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TallerdeDiseñodePicosatélites(CUBESATS)yEstacionesdeTierra
TallerdeDiseñodePicosatélites(CUBESATS)yEstacionesdeTierra.©GuillermoOrtega 1
AnalysisofSpaceMissionswithapplicationtopico‐satellites
Wed.October14th,200914:00to18:00
Control Division, TEC-ECM
TallerdeDiseñodePicosatélites(CUBESATS)yEstacionesdeTierra
TallerdeDiseñodePicosatélites(CUBESATS)yEstacionesdeTierra.©GuillermoOrtega
• Part1:Fundamentals(30min)– Backgroundonspaceproject’sanalysis,roles,andresponsibilities,inputandoutputoftheanalysisphases
• Part2:Analyzing(1.5h)– Practicalstepbysteptechniques,howto’s,examples,etc.
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TallerdeDiseñodePicosatélites(CUBESATS)yEstacionesdeTierra
TallerdeDiseñodePicosatélites(CUBESATS)yEstacionesdeTierra.©GuillermoOrtega
Part 1: Fundamentals (30 min)
• Definitionsandbackground• Roleofspaceanalystinaspaceproject• Spaceprojectphasesandspaceanalysis• Analysistechniques• Analysistools
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Control Division, TEC-ECM
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Definitions and background
• Analysisofamission:processofstudyingandanalyzingmissionrelationsbetweenorbit,attitude,andbudgets(link,mass,power,thermal)tofulfilltherequirementsofagivenmission
• Missionanalyst:thepersoninchargeofperformingtheanalysis
• Satellitecategories:– Pico<2Kg– Nano<10Kg– Micro<100Kg– Mini<500Kg– Small<500Kg– Large>1500Kg
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Control Division, TEC-ECM
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Role of space analyst in a space project
• Identifyrelevantrequirements,needs,andconstraints
• Trade‐offalternativemissionscenariostofulfillrequirements
• Analyzesystembudgets• Defineamissionconcept• Sketchamissiontime‐line• Shareresultsandproducereport
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Control Division, TEC-ECM
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Space analyst skills
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Ascent Entry
Interplanetary
Rendezvous
Loitering
Mission Arcs
Disciplines
Technologies
Propulsion
Aerodynamics
Structures
Systems Optimization
MathematicalmodelingSoftware design and
development
Informatics skills
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Space project phases and space analysis
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Production-ground qualification testing
Detailed definition
Utilization
Disposal
ECSS-E-10 http://www.ecss.nl
B C E FD0 A
Mission needs identification
Feasibility
Preliminary definition
Control Division, TEC-ECM
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Space project phases and space analysis
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0 A
Mission concept definition
Mission feasibility analysis
Control Division, TEC-ECM
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Phase 0 work flow
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KoMStudy of
mission requirementsmission needs
mission constraints
Identification of mission concepts
Mission Definition Review (MDR)
Analysis of programmatics
Control Division, TEC-ECM
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Analysis techniques
• Timemeasurement:aJuliandateisdefinedastheintervaloftimeindaysandfractionsofaday,sinceJanuary1,4713BCGreenwichnoon,Julianprolepticcalendar
• Spacemeasurement:coordinatesystemsandtheircorrespondingtransformations
• AstrodynamicsIntegratorsandPropagators:Anintegratorisanalgorithmtoperformthemathematicaloperationknownasintegration,afundamentaloperationincalculus.Apropagatorisamathematicalalgorithmabletocomputeapredictedstateofaspacecraftbasedonitspresentstate
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Analysis techniques: Orbital Elements
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νω
Ω
i
Ascending node
Vernal Equinox
ApoaxisOrbital plane
Equatorial plane
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Analysis tools
• Simplespreadsheet–SMADSbook
• Mediumcomplexitytools–STK,SIMvis,STA
• Highaccuratetools–GNCDE,SpaceLIB,ATPE
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Analysis tools: Spreadsheet
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Control Division, TEC-ECM
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Analysis tools: ASTOS
• Usedforascent,re‐entryapplications
• DevelopedbyASTOSSolutionsGmbH
• Version6.1AvailableinWinXP,Linux(sooninMAC)
• http://www.astos.de
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Analysis tools: LAREDO
• CalculatetrajectoriesofrendezvousanddockingbetweentwospacecraftinanyplanetoftheSolarSystem
• Thetoolisabletoperformthecalculationoftrajectoriesbyusingasetofpredefinedmaneuversspecificallydesigntoperformtherendezvousanddockingbetweentwospacecraft
• Developedby“GMV”
• Version1.7.1inWinXPandMATLABR14
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Analysis tools: POINT
• POINTisintendedtosupporttheanalysisanddesignoflowthrusttrajectories
• ItcanbeusedinfeasibilitystudiesforthefastassessmentoftypicalquantitiescomingfrommissionanalysisliketotalVrequirements,timeofflight,departureandarrivalconditions
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Analysis tools: STK
• CommercializedbyAGIinUS
• Calculatepositionandorientation
• Evaluateinter‐visibilitytimes
• Determinequalityofdynamicspatialrelationships
• OnlyWindows
• http://www.agi.com
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Analysis tools: STA
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http://sta.estec.esa.int
TallerdeDiseñodePicosatélites(CUBESATS)yEstacionesdeTierra
TallerdeDiseñodePicosatélites(CUBESATS)yEstacionesdeTierra.©GuillermoOrtega
Part 2: Analyzing (1.5 h)
• Studyingtherequirements• Performingtheanalysis
– Problemphasing– Launchandorbitinjection– Deploymentandcommissioning– Stationkeepingandorbitmaintenance– De‐commissioningandgraveyarding
• Reportingandsharing
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Analysis steps of phase 0
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Studying the requirements
Performing the analysis
Reporting and sharing
KoM
MDR
Time-Line
Control Division, TEC-ECM
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Study case
• StudyofthelowEarththermosphere
• Thethermosphereisbiggestofallthelayersoftheearth'satmospheredirectlyabovethemesosphereanddirectlybelowtheexosphere
• Withinthislayer,ultravioletradiationcausesionization
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Troposphere
Stratosphere
Mesosphere
Thermosphere
Exosphere
500
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Analysis steps of phase 0
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Studying the requirements
Performing the analysis
Reporting and sharing
KoM
MDR
Mission Statement + Requirements
Time-Line
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Mission statement
• TostudyinsituthetemporalandspatialvariationsofanumberofkeyparametersinthelowerEarththermosphereataltitudesbetween90‐300km:– Density– Temperature– Pressure– Particleconcentration– Radiation– Dragmodeling– etc
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Mission Statement
must be cle
ar, and
brief
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Needs and Constraints
• ThesetofmeasurementshallprovideacomprehensivedatabaseastoallowtoupdatetheEarththermospheremathematicalmodels
• Thesetofmeasurementshallbeobtainedinlessthanhalfayear(<6Months)fromthebeginningofthemission
• Thetotalcostofthemissionshallbelessthan5MEUR,includingoperationsbutexcludinglaunchcostthatshallbetreated
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Requirements
• Themeasurementshavetotakeplaceeveryday(dayandnightvariations)
• ThemeasurementshavetotakeplaceinalllongitudesoftheEarth
• ThemeasurementshavetotakeplaceinlatitudesoftheEarthbetweenZerodegand80deg
• ThemissionshallcomplywithESAECSSStandardsantheESAcodeofconduct
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Analysis steps of phase 0
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Studying the requirements
Performing the analysis
Reporting and sharing
KoM
MDR
Mission analyst studies all details of
the requirements and proposes alternative scenarios to trade-off
Time-Line
Control Division, TEC-ECM
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Studying requirements, needs, and constraints
• Payloadshallbeformedbyasetofinstruments:densitometer,thermometer,radiometer,etc
• WeneedalmosttotalEarthcoverage• Weneedabrieflastingspacecraft(only6months)• Orbitshallbebetween300and90Km=>Allows
decay• Continuosmeasurementanddownloadtoground
station• Levelofautonomyisrelativelylow• Costisamaindriver!(5MEUR)
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Studying requirements, needs, and constraints
• Orbitshouldnotrepeatgroundtrack• Orbitshouldswapallaltitudesbetween300and90
• Allmeasurementsshallbespatiallycorrelated
• Downloadtogroundshouldtakeplaceassoonasmuchaspossible(noon‐boardstoragecapabilities)
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First mission scenario
• 1singlespacecrafttypeMINI(about500Kg)• Possibleorbittypestostudy:
– Polarorbit– Inclinedorbit– SunSynchronousorbit
• Impossibleorbittypes(discarded):– GEOstationary– Molnya– etc
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MiniSAT possible concept
• MiniSATfeatures– Mass:500Kg– Side:50cm– Area:0.25m2
– Cd:1.05
• Control– activewithIMUand
RWA
• Propulsion:– 6redundantthrusters
• Power:– Smallsolararrays
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First mission scenario: Polar
• PolarorbitsaregoodforentireEarthcoverage
• At300Km,thisorbitswapstheentireEarthafterabitmorethanaday
• Earthrevolvesunderneath
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Control Division, TEC-ECM
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First mission scenario: Polar
• Semimajor‐axis:• Eccentricity:• Inclination:• RAAN:• Arg.ofperiapsis:• Trueanomaly:• Apogeeradius:• Perigeeradius:• Period:• Meanmotion:
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First mission scenario: Inclined
• Inclinedorbitsonlysatisfytherequirementofcoverageoflatitudesbetween80degandzerodegwhentheyhave80deginclinationormore
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First mission scenario: Inclined
• Semimajor‐axis:• Eccentricity:• Inclination:• RAAN:• Arg.ofperiapsis:• Trueanomaly:• Apogeeradius:• Perigeeradius:• Period:• Meanmotion:
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First mission scenario: Sun-Synchronous
• WillaSun‐Synchronousorbitwork?
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First mission scenario: Sun-Synchronous
• ASun‐Synchronousorbitcombinesaltitudeandinclination
• anobjectonthatorbitascendsordescendsoveranygivenpointoftheEarth'ssurfaceatthesamelocalmeansolartime
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First mission scenario: Sun-Synchronous
• SSOorbitsaregoodforEarthobservationmissionssincethesatellitecrossestheEquatoralwaysatthesamelocaltime
• Theysimplifythesatellitedesignsinceeclipsedurationsarealmostconstant
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Control Division, TEC-ECM
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First mission scenario: Sun-Synchronous
• Semimajor‐axis:• Eccentricity:• Inclination:• RAAN:• Arg.ofperiapsis:• Trueanomaly:• Apogeeradius:• Perigeeradius:• Period:• Meanmotion:
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Control Division, TEC-ECM
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Checking mission life time possibilities
• Missionshalllastlessthan6months:studydecayandmeanstoprolongmission
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Alternative mission scenario: PicoSAT
• Severalsatellites(flotilla)typePICO(2Kg)
• Possibleorbittypes:– Polarorbitconstellation– Walkerconstellation
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Student with CubeSAT at the PicoSatellite workshop at ESTEC, Netherlands, January 2009
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PicoSAT possible concept
• PicoSATfeatures:– Mass:2Kg– Side:10Cm– Area:0.010m2
– Cd:1.05
• Control:– Magneticfield
• Propulsion– None
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Alternative mission scenario: Polar constellation
• PolarconstellationsallowcoverageofentireEarth
• Caseof5satellitesat300Km
• Temporalandspatialseparation
• Orbitsencounteratthepoles
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Control Division, TEC-ECM
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Alternative mission scenario: Polar constellation
• Semimajor‐axis:• Eccentricity:• Inclination:• RAAN:• Arg.ofperiapsis:• Trueanomaly:• Apogeeradius:• Perigeeradius:• Period:• Meanmotion:
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Control Division, TEC-ECM
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Alternative mission scenario: Polar constellation
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Avoiding collisions on Polar constellations
• Collisioncanoccurwhensatelliteencountereachotheratthepoles– RAANseparatesthemtemporarily– ArgumentofPeriapsisseparatesthemspatially
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Alternative mission scenario: Walker constellation
• Isawellknowpatterndesignforconstellations• Use3numberstodefineaconstellation:T/P/F
– Tisthenumberofsatellites– Pisthenumberoforbitalplanes– Fistherelativespacingbetweensatellites
• S=T/Pnumberofsatellitesperplane• PUisthePatternUnitanis360deg/T• PlanesarespacedatintervalsofSPUsinnode
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Alternative mission scenario: Walker constellation
• PossiblegoodsolutionwithWalker=N/5/30
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Control Division, TEC-ECM
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Alternative mission scenario: Walker constellation
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Control Division, TEC-ECM
TallerdeDiseñodePicosatélites(CUBESATS)yEstacionesdeTierra.©GuillermoOrtega
Alternative mission scenario: Walker constellation
• Semimajor‐axis:• Eccentricity:• Inclination:• RAAN:• Arg.ofperiapsis:• Trueanomaly:• Apogeeradius:• Perigeeradius:• Period:• Meanmotion:
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Control Division, TEC-ECM
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Trade-off between the two scenarios
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Singlesatellite FlotillaDeployment X
Operations X
Coverage X
Resolution X
Failuretolerance X
Cost X
FINALSELECTION X
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Orbital perturbations
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• Earthoblateness:
• SunandMoon:
• Earthatmosphericdrag:
• Solarradiationpressure:
Control Division, TEC-ECM
TallerdeDiseñodePicosatélites(CUBESATS)yEstacionesdeTierra.©GuillermoOrtega
Analysis steps of phase 0
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Studying the requirements
Performing the analysis
Reporting and sharing
KoM
MDR
Detailed analysis of the performance of a single PicoSAT in our Walker constellation
Time-Line
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Problem phasing
• PicoSATlaunchandorbitinjection• PicoSATdeploymentandcommissioning
• PicoSATstationkeepingandorbitmaintenance• PicoSATde‐commissioningandgraveyarding
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Time-Line
Launch and orbit injection
Station Keeping
De-commissioning
Graveyarding
Deployment
Control Division, TEC-ECM
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Launch and orbit injection
• Analysisofascenttrajectorywithorbitalparameters:– Altitude:300Km– Inclination:78deg
• Erroratlauncher’sinjection:1Kmallaxis3‐sigma• Launchvehicle:VEGA
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ELA launch pad
300 x 300
VEGA launch
PicoSAT: 2Kg
Control Division, TEC-ECM
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Deployment
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P80 flight
Z23 flight
Z9 flight
AVUM1st ign.
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VEGA AVUM release strategy
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2nd satellite: 2 Kg
3rd satellite: 2 Kg
4th satellite: 2 Kg
5th satellite: 2 Kg
30 deg RAAN
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Deployment and commissioning
• Deploymentmustbedoneongroundstationcoverageandvisibility– Findoutwhich
groundstationcanhavecontactwithPicoSATafterthelauncher’srelease
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Control Division, TEC-ECM
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Deployment and commissioning
• 10minutestransmissionandantennadeploymentdeadtime
• Switch‐onandantennadeployment.• Initialsatelliteacquisition• Validationofthecorrectoperationenvironmenton‐boardthesatellite
• Validationofthespace‐grounddatalink(RFTransceiver)
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Deployment and commissioning
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Cebreros Kiruna
Trad
e-off
be
twee
n Kiru
na an
d
Cebre
ros
Control Division, TEC-ECM
TallerdeDiseñodePicosatélites(CUBESATS)yEstacionesdeTierra.©GuillermoOrtega
Station keeping and orbit maintenance
• Analysisofbudgets:– Massbudget
• PicoSATwillhavenopropulsion.Hence,themassbudgetwillbeconstant
– Linkbudget• EstablishlinktocommandPicoSATanddownloaditsdata
– Powerbudget• HowPicoSATwillhaveitspower
– Thermalbudget• Howitwarmandcooldown
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Control Division, TEC-ECM
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Link budget
• Frequency:2.2GHz• PicoSAT
– Power:0.15W– Downlink:1.2Kbps– Pointingerror:25deg
• Groundstation– Power:0.70W– Uplink:0.3Kbps– Pointingerror:0.1deg
• Contactsperday:1
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Coverage
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Coverage: GENSO
• Aworldwidenetworkofgroundstationsandspacecraftwhichcaninteractviaasoftwarestandard
• http://www.genso.org
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Coverage: ESAC ground station
• EducationalgroundstationsatESAC• http://www.esa.int/esaMI/ESAC/index.html
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Power and thermal analysis
• Thermal:passivethermalstabilization
• Power:solararraysmountedinallpossiblecubefaces
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Solar array
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De-commissioning and graveyarding
• ESAcodeofconduct:ESA/ADMIN/IPOL(2008)2Annex1
• http://www.esa.int/esaMI/Space_Debris/SEMQHL05VQF_0.html
• Endoflifeoptions:
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De-commissioning and graveyarding
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• PicoSATdragsintotheEarththermosphere• In84daysitwillre‐enterandburn
Control Division, TEC-ECM
TallerdeDiseñodePicosatélites(CUBESATS)yEstacionesdeTierra.©GuillermoOrtega
Analysis steps of phase 0
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Studying the requirements
Performing the analysis
Reporting and sharing
KoM
MDR
Write a document for the MDR Review
Time-Line
Control Division, TEC-ECM
TallerdeDiseñodePicosatélites(CUBESATS)yEstacionesdeTierra.©GuillermoOrtega
Reporting and sharing
• TableofcontentsforMDRreview:–Problemphasing– Launchandorbitinjection–Deploymentandcommissioning– Stationkeepingandorbitmaintenance–De‐commissioningandgraveyarding
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Backup material
• QB50project:http://www.vki.ac.be/QB50/index.php
• QB50,ANINTERNATIONALNETWORKOF50CUBESATSFORMULTI‐POINT,IN‐SITUMEASUREMENTSINTHELOWERTHERMOSPHEREANDRE‐ENTRYRESEARCH
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