 4 8 12 DOWNLINK datagram eere 111 Table 4 8 19 Kee Re EE 112 Table ANNUI M 123 Table 5 1 1 Verification Matix err 123 Table 5 2 1 Software test 2 Errore Il segnalibro non definito Table 6
128. on Pre Launch state is a checklist go no go of the functions that need to be performed to initialize the instruments Starting sequence calibration test etc Each instrument is powered on and successfully tested first of all GS communication If the component is properly working the checklist goes on otherwise an error arises and the component is restarted or fixed Communication links d Start Sensors Data loggers Set MANUAL Mode Air lon Counters Particle Counter Reboot YES Table 4 8 1 Pre launch state Perform test on n th component NO n4 YES Set Set AUTONOMOUS Mode IDLE State Figure 4 8 1 Pre launch state Page 104 EUROLAUNCH RUN end 80 ec Student Experiment Documentation Idle Enter condition All tests successfully passed Exit condition GS submits a request for launch or the altitude starts increasing Operating Mode Manual Description In Idle state ECU is in a stand by status in which power consumption is reduced to minimum levels nevertheless GS communication GPS and AICs still operate Idle phase is left after GS request or if GPS detects a significant increase in altitude a Start Jj Check altitude Communication links FF sensors O Data loggers Valves GS NO Air lon Counters communication Particle Counter GPS NO
129. onsider using a pack of 8 SAFT MP176065 rechargeable cells This pack will provide 200Wh of energy and can handle currents up to 10A then use switching regulators to create secondary voltages Team should use batteries within specifications at 20C you will have 50 of batteries power team clarified this was worst case simulation to decide if heaters are necessary OC would be better for batteries Heavy load on battery gives you less power especially at low temperatures chosen battery is not suitable for BX you are on limit of battery s power Consider adding some high power DC converters to account for high power needs Remember that your own battery will discharge during countdown not connected to Hercules umbilical team clarifies they have spare battery packages Overview of power consumption diagram time power amp consumed energy should be included easier for you to see when you have highest currents Include a simple quick glance diagram for the power supply so we can see what includes your own batteries what is powered from BEXUS and how A timeline of not only power but whole mission data rates buffers transmissions software is very helpful No BEXUS power required included in electrical interface but mentioned in power system P74 a 3 wheel diode is missing over relay You should have recovery diode in parallel to the relays you use as seen on presentation Don t use melting fuses use current limiting
130. output current Heater Board It will be powered by the 28V gondola battery without any voltage regulator LOAC It works at 7 2V and 450mA of current For this purpose we have used the adjustable switching voltage regulator DE SWADJ that regulates the voltage at 7 2V Figure 4 5 22 shows the schematic regarding the switching and current limiting section of the PCU board For the switching of the three main power lines we used two different types of relays For PL1 we used a GSLA relay that can quietly afford 4A of current For PL2 amp PL3 we ve used a solid state relay AQY211EH that allows the passage of 1A maximum of current So in the 28V line two of them have been paralleled Page 81 Student Experiment Documentation EuroLAUNCH J E Lun e EN d T e T gl f Figure 4 5 22 PCU Switch and Current limiting block For the current limiting an IC of the type MIC2545A has been used due to its flexibility since it has a wide choice of current limiting up to 3A Because of its supply voltage which is between 2 7V and 5 5V a voltage divider has been added considering possible current flows inside the IC Verification test will be done Page 82 EUROLAUNCH i TORANN Student Experiment Documentation Finally some photo transistor opt couplers FOD817 series have been used in order to exchange signals from voltage referred to GROUND IN and voltage referred to GROUND DIGITAL i 5 q
131. output lines will be needed during the tests to simulate PL1 and PL2 e Compressed air blower for AIC s cleaning e A cleaned room where to assemble the SU and install the Sioutas Page 140 EUROLAUNCcH Student Experiment Documentation Sampler once delivered at Esrange In addition to these we will also bring with us the following items necessary for the sampling unit preparation e Analyslide Petri Dishes e Cleaning solution isopropyl alcohol e Stainless steel forceps e Particle free gloves e Ultrasonic bath to clean the pipes and all the components exposed to the airflow 6 2 2 Flight requirements We have no strict requirement about the flight however as explained in section 4 3 4 a flight duration of at least 3 or 4 hours would increase the chance of a meaningful particle detection Moreover to reduce the amount of heating to be given by the foil heaters a daytime flight is preferable due to the presence of higher temperatures and of solar radiation 6 2 3 Preparation of the SU The Sioutas sampler will be prepared and mounted with the instalment of the filters at our facilities at the University of Bologna then the whole unit will be shipped to Esrange where it will be installed inside the Sampling Unit This choice has been made based on the following reasons e Aclean room of at least class 1000 or 100 if available is necessary in order to safely install the filters without the risk of contamination a
132. puter Engineering at University of Bologna During this time he had the opportunity to study and work on several challenging topics like computer vision distributed systems and embedded systems He took his master degree in spring 2014 with the thesis ICT Security Testing methodology for targeted attack defence tools Concerning A5 Luca contributes to the design and the development of the software systems and communications Page 21 E UROLAUNCH Student Experiment Documentation Mattia Baldani Mattia was born in Urbino in 1989 He lives in Carpegna a small town near Rimini He took his bachelor degree in Computer Engineering at the University of Bologna in 2012 He has experience in the development of large distributed networked systems embedded system design and programming Concerning A5 Mattia contributes to the design and the development of the software systems and communications Svetlozar Orlovski Page 22 DLR and SSE cooperation Student Experiment Documentation 2 EXPERIMENT REQUIREMENTS AND CONSTRAINTS 2 1 Functional Requirements See also Verification Matrix in chapter 5 Table 2 1 1 Functional requirements R1 The experiment shall measure particles size distribution outside the gondola during the whole flight R2 The experiment shall measure ion densities outside the gondola during the whole flight R3 The experiment should measure outside ambient temperature during the whole fli
133. rge Table 6 3 2 Flight sequence Flight sequence Page 142 EuvRoLAUNCH i DLR and SSE cooperation Student E Student Experiment Documentation Documentation H30 ECU preparation with E Link remote access A5 Unibo team physical Ethernet connection 20 30min Hemove all RBF objects BUT the SU inlet WARNING Removing SU inlet protection would expose the SIOUTAS to direct flow when checking valves If removed immediately reinsert it Perform structure visual inspection 15 min Switch on the ECU Perform hardware checklist 30 min start Pre launch test by GS 10 min max Turn on valves Turn off valves Start OPC data acquisition Start AIC data acquisition Check AIC offset switch Start AIC data acquisition Check AIC offset switch Switch on Pump Check control by ESC Motion Mind 10 owitch off Pump 11 Start Pressure sensor acquisition 12 Start Humidity sensor acquisition 13 Start Temperature sensor acquisition 14 Start GPS data acquisition Check battery charge if necessary substitute 5min Set SW IDLE state if checklist is verified T 4 T 3H30 Declare READY FOR LAUNCH Nani T 2H30 Payload moved from Cathedral EuroLaunch NO MORE PHYSICAL ACCESS TO GONDOLA T 1H45 Payload to launch position EuroLaunch T 1H30 Decision meeting Balloon Operations EuroLaunch T 1H Switch on pump by GS request Igor Start offset measurements the two AICS T 0H55 Remove all RBF objects and t
134. rge positive ion clusters and recent observations in the Upper Troposphere and Lower stratosphere have shown high concentrations of UCN s from 4 to 9 nm that indicate very recent particle formation consistent with numerical simulations for lon Induced Nucleation IIN 5 The search for a link between CR s and Cloud formation is also one of the main drivers for the CLOUD experiment conducted at CERN since 2009 where a chamber filled with atmospheric gases is crossed by charged pions that simulate ionizing CR s Some preliminary results suggest that indeed IIN is a relevant factor to determine nucleation rates in the upper troposphere 6 Page 14 EUROLAUNCcH Student Experiment Documentation 1 2 Experiment Concept The experiment we suggest has the advantage of covering a wide range of topics related to cloud formation We will mount an Optical Particle Counter OPC that uses back scattered radiation of a laser diode to measure particle densities and size distribution of aerosols throughout the whole troposphere and stratosphere with a size range from 0 3 um to 100 um Thanks to the slow ascending speed of the BEXUS balloon and the short sampling time of the OPC we will be able to create detailed vertical profiles for particulate matter and also CCN s and CD s In parallel to particle size distributions also ion densities both positive and negative will be measured throughout the flight with Air lon Counters leading to the
135. riment shall be able to operate while exposed to outside temperatures down to 15 C for the whole duration of pre flight phase The experiment shall be able to operate while exposed to outside temperatures down to 80 C for the duration of the flight The experiment and in particular the SD shall withstand storage temperatures down to 15 C for the duration of the recovery procedures up to 48 hours Integrity of samples shall be guaranteed in case of water landing DR7 On the outside of the experiment housing a 4 pin connector type MIL C 26482P series 1 connector shall be installed in order to access the gondola s power bus DR8 The experiment batteries shall be qualified for use on a BEXUS balloon The experiment batteries shall either be rechargeable or shall have sufficient capacity to run the experiment during pre flight tests flight preparation and flight DR1 DR2 DR3 DR4 R5 D DR10 The batteries in the gondola mounted experiment should be accessible from the outside within 1 minute DR11 The experiment housing shall be supplied with a sufficient number of brackets or a bottom rail plate to facilitate safe mounting of the experiment DR12 The experiment housing shall have mounting provision to interface on to M EGON gondola DR13 A panel mounted connector for the E Link of the type Amphenol RJF21B must be used Components that can represent a possible hazard for the recovery team OPC s laser a
136. ring experiment C 4 Arrange early shipping PE shipping to Esrange Help from university professors and technicians Use and update Gantt chart Set milestones Testing and introduction of GS override R28 Software program in TC micro controller fails during flight R29 Instruments are C Test and simulate resistance VE damaged at landing of the mechanical structure Dampers Page 44 EUROLAUNCcH Student Experiment Documentation 4 EXPERIMENT DESCRIPTION 4 1 Experiment Setup The experiment is composed of different sub sections each one with specific functions and features e Instruments Housing Assembly IHA It contains all the main scientific instruments the two AlC s the OPC the Pump and the Sampling Unit SU e Electronic Control Unit ECU It is located into the EHA and it contains the Arduino Micro controller the stacked PCB s pressure sensor humidity sensor power board and thermal control board e Battery Unit It is located inside the BHA and it hosts the two battery pack Figure 4 1 1 Experiment overview The core of the experiment is represented by the instruments inside the IHA e Optical Particle Counter OPC this device uses a pump to create an airflow through the inlet tubing and draw air from outside the gondola The air then passes through an optical system capable of determining Page 45 EUROLAUNCH Student Experiment Documentation A DLR and SSC cooperation th
137. rite num write a byte myWire read read a byte myWire crc8 dataArray length compute a CRC check on an array of data Page 177 Student Experiment Documentation wssesst cooperation UART The UART Universal Asynchronous Receiver Transmitter is an asynchronous serial data bus UART communication has two line for exchange data transmitting line and reciving line The Arduino Mega has four serial ports Serial0 on pins 0 RX0 and 1 T XO Seriali on pins 19 RX1 and 18 TX1 Serial2 on pins 17 RX2 and 16 TX2 Serial3 on pins 15 RX3 and 14 TX3 Lo RX TX es LoC LOAC External RXO 0 TXO 4 UART LIBRARY The UART communication uses the library lt Serial h gt The functions used are e Serial begin 9600 sets the data rate in bits per second baud rate e Serial available get the number of bytes characters available for reading from the serial port This is data that s already arrived and stored in the serial receive buffer which holds 64 bytes e Serial read Serialt read Serial2 read Serial3 read reads incoming serial data
138. roposal we wrote for funding and we expect positive results soon 3 3 5 Analysis and testing support facilities Flight Mechanics Laboratory of University of Bologna We have the possibility to perform sensor calibration measurements mechanical and electrical integration of the instruments and software programming and simulations The assembly of the instruments will be also performed there Micro propulsion Laboratory where we can performance vacuum chamber tests for our instruments We can do mechanical tests vibration in University of Bologna Hangar facilities Page 39 l EUROLAUNCH Student Experiment Documentation ees Dep of Chemistry G Ciamician University of Bologna offers the possibility to analyse the retrieved samples also thanks to their collaboration with external Laboratories PIXE Analysis c o Laboratori Nazionali INFN Legnaro PD Italy to determine trace elements 11 lt Z lt 92 SEM Analysis at BIGEA Dipartimento di Scienze Biologiche Geologiche ed ambientali University of Bologna useful method to observe single particles to determine their sizes and to identify the sources of emission of particulate matter 3 4 Outreach Approach The goal of this activity is to create a link between the general public and the work performed in Flight Mechanics Laboratory to encourage and motivate people s personal careers As outreach activities we would like to introduce students from schools universi
139. s battery pack was designed to feed PL1 which has a high demand in terms of power and could not be supplied by the BEXUS battery alone Moreover the use of separated batteries for the two lines ensures a better insulation between the different components of the experiment A scheme of A5 battery pack is shown in figure 4 7 3 Page 97 EUROLAUNCcH Student Experiment Documentation 175V RK 3 75 V H KH Ct 3 95 V em Fo IL 3 754 3 754 3 75 375 V 15 V 20 4 Ah 305 Wh d 175 H 375V opg KOU c 375 V Bi Figure 4 7 3 A5 battery pack The weight of each battery cell is 143 g while the total weight of the battery pack is approximately 2 Kg also considering cover and heaters Batteries performances degrade at low temperatures see MP 176065 Datasheet To compensate for this effect we will install foil heaters in each sub pack to keep their temperature close to 0 C and ensure sufficient available power for experiment oince the chosen batteries are rechargeable we do not need to buy more than one battery pack for the tests In total we need to buy e One flight battery pack e One battery pack for tests and for possible launch delays Tables 4 7 4 and 4 7 5 respectively show the overall performance required by PL1 and PL2 PL3 compared to the nominal values supplied by the battery packs As shown the safety margin in large for both the solutions adopted giving us both operational margin and
140. selected Experiment Selection Workshop ESA ESTEC information about selected Experiment Ak UNIRBC Selected POR deadline Sudent Training Week BEXLI COR ESATE I EL BEXLIS PRS BEXUS EAR EI SEXUS Launch Campaign Fral Student Report OfFrojea Management 11 8 Page 167 e Is o ba EUROLAUNCH ADLR and SSC cooperation Gtr 1 2014 Gtrz 2014 Qtr 3 2014 Qtr 4 2014 Qe 1 201 New Dec Jan Feb Mar Apr May Jun Jul Aug Sep Oct Now Dec Jan Feb 12 16 L 2 17 E l atta ES WW WD M WDR M Mami Fraject planning Review project planning Companies canracr Technical support feedback Fi Documentation E POR Recening doc from subsyspems FOR Gling format for PDR Preparing Sides POR ECDR Recehing doc from subsystems COR Clving format to the document COR Preparing Sides COR CPR Recehing doc fram subsystems ER Giving format to the document IPA Preparing ER visit FEAR Receiving doc from subsystems EAR Giving armar to the documen EAR Freparing Slides EAR FiSystem Preliminari experiment design Flighr planning m m mom m wmm m mEM M m wmm mmm mmm mmm ua mw SS eee eee Re m m mw m REE EB EH Sa a a Sa e a WR WR WR SS EE Riccardo H Riccardo E ren ESA Riccardo Ri Race arde S Riccardo GIS Riccardo Int Riccardo pos Riccardo I Urat ara n n Riccardo i m NN OM NN EM e es ge LM m Ww RR E E m M m mj Riccardo EuroLaAuncH ae ae TS Student Experiment Documentation
141. ss of the caught particles can be estimated as follows Be P up PLA 1 Mf nr Mp my Where C is the relative mass of the caught particles a is the sticking ratio M pis the total mass of the caught particles kg M the mass of the filter kg N the total number of particles m p the average mass of the particles kg n the particle density m Page 52 EUROLAUNCcH Student Experiment Documentation V the total volume of air sucked m the air flux m bi t the total sampling time h One can estimate values for the different quantities in equation 1 and therefore make a first rough estimation of the relative mass of the particles taking a 0 5 n 10 5m3 p 0 54 m h 2 3 h mp 1 ug and m 100g one gets a relative concentration of m 1 h 3 h 196 All these values are very rough estimates but the obtained relative value is five orders of magnitude larger than the needed value of C 1 ppb 1 10 With a floating phase of only 1 hour we would have C 2 7 10 that is still a suitable value for particle detection However if possible a 3 4 hours floating phase would ensure a higher probability of collecting stratospheric particles with our assembly his estimation does not take into account the contamination which must be avoided C 0 5 10 m 054 8 1 x 1074 Filter Choice SKC producer recommends to use four 25 mm 0 5 um thick PTFE Polytetrafluoroethylene filters wi
142. stacked on top Although for A5 Unibo Experiment the Ethernet Shield will be on the top The Ethernet Shield has a standard RJ 45 connection with an integrated line transformer and Power over Ethernet enabled There is an on board micro SD card slot that cannot be used simultaneously with Ethernet A5 Unibo has decided to include another logger shield Open Log for data logging Page 76 EUROLAUNCH A DLR and SEC cooperation Student Experiment Documentation It fits with the Arduino MEGA 2560 pin out and the schematics are shown in Fig 4 5 17 d T TTA LTEM LI d hu rs D pic ET m RI d LE 1 Lol LAM if SEEMS an Tan al apa Laf O O O O ae EE 2c D eege oe ee I i e DST RIE i E I rara MN N HHN e T ee e a L go ow vx Z ABDI 15TLI E ONE eme T Ce DI F T LEE E IL 2635 amm m UN JN r coss Mateo Figure 4 5 17 Arduino Ethernet Shield 4 5 5 Heaters Board H Board o PASO T y RAG Ret 4M l4 hA E Lt e _ A 2 amp 2 ae 4 AMRZOTPAN2004 2 1 ro B az Figure 4 5 18 Heaters Board H Board Page 77 EUROLAUNCH Student Experiment Documentation A5 Unibo Thermal Subsystem requires an electronic control of the heaters The H Board is divided in two different parts logical and control Regarding the logical part two fundamental ICs are distinguished e OPA4180 quad operation
143. stratosphere OR5 The experiment shall autonomously close the pinch 18 R T valves and re seal the sampling filter prior to the descent The experiment shall be turned off prior to entering the descending phase Pump AIC s and OPC should be disabled The amount of Offset for the AlC s shall be measured prior to the flight and it shall not be higher than 100 mV 5 2 Test Plan The following tables show a summary of all the main scheduled test and their procedures Detailed procedures and results can be found in the BEXUS repository at https rexusbexus zarm uni bremen de share page repository in the TEST folder for our experiment 5 2 1 Pump Tests PT Test number PT1 Test type Pump performance at ground conditions Test facility Flight Mechanics laboratory University of Bologna Test Pump is turned on and its performance is evaluated at procedure different DC voltage levels to verify if a linear correlation between voltage and flow exists Volumetric flow is evaluating in two different ways Page 128 EUROLAUNCcH i I Student 0 o mee Student Experiment Documentation Documentation Measuring the time required to complete the inflation of a known fixed volume inflatable bag and measuring a differential pressure through a Pitot tube The first method is not so accurate and will be used only to assess the validity of the latter PT2 Also a hot wire anemometer is employed for the calibration of the Pitot tube
144. switch instead e g Infineon series ITS414x Take care of grounding include grounding diagram Compatibility between currents and voltages of sub units should be considered Is the Ethernet shield compatible with fixed IP addresses used on BEXUS Verify compatibility and how IP address is configured Thermal SED chapter 4 2 4 amp 4 6 o O O Very good thermal design Team clarified they used a static simulation Airflow should be considered as a loss of heat too consider adding to simulation a Software SED chapter 4 8 O O O O o O O How W hen do you time tag data after a loss of data Think about it System introduction should be added to beginning of chapter Team uses sequence flow programme Is this the right approach Are you sure you can take measurements in every state Need timer event which pulls Ethernet port interrupt timing routine through a server You need to use more events and interrupt possibilities of Arduino Do low level routines for lab view work together with Ethernet shield of Arduino Simon to email possible options to team Figure 4 8 3 Climb state check altitude should have a decision i e climb rate constant or lt x etc Verification and testing SED chapter 5 O O O Good chapter Explain v of the test column in legend A lot of full system tests are very late in schedule do earlier Student Experiment Documentation Page 159 E P d a Be
145. t with values obtained in ambient pressure Test date 20 03 14 Completed YES O Page 130 E UROLAUNCH Ee Student o0 o mee Student Experiment Documentation Documentation Hesults Test has shown that down to 500 mbar the internal pump is able to compensate for pressure drop and maintain an airflow of 1 l m but as we go down to 400 mbar this threshold level cannot be reached anymore and the alarm code appears meaning that pump is at its maximum but flow is not achieved From this point onwards collected data cannot be considered reliable Since these pressure levels are way higher than the ones we expect to encounter at floating phase we decided to use a different OPC As soon as the new instrument is delivered a new series of test is going to be performed 5 2 3 Air lon Counter tests AICT Test type AIC performance at ground conditions Test acy Flight Mechanics laboratory University of Bologna Test AIC s are turned on and output values are evaluated and procedure should be in agreement with the reference values from literature Data acquisition through ADC and SD are checked The Offset value is evaluated by turning off the fan while AIC s are still on and its value should be below 100 mV Test date 17 04 14 completed MBS Results Data is successfully acquired and is in agreement with reference values Offset values are measured to be around 2 mV for the positive unit and 8 mV for the negative one Tes
146. t type AIC performance at stratospheric conditions Test Sen SEH Mechanics laboratory University of Bologna Test The AIC is put into a vacuum chamber and turned on Output procedure values for ion densities are recorded and evaluated at several ambient pressures ranging from 1000 to 5 mbar Offset is then measured at several ambient pressures to see If a relationship between offset and pressure exists Test date 06 05 14 Page 131 UROLA Student Experiment Documentation EuroLAuNcn Completed Results Both the AlCs work properly in a low pressure environment Offset is found to be independent from pressure levels Test type AIC performance at stratospheric conditions Test facility Flight Mechanics laboratory University of Bologna Tested item Air lon counter Test Offset values are measured at several ambient temperatures procedure ranging from 0 C to 70 C depending on the facility to create a Temperature Offset profile Completed 5 2 4 Software Tests ST Test type Transmission Ground station Test facility University of Bologna Tested item ECU Arduino Ethernet shield GS Test Arduino is connected to PC via bridge using an Ethernet procedure 10 100 cable IP and subnet mask are set as specified in E link user s manual Arduino and LabVIEW compatibility with IP range is checked Data exchange is performed between Arduino and PC by using LabVIEW to check various types of data A first attempt
147. th laminated PTFE support as filters for the stages and 37 mm 2 0 um PTFE filter with PMP support ring as after filter We are currently following this choice due to the following considerations e Teflon filters result in high collection efficiency of particles above the cut point of each stage without the use of adhesive coatings and do not collect excessively particles below the cut point e They can efficiently be used for gravimetric analysis 17 e he fibre remains flexible and non brittle from 73 C to 260 C without degradation e hey have zero moisture absorption Sampling Unit design Driven by the design and operational requirements and following previous experiments for the collection of stratospheric particles such as DUSTER 7 and Stratospheric Census 8 the following design has been chosen in order to minimize the contamination of the samples e he SU will be sealed by Pinch Valves when in non sampling mode so prior to reaching the floating phase e wo pinch valves are mounted both upstream and downstream of the Page 53 Student Experiment Documentation EuroLAUNcH SS to ensure insulation during non sampling mode The contamination from the balloon can be estimated to be maximum during launch and descent phase so valves have to be closed during these phases and will stay open only during the floating phase e Upstream valve has to be mounted as close to the inlet port as possible in this way the number of parti
148. tic B EN interference from other experiments R11 Electronics operational C TC temperature range is exceeded R12 OPC s operational C TC temperature range is exceeded Page 41 DLR and SSC cooperation valves work properly in flight conditions Execute tests to ensure valves to work properly in flight conditions Ensure redundancy and introduce possibility of override by ground station Altitude determination using both GPS and barometric pressure sensor Redundancy employing data logging Autonomous mode in case of no GS ACK Valves posed both on mount and valley of the filters Accept the idea of losing electronics Transmit data with E link system in order to save data Implement strict flight procedures Put spare control filters for analysis Assure correct grounding Select low charging materials Vibrational tests Dumpers Shielding of sensitive electronics guarding circuits correct grounding Detailed thermal simulation and testing Include external heaters Detailed thermal simulation and testing Include external heaters Page 42 DLR and SSC cooperation Student Experiment Documentation R13 AIC s operational C 3 TC temperature range is exceeded R14 Pump overheats B 3 TC R15 Battery fails B A TC R16 Battery explodes A 5 TC R17 Temperature sensors fail B 3 TC R18
149. ties and general public to our experiment and other ESA Educational activities and projects A5 Unibo team activities will be presented to undergraduate and graduate students of School of Architecture and Engineering and Earth Science faculties of the University of Bologna in programmed conferences We have some contacts with Italian press La Repubblica Bologna has published an article about us on the 22 Jan 2014 titled Ingegneri in Svezia per studiare la vita delle nuvole Emilia Romagna media are very receptive to research and innovation University of Bologna press is also very interested in our work Experiment achievements as well as pictures current information new sponsors details about our daily activities will be shown in Flight Mechanics Laboratory University of Bologna webpage You can find it between the research activities http www flightlab unibo it research htm Website _http www thedf com bexus Facebook page _hitps www facebook com A5Unibo The scientific results of the experiment will be proposed as a contribution paper in suitable international conferences or journals For more details see also Appendix B 3 5 Risk Register Page 40 EUROLAUNCH RUN end 80 ec Student Experiment Documentation Risk ID TC technical implementation MS mission operational performance SF safety VE vehicle PE personnel EN environmental Probability P A Minimum Almost
150. tion Fm A5 Unibo Publicado por Mani Serrano Castillo 14 de abril Editado i Today 45 students from SCUOLA MEDIA STATALE COVA LANZONI Faenza Italy have visited Flight Mechanics Laboratory and they have learnt how ASUnibo works within BEXUS Programme They have also been divided in teams and everyone has become an engineer for two hours Then they have shown the proposals of different experiments with their requirements in the same way as we did for PDR Oggi 45 studenti della SCUOLA MEDIA STATALE COVA LANZONI Faenza Italia hanno visitato il Laboratorio di Meccanica del Volo hanno imparato come A5Unibo lavora nell ambito del programma BEXUS Si sono divisi in gruppi e ognuno diventato ingegnere per due ore In seguito hanno illustrato le loro proposte ai loro compagni descrivendo i diversi esperimenti e relativi requisiti cos come ASUnibo ha fatto per la PDR Hoy 45 estudiantes de SCUOLA MEDIA STATALE COVA LANZONI Faenza Italia han visitado el Laboratorio del Mec nica del Vuelo y han aprendido c mo ASUnibo trabaja en en programa BEXUS Se han dividido en grupos y cada uno de ellos se ha convertido en ingeniero durante dos horas Despu s han mostrado sus propuestas de los distintos experimentos y los requisitos del mismo modo que nosotros hicimos para la PDR 8 2 9 A5 Unibo Elementary School Avtivities Student Experiment Documentation APPENDIX C GANTT CHART 4 2013 Mame Iintormation about pre
151. to check connection stability is performed Test successfully completed Some improvements to be performed in GST2 Test type Transmission Ground station Test facility University of Bologna Page 132 i Student Experiment Documentation Test Arduino is connected to PC via bridge using an Ethernet procedure 10 100 cable IP and subnet mask are set as specified in E link user s manual A deeper connection stability test is successfully performed Best timing delays to have a good transmission are evaluated Forcing conditions to crash the GS VI are investigated Completed Results Test successfully completed Other improvements to be implemented in GST3 Test type Transmission Ground station Test facility University of Bologna Tested item ECU Arduino Ethernet shield GS Test Arduino is connected to PC via bridge using an Ethernet procedure 10 100 cable IP and subnet mask are set as specified in E link user s manual Connection stability is tested also by physically forcing It Performance in terms of data rate and PC memory usage are investigated CRC algorithm is checked on both sides Test duration 5 hours Completed NO Test type Software performance Test facility University of Bologna Tested item ECU instruments GS Test ECU is assembled and connected to the scientific instruments procedure OPC AIC s pressure sensor temperature sensors humidity sensor and GPS and to GS via e link conne
152. tor status and parameters of the components 2 Monitor altitude readings both from GPS and pressure sensor to control the status of the experiment In particular it is required to e Open valves in the SU once the established altitude is reached e Close valves in the SU when a set displacement from established altitude is reached 3 Handle communication with GS 4 Store critical data in internal flash memory 4 8 2 Operating modes Autonomous Mode Default mode Autonomous functions no user action requested All collected data are send to GS Ground Station Acknowledgement GS ACK Mode oystem switches from Autonomous Mode when it needs a confirmation oystem waits for the users answer for a given amount of time then it automatically switches back to Autonomous Mode Page 101 Student Experiment Documentation wssess cooperation Manual Mode Requested by GS to force a command when a failure or error arises This mode can be seen as a Task Manager to handle directly with the source of the trouble or to prevent it Both Autonomous and Manual modes should be equally able to perform the whole mission providing ECU to be completely independent in case of connection loss However whatever mode is set the system automatically provides to switch to Autonomous Mode after a timeout occurs 2 min without commands to prevent the system from remaining locked in Manual mode while E Link connection does not work As long
153. troller and optimize the space and volume used for the electronics subsystem and to avoid possible flying cables and failures due to bad contacts Table 4 5 3 SB1 S 4 5 3 SB1 Sensors an and Instruments connected connected SCL SDA are pulled up with 2 2KOhm resistor Humidity sensor HIH9120 power line In order to change the voltage levels from 3 3 to 5V a voltage divider TXB0101 has been included for sensor input pins and a level translator IC for the output Pulled up with 4 7KOhm resistor wire Optical particle 7 2V UART 7 2V powered directly from CPU counter OPC T Connected to Arduino 3 3 V Temperature sensor Pressure sensor MS5607 Page 67 EUROLAUNCH Student Experiment Documentation ADUR and SSC cooper LOAC Converting RX and TX for UART using a RS232 to TTL converter e Motor 14 4V UART 8 pin connector Controller for PUMP The PCB has four layers in order to reduce the space needed by the circuit and to have facilitate the separation of the different grounds To make the system more reliable in terms of failure detection some test points have been included in the PCB In the following figures the general circuit schematics are shown HEH GH 3 GG Ci GREG Figure 4 5 4 Stacked board SB1 schematics part 1 Page 68 AUNCH j EuroLaun Student Experiment Documentation Figure 4 5 5 SB1 part 2 schematics Fig 4 5 5 is fr
154. umentation ADR and SSC cooperation Competed 5 2 2 OPC performance tests Test type OPC performance at ground conditions Test facility Flight Mechanics laboratory University of Bologna Tested item Optical Particle Counter Test The OPC is turned on and output values for particle densities procedure are compared with another already used instrument Internal sensors performance flow temperature RH is checked and average flow rate evaluated Test date 14 02 14 completed WEB Results Output values obtained are consistent with the expected ones Temperature RH and flow sensors are functional The nominal flow rate is measured by the internal sensor to be of 1 I m 3 I m considering air sheet for optics cleanliness Test type OPC performance in near vacuum conditions Test facility Flight Mechanics laboratory University of Bologna Tested item Optical Particle Counter Test The OPC is put into a vacuum chamber output values for procedure particle densities flow rate and RH are recorded in micro pressure conditions Internal pump performance is evaluated using the internal flow sensor by operating the pump at several ambient pressures ranging from 900 to 5 mbar Pressure is decreased until a specific alarm code is read in the output meaning that internal rotary vane pump has reached its maximum power but is not able to maintain the nominal flow of 1 I m Collected data is evaluated and should be consisten
155. unch 500 und BN campaign Travel and accommodation TOTAL OO S Table 3 3 5 shows a more detailed description of the FML and DEC contribution Green cells represent the funds we already have instruments already purchased or those that have been donated The orange cells represent costs that are not covered yet and for which we are currently looking for sponsors FML will cover the costs of the components in case we won t find external sponsorship while a critical issue remains the cost for travel and accommodation for the flight campaign which will have to be covered by the students themselves in case of no sponsorship Table 3 3 5 Sponsorship table Page 35 EUROLAUNCH Student Experiment Documentation ADR and SSC cooperation Electronics 3857 82 Structure Already purchased instruments LOAC 3000 Sioutas ert BOXER PUMPS i SAFT BATTERIES 1185 SB1 SB1 PCU 600 Air lon Counter 550 Travel amp accommodation CDR Travel amp accommodation Launch Campaign Beam oH 3 3 3 Educational support We are mainly supported by Professor Fabrizio Giulietti coordinator and supervisor of Flight Mechanics Laboratory University of Bologna Fabrizio Giulietti Assistant Professor ING IND 03 MECCANICA DEL VOLO ING IND 03 http www unibo it faculty fabrizio giulietti Dipartimento di Ingegneria Industriale Viale Risorgimento 2 Bologna Go to map Other Contacts al 390
156. us some status flags Moreover a Life Signal is used as incremental value to have the number of cycles executed by on board software Both should be useful to evaluate the number of lost packages 4 8 6 Total data rate Finally we can provide an estimation of the total data rate required for data communication through E link Note that UDP header is due to UDP protocol itself and it is not handled by A5 Unibo software Table 4 8 13 shows the different packet s dimensions without any safety factor applied data rate are the simple summation of all datagram fields Table 4 8 13 Total data rate soel ARE Sec 32 byte 3 byte 2 byte ZS cu LONE uel Minimum data rate 0 83 kbit s in DOWNLINK Normal data rate Page 113 EUROLAUNCH Student Experiment Documentation ADR and SSC cooperation 0 83 kbit s in DOWNLINK Maximum data rate 1 44kbit s in DOWNLINK 0 83 kbit s 0 62 kbit s on request and 0 66 kbit s in UPLINK on request Applying a safety factor of 1 5 data rate would be Minimum data rate 1 24 kbit s in DOWNLINK Normal data rate 1 24 kbit s in DOWNLINK Maximum data rate 2 16 kbit s in DOWNLINK 0 98 kbit s in UPLINK on request Altitude 30000 25000 20000 15000 10000 5000 5 00 4 00 3 00 2 00 1 00 0 00 1 00 2 00 3 00 4 00 5 00 Bandwidth 160 140 120 100 80 Bytes 60 20 5 00 4 00 3 00 2 00 1 00 0 00 1 00 2 00 3 00 4 00 5 00 Time h
157. ution Access to gondola after FCT is very limited 1 person at a time under SSC surveillance Remove all RBFs at pick up remove SU inlet RBF at line up Gondola is lifted after pick up the whole time Team has an arm key for RBFs make sure you have it in a place where you find it Be sure to have a check list and a place for the RBFs and key clearly labelled a case with silhouettes is a good idea Recovery actions required SU protection back on to be included in SED Include flight requirements float duration height day flight or night flight in chapter 6 Organisation project planning amp outreach SED chapters 3 1 32 3 3 amp 3 4 O O OO OD 0 0 0 o Q O a Others O O Chapter improved a lot since PDR Add new members in join space even if you can t link them to team there Man power very clear If helpful for you include more details in WBS Add legend to Gantt Chart Travel money for non sponsored students is not enough Budget deficit unclear show clearly what is lacking Good outreach Facebook maybe in 3 languages Show more status updates small things that happen some pictures etc Website translation still on going Sponsors and Partners on website are wrong program sponsors are SNSB DLR and ESA those are no partners SNSB logo more important than SSC don t include MORABA maybe do this section more general Wrong link to ZARM on website Lessons learned are good for this
158. vertical resolution of 80 100 m given the average ascending speed of 4 5 m s PR3 The temperature measurements outside the balloon should be FR3 possible in a range between 90 and 30 C PR4 The temperature measurements outside the balloon should be FR3 made with an accuracy of 0 2 C PR5 The pressure measurements shall be possible in a range between FRA 5 and 1100 mbar PR6 The pressure measurements shall be made with an accuracy of FRA 1 mbar PR7 The humidity measurements should be possible in a range from FR5 0 to 100 RH PR8 The humidity measurements should be made with an accuracy of ERD 2 PR9 The pump shall suck a nominal flow rate of 9 l min at stratospheric FR6 conditions in order to maximize the efficiency of the collecting filter more details given later PR10 The altitude shall be measured with an accuracy of at least 40 m FR7 PR11 The coordinates shall be measured with an accuracy of at least FR7 40 m PR12 The temperature measurements inside the gondola shall be FR8 possible in a range from 20 to 50 PR13 The temperature measurements inside the gondola shall have an FR8 accuracy of 1 C Page 24 DLR and SSE cooperation Student Experiment Documentation NO A Design Requirements Table 2 3 1 Design requirements The experiment shall withstand vertical loads of 10 g and horizontal loads of 5 g The experiment should withstand landing shocks of up to 35g The expe
159. ween adjacent nodes is given by the following relation d Qconv i ES dconvdAi T E Do Nodal breakdown bulk and thermo optical properties Table 8 2 1 Node numbering and architecture Node number Description Notes BOUNDARY NODES B_SKY Sky background ei 8A Emi Page 172 EUROLAUNCcH Student Experiment Documentation e E e Medium plate Medium plate Internal air Support plate Table 8 2 2 Node Properties C1 Insulating wall external Multilayer 0 12 0 03 Insulating wall internal up nsulating wall internal medium Insulating wall internal down Internal air up Medium plate up Medium plate down Internal air down Support plate up Support plate down Gondola deck Batteries Other instruments Table 8 2 3 List of materials ILE O O1 C1 O mo zl pol zl zl zl zl zl lt I O O1 C1 O O C1 O O 00 O o 00 O O 00 ol CO O CH CDI CO Oil Cl AI6061 T6 2700 175 Polyurethane foam 1458 0 023 Page 173 EUROLAUNCH Student Experiment Documentation ADR and SSC cooperation APPENDIX E COMMUNICATION PROTOCOLS SPI The Serial Peripheral Interface SPI is a synchronous serial data bus The communication is established between a Master that will be the microcontroller and a Slave that in our case will be the SPI sensors Data can travel in both directions at the same time
160. while the second one has an active surface of 1500 mm and FWHM of 0 73 keV at 122 keV Spectra are processed with a specific software package GammavVision 32 version 6 07 Ortec Figure 7 1 3 Germanium detectors at ERL Page 149 Student Experiment Documentation EuroLAUNcH 7 2 Launch Campaign TBD 7 3 Results TBD 7 4 Lessons Learned Even though we are only in the preliminary phases of launch campaign some lessons have already been learnt during the PDR and CDR preparation phases Deadlines are necessary for the group and the single members in order to be able to keep on track and follow the schedule It is very important to have team meetings at least once a week and to work all together whenever possible Problems that can take long time for a single person to be solved are often solved really quickly when the whole group gathers Components have to be identified and ordered as quickly as possible since communication with companies often requires a lot time and work data sheets unavailable communication delays or misunderstandings Conflicts can arise within the group and a lot of effort has to be put into building a strong team spirit and cohesion Team members can become unavailable for some periods of time due to work or personal issues and backup solutions have to be arranged in time Page 150 EUROLAUNCcH Student Experiment Documentation 8 ABBREVIATIONS AND REFERENCES 8 1 Abbreviations AIT Asse
161. y good schematics colours etc System levels budgets and according timeline missing Stick to the file naming convention for your CAD models Ooooocoooooo 4 Panel Comments and Recommendations Requirements and constraints SED chapter 2 o Very good requirements o Think about constraints o Software itself should not be redundant but use redundant data o Include a requirement for the BEXUS power interface Page 158 ge Le e ee ay EUROLAUNCH A DLR and SSC cooperation a Mechanics SED chapter 4 2 1 amp 4 4 O oo000 On a good way Design and assembly of each sensor is missing Update manufacturing drawings etc on teamsite More information on single components is needed Maybe annotate figure 4 1 4 1 1 experiment overview with some of the text below it How will you access the mounting Electronics and data management SED chapter 42 2 42 3 4 5 4 7 4 9 O O O o o Doo o oO 0 o0 Unclear when you talk about batteries if you mean your own batteries or gondola batteries specify terms Don t be over tolerant to failures battery AND E Link failure is very unlikely better move to single failure tolerant system if at all needed out of scope of BX experiment Loss of ground communication might be critical focus on this rather than battery redundancy You should rely on the batteries a redundancy switching is unnecessary Redundancy makes power system to complicated c

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