BEXUS User Manual
Contents
1. Figure 10 3 Local Tangent Coordinate System LTC Two observation angles define the position of the vehicle from the observation location The azimuth p is measured clockwise around the observation location starting at North It varies between 0 and 360 and is calculated with following equation Page 52 BEXUS User Manual EuroLAUNCH east B arctan 2E Eq 10 4 north The Elevation e is measured between the horizon and the vehicle position It varies between 90 and 90 and is calculated with the following equation E sul Pure Eq 10 5 east north yo The transformation between azimuth and elevation to Cartesian LTC coordinates is done with following equation east ire sin J cos north d cos J cose Eq 10 6 hrc sing The distance d between the vehicle and the observation location is also called Slantrange BEXUS User Manual OSO PAA APPENDIX A GONDOLA DRAWINGS ce O pa e rm ds Oi 1160 MIA WOLLO9Y MIIA dOL 31 4190 0 G 231vOoS ovid 3 11019P giba Buyunow siqnog S IDI Bulpunouw a Bul Figure A 1 Gondola dimensioned drawing Page 54 BEXUS User Manual EuroLAUNCH A DUR and SSC cooperation Figure A 2 Section view A A Isometric of gondola floor Page 55 BEXUS User Manual EuroLAUNcCH APPENDIX B ESRANGE SAFETY AND SECURITY COMPLIANCE CONFIRMATION BALLOON This document clarifies the basic safet2. EuroLauncH ADLR and SSC cooperation This document remains our property and should not be copied without our written allowance Nor is it permitted to show or give this document to a third person Contravention will be prosecuted with the support of existing law BEXUS User Manual Document ID BX_REF_BX_user manual v6 10_05Feb14 Version Issue Date Document Type Valid from 6 10 05 Feb 2014 Spec 05 Feb 2014 Current version issued by REXUS BEXUS Organisers Contributors Please see Change Record for a list of contributors Current version approved by A Kinnaird Distribution Change Record Version Date Changed chapters Remarks 33 paan Pe 3s pag IS CE 4 7 2008 12 08 A Stamminger MCU meum ap Cock 6 2 2010 12 23 2 5 1 6 2 6 6 9 3 M Siegl 6 3 2011 08 31 6 1 Appendix A EuroLaunch logo M Siegl Addition of trajectory information and 6 4 2012 12 06 correction of references A Kinnaird 66 2013 02 15 4 4 6 3 6 4 6 6 6 7 8 3 8 7 9 4 9 3 9 5 2013 09 11 1 2 2 2 2 4 3 1 3 5 6 2 6 4 6 6 8 3 9 3 9 5 A 2013 11 09 1 2 3 3 3 5 1 3 5 2 3 5 3 42 4 4 3 444 N Newie A Kinnaird 5 2 1 6 1 6 2 6 3 1 6 3 2 6 7 3 6 8 7 1 8 5 Appendix A Gondola drawings picture captions 2014 02 05 6 1 Appendix A Gondola drawings A Kinnaird Abstract This document has been created to aid experimenters taking part in a BEXUS flight as part of the REXUS BEXUS Pr
3. Inflammable material Chemical hazards Electrical facilities Radiological work All the above mentioned laws and regulations are available at http www av se inenglish lawandjustice workact The experimenter shall state that the module fulfils the applicable requirements and establish a list of hazardous materials which shall be communicated to EuroLaunch no later than the MTR This information shall always accompany the experiment Safety at Esrange Space Center The Safety Regulations that apply at Esrange may be found in the Esrange Space Center Safety Manual Ref 4 It is a requirement that all personnel participating in the campaign shall have read the safety regulation in Ref 5 prior to their arrival at Esrange Space Center Each team leader will have to sign a document to verify that all team members have been provided with a copy of the safety manual See Appendix B Esrange safety and security compliance confirmation balloon 11 11 1 Page 49 BEXUS User Manual EuroLauncH COORDINATE SYSTEM DEFINITION This chapter will give a short overview on the coordinate systems that are used for the BEXUS onboard sensors GPS and tracking systems Knowledge about the coordinate definition and transformations is important for the analysis of sensor data during the flight and for the post flight analysis The following table lists the used coordinate systems Table 11 1 Coordinate Systems ECEF Earth Centered Earth Fix
4. operation and any other mission related issues Final decisions are normally left to the experimenters but if required by safety or otherwise EuroLaunch withholds the right to enforce decisions on any issue Before flight the experimenters must successfully convince EuroLaunch through testing simulation and documentation that their experiment is fit and safe for flight The experimenters are responsible for developing and providing the scientific payloads and support equipment provided EuroLaunch can aide with many of these issues but the teams are responsible for ensuring that these are organized in a timely manner They are also responsible for ensuring that the experiments conform to all required electrical and mechanical interface specifications meets safety requirements and survives the flight EuroLaunch assists in all these issues where possible but the experimenters must keep in mind that ensuring the resolution of issues is their responsibility Project Planning A detailed project plan and time schedule will be released by EuroLaunch as soon as possible after the selection workshop These will be regularly updated during the project Experimenter Documentation Requirements Student Experiment Documentation SED The SED provides EuroLaunch and other stakeholders from SNSB ESA DER and ZARM with all the important information on a particular experiment During the phases of experiment development production and flight the SE
5. campaign or project at Esrange has to be accepted by the Esrange Safety Board A standard balloon is normally no problem If there are hazardous items such as chemicals lasers radiation etc included in the experiments there may be a need for further investigation This may take some time and should be done early in the design process well ahead of the start of the campaign Campaign Requirements Plan CRP The BEXUS Project Manager provides Esrange Space Center as well as all parties involved in the project with the Campaign Requirements Plan This document gives a complete description of the specific project including payload information a list of hazardous materials experiment requirements on the launch operations tools required participants expected etc This is an important document used to inform all participants in the campaign The first version of the CRP will be distributed after the PDR training week Inputs are requested from every experiment team regarding interfaces telemetry power consumption and special experiment requirements Payload Assembly and Integration The payload integration tests are performed at EuroLaunch premises and or premises leased by EuroLaunch Nominally these tests start two weeks before the planned start of the launch campaign 7 3 1 Experiment Incoming Inspection All experiment mechanical and electrical interfaces will be inspected upon delivery to the payload assembly and integration
6. experimenter to perform this test 1f necessary Basic Procedure The experiment should be assembled as for flight in a safe area removed from interference both environmental and human Monitoring of temperature and voltages for critical electronic components should be set up where desired The experiment should be run through a simulated countdown chap 9 5 including Ethernet connection external internal power and wait period after switching on During this period procedures for interaction with the experiment should be tested Following simulated launch the experiment should be run as desired for ascent float and descent of 6 hours Here the possibility of E Link dropouts should be simulated where appropriate to ensure that correct operation of the experiment will occur when there is no telemetry available Experimenters should also seriously consider running the experiment as they plan for another 24 hours to simulate the wait time on ground before recovery 6 9 Page 32 BEXUS User Manual EuroLauncH General Design Considerations 6 9 1 Experiment Accessibility Bear in mind that designing for accessibility will make your task easier throughout the assembly and testing phases This is an important point that is often overlooked by experimenters It is in your interest that items such as switches battery packs and cable connections are easy to access Considering access to fasteners is also worth the time
7. gondolas landings Chapter 4 4 5 the experimenter should be prepared for a wide range of possible environmental influences Submersion of the experiments in water is possible if this will be an issue for the experimenters precautions should be taken During the landing organic matter and soil may become lodged in the experiments especially if they protrude beyond the gondola If the experiment protrudes beyond the gondola sacrificial joints or other contingency plans should be considered if it is foreseen that an impact could damage the experiment seriously 6 8 Page 30 BEXUS User Manual EuroLauncH Recommended Tests for Experimenters 6 8 1 Vacuum test This test is applicable not only for experiments which will take place under vacuum conditions but also helps to verify that systems mainly electrical have nominal performance in the absence of convective cooling It is the responsibility of the experimenter to perform this test 1f necessary Basic Procedure The experiment shall be integrated and placed in a vacuum chamber pressure below 5 mbar Experiment data shall be supervised and recorded during the test The experiment shall be operating during the lowering of the pressure in the vacuum chamber The experiment shall be in a similar mode as during the real BEXUS flight After this functional test flight sequence has been performed it is recommended that the module is kept operating for an additional 15
8. memory etc to survive these activities in addition to that which is required for the flight All experiments must have a power connector for external power even if own internal batteries are used power will be supplied via this connector from the gondola power system or a power source on the launch vehicle Hercules At approx T 40 min the power will be switched over to internal gondola or experiment batteries and the external power umbilical between Gondola and Hercules will be removed Note that there will be no access to experiments at that time When considering the power budget see chap 9 5 for count down and launch the possible wait times when the experiment is turned on but cannot be accessed should be taken into account most commonly testing and launch attempts Be prepared to have power supplies for 2 hours of testing 2 hours on ground and for a flight time of 6 hours as a minimum tot 10 hours minimum Be prepared for possible aborted launch attempts as it is not uncommon to go through a countdown 2 or 3 times before a launch is achieved 6 7 3 Hercules impact Although relatively rare for experiments that protrude from the gondola it should be considered that an impact with the Hercules during the launch is a possibility Location on the gondola housings and materials can be selected to minimize a component failure in the case of a collision 6 7 4 Landing considerations Due to the unpredictable nature of the
9. minutes in order to detect any leakages or overheating problems 6 8 2 Thermal test A thermal test is mainly performed in order to verify a nominal function of the experiment during the worst case temperatures that can be experienced during count down and launch It is the responsibility of the experimenter to perform this test if necessary The heating of the outer structure gondola is normally not included or tested Basic Procedure The experiment shall be integrated and placed in a thermal chamber Experiment data shall be supervised and recorded during the test The temperature shall preferably be measured in several places in the experiment Low temperature test Regulate the temperature in the thermal chamber preferably down to 80 C but at least to 40 C When the measured temperatures in the experiment have stabilised perform a functional test flight sequence Be aware of condensation problems if the test is performed in normal humidity 6 8 3 Mechanical Test Mechanical tests are necessary to ensure performance of the experiment during flight after possible shocks that occur during launch If not it is possible that the balloon will be launched with the experiment non operational There are two major risks to be identified structural integrity and experiment durability It is the responsibility of the experimenter to perform this test if necessary Basic Procedure 1 The experiment should be placed on a
10. pole radius Rs u R pote m Eq 10 2 fe R q The WGS84 Ellipsoid has a flattening of fe 1os257223563 and the equator radius Re is 6378137 m Ref 9 The Earth eccentricity es can be calculated with following equation eaill Eq 10 3 The position of the vehicle is given in geodetic coordinates relative to the reference ellipsoid The geodetic longitude O corresponds to the geocentric longitude Not like the geocentric latitude gc which is the inclination of the position vector to the equatorial plane the geodetic latitude Pza describes the angle between equatorial plane and the normal to the reference ellipsoid It is positive to the North and negative to the South The difference of geodetic and geocentric latitude is shown in the following figure BEXUS User Manual Eolo Reference Ellipsoid Figure 10 2 WGS84 Reference Ellipsoid The flattening of the Earth is very small because the difference between the Earth radius at the equator and the poles is less than 22 km Therefore the difference between geodetic and geocentric latitude is 12 arcminutes 11 2 Local Tangential Coordinate System LTC The LTC system rotates with the Earth The E axis points to East the N axis points to the North and the Z axis is the zenith that is perpendicular to the tangential plane at the observation location usually Launcher This location is defined by the geodetic latitude Pea and geodetic longitude 0 North Pole
11. premises 8 1 8 2 Page 35 BEXUS User Manual EuroLAUNCH CAMPAIGN ACTIVITIES BEFORE START OF COUNTDOWN Description of Esrange Space Center All the necessary information for a user of Esrange can be found at www sscspace com under Science Services Esrange Space Center Its main content is Range description capabilities layout environment Range administration communications accommodation freight supplies Safety regulations Instrumentation telemetry tracking observation scientific Operations assembly checkout flight control recovery requirements procedures Satellite facilities Safety Safety always comes first at Esrange Before the start of a campaign a safety briefing will be held It is mandatory for all visiting personnel to attend this briefing 8 2 1 Additional Esrange Safety Board meetings If a safety issues arise during a campaign there might be a need for extra Safety Board meetings before a launch is possible Page 36 BEXUS User Manual EuroLAUNCH 8 3 Time schedule The BEXUS launch campaign takes place over approximately 10 days This does not allow any time for errors or delays and it is important to be well prepared Every morning there is a status meeting in one of the conference rooms where the upcoming activities are discussed 8 3 1 Overview of build up schedule A more detailed schedule will be issued closer to the campaign week Dependi
12. someone else to operate and document the functions of your experiment if the launch is postponed to a later opportunity This should be documented in the SED Balloon launch conditions Launch period September October Launch window 05 00 20 00 LT Ground wind less than 4 m s Vertical visibility more than 75 m Conditions should be sufficient for helicopter recovery on the same day for a short flight or on the next day for other cases Safety on the balloon pad Esrange has the overall responsibility for safety and has the Veto right in all safety issues during all activities within the Esrange base area In the case of clients guests with stronger safety rules then those of Esrange the stronger rules will apply No one is allowed on the pad during count down without the permission of the Operations Officer There are several heavy vehicles with limited visibility moving on the pad To be visible to the drivers Esrange provides participants with fluorescent safety vests It is mandatory to wear these when entering the launch pad When E link is in a high power transmitting mode there is a 10 meter safety distance around the gondola This is marked with cones In the final 1 hour and 30 minutes before launch after the sweet spot tests there is no more access to the experiments At launch everyone must be inside the balloon pad buildings and remain there until instructed otherwise 9 4 Page 43 BEXUS User Manual EuroLau
13. train Argos GPS and ATC Transponder AGT strobe light radar reflector and the gondola The total length of this system is up to 75 m Figure 4 1 Valve Balloon Ballast Mass Strobelight Figure 4 2 BEXUS 15 Experiment Gondola M Egon Flight Train AGT Radar Reflector Payload Gondola Figure 4 3 Hercules Launch Vehicle with Gondola Figure 4 1 BEXUS Vehicle 4 2 4 3 4 4 Page 17 BEXUS User Manual EuroLAUNcH Gondolas There is one primary size of experiment gondola available for the BEXUS programme Medium Esrange gondola M Egon is a medium sized gondola with dimensions of 1 16 m x 1 16 m x 0 84 m It is designed to carry experiment loads up to 100 kg It is possible to cover the sides of the gondola with heavy duty canvas material It is possible to cover the top of the gondola with heavy duty canvas material or aluminium sheeting These coverings are not nominal and should be requested to Eurolaunch Homing Aid The flight train and balloon envelope are equipped with separate ARGOS GPS receiver transmitters AGT from which the position information can be assessed by satellite both during the flight and after landing The GPS position is also transmitted via the telemetry stream through the EBASS system The recovery team in the helicopter can be equipped with a homing receiver in order to acquire the GPS position for a quick and easy way to locate the payload
14. will be suitable for different experiments In special cases due to scientific requirements a total isolation approach may be required this should be done in coordination with your FuroLaunch contact It is suggested that a possible good approach for power complex BEXUS experiments is to utilise Distributed Single Point Grounding DSPG If required an equipotential reference plane to the gondola electric can be provided It is also important to consider the grounding scheme of any EGSE used as problems can also arise during testing due to physical connection with the experiment s EGSE 6 7 Page 29 BEXUS User Manual EuroLauncH Operations and durability 6 7 1 Operations During the pre flight tests and the count down the experiments must be turned on and off several times to test systems such as E Link and power and to check for interference with other experiments and balloon systems These operations are partly performed outdoors during the RF interference test under difficult conditions Also once carried out they may have to be repeated several times BEXUS experiments should be designed with these operations in mind The procedures to turn and experiment on and off should be kept simple and should be possible with a minimum set of tools in a short period of time 6 7 2 Power Operations during the pre flight tests have a significant impact on the experiment s power and memory budget Make sure that there is enough battery
15. 6 9 2 Availability of Parts A major issue for many experimenters is late delivery and procurement delays Rather than merely basing a design on parts from catalogues ensure that they are available this can save a lot of time and money for experimenters Avoid designs based on hard to procure items or irreplaceable items where possible 6 9 3 Experiment Construction Costs Consider enforcing a three quote minimum on components where possible this is often not possible due to the specialized nature of items When designing remember that the cost for machining can differ greatly depending on early design decisions Avoid close tolerances wherever possible not only is it cheaper but it can save time with assembly Remember to use experience and judgement the cheapest items are not always the best selection 6 9 4 Redundancy Redundancy is desirable especially where there are safety or failure risks It is not as simple for mechanical as electrical but it should be considered during the design process Redundancy can be simply achieved by separate battery packs multiple switches check valves and other solutions 6 9 5 Weight and Size Considerations Minimizing weight is commonly overlooked by experimenters However keeping weight low where possible serves multiple functions For payload organization when experiments are light and small it gives EuroLaunch more flexibility in selecting locations for each experiment It can also result i
16. Both the balloon envelope and the payload are equipped with an air traffic transponder and altitude encoder ATC to aid tracking Flight sequence For details of previous flights please refer to the past campaign reports and flight data If these cannot be found on the REXUS BEXUS webpage or teamsite they can be made available upon request 4 4 4 Launch The payload is held by a launch vehicle and is released when the balloon inflation Helium is completed Page 18 BEXUS User Manual EuroLauncH 4 4 2 Ascent phase The nominal ascent speed is 5 m s Depending on float altitude and variations in speed this phase takes approx 1 5 hours A slight oscillating movement is experienced Expect an initial drift above ground of 5 10 m s 4 4 3 Float phase When the total mass of the system and the buoyancy of the gas reaches equilibrium the ascent phase stops During float there are only minor changes in altitude 200 m If the sun sets during flight the balloon will begin to descend due to the cooling of the gas The payload mass influences the maximum altitude The final altitude is calculated shortly before launch and may vary between 25 and 30 km The nominal flight time is one to five hours 444 Descent phase To end the flight the cutter is activated causing the balloon to separate from the rest of the flight train and rip open There is a parachute system that brings down everything below the cutting device A small per
17. D will be the main documentation for students to describe their experiment and 5 frozen versions will be provided All documentation relating the requirements of this document can be found at the REXUS BEXUS Teamsite including the SED guidelines and SED template documents Campaign Requirements Plan CRP Any requests for input from EuroLaunch must be fulfilled by the student teams This document is a reference document for the many people who will be involved in the launch of experiments and care must be taken that information is correct and clear to avoid errors 3 5 3 Page 15 BEXUS User Manual EuroLAUNCH are made concerning the experiments These requirements will be made on an individual basis with each of the teams Flight Report Documentation FuroLaunch requires a post flight report document for inclusion in the Flight Report that must be produced following each launch The experimenters must submit only one to two pages regarding performance of their experiment during the flight and preliminary results when possible This must be submitted two weeks after the launch campaign each experiment team is expected to present a preliminary performance overview whilst at the campaign following the launch JON Page 16 BEXUS User Manual EuroLauncH 4 BEXUS SYSTEM 4 1 BEXUS flight configuration The typical BEXUS configuration consists of 12 000 m balloon valve cutter parachute Esrange Balloon Service System EBASS flight
18. RF interference test 9 4 7 Esrange Telemetry Station ETM The Esrange Telemetry Station ETM handles the receiving transmitting and recording equipment during preparations and launch 9 4 8 Balloon Pilot The Balloon Pilot handles the balloon piloting system and monitors the housekeeping data 9 5 Page 44 BEXUS User Manual EuroLAUNCH Count down and launch During the countdown phase important count down information is displayed on PA video monitors at various locations around the launch site The nominal lift off time is planned for between 0500 and 2000 LT The launch window is determined by the payload preparation time hold requirements and the time of daylight The decision to start the countdown is taken at a weather briefing immediately before the planned start of count down This decision is based on dedicated weather forecasts as well as wind data obtained by a meteorological balloon released from Esrange some minutes beforehand If the weather conditions are unsuitable for launching the vehicle the launch will be delayed until the flight conditions are fulfilled The general launch procedure may be subject to changes Be sure to design your experiment so it can handle not only the flight but also tests and at least 2 hours of CD on internal batteries in case of possible holds Experiment teams ground equipment will be situated in the Cathedral building transparent communication with the experiment is provi
19. S The inside of the connector requires a standard RJ45 Ethernet connector Connector and drilling pattern are depicted below 134 527 333 1 311 26 97 1 062 H 11 8 1 464 26 97 1 062 E A j o 932 NS 125 39 1 1 539 dim in mm inch o dl f 927 3 1 075 MAX 28 58 1 125 1 Figure 6 4 Drilling pattern for the RJF21B connector source http datasheet octopart com RJF21B Amphenol datasheet 11361 pdf Rightmost Insert CODE A 6 4 Page 27 BEXUS User Manual EuroLAUNCH Thermal Environment 6 4 1 Pre Launch Phase In normal conditions the preparation of the payload is done at a room temperature of approximately 2045C After preparation the payload is brought outdoors to the launch pad The outdoor temperature at the launch pad in Sept Oct is normally between 0 C and 15 C and the exposure time can be up to several hours 6 4 2 Count Down Phase Experience shows that during count down the experiment modules tend to see an increase in temperature over time especially if long holds are required Some actions can be taken at the launch pad to improve the situation however it is recommended that heat sensitive experiment modules or experiment modules that create high temperatures within the gondola should include temperature regulation in the experiment design 6 4 3 Flight phase The thermal environment of the flight may
20. and checklists for your experiment Without these there is a significant risk of failures and delays during the campaign week Safety on balloon pad No one is allowed on the balloon pad without the permission of the Operations Officer In the final 1hour and 30 minutes before launch after the sweet spot tests there is no more access to the experiments Campaign Requirements Flight Requirements Plan This is a document that is compiled by the EuroLaunch Project Management based on input and requests from all experimenters Without good information well before the campaign it might be impossible to fulfil a requirement such as the provision of gases special tools etc Our goal is to have a successful and enjoyable campaign with all teams and their experiments You are always welcome to contact us with any questions 2 1 BEXUS User Manual Definitions Page 9 EuroLAUNcH The BEXUS system consists of the following components according to the EuroLaunch definition BEXUS Ground Equipment EBASS E Link Esrange Facilities Ground Support Equipment Balloon Payload Subsystems Experiment Gondola The complete integrated vehicle to perform the flight BEXUS supporting systems on ground Balloon service system Ethernet up amp downlink Equipment used to monitor and control the flight and telemetry receiving equipment Equipment used to control and communicate with various modules during test and count do
21. curity regulations and arrangements related to the campaign Head of Esrange Launch Team is responsible for the ground safety in the launch areas and also all work with explosives at Esrange Operations Officer OP coordinates all operational work and is the interface with the customer and with Swedish and foreign authorities during countdown flight and recovery Safety Officer Flight Control Officer SO is responsible for flight safety during countdown and flight He she decides in coordination with the customer when to abort a flight Launch Officer LO is during countdown responsible for the ground safety in the launch areas and also all work with explosives at Esrange We accept the content of the text above Customer Mission Manager Project Manager Esrange Project Manager Page 56 BEXUS User Manual EuroLAUNcCH A DUR and SSC cooperation APPENDIX C GONDOLA EXPERIMENT INTERFACE IMAGES Figure C 1 BEXUS 8 exterior with experiment equipment mounted to the outside of the Gondola s Page 57 BEXUS User Manual EuroLauncH Figure C 3 BEXUS 15 showing different mounting techniques
22. ded via a designated Ethernet network The schedule below indicates the standard count down actions relative to launch T 0 A final version of these actions is issued at the pre flight meeting Time Operations Comments T 4H30 Decision meeting T 4H00 Start of Count Down Start pad preparations Experiments on external power External Power Supply Experiment check outs T 2H30 Gondola pick up Experiments on external Power Hercules Power Sweet spot tests Final experiment preparations Latest Access to experiments Go decision from experimenters Ready for Line up T 1H30 Line up T 1H00 Balloon unfolding Point of no return Experiments on gondola internal batteries Removal of external power umbilical T 0H40 Start of balloon inflation 0H00 Balloon release Launch T 4H00 Command cut down followed by recovery 9 6 Page 45 BEXUS User Manual EuroLAUNCH Radio discipline Please observe the following regarding radio communication Use functional names avoid personal names Use basic English Spell by analogy if necessary Use pro words below to minimize the risk of mis readings No horse play or bad language Minimize all radio traffic from 5M until 1M Table 9 1 Radio pro words and meaning Pro words Meaning Affirmative YES Negative NO Active Work commanded is in progress completion will be reported Break Break I must interrupt this conversation because of an urge
23. e Rocket Base MORABA of DLR is responsible for the campaign management and operations of the launch vehicles Experts from DLR SSC ZARM and ESA provide technical support to the student teams throughout the project Figure 1 1 SSC Esrange Space Center near Kiruna in northern Sweden BEXUS experiments are lifted by a balloon with a volume of 12 000 m3 to an altitude of 25 30 km depending on total experiment mass 40 100 kg The flight duration is 2 5 hours The BEXUS payload is modularised to provide simple interfaces good flexibility and independence between experiments All payload service systems necessary for telecommunication payload control and recovery are included in the system High speed telemetry and up link command control of experiments is provided This document describes all the necessary information for a user of the BEXUS system including the services offered by EuroLaunch It defines the requirements that apply to the BEXUS experiment modules and gives design recommendations It also includes a description of the BEXUS system the programmatic elements the pre flight tests and the campaign schedule and finally there is a chapter on quality assurance and safety If you require additional information on the BEXUS system please contact the EuroLaunch project manager or the system engineer of the current project Page 8 BEXUS User Manual EuroLAUNCH ALWAYS READ THIS There is plenty of useful information in t
24. ed EGS84 World Geodetic System 1984 LTC Local Tangent Coordinate System The global reference system World Geodetic System 1984 WGS84 is used for the BEXUS GPS position data This system is based on the ECFF system The Local Tangent Coordinate System LTC is important for observation of the vehicle from Launcher Tracking or Radar Station Details are described in Ref 9 Earth Centered Earth Fixed ECEF If a geocentric coordinate system rotates with the Earth it results in Karth Centered Earth Fixed Coordinate System abbreviated as ECEF The main difference with this system is that the primary axis is always aligned with a particular meridian The xgcgr Axis points toward the Greenwich Meridian which is defined as longitude 0 This coordinate system rotates with the Earth with the primary axis x always through the Greenwich Meridian The position of an object is defined with the geocentric Latitude which is measured positive North of the equator the Longitude 0 which is measured positive towards East from the Greenwich Meridian and the distance d from the Earth center an COS p cos O Facer Yecer d Coso sin O Eq 10 1 ZECEF SIN P Page 50 BEXUS User Manual EuroLauncH Figure 11 1 ECEF Coordinate System The reference ellipsoid is rotation symmetric and every plane cuts the ellipsoid to an ellipse with the flattening fe which is defined with the relative difference of the equator and
25. edule uso dede desde eite ii 36 BA Planning saaan ou iter kain doha mako hahhaha ue Rn 37 8 5 Assembly of balloons and payloads serene 38 8 5 1 Assembly of DallODHss tii 38 8 5 2 Assembly and checkout of payloads sees 38 SONS BOuippmHenDt ui oe oe ee ee AA NAA ANAN 39 8 6 Flight Simulation Test EST esee RUG KABABATA ARAL 40 8 7 Flight Compatibility Test FCT inn GA NTG ADA kA SUN 40 8 8 Flight Readiness Review PR ia 40 8 9 Pre AMEN id 41 9 CAMPAIGN ACTIVITIES cirio iia 42 OT WG A pagdanak led cases uate Mindat Aga ba men cae etna 42 9 2 Balloon launch GANANG Nan NANG is 42 0 3 Safety onthe balloon padi aai io isan 42 9 4 Personnel during the lao NN KALAN 43 9 4 1 Esrange Project Manager id 43 Qr Payload Manati qo estero NANANA AR Na 43 OAS Operations One 43 944 Launch OMcer 224 84 Ga Oh eof edet 43 OAD abet OPE aseo e oe e fot tbe GAGA NAGA 43 9 46 Flectronic SUpETVISOL cis cosi BU HABABABIGAGUGIIKAW GANANG 43 9 4 7 Esrange Telemetry Station ETM eere 43 94 8 Balloon Pit reiten teer e etie eee 43 OS countdown and dun a Aa aries 44 0 0 RA Ec a ha NGA AG 45 9 7 Deliverables data iier ert a ANA BANG 46 2 35 2Durine lolog DITE HE AA AA ae he AA NPA LE Re 46 OO RECOVER naaa AA AA AA a GE 46 9 10 Posteb Hane MCCS aaa KA a AA Aa ANA 46 10 EXPERIMENT QUALITY ASSURANCE oococococccoccnonnnconncconocnnnn
26. een Esrange and the gondola the maximum range is about 400 km Flight profiles are available in numerical form upon request and some typical examples from previous missions are given below gt Page 20 BEXUS User Manual EuroLauncH 30 000 Altitude vs Time BEXUS 08 BEXUS 09 25 000 BEXUS 12 BEXUS 13 20 000 15 000 Alttitude m 10 000 5 000 0 2000 4000 6000 8000 10000 12000 14000 16000 Time s Figure 4 8 Altitude vs Time for typical BEXUS flights DEA VI 25 000 BEXUS 12 BEXUS 13 20 000 B 9 15 000 E 10 000 5 000 o 0 50 000 100 000 150 000 200 000 Ground Range m Figure 4 9 Altitude vs Ground Range for typical BEXUS flights 40 1000 Temperature vs Flight Time 900 Air Pressure vs Flight Time 20 800 E 700 g 0 E 600 5 000 10 000 15 500 9 i 20 Flight Time s 3 eid y E 400 300 rm Outside Air 200 Temperature 100 50 Inside EBASS o Temperature 0 5 000 10 000 15 000 80 Flight Time s Figure 4 10 Measured Atmospheric Data from BEXUS 12 4 6 f Page 21 BEXUS User Manual EuroLauncH Percentage of Apogee Y 100 Esrange dc R UC s gt ES EP Bexus 13 Apogee 25146 m g Figure 4 11 Example of previous BEXUS Flight Trajectory Recovery The payload will be picked up by helicopter for further transport by truck back to Esrange The payload is normally br
27. ett os bea NAG 29 6 7 4 Landing Considerations i sederet en testa tassi TANG AGA 29 6 8 Recommended Tests for Experimenters oooooocccnnocccnoncncnonnncnnnnncnnnnnonnncccnnacinnnos 30 6 3 Vacum testiaine AA AA 30 6 9 2 KE 30 9 9 Mechanical Testos Aa Na di 30 GSA Bench Test enea eae eek ae ee eee elu toes 31 6 9 General Design C OBSIderatlOTIsu ca os cote lesa ret eiui a tere ide Ress 32 6 9 1 Experiment Accessibility aiiis i BAN E He RUE TER AA 32 6 9 2 Availability Of Parts 2 5 siet iie OSA TI ANI REA E RUPEE 32 6 9 3 Experiment Construction Costs sess 32 6 9 4 RedundanCcy eerte os AMAG Pe eara qve Pe PEE 32 6 9 5 Weight and Size Considerations essere 32 6 9 6 Effectiveness of Testing iii deis 32 RAT ABE A AA AA SS 32 6 9 9 Safety inam ANG eaea E T AA RN BAL G E Tia 33 PRE CAMPAIGN ACTVITIES 0 aa a a TE EE 34 7 1 Esrange Safety Board BSB s miii aa NIA Gee PR oie paaa 34 7 2 Campaign Requirements Plan CRP a retia Ble ieee 34 7 3 Payload Assembly and Integration oconnnnccnonncccnnnnnnnnnnononcnonnnaconnnnncnnncncnnnnnnno 34 7 3 1 Experiment Incoming Inspection eese 34 CAMPAIGN ACTIVITIES BEFORE START OF COUNTDOWN 35 8 1 Description of Esrange Space Center sse 35 o e CE 35 8 2 1 Additional Esrange Safety Board meetings coococnnocccooncncnoncninananinnnos 35 8 35 Time Sn e Ea aS 36 8 3 1 Overview of build up sch
28. his manual Make sure that you have found and understood the meaning of the following information Experiment safety If there are hazardous items such as chemicals lasers radiation etc included in the experiments there may be a need for further investigation by the Esrange Safety Board This may take some time and should be done early in the design process Durability of your experiment During the pre flight tests and the count down the experiments will be turned on and off several times over the course of many hours and multiple days Make sure that there is enough battery memory etc to survive these activities in addition to that which is required for the flight Transceivers All equipment that emits or receives RF must have Esrange permission to do so Radio Frequency interference test After the RF test it is not permitted to make any changes to the gondola or experiments before flight If you miss this test during the campaign preparation phase it may be necessary to remove your experiment or fly the gondola with your experiment turned off If your experiment disturbs any of the flight systems it will not be flown at all Weather constraints It is not possible to guarantee a launch during any specific week due to weather constraints Make sure that your experiment can be operated by Esrange staff in case the launch is postponed beyond the date when you have to leave Planning It is essential to have a build up plan
29. his system is used by Esrange for piloting of the balloon It is not used by BEXUS experiments and interference with it must be avoided at all costs 5 2 1 EBASS Overview The Esrange Balloon Service System EB ASS provides functions for e Altitude control e Flight termination e Load cell controlled emergency termination e On board GPS e Housekeeping e Three full duplex asynchronous transparent serial connections for payload control and data reception Figure 5 2 EBASS Unit 5 2 2 Technical Specification of the EBASS Ground Unit Transmitting frequency 449 95 MHz Modulation FM Total data bandwidth 38 4 kbps Nominal Receiving frequency 402 2 MHz Nominal 400 405 MHz Modulation FM Total data bandwidth 38 4 kbps IF bandwidth 50 KHz 100 KHz 250 KHz and 500 KHz Output power 100 Watt Antenna type Helical Antenna Antenna polarisation RHCP Antenna gain 12 dBiC Maximum range 550 km at 30 km float amp LOS 5 2 3 Technical Specification of the EBASS Airborne Unit Antenna type Cross Broadband Dipole Maximum range 550 km at 30 km float amp LOS Transmitting frequency 402 2 MHz Nominal 400 405 MHz Modulation FM Total data bandwidth 38 4 kbps Nominal Receiving frequency 449 95 MHz Modulation FM Total data bandwidth 38 4 kbps Nominal Output power 100 Watt Operation time with maximum battery configuration 40 hours Cut down system Two independent one is timer controlled Altitude control Valve and ba
30. ic requirements of the project or product concerning cleanliness contamination and environment shall be stated in the input to the Flight Requirements Plan When positioning the parts or components the sensitivity to heating ESD and electrical disturbances shall be considered Connectors shall be well marked and preferably keyed Re used item Page 48 BEXUS User Manual EuroLAUNCH 10 4 10 5 It is important to consider the complete history of the re used item by consulting the hardware logbook or former project log book to be sure that it does not include any hidden failures Availability and maintainability Spare parts for components susceptible of failure shall be available during the payload AIT and the launch campaign The design shall allow for easy and fast replacements of such components Handling storage and packing ESD susceptible components shall be handled in an ESD protected environment Before transport the product shall be thoroughly packed to withstand the expected loads The use of a bump recorder is recommended Personnel Safety The BEXUS experiments and dedicated equipment must fulfil safety requirements according to Swedish law The Swedish Work Environment Act is a general act that is backed up by special laws and regulations in different fields The Swedish work environment authority issues these regulations Special provisions apply among others to the following fields Explosives
31. iod of reduced gravity will be experienced but the gondola may tumble and it s suggested that this is not particularly suitable for microgravity experiments The descent speed is high from the start due to the thin atmosphere Closer to the ground it will stabilize at approximately 7 8 m s 4 4 5 Landing Landing is always planned to be in sparsely populated areas preferably without any lakes The landing velocity is approximately 7 8 m s This is equivalent to a drop from approximately 3 m There is a shock absorbing material at the bottom of the gondola that lowers the shock load at landing Nominally the landing is gentle with no damage to the experiments On rare occasions we have seen landing shocks up to 35 g when landing in rocky terrain A water landing is softer but comes with another problem since the gondola is not watertight 4 5 o Page 19 BEXUS User Manual EuroLauncu Figure 4 5 Soft landing BX 14 Figure 4 6 Hard landing BX 15 Launch Ascent Float Open Valve New float Ballast release Cut Down Parachute descent Impact Figure 4 7 BEXUS Flight Profile The performance of the BEXUS balloon may be adapted to the respective mission requirements Ballast release 6 operations are optional and not normally flown on BEXUS Flight trajectory The total distance covered is different for all missions Since all flight systems depend of Line Of Sight LOS betw
32. ion when available During the flight As soon as the balloon is in a steady ascent the Balloon Pilot and Operations Officer will move to the Operations Office in the main building The flight will then be monitored by the Balloon Pilot and the Safety Officer Recovery The helicopter is equipped with tracking receivers for the payload beacon signal and can also be equipped with a payload TM receiver for data reception of the payload s GPS position During the flight the payload trajectory will be tracked by means of the transmitted GPS data in the TM ground stations During the descent of the payload the prediction on the impact point co ordinates is reported to the helicopter from Esrange The helicopter starts their operation to locate the payload after the impact At the impact site the helicopter crew disassembles the flight train for transport by truck back to Esrange Your experiment will then be exposed to vibration shock loads and the hostile environment on the back of the truck The whole operation is normally completed within two days after launch Post Flight Meeting After the recovery a Post Flight Meeting is held to debrief the flight and a short flight performance report is stated A short presentation of the performance of each experiment is requested 10 10 1 10 2 10 3 Page 47 BEXUS User Manual EuroLauncH EXPERIMENT QUALITY ASSURANCE The major concerns of EuroLaunch related to Quality Assura
33. llast release Page 25 BEXUS User Manual EuroLAUNCH A DUR and SSC cooperation DESIGN CONSTRAINTS Mechanical design The balloon gondola M Egon used within BEXUS is shown below At the bottom bulkhead in each gondola rails are provided for experiment fixation Distances between the rails centre points are 360 mm See drawing of rails and gondola in Appendix A Gondola drawings and more gondola images in Appendix C Gondola Experiment Interface Images 3D CAD Models are available on the REXUS BEXUS Teamsite Figure 6 1 M Egon 6 1 1 Experiment mounting Each experiment must be supplied with a sufficient number of brackets or a bottom plate in order to facilitate a safe mounting of the experiment Nominally this happens by bolting to the gondola rails see profile in the figure below Bolt M6 with 23 mm thread length AM o Fo N O Figure 6 2 Experiment mounting rails and anchor bolt M6 The experiment should be structured to withstand the loads mentioned below as well as the loads that will be applied during the integration tests It is the experimenters responsibility to show that the structure and attachment of an experiment is strong enough This can be done by stress calculations or load tests Under no circumstances will there be a flight with an experiment that has a risk of falling off the gondola 6 1 2 Acceleration The design load used for the payload is 10 g vertically and 5 g horizontal
34. ly 6 2 6 3 gt al Ts Page 26 f hy BEXUS User Manual re A DUR and SSC cooperation Electric power Placed on the outside of the experiment structure housing the experiment must have a 4 pin male box mount receptacle MIL C 26482P series 1 connector with an 8 4 insert arrangement MS3112E8 4P Figure 6 3 Pin A Pin B do not connect to chassis or ground Figure 6 3 Amphenol PT02E8 4P A 28 V 1 A 13 Ah battery pack can be supplied to each experiment if needed This battery pack consist of eight SAFT LSH20 batteries in series the battery pack has got a built in 5 A fuse not changeable If the experimenter chooses to use some other electrical system or batteries it has to be discussed with the BEXUS project manager before the critical design review CDR Interface Description for E Link Experiment Channels 6 3 1 Front panel connector E Link side The E link is a fully transparent connection between the ground based local user and the experiment This wireless data link can be used for bi directional purposes the same way as an LAN network connection with the experiment A RJ45 connection will be supplied by SSC for between the experiment and the E link system 6 3 2 Cable mating connector Experiment side A panel mounted connector for the E link is to be used This connector Amphenol RJF21B can be mounted to the front or side panel of the experiment Insert CODE A should be used for BEXU
35. n more experiments being flown In order to do this early system design solutions must be generated so that the mechanical engineers can determine the best approaches to minimizing size and weight Perhaps most importantly lighter payloads will general allow a higher float altitude 6 9 6 Effectiveness of Testing When designing your experiment please take into consideration the testing in the future This is an issue of accessibility but also of design Fast and simple methods of testing calibrating or adjusting important items will save experimenters time This will also make it simpler for testing carried out by EuroLaunch 6 9 7 Shipping When designing your experiment please take into consideration the need for shipment possible configurations and storage transport requirements Page 33 BEXUS User Manual EuroLAUNCH 6 9 8 Safety Safety is of the utmost importance to EuroLaunch Any experiment that is deemed risky to the public staff or experimenters will not be flown Take care to ensure that you perform any simulation analysis and testing that will help to convince EuroLaunch that the experiment is safe to fly If there are any items that you can identify as safety risks keep them in mind during your design as the possibility exists that the experiment will be removed from the vehicle if it poses a danger 7 2 7 3 Page 34 BEXUS User Manual EuroLauncH PRE CAMPAIGN ACTVITIES Esrange Safety Board ESB Every
36. n to Esrange well in advance in order to receive permission to transmit RF At Esrange the reception of weak satellite signals might be jammed and special care must therefore be taken regarding when and how RF transmitting occurs It is also necessary to apply for frequency permission at the PTS Swedish Post and Telecom agency SSC Esrange can either apply on behalf of experimenters or give the information needed to perform such applications The information required in advance includes parameters such as transmitting frequency radiated power bandwidth of signal antenna antenna pattern and modulation type The following frequencies are used in safety telemetry and recovery systems and are therefore not allowed for use by any experiment Table 6 1 Frequencies that are not allowed for use by any experiment 400 405 MHz 449 451 MHz 1025 1035 MHz 1089 1091 MHz 2405 2496 MHz Ch 2 14 in 2 4 GHz band Electrical Grounding Having a well considered and documented grounding concept for your experiment is important in particular to To provide an equipotential reference plane To minimise the common mode based on the requirements To avoid ground loops To protect against shock hazards due a high voltage ESD on a frame or box housing due to electrical harness damage Several grounding options are available to teams such as single point grounding multi point grounding and hybrid systems Different approaches
37. ncH Personnel during the launch 9 4 1 Esrange Project Manager This person acts as an interface between the guests and Esrange personnel All requirements must be sent to him before the campaign so that he can compile the Flight Requirements Plan It is important that he has all information as early as possible in order to avoid delays during the campaign week 9 4 2 Payload Manager This person acts as the contact point for the experimenters during the count down He relays questions between the experimenters and the Operations Officer via WT or telephone He also informs the Operations Officer about status of the Gondola and the experiments and informs him when the PL is ready for pick up The Payload Manager communicates with the Electronic Supervisor and the electronic team regarding the E Link telemetry issues Finally he is responsible for keeping experimenters and guests at the necessary safe distances during pick up and launch 9 4 3 Operations Officer The Operations Officer handles the count down and is the focal point for all activities 9 4 4 Launch Officer The Launch Officer handles all personnel and equipment related to the launch He is also responsible for safety on the launch pad 9 4 5 Safety Officer The safety for third parties is the concern of the Safety Officer He authorises the Balloon Pilot to send commands to end the flight 9 4 6 Electronic Supervisor Handles all issues related to EBASS E Link and the
38. nce QA on the experiment level are that the experiment shall fulfil the interface requirements and that the module can fly in a BEXUS payload without jeopardising the performance of the other systems or experiments In addition EuroLaunch has a strong concern that the experiments shall perform nominally The following advice reflects this concern Materials In addition to normal concerns when choosing materials special attention shall be paid to out gassing phenomena due to vacuum environment during flight As an aid the ECSS Q 70 71 6 Data for selection of space materials and processes may be used Components All electrical and mechanical components must have a reliability that is consistent with the overall reliability of the payload For electronic components MIL std specified types are recommended Additional quality topics In addition to the QA topics above the following topics shall be treated 1f required by EuroLaunch Procured products and audits Careful planning of the procurement and manufacturing must be made for identification of long lead items Preferably a flow chart shall be made which shows the sequence of operations Manufacturing control and inspection For the manufacturing and inspection of critical processes the personnel should be aware of standards in applicable areas such as e Manual soldering according to ECSS Q ST 70 08C e Crimping of connections according to ECSS Q ST 70 26C Specif
39. ndola Electrical Interface Test Ethernet up amp downlink system Electro Magnetic Compatibility Electro Magnetic Interference European Space Agency Electrostatic Sensitive Device Esrange Space Center Flight Acceptance Review Hlight Requirements Plan Flight Readiness Review Flight Simulation Test Ground Ground Support Equipment Hardware Hot Countdown Balloon launch vehicle House Keeping Interface Interface control document Interface Unit Integration Progress Review Line of sight Local Time Local Tangent Coordinate System Page 12 BEXUS User Manual EuroLauncH Mbps Mega bits per second MFH Mission Flight Handbook MORABA Mobile Raketenbasis DLR NC Not Connected NCR Non Conformance Report PCM Pulse Code Modulation PDR Preliminary Design Review PFR Post Flight Report PI Principal Investigator PST Payload System Test QA Quality Assurance RNRZ Randomized NRZ a signalling modulation RX Receiver S W Software SED Student Experiment Documentation SNSB Swedish National Space Board STW Student Training Week T Time before and after launch noted with or TBC To Be Confirmed TBD To Be Determined TC Tele Command TM Telemetry TX Transmission WGS84 World Geodetic System 1984 WT Walky Talky handheld radio ZARM Center of Applied Space Technology and Microgravity 3 2 Page 13 BEXUS User Manual EuroLauncH BEXUS PROJECT OVERVIEW AND MILESTONES Project Organisation The technical supp
40. ng on how the preparation work progresses and the weather forecasts there might be changes during the campaign week itself Table 8 1 Typical BEXUS Campaign schedule Day Action Location 0 Nominal day of student arrival Esrange Safety briefing Polaris Launch Safety briefing Polaris 1 SSC DLR ZARM ESA Team introduction Campaign Information Experiment Preparation Morning meeting Polaris 2 Experiment Preparation CATH Electrical Check Quts CATH Interference Tests CATH Morning meeting Polaris 3 Flight Compatibility Test FCT CATH Meteorology briefing Polaris Flight Readiness Review FRR Polaris 4 Morning meeting Polaris 1 balloon launch opportunity 5 Morning meeting Polaris 2 balloon launch opportunity 6 Morning meeting Polaris OPTIONAL Launch opportunities Experiment results presentations 7 Spare day 8 Spare day 9 Spare day 10 Nominal day of student departure 8 4 BEXUS User Manual EuroLauncH R and 85 cooperation Page 37 Note Test Comment 1 Electrical Check Out All experiments are mounted and connected e External power connection e Power on off e E Link communication test Carried out for all experiments one by one 2 Interference Test Experiments are checked e For interference amongst themselves e All Experiments switched on and verified 3 Flight Compatibility Test Gondola moved to the balloon launch pad by Hercules FCT e Check for i
41. nt message Correction You have made a mistake You should have said or performed or I have made a mistake I should have said Disregard Disregard what I have just said It is not applicable or is in error Execute Carry out the instruction Go ahead I am on the net Proceed with your transmission I say again I am repeating the message for clarity Out I have completed this conversation Proceed Go ahead with your task I copy I received your last message satisfactorily and understand I copy Wilco I have received your message understand it and will comply Say again Repeat your last communication Speak slower You are talking too fast Standby I must pause for time or wait a few moments Verify Check status or correctness Roger Acknowledge your transmission 9 7 9 8 9 9 9 10 Page 46 BEXUS User Manual EuroLauncH Table 9 2 Call sign during pad preparation Functional names Function in the balloon processes Operation Operations Officer Launch Officer Launch Officer on balloon pad Electronics Electronicresponsible person at launch pad for EBASS E Link Assistant Electronics Assistant electronic responsible at launch pad for EBASS E Link Safety Safety Officer TM Telemetry station Pilot Balloon Pilot Scientist Scientist experimenter responsible Payload Payload Manager Deliverables data EuroLaunch will add this informat
42. nterference with EBASS etc e Experiments switched on one after the other e All experiment systems must be running e Mass measurement Long waiting times 3 4 h possible Notice that after this test e No more experiment preparation are allowed e Only the batteries can be exchange charged Planning Experiment teams are strongly advised to think through all aspects of the experiment the build up all tests the launch and the flight phase With this input make a detailed plan of how to work who is doing what team member Esrange staff etc and how much time is needed to do all this A checklist is the key item to success even the smallest thing such as flipping a switch should be in the list Without good build up plans and checklists there is a significant risk of failures and delays during the campaign week All of this should be documented in the SED 8 5 JON Page 38 BEXUS User Manual EuroLauncH Assembly of balloons and payloads 8 5 1 Assembly of balloons All assembly and preparation activities related to the balloon and its subsystems are the responsibility of the EuroLaunch team This is normally done in the Basilica building 8 5 2 Assembly and checkout of payloads Payload assembly and preparations are conducted by the BEXUS Project Manager together with EuroLaunch staff and the experiment teams A dedicated person will be assigned to each gondola Working space in the launching area will be alloca
43. ogramme It is continually updated and developed in order to serve the experimenters and operators better It describes important information about flights for experimenters interface details design guidelines and testing Keywords BEXUS manual interface EuroLaunch testing design This is not an ICD document Table of Contents 1 INTRODUCTION o 7 2 ALWAYS READ TAS a sate aa a ends gate ea san AA E eG acne teas 8 A A AA 9 DAMEN a canc O O ac ails Mate ia acd le Gail dc 10 23 Applicable OCIOSO GNUN 10 2A oXDBreVIALIOHS aap NAA aako 11 3 BEXUS PROJECT OVERVIEW AND MILESTONES eee 13 3 1 Project Organisation e ER ESOS SERT TAA UR Ra a QUE da tO Inn 13 3 2 BEXUS Flight Tia focii qoaa Ped Meo ed mq 13 3 3 Experimenter Role an nA a R a a altea 14 A EU UM 14 3 5 Experimenter Documentation Requirements esee 14 3 5 1 Student Experiment Documentation SED sese 14 3 5 2 Campaign Requirements Plan CRP eene 14 3 5 3 Flight Report Documentation ma maana makan 15 4 BEXUS SYSTEM suscitadas 16 4 1 BEXUS flight configuration sat ia hacia tica 16 2 2 EU A 17 4 3 A O e e e 17 44 Flight sequence uie ue dI ERES REA i 17 ql dqJdunelb AA PAA 17 AAD JAscent phase mma ai seres 18 41 3 AA AA 18 Bod A Descent INAS aaa a aaa an mada 18 44S iron d D PP aaa a LABAN PENNE 18 25 Erst TA SOUL AA AA AA 19 Ao ReCOVELY LAAL a t
44. onncconccconocannnnnncconnc ns 47 101 Materials AA NA AA 47 10 2 Components aNG GABI BUNGANGA AG E ERE 47 10 3 Additional quality TOPLESS 47 10 4 Personnel Satelital iia 48 10 5 Safety at Esrange Space Center apa Nama a Naan rias da 48 11 COORDINATE SYSTEM DEFINITION NG NIAN 49 11 1 Earth Centered Earth Fixed ECEF 1 111111212112 aaa 49 11 2 Local Tangential Coordinate System LTC eee 51 APPENDIX A GONDOLA DRAWINGS eeeseeeeeeeeeeeen enne tnnt netn netten enne tnnt nnne 53 APPENDIX B ESRANGE SAFETY AND SECURITY COMPLIANCE CONFIRMATION BALLOON aps ap ANA ANA IBANAG 55 APPENDIX C GONDOLA EXPERIMENT INTERFACE IMAGES f Page 7 BEXUS User Manual EuroLauncH INTRODUCTION The REXUS BEXUS programme allows students from universities and higher education colleges across Europe to carry out scientific and technological experiments on research rockets and balloons Each year two rockets and two balloons are launched carrying up to 20 experiments designed and built by student teams The REXUS BEXUS programme is realised under a bilateral Agency Agreement between the German Aerospace Center 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 Center of SSC and the Mobil
45. or simulator shall be connected via the interface harness Experiment data shall be supervised and recorded during the test A nominal realistic count down and flight procedure shall be followed Flight Compatibility Test FCT When all experiments are installed in the gondola a RF interference test is conducted The gondola is picked up by the launch vehicle and placed together with all other transmitting electrical hardware at the same distances as in a real flight A test with all electronic equipment as well as experiments operating in flight mode is then performed If an experiment is causing interference with EBASS or E Link it will not be granted permission to fly If there is interference between two experiments the problem will be discussed and a solution or compromise will be found After the FCT the gondola is sealed and there are no further changes possible to any experiment During count down there are very limited possibilities to fix any problem If there is no quick fix available the experiment may have to fly with limited functionality or in switched off mode Flight Readiness Review FRR The Flight Readiness Review FRR is conducted by the EuroLaunch coordinator of the launch campaign after successful completion of the RF test and ground support stations checkout The purpose of the FRR is to authorise start of the count down phase In order to do this it is necessary To ensure that all experiments are ready f
46. or the flight For this each appointed experiment module manager team leader shall give a status report at the meeting In addition the PI is requested to state the operative status of the experiment To ensure that all ground and payload service systems essential for a successful launch flight and recovery are operating nominally For this each appointed system responsible shall give a status report at the meeting To review the count down list To inform all relevant personnel of the safety regulations applicable during the count down phase 8 9 Page 41 BEXUS User Manual EuroLauncH to inform all relevant personnel of general arrangements implied during the count down phase Pre flight meeting After a successful FRR meeting there will be a pre flight meeting The objective of this meeting is to verify that all flight hardware is ready Esrange stations are prepared and other flight conditions are in favour of a possible start of count down 9 2 9 3 Page 42 BEXUS User Manual EuroLauncH CAMPAIGN ACTIVITIES Weather constraints Wind flight trajectory and visibility are important variables taken into consideration before starting a count down There is no magic numbers and the decision to start a count down is solely in the hands of Esrange personnel Note It is not possible to guarantee that a launch can take place on one of the 5 days allocated during the campaign week Plan and prepare so that it is possible for
47. ort in the integration and testing phase as well as the campaign management and operations is provided by EuroLaunch EuroLaunch is a joint venture of SSC and the Mobile Rocket Base of MORABA the German Aerospace Center DLR The DLR service part concerning experiment integration testing and student support is provided by ZARM in Bremen The scientific evaluation of the experiment proposals and the financial support of the students are the responsibility of the German Space Agency DLR and the Swedish National Space Board SNSB in the latter case through cooperation with the European Space Agency ESA At EuroLaunch the following key positions will be assigned for every flight project e Project manager e Payload manager e Mechanical design responsible e Electrical design responsible e Telemetry TM and Telecommand TC systems responsible e Electric Ground Support Equipment EGSE responsible One person can have dual assignments Additional positions will be assigned during the campaign see chapter 9 4 The majority of the communication between EuroLaunch and the experiment teams shall pass through the Project managers BEXUS Flight Ticket In the BEXUS flight ticket which is offered to the international student community the following services are included General management and planning of the BEXUS project Provision of launch vehicle and subsystems necessary for a flight mission of 2 5 hours with recove
48. ought back to Esrange within a day or two after launch During the design phase experimenters should keep recovery accessibility in mind It is a good idea to create a recovery plan document for the helicopter crew early in the design process in order to avoid overlooking how this aspect will affect accessibility and other issues 3 pA i Figure 4 12 Landing position of BEXUS 7 5 1 Page 22 BEXUS User Manual EuroLAUNCH TELEMETRY SYSTEMS The two telemetry systems used are E Link and EBASS E Link is used by experimenters to transfer data to and from ground EBASS is used by Esrange for piloting and data taking EB ASS is used only by Esrange and not by BEXUS experimenters E Link telemetry system Esrange Airborne Data Link E Link is a telemetry system that offers a simplified interface to experiments with a standard Ethernet protocol The system can also handle other types of synchronous and asynchronous user interfaces Only the Ethernet interface is provided for BEXUS Experiments 5 1 4 E Link System Overview The E Link system consists of a ground station and an airborne unit The ground station consists of an antenna an antenna controller and a Monitor amp Control Unit The airborne system includes the main unit an antenna a battery and an RF interface unit At least one connection is available to all experimenters The main features of the system are e A standard and easy to use interface for payloads Ethe
49. rnet 10 100 Base T Protocol e MIL C 26482 MS3116F 12 10P connectors as seen in Figure 5 1 e High data bandwidth 2 Mbps duplex nominal e Optional synchronous and asynchronous interfaces e All electrical parts are approved by FCC and ETSI standards e Fixed IP address allocations mda a PA Figure 5 1 E Link Airborne Unit BEXUS User Manual Page 23 EuroLAUNCH 5 1 2 Technical Specification of the E Link Airborne Unit Antenna Operating frequency Max output power Modulation Channel bandwidth Maximum range at LOS Data bandwidth User interfaces Power supply Operation time Weight Vertical polarised omni S band Peak 10 watt DSSS Nominal 11 MHz 500 km at 30 km altitude TBC 2 Mbps duplex nominal 2 Ethernet 10 100 Base 3 asynchronous duplex RS 232 422 channels 20 to 38 volt DC Nominal 5 11 hours Nominal 20 kg including batteries 5 13 Technical Specification of the E Link Ground Unit Antenna Operating frequency Max output power Modulation Channel bandwidth Maximum range at LOS Data bandwidth User interfaces 1 8 meter parabolic dish S band Peak 10 Watt DSSS Nominal 11 MHz 500 km at 30 km altitude TBC 2 Mbps duplex nominal Ethernet 10 100 Base T 2 asynchronous RS 232 422 channels l synchronous channel up to 1 Mbps Page 24 BEXUS User Manual EuroLauncH 5 2 A DUR and SSC cooperation Esrange Balloon Service System EBASS T
50. ry Integration of participating modules into the flight configured payload and pre flight testing of payload TM TC flight simulation test Assembly of the payload into the gondola and pre flight testing at the Esrange launch site Provision of laboratory facilities at the Esrange launch site Launch and recovery of payload Data acquisition with provisions of real time quick look and replay data from gondola and payload subsystems Disassembly of payload and return of experiments BEXUS Campaign report 3 3 3 4 3 5 3 5 1 3 5 2 Page 14 BEXUS User Manual EuroLauncH Experimenter s Role Once selected to participate in the REXUS BEXUS programme the teams become a part of the mission team Their primary responsibility is to ensure the timely delivery of their portion of the scientific payload in good order This responsibility extends to defining the investigation providing the instrumentation timely processing of data and publishing of results The experimenters must also contribute to establishing and conducting the operational programme through correspondence and fulfilment of the documentation requirements The successful operation of experiments is vital to the overall success of the REXUS BEXUS missions EuroLaunch supports the teams in order to see the good scientific returns Information and expertise is available where required for assisting decisions relating to design component materials
51. safety manual pdf 5 SSC Esrange Space Center User s Handbook ver 2 11 April2011 http www sscspace com file usershandbook pdf 6 ECSS Space product assurance Data for selection of space materials and processes ECSS Q 70 71A rev 1 ESA Publications Division 2004 http ecss nl forums ecss dispatch cgi standards showFile 100362 d200406221232 17 No ECSS Q 70 71Arev1 2818June2004 29 pdf 7 EuroLaunch RXBX REF SED Template v4 0 06Dec12 8 EuroLaunch RXBX REF SED Guidelines v4 0 06Dec12 Applicable documents 9 Montenbruck Oliver amp Gill Eberhard Satellite Orbits Springer Verlag 2000 10 Vallado David A Fundamentals of Astrodynamics and Applications McGraw Hill Companies Inc 1997 2 4 BEXUS User Manual Page 11 EuroLAUNCH Abbreviations AGT AIT APID ASAP ATC BCR BEXUS CD CDR CRP DLR EAR EAT EBASS ECEF EGon EIT E Link EMC EMI ESA ESD ESRANGE FAR FRP FRR FST GND GSE H W HCD HERCULES HK I F ICD IFU IPR LOS LT LTC Argos GPS and ATC Transponder Assembly Integration and Test Application Identifier As Soon As Possible Air Traffic Control BEXUS Campaign Report Balloon borne EXperiments for University Students Count Down Critical Design Review Campaign Requirement Plan Deutsches Zentrum f r Luft und Raumfahrt Experiment Acceptance Review Experiment Acceptance Test Balloon piloting system Earth Centered Earth Fixed Esrange balloon Go
52. see temperatures down to 80 C Figure 6 5 below shows temperature graphs of a number of PTU sondes flights during the normal BEXUS campaign period PTU Data 30 17 T T T T I f Std Atmosphere 76 F 2008 09 24 08 44 E 2008 10 03 07 04 25 a ES m m T Biss i ete eR SIRE dnd EEROR AASE TOTEE E Ya RAS ETE i 2009 10 10 06 01 EC 2010 10 06 07 19 E il 2010 10 11 03 58 E 2011 09 27 10 30 20 TO 4 EUH Weseepeesessssessssesssmeereseeesseecsesesltsseveeececesersscseesvosevececesseeeqeeecseevovecececis PAANAN ANAN AA AA dr E A 2 15 e AP A AAN 4 E ri 10 iaa aure TT RR ui rssauwsuxetePresvesasvezaawhTAsfAaaes VERRE A VENERE ERRERERARTEPEECEVENE AA a 5 YATA AAP AA ss O c o o A AA Q o 70 60 50 40 30 20 10 0 10 20 Temperature C Figure 6 5 PTU Sondes Temperature graphs 6 4 4 Post flight phase After the impact the payload will most likely be subjected to snow and cold air in the impact area for a period of typically one to two days The temperature during the season when BEXUS is launched is normally between 0 C and 15 C Experiments sensitive to low temperatures must be designed for these post flight conditions 6 5 6 6 Page 28 BEXUS User Manual EuroLAUNCH Radio frequency constraints In general for every transmitter or receiver that will be used at SSC Esrange during a campaign information must be give
53. solid surface with a clear area around the test area Page 31 BEXUS User Manual EuroLAUNcCH The experiment should then be loaded with between 10 and 30 times the experiment s own weight depending on the structural design in a stable and secure manner Basic Procedure 2 An area should be cleared in which the experiment can be safely dropped the persons carrying out the procedure should be wearing a sufficient level of safety gear The experiment should be dropped from a height of 1 3 metres onto a solid surface Afterwards the experiment should be checked for full functionality by system tests but a visual check is also important to see if any cabling or mechanisms have been affected 6 8 4 Bench Test All experiments should carry out a bench test of their experiment before transport The test should be carried out for a maximum duration mission 2 hours wait before launch 6 hour flight and possibly a wait time before recovery when appropriate This test should be carried out as there are many issues which arise only after long duration of operation Where possible this is best done using the same power system as for flight with voltage and temperature monitoring of the batteries Possible issues that have occurred in the past are microcontroller malfunction with low power and battery rupture due to overdrawn current The experiment should be supervised at all times in case of a failure It is the responsibility of the
54. ted to each team normally in the Cathedral building Figure 8 1 From left to right the Dome the Chapel Cathedral and Basilica preparation assembly buildings e me SY V Page 39 BEXUS User Manual EuroLAUNCH 8 5 3 Equipment There is one soldering station located in the Cathedral assembly hall There is also basic measurement equipment and toolboxes available to borrow If you need some special tools or equipment be sure to either bring it with you or specifically state that you need it when you give input to the Flight Requirements Plan Figure 8 2 Standard Equipment Set at Esrange O 30V 2 54 DC POWER SUPPLY Figure 8 3 Standard Power Supply at Esrange 8 6 8 7 8 8 Page 40 BEXUS User Manual EuroLAUNCH Flight Simulation Test FST When all experiments are operating nominally and there is enough time for this test a simulated count down and flight sequence is performed All telemetry and telecommand signals will be recorded in the telemetry ground station during the test It is important that the any changes modifications made to H W or S W after the Flight Simulation Test are restricted to a minimum Non conformances discovered during the test can of course be corrected but care must be taken to verify that no further malfunctions are induced by the correction Basic Procedure The experiment shall be integrated and in flight configuration The telemetry and telecommand checkout system
55. to din edo e 21 5 TELEMETRY SYSTEMS tapa a put eiat ANAN 22 5 1 H Linktelemetry System cose GANANG i EU Heo SER Sete Lee qa a rines 22 dill E Eink System OvervieW Goes soot te ais rer codes 22 5 1 2 Technical Specification of the E Link Airborne Unit 23 5 13 Technical Specification of the E Link Ground Unit 29 5 2 Esrange Balloon Service System EBASS eene 24 Sub EBASS OTEN di dde teas 24 5 2 2 Technical Specification of the EBASS Ground Unit 24 5 2 3 Technical Specification of the EBASS Airborne Unit 24 6 DESIGN CONSTRAINTS aaa 25 GA Mecha Cal G1 OT ha n a qu as AA 25 6 1 1 Experiment mounting PA AA AA AN 23 6 L2 Acceleration KA KAMANG i AS ANAKAN EN 25 6 2 NP e kanta 26 6 3 Interface Description for E Link Experiment Channels 26 6 3 1 Front panel connector E Link side see 26 6 3 2 Cable mating connector Experiment side ssesssss 26 6 4 Thermal EXITO MEL Aa GAL 27 6 4 1 Pre Launch Phase ini 27 64 2 Count Down Phase tdt ANG od aan teu 27 Ga A NANA AL PBA BANA NANGKA GRAN 27 GAA Post tlisht phas iii tii 27 6 3 Radio Irequelie y consta 28 6 6 Electrical KK 28 6 7 Operations and durabllit asii nn e ttn i Heo inset e leet dac a rase 29 Gal Opera Aah AA NAKA ON 29 FP MN ood 29 Gua Hercules IPAG aa AN KG
56. wn The parts of BEXUS giving the lifting force Experiment modules and all subsystems All systems required for flight control recovery and telemetry Experiment equipment and the carrier structure 2 2 2 3 Page 10 BEXUS User Manual EuroLauncH References NOTE All references documents can be found on the BEXUS Teamsite along with the manual The ECSS references link directly to the documents themselves firstly though in order to access the documents registration is required this is easy and free for the user 1 ECSS Space project management Project planning and implementation ECSS M ST 10C ESA Publications Division 2008 http www ecss nl forums ecss dispatch cgi standards showFile 100743 d2009030 6173339 No ECSS M ST 10C_Rev 1 6March2009 pdf 2 ECSS Space product assurance Manual soldering of high reliability electrical connections ECSS Q ST 70 08C ESA _ Publications Division 2009 http ecss nl forums ecss dispatch cgi standards showFile 100753 d200903061908 30 No ECSS Q ST 70 08C 6March2009 pdf 3 ECSS Space product assurance Crimping of high reliability electrical connections ECSS Q ST 70 26C ESA Publications Division 2008 http ecss nl forums ecss dispatch cgi standards showFile 100679 d200811111311 54 No ECSS Q ST 70 26C 31July2008 pdf 4 SSC Esrange Space Center Esrange Safety Manual REA00 E60 ver 3B 23June2010 http www sscspace com file esrange
57. y and security conditions for the campaign O RN at the Esrange Space Center This document shall be signed by the customer s range user s prime contractor s Mission Manager Project Manager and by the Esrange Project Manager One copy of this document and of the Esrange Safety Manual ESM REA00 E60 is submitted to the customer s Mission Manager Project Manager Swedish law and Swedish safety and security regulations apply to all activities at Esrange The Esrange Safety Manual provides safety regulations and criteria associated with launching of sounding rockets UAV s and stratospheric balloons and must be followed by all parties involved Temporary and complementary regulations may be issued at any time via the Esrange Project Manager and conveyed to the Mission Manager Project Manager If the customer has own rules that are more stringent the customer s rules shall be respected when relevant and applicable Customer Positions and Responsibilities Mission Manager Project Manager is responsible for the customer s work at Esrange and is responsible to see that all customer and customer s contractor personnel follow existing rules and instructions He she is the contact point between the customer and Esrange SSC Esrange Positions and Responsibilities Esrange Project Manager is responsible for the campaign coordination at Esrange and is the contact point between Esrange and the customer He she shall also superintend all safety and se
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