Spaceflight,Inc.PayloadUsersGuide
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Spaceflight, Inc. General Payload Users Guide
1505WestlakeAveN.,#600Seattle,WAUSA98109
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DocumentRevisionHistory
Rev Approval
Date
Changes ECNNo. Sections/Pages
ApprovedCM
A 2011-09-16 InitialRelease
B 2012-03-30Updatedelectricalinterfacesandlaunchenvironments
C 2012-07-18 Officialrelease
D 2013-03-05Updatedelectricalinterfacesandlaunchenvironments,reformatted,andaddedtosections
E 2014-04-15Updatedorganizationandformatting,addedcontentonSHERPA,Mini-SHERPAandISSlaunches,updatedRPACG
F* 2015-05-22 Overallupdate
*TheSpaceflightPayloadUser’sGuideiscurrentlyunderrevisionwithanupdateplannedforreleasebyendof2017.Spacecraftaccommodationdetailsincludedhereinshouldnotbeusedtodeterminetheabsolutecompatibilitywithlaunchopportunities.SignupforSpaceflight’smailinglisttobenotifiedwhenthenextrevisionisreleased.
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TableofContents1 Introduction...........................................................................................................................8
1.1 DocumentOverview........................................................................................................................8
1.2 SpaceflightOverview.......................................................................................................................8
1.3 HardwareOverview......................................................................................................................10
1.4 MissionManagementOverview...................................................................................................11
2 SecondaryPayloadIntegrationandHostingProducts........................................................13
2.1 SHERPA..........................................................................................................................................14
2.2 SHERPA400/1000/2200................................................................................................................14
2.3 MiniSHERPA...................................................................................................................................16
3 SecondaryPayloadInterfaceAdapters................................................................................17
3.1 Directly-MountedPayloadtoESPARingPortInterfaceAdapter..................................................18
3.2 RPAMountingInterfaceDefinition...............................................................................................21
3.3 VPAMountingInterfaceDefinition..................................................Error!Bookmarknotdefined.
3.4 DPAMountingInterface................................................................................................................26
4 CubeSatRequirementsandDispensers...............................................................................28
4.1 GeneralCubeSatRequirements....................................................................................................28
4.2 ISISISIPODDispensers...................................................................................................................29
4.3 PlanetarySystemsCorp.CanisterizedSatelliteDispenser............................................................30
4.4 CubeSatdeploymentfromtheInternationalSpaceStation.........................................................31
5 SecondaryPayloadSeparationDevices...............................................................................33
5.1 MarkIIMotorizedLightband.........................................................................................................33
6 AnalysesCoordinatedwithLSP...........................................................................................35
6.1 TrajectoryAnalysis........................................................................................................................35
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6.2 CoupledLoadsAnalysis.................................................................................................................35
6.3 RFCompatibilityAnalysis..............................................................................................................35
6.4 ThermalAnalysis...........................................................................................................................36
6.5 SeparationTimingandRe-contactAnalysis..................................................................................36
6.6 RangeSafetyAnalysis....................................................................................................................36
6.7 Post-flightDataAnalysis................................................................................................................36
6.8 Documentation.............................................................................................................................36
7 AnalysisofAdherencetoOtherRequirements...................................................................39
7.1 CommonEnvironments.................................................................................................................39
7.2 PayloadDesignandConstructionConstraints..............................................................................44
7.3 PayloadSafetyandHazards..........................................................................................................45
7.4 ElectricalandDataInterfaces........................................................................................................46
8 FinalIntegrationandLaunchOperations............................................................................47
8.1 PayloadTransportation.................................................................................................................47
8.2 SecondarypayloadproviderInvolvementduringIntegration......................................................47
8.3 IntegrationandHandoff................................................................................................................47
AppendixA:AcronymsandAbbreviations.................................................................................................49
AppendixB SecondaryPayloadQuestionnaireTemplate......................................................................50
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ListofFigures
Figure1-1Spaceflightisresponsiblefortheinterfacebetweenallsecondarypayloads............................9
Figure2-1SHERPAwithAdapters..............................................................................................................13
Figure2-2Delta-VCapabilities...................................................................................................................15
Figure2-3PropulsiveSHERPACapabilities.................................................................................................16
Figure2-4MiniSHERPADelta-VCapabilities..............................................................................................17
Figure3-1SHERPAwithInterfaceAdapters...............................................................................................18
Figure3-2Directly-MountedPayload-ExplodedView.............................................................................19
Figure3-3BoltHolePatternforDirectlyMountedPayload......................................................................20
Figure3-4VolumeConstraints(5.2mfairingbaselined)............................................................................21
Figure3-5RadialPayloadAdapterSecondaryPayloadCoordinateSystem..............................................22
Figure3-6Boltholepatternforradialportadapter..................................................................................23
Figure3-7VolumeConstraints(5.2mfairingbaselined)............................................................................24
Figure3-8PrimaryCoordinateSystemontheVPABack-plateandSecondaryCoordinateSystem(right).......................................................................................................................Error!Bookmarknotdefined.
Figure3-9VPAmechanicalinterfacewithdimensionsininches[mm].....................................................25
Figure3-10AllowableStaticPayloadEnvelopewithintheDeployableShroudwithdimensionsininches[mm]...........................................................................................................................................................26
Figure3-11DPASystem.............................................................................................................................26
Figure0-1ISIPOD3UCubeSatDispenser...................................................................................................30
Figure0-2NanoRacksCubeSatDeployer...................................................................................................31
Figure0-3NanoRacksElectricalInhibitDiagram........................................................................................32
Figure5-1MarkIIMotorizedLightbandManufacturedbyPlanetarySystemsCorporation(8-inch)........33
Figure7-1MaximumPredictedAcousticEnvironment..............................................................................40
Figure7-2SecondaryPayloadGeneralizedRandomVibrationEnvironment............................................41
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Figure7-3MaximumPredictedElectromagneticEnvironmentduringPadOperationsandLaunch.........42
Figure7-4MaximumPayloadFairing(PLF)TemperatureSeenbythePayload........................................43
Figure7-5NarrowbandRadiatedE-fieldLimits.........................................................................................45
Figure7-6BroadbandRadiationLimits......................................................................................................45
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ListofTables
Table1-1StandardMissionIntegrationProcess.......................................................................................11
Table2-1PropulsiveSHERPATechnicalDetails.........................................................................................14
Table2-2MiniSHERPACapabilities............................................................................................................16
Table3-1AllowableSpacecraftWetMassperInterfaceAdapter.............................................................18
Table3-2DirectlyMountedPayloadMassProperties...............................................................................19
Table3-3RadiallyMountedPayloadMassProperties...............................................................................22
Table3-4VerticallyMountedPayloadMassProperties............................................................................25
Table3-5VerticallyMountedPayloadMassProperties............................................................................27
Table5-1MarkIILightbandOptions..........................................................................................................33
Table6-1RequiredMission-SpecificDeliverables.....................................................................................38
Table7-1MaximumPredictedAcousticEnvironment...............................................................................40
Table7-2SecondaryPayloadGeneralizedRandomVibrationEnvironment.............................................41
Table7-3MaximumPredictedElectromagneticEnvironmentduringPadOperationsandLaunch..........42
Table7-4Payloadenvironmentsduringgroundprocessing......................................................................43
Table7-5MaximumPLFTemperatureseenbythePayload......................................................................43
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1 Introduction
1.1 DocumentOverview
ThisSpaceflightPayloadUsersGuide(SPUG)ispublishedbySpaceflight,Inc.toprovidegeneralinformationtopayloaddeveloperswhomwilllaunchtheirpayloadorspacecraftusingSpaceflight’sintegrationservices.Itincludesdescriptionsonthevariousflightsupporthardware,interfaces,capabilities,launchenvironments,policiesandtoplevelprocessesSpaceflightusestomanifestyourpayloadanddeliveryoutoyourmissionorbit.FurtherinformationmaybeobtainedbycontactingSpaceflightdirectlythroughwww.spaceflightservices.com.
1.2 SpaceflightOverview
Spaceflight,Inc.(Spaceflight)provideslaunchservicesthroughvariousmissionconceptsthatprovidesharedlaunchcapabilitytomultiplespacecraft.Spaceflightaccomplishesthisthroughseveralmethodsandprovidesvaryinglevelsofmissionintegrationsupporttoourcustomers.SpaceflightservesastheintegratingentityacrossourplatformofmissionconceptswhereSpaceflightcontractsdirectlywithmultiplepayloadsandtheLaunchServiceProviders(LSP).Spaceflighthassuccessfullyopenedanentirelynewmarkettothosepayloadsthatcannotaffordthecostofadedicatedlaunch.OneofthebiggestchallengesofthepasthasbeengettingtheLSPstosupportthemanagementofmanydisparateprogramsintegratingonasinglelaunch.SpaceflighthasbrokendownthisbarrierbypresentingasinglepointofcontacttotheLSPsrepresentinganintegratedpayloadstackthatconsistsof1ormore(atthedateofthisSPUGrevisionSpaceflighthasdevelopedanintegratedpayloadstackthathasfreeflyingpayloads)payload.ThisconcepthasprovensosuccessfulthatSpaceflightnowhasagreementsinplaceand/orweeklydiscussionswithallthemajorlaunchproviders,ensuringthatthereisalaunchtomatchyourmissionrequirements.
Spaceflighttakesonthefinancialriskofthelaunchopportunitiesbyprocuringtheexcesscapacityondedicatedlaunchesofaprimarypayloadorthroughprocuringtheentirelaunchcapabilityourselvesandsellingthelaunchopportunitiestomultiplecustomers.Ineitherofthesetwoscenariosweareabletoprovideaccesstospacethatisatrueenablerfortheemergingsmallsatelliteconstellations,one-offdemonstrations,GovernmentscienceandoperationalobjectivesandtheboomingbusinesssparkedbytheCubeSatcommunity.Toofferthebestcoststoourcustomerswehavedesignedoursupporthardwaretothecommonstandards,yetourinnovativestaffofengineersandqualifiedvendorsallowSpaceflighttoaccommodatetheone-offdesignsaswellaskeeppacewiththechangingtechnologies.
Spaceflightisalsouniqueinthatourservicecostsarepostedonlineatwww.spaceflightservices.com.Whilecommittingtoadvertisedfirmfixedpricesintheaerospaceworldhasalwaysbeenachallenge,Spaceflight’sapproach,laidoutinthisdocument,allowsustoconfidentlyandroutinelyprovideourlaunchservicestothewhatmaybetermedasthedisadvantagedsatellitecommunity.Whenthebusinessstartedwefrequentlylabeledourcustomerbaseassecondaryandsmallsatellites.Thathaschangedandwearenowsupportingpayloadsthatrangefrom1UCubeSatstoGeostationarysatellites
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thatmassupwardsof2,000kgs.ThishasallowedustoalsoexpandourservicesfromprovidingsecondaryservicesonanLSP’sprimarymissiontoSpaceflightprocuringtheentirelaunchcapability.Infact,startingin2017andeveryyearthereafter,SpaceflightwillbeprocuringaSunSynchronouslaunchdedicatedtoprovidingourcustomersconsistentandreliableaccesstospace.
AsecondarypayloadprovidercanpurchasepayloadlaunchservicesfromSpaceflight,whothencoordinatesandarrangesforintegrationandlaunch.Spaceflight,supportedbythesecondarypayloadproviders,isresponsibleforanalysesandphysicalintegrationofmultiplepayloadsintoapackagethatistreatedasadiscretepayload.ThisorganizationalstructureisshowninFigure1-1.
Figure1-1Spaceflightisresponsiblefortheinterfacebetweenallsecondarypayloads
BenefitsforSatelliteDevelopers• Fullyarrangedlaunch,fromcontracttoorbitalinsertion• Experiencedpayloadintegratorswithexistingdispensersandinterfaces• Experiencedlicensingandexportcontrolassistance
BenefitsforLSP• Broadaccesstothesmallsatellitemarket• ExperiencedpartyasrepresentativeofALLsecondarypayloads• Standardizedinterfacecontrol,documentationandtestreports
Spaceflightprovidesasingle“one-stopshop”forintegratingawiderangeofsuborbitalandorbitalpayloadsandprovidingthemwithresponsivespaceaccess.
1.2.1 ProcuringSpaceflightServices
Payloadprovidersbeginthemissionintegrationprocessbycompletingapayloadquestionnaire(seeAppendixB).Thequestionnaireincludespayloadinformation,requirements,andinterfacedetailsallowingSpaceflighttomatchthepayloadwithoneormoreofourlaunchopportunities.Adherencetothisuser’sguideandthereferenceddocumentsincreasesthepayload’sopportunitytobequicklymanifested.Forthosepayloadsthathaveuniquerequirementssuchas;volumeexceedance,propulsionornon-standardorbitswillbeaccommodated,howeverthelaunchopportunitiesmaybemorelimitedandultimatelytheacceptanceofthepayloadissubjecttoapprovalbytheLaunchServicesProviderand
Multiple Secondary Payload OperatorsMultiple Secondary
Payload OperatorsMultiple Secondary Payload Operators
Launch Service Providers
Primary Payload Operator
Multiple Secondary Payload Operators
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Spaceflight.
BasedonthepayloadinformationandtheidentifiedlaunchopportunitySpaceflightprovidespreliminarypricingandmissioninformationandbeginsthecontractprocess.ThisbeginswithaLetterofAgreement(LOA)whichisfollowedbyaLaunchServicesAgreement(LSA)committingthepayloadtoalaunchopportunity.Ifthepayloadisanon-U.S.companyororganizationaTechnicalAssistanceAgreement(TAA)isinitiatedthatoncesignedbytheU.S.StateDepartmentallowsSpaceflighttoexchangethetechnicaldataneededtosuccessfullyintegratethepayload.ThisprocessislengthyandSpaceflightstartsdraftingthedocumentsassoonasthenon-U.S.payloaddemonstratescommitmenteitherthroughsigningtheLOAorthroughtheirinteractions.
OncetheLSAissigned,Spaceflightentersintotheprocessesandtimelinesdefinedwithinthisdocument.
1.3 HardwareOverview
Spaceflightoffersallthehardwarerequiredtosuccessfullyintegrateapayloadintothespecificintegratedpayloadstackforaspecificlaunchvehicleand/ormission.AtaminimumSpaceflightprovidesthephysicalintegrationstructure,adispenser(forCubeSats)andaseparationsystemasourstandardservice.Inanefforttosupportthewidestrangeofcustomerrequirements,Spaceflighthasdevelopedarangeofhardwarethatcomestogetherinamodularmanner.Spaceflight’shardwareiscurrentlyqualifiedwithflightheritageandintheeventthatnewhardwareisrequired,Spaceflightensuresthateachitemisfullyqualifiedthroughindustryrecognizedstandards.Spaceflight’sintegrationproductsarebrokendownintovariouscategoriesandareexplainedindetailinthefollowingsections:
SecondaryPayloadIntegrationorHostingProducts(Section2)
TheseareSpaceflight’sproductsthatintegratedirectlywiththelaunchvehicletoincludenon-propulsiveandhostedoptionsinavarietyofsizes.
SecondaryPayloadInterfaceAdapters(Section3)
Theseproductsconnectthepayloadtotheintegrationproductsexplainedabove.Therearefouroptionsavailable,dependingonthemassandsizeofthepayload.
SecondaryPayloadDispensers(Section4)
SpaceflightoffersavarietyofCubeSatdispensersthatarecompatiblewiththeintegrationproductsdescribedinSection2.
SecondaryPayloadSeparationDevices(Section5)
ForsatelliteslargerthanaCubeSat,Spaceflightprovidesseparationsystemsofvarioussizes.
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Spaceflightphysicallyintegratestheselectedhardwareintoonediscretepayload,theintegratedpayloadstack,forlaunch.Formoredetailsonhowthefinalintegrationandlaunchoperationswork,pleaseseeSection8.
1.4 MissionManagementOverview
Spaceflightprovidesfullintegrationservicesforeachpayload.Theseservicesincludeengineeringanalysis,documentationsupportforthelaunchvehicleenvironments,interfacecontroldocumentation,rangesafety,ITARandExportControlsupport.Thegeneralmissionmanagementprocessfora24monthtimelineissummarizedinTable1-1.
Table1-1StandardMissionIntegrationProcess
MilestoneDate Purpose SpaceflightDeliverables SecondarypayloadproviderDeliverables
ContractSigningTypicallyL-24Months
ProvidesAuthoritytoProceedwithwork
• SecondaryPayloadUser’sGuide• Procuredeploymentsystem• PointofContact• RequirementsforPayloadCAD
model,FEM• ICDTemplate
• SignedLSA• PointofContact• CompletedPayload
Questionnaire
KickoffLSAsignature+2months
Initiatestechnicalmissiondevelopment
• MissionScheduletoaLevel2Detail• Summaryofmission-unique
requirementsandimplementation• MSPSPTemplateDelivery• FileforTechnicalAssistance
Agreement(ForeignPayloadProvidersOnly)
• RequirementsforPayloadThermalModel
• PayloadCADmodel• PayloadFEM• SpacecraftTestPlan
MCDRLaunch-9months
Servesasthegateforfabricationandtestofflightsystems
• UpdatedMissionScheduletoaLevel2Detail
• MissionspecificICD• Best-estimatelaunchcampaign
datesandlaunchdate• PreliminaryIntegrationSchedule• PreliminaryLaunchOperationsPlan
• UpdatedPayloadCADmodel(ifapplicable)
• UpdatedPayloadFEM(ifapplicable)
• PayloadThermalModel• UpdatedPayloadMass• CompletedMSPSP• Spacecraftlaunchsite
operationsplan
SystemReadinessReviewLaunch-3months
Verifiesthatallpeople,parts,andpaperarereadyfortheshipmentofthePayloadtotheLaunchSiteandreadytobeginLaunchSiteactivities
• Updatedmissionanalysesresults(ifapplicable)
• Finalintegrationschedule• Finallaunchoperationsplan• Alistoffacilitiesandservices
availableforPayloadcheckout
• VerificationofPayloadcompliancetoICDrequirements(i.e.qualificationreport)
• UpdatestoCADmodel,FEM,thermalmodel,andMSPSP(ifapplicable)
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MilestoneDate Purpose SpaceflightDeliverables SecondarypayloadproviderDeliverables
IntegrationProcessStartLaunch-8weeks
SHERPAintegrationactivity
• IdentifylastaccesstothePayload• Spaceflightwillprovideand
operateafacilityfortheintegrationactivity
• Finalas-measuredPayloadmassandbestestimatedwet-mass
• DeliveryofPayloadandassociatedelectricalandmechanicalGSEtointegrationfacilityforsystemlevelintegration
• DeliveryofPayloadmassmodeltointegrationfacilityforsystemlevelintegration
LaunchReadinessReviewLaunch-1day
Finalactivitiesbeforelaunch
• Approximateseparationtime
• LaunchReadinessReview(LRR)
LaunchLaunch+0hours
IgnitionofLaunchVehicle
• None
• None
PayloadSeparationLaunch+4hours
SupportSecondarypayloadproviderAcquisitionofPayloadon-orbit
• Separationconfirmationandstatevector
• None
AcquisitionNotificationPayloadAcquisition+12hours
SupportSpaceflightmissiongoalverification
• None
• IndicationofPayloadAcquisition,command/telemetrystatus,andinitialvehiclestate-of-healthassessment
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2 SecondaryPayloadIntegrationandHostingProductsSpaceflightusesastandardauxiliarypayloadaccommodationsystemformediumandintermediateclasslaunchvehicles(e.g.Falcon9,Antares™,EELV),knownasSHERPA.IthasaMoogCSAEngineeringadapterringatitscore,derivedfromanESPAGrandering,andfeaturesfive61cm(24inch)diameterports,eachcapableofcarryingpayloadsweighingupto300kg(660lb).TheSHERPAprovidestwocommonmechanicalinterfaces(topandbottom)andsupportsmultipleintegratedpayloadstackdesignconcepts.TheSHERPAsystemisqualifiedandthefirstflightinaconfigurationsimilartoFigure2-1isscheduledforDecember2015onaFalcon9launchvehicle.
Figure2-1SHERPAwithAdapters
Largeminisatellites,withwetmassgreaterthan190kg(419lb),arecantilevereddirectlyfromtheSHERPA61cm(24in)RadialPortInterface(RPI)usinga24-inch-classseparationsystem.Microsatellites,withwetmasslessthan190kg(419lb),arecantileveredfromaportbymeansofaRadialPortAdapter(RPA)anda20.32cm(8in)or38.10cm(15in)separationsystem.Ifrequired,secondarypayloadscanbemountedinaverticalorientationusingaVerticalPayloadAdapter(VPA),ashelf-likestructureshowninError!Referencesourcenotfound..TheVPAaccommodatesboth20.32cm(8in)and38.10cm(15in)payloadseparationsystems.MoredetailsaboutthesesystemsisavailableinSection3.
Thesimplestversion,theSHERPA,hasonlyanavionicssuite,whileaproposedSHERPA2200designis
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Thesimplestversion,theSHERPA,hasonlyanavionicssuite,whileaproposedSHERPA2200designispropulsiveandcanprovidepayloadpowertoeachESPAport.ForCubeSatsandnanosatellites,aMiniSHERPAcanprovidepropulsion.DetailsaboutthecapabilitiesofeachSHERPAareoutlinedbelow.
2.1 SHERPA
TheSHERPAisafree-flierauxiliarypayloaddeploymentsystemcapableofdeployingupto1500kg.UnliketheSHERPA400/1000/2200,itisnotpropulsive.SpaceflightusesthecapabilitiesoftheSHERPAtoprovidethefollowing:
• Physicalintegrationofthepayloads• Sequencepayloaddeployments• Transmitseparationdata• Interfacetothelaunchvehicle• Electricalgroundsupport(pre-launchchargingandpayloadcheckout)• Recordselecteddeploymentsviavideocamera(non-standardservice)
Not every function is available for each launch. The capability of the SHERPA is dependent on theSpaceflightcustomerrequirementsandrestrictionsleviedonSpaceflightbyLaunchServiceProvidersandtheirprimarypayloadproviders.IfaspecificfunctionisrequireditshouldbecoordinatedwithSpaceflight.
2.2 SHERPA400/1000/2200
Toprovideunprecedentedflexibilitytotheauxiliarypayloadprovider,SHERPA400/1000/2200incorporateapropulsionsystem,solararrays,andanAttitudeDeterminationandControlSystem(ADCS).TheADCSusesacombinationofstartrackers,GPS,andInertialMeasurementUnits(IMUs)toupdatetheflightcomputeronattitudeandorbitalvelocityandposition.
InadditiontothecapabilitiesoftheSHERPA,SHERPA400,1000and2200offer:
• Auxiliarypayloadpointing• Auxiliarypayloadpower• Collisionavoidancemaneuvers• Orbitchanges(inclinationandaltitude)• DeepspaceaccessfromGTO• Payloadhosting
FeaturesforhostedpayloadsaredetailedinTable2-1
Table2-1PropulsiveSHERPATechnicalDetails
FeatureSpecification
MissionDuration1year
PayloadPower50W(average)toeachport
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AttitudeAccuracy<50arc-sec
PayloadDataRAMCapacity4GB
PayloadDownlinkUpto100Mbps
Delta-VCapabilitiesofeachSHERPAlevelareshowninFigure2-2
Figure2-2Delta-VCapabilities
ThedeepspacecapabilitiesofSHERPAfromGTOareoutlinedinFigure2-3
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Figure2-3PropulsiveSHERPACapabilities
NoteveryfunctionisavailableduetorestrictionsleviedonSpaceflightbyLaunchServiceProvidersandprimarypayloadproviders.IfaspecificfunctionisrequireditshouldbecoordinatedwithSpaceflight.
2.3 MiniSHERPA
Spaceflight’sMiniSHERPAenablesorbitalchangesandhostedpayloadchargingfornanosatellites.ItisanexcellentoptionfordeployingCubeSatconstellationsbecauseitcanhostnine3UCubeSats,whichcanbedeployedinapredeterminedorbitusingMiniSHERPA’spropulsiveandpointingcapabilities.TechnicaldetailsregardingMiniSHERPA’scapabilitiesareoutlinedinTable2-2andFigure2-4.
Table2-2MiniSHERPACapabilities
FeatureSpecification
AvailablePayloadVolume40x40x60cm
PayloadPeakPower40W
PointingKnowledge<15arc-sec
PointingAccuracy<50arc-sec
PositionKnowledge10m
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Figure2-4MiniSHERPADelta-VCapabilities
MiniSHERPAoffersflexibilitytonon-propulsivenanosatellitesthatwantaccesstoorbitsotherthanthatoftheprimarypayloadsandprovidescoordinateddeploymentforCubeSatconstellations.
3 SecondaryPayloadInterfaceAdaptersSpaceflighthasfourinterfaceoptionsavailableatthistimetomaximizeavailabilityforindividualmissions.ThesevariousoptionscanaccommodateCubesatsandpicosatellites,aswellasmicrosatellitesweighingupto300kilograms.Figure3-1displaysdifferentadapterswithpayloadaccommodationsattached.
25 30 35 40 45 500
5
10
15
20
25
30
35
40
45
50
Total Delta V (m/s)
Payl
oad
(kg)
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Figure3-1SHERPAwithInterfaceAdapters
Adapterselectionislimitedbywetmassofthepayload.Secondarypayloadswithawetmassgreaterthan190kgcanonlybeintegratedviathedirectlymountedinterfaceoption.Table3-1showsthewetmasslimitsforeachinterfaceoption.
Table3-1AllowableSpacecraftWetMassperInterfaceAdapter
WetMass
InterfaceOption
Lessthan300kgDirectlyMountedtoESPA
Lessthan190kgRadialPortAdapter
Lessthan120kgVerticalPortAdapter
Lessthan100kgDualPortAdapter
3.1 Directly-MountedPayloadtoESPARingPortInterfaceAdapter
Forlargerpayloads,Spaceflightoffersdirect-mountingtotheESPAport.Thisconfigurationconsistsofa24”(61cm)diametercircularseparationsystem,suchasthePlanetarySciencesCorporationMotorizedLightBand(5.1)ortheRUAGclampband,whichconnectsthespacecrafttotheESPAring.Figure3-2showsanexplodedviewofapayloaddirectlymountedtotheSHERPApayloadinterface.
(2)
(3) (4)
DirectlyMountedOption(1)
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Figure3-2Directly-MountedPayload-ExplodedView
Thepayloadportcoordinatesystemisright-handed;theoriginiscenteredontheboltpatternattheradialportinterface(RPI)ontheSHERPAcoreasshowninError!Referencesourcenotfound..The+X-axisdirectionispointingoutwardfromtheexternalsideoftheRPItowardtheLVpayloadfairing.The+Y-axisdirectionispointingtowardtheforwardendofthelaunchvehicle.The+Z-axiscompletestheright-handedcoordinatesystem,andisperpendiculartotheplaneformedbytheX-andY-axes.
3.1.1 PayloadRequirements3.1.1 PayloadRequirements
AuxiliarypayloadsutilizingdirectmountingtotheESPAringmustcomplywiththefollowinginterfacesaswellastheenvironmentsdetailedinSection7.AfurtherrefinedinterfacecontroldocumentwillbeprovidedbySpaceflightaftercontractingforserviceswithSpaceflightInc.
Table3-2DirectlyMountedPayloadMassProperties
Feature Requirement
CenterofMass Lessthan50.8cmfromESPA/PayloadInterface
Mass Lessthan300kg
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Figure3-3BoltHolePatternforDirectlyMountedPayload
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Figure3-4VolumeConstraints(5.2mfairingbaselined)
AvailablevolumeisdefinedfromtheESPAGrandering interface,thereforeadditionalsystemssuchasadapterplatesandseparationsystemsmustbeaccountedforinthetotalvolumeofthepayload.
3.2 RPAMountingInterfaceDefinition
Spaceflightalsooffersmountingtoaradialportadapterplate.Thisconfigurationconsistsofa15”(38.1cm)diametercircularseparationsystem,suchasthePlanetarySciencesCorporationMotorizedLightBand(5.1),whichconnectsthespacecrafttotheESPAring.
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Figure3-5RadialPayloadAdapterSecondaryPayloadCoordinateSystem
TheRPAcoordinatesystemisright-handed;theoriginiscenteredontheboltpatternattheradialportadapterasshowninFigure3-5.Thesecondarypayloadaxial+X-axisbeginsattheexternalsideoftheRPAplateandpointsoutwardtotheLVfairingasshown.TheY-axisisparalleltothelaunchvehiclelongitudinalaxis,andpointstowardtheforwardendofthelaunchvehicle.TheZ-axiscompletestheright-handedcoordinatesystem,andisperpendiculartoXandYplane.
3.2.1 PayloadRequirements
AuxiliarypayloadsutilizingmountingtotheESPAradialportadapterplatemustcomplywiththefollowinginterfacesaswellastheenvironmentsdetailedinSection7.AfurtherrefinedinterfacecontroldocumentwillbeprovidedbySpaceflightaftercontractingforserviceswithSpaceflightInc.
Table3-3RadiallyMountedPayloadMassProperties
Feature Requirement
CenterofMass Lessthan40cmfromESPA/PayloadInterface
Mass Lessthan190kg
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Figure3-6Boltholepatternforradialportadapter
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Figure3-7VolumeConstraints(5.2mfairingbaselined)
PleasecontactSpaceflightfordetailsregardingtheuseofthissystem.
3.2.2 PayloadRequirements
AuxiliarypayloadsutilizingtheverticalportadaptermustcomplywiththefollowinginterfacesaswellastheenvironmentsdetailedinSection7.AfurtherrefinedinterfacecontroldocumentwillbeprovidedbySpaceflightaftercontractingforserviceswithSpaceflightInc.
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Table3-4VerticallyMountedPayloadMassProperties
Feature Requirement
CenterofMass Lessthan48cmfromVPA/PayloadInterface
Mass Lessthan120kg
Theboltholepatternandvolumetricconstraintsareshownonthefollowingpage.
.
Figure3-8VPAmechanicalinterfacewithdimensionsininches[mm]
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Figure3-9AllowableStaticPayloadEnvelopewithintheDeployableShroudwithdimensionsininches[mm]
3.3 DPAMountingInterface
TheDualPortAdapterhasthecapabilitytomountuptotwosmallmicrosatellites,<100kg(220lbs)toasingleradialportoftheSHERPA.Microsatelliteshavingamasslessthan100kg(220lbs)canalsobemountedtoaDPA.
Figure3-10DPASystem
TheprimarycoordinatesystemusedformicrosatellitesattachedtoaDPAisaright-handedcoordinatesystemasshowninFigure3-10.The+X-axisbeginsattheexternalsideoftheDPAback-plateandpointstowardtheLVfairing.The+Y-axisisparalleltothelaunchvehiclelongitudinalaxis,andpointstowardtheforwardendofthelaunchvehicle.The+Z-axiscompletestheright-handedcoordinatesystem,andisperpendiculartotheplaneformedbytheX-andY-axes.
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3.3.1 PayloadRequirements
AuxiliarypayloadsutilizingthedualportadaptermustcomplywiththefollowinginterfacesaswellastheenvironmentsdetailedinSection7.AfurtherrefinedinterfacecontroldocumentwillbeprovidedbySpaceflightaftercontractingforserviceswithSpaceflightInc.
Table3-5VerticallyMountedPayloadMassProperties
Feature Requirement
CenterofMass20.32cm(8”)interface:<28cm
38.1cm(15”)interface:<50cm
Mass Lessthan100kg
Volumeconstraintsaredefinedonanindividualbasis;volumelimitationsaredependentuponthesizeofthespacecraftsharingtheport.
PleasecontactSpaceflightfordetailsregardingtheuseofthissystem.
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4 CubeSatRequirementsandDispensersSpaceflighthasagreatdealofheritageinprovidinglaunchopportunitiesforCubeSatsonavarietyoflaunchvehiclesanddeploymentsystems.Apayloadproviderlookingforalaunchopportunityisencouragedtofollowthespecificationsandguidelinesinthisdocumenttomaximizetheiroptionsaswellasbeingapproved/acceptedforlaunchasasecondarypayloadbySpaceflight,thelaunchserviceprovidersandmostimportantlytheprimaryspacecraft.Thenumberonethingapayloadprovidercandotooptimizetheiropportunitiesistocomplywiththeindustrystandardsanddevelopasimplesystembothinoperationandgroundhandling.Section4.1ofthisdocumentdefinesthegeneralrequirementsCubeSatdevelopersshouldconsiderwhendesigningtheirspacecraftforSpaceflightlaunchopportunities.Spaceflightrealizesthatnotallmissionrequirementscanbemetwithintherequirementslistedandwillworkwithpayloadproviderstoensurethereisasolutiontomeettheiruniquerequirements.SpecificrequirementsagreedtobetweenSpaceflightandtheircustomersaredocumentedinthemissioninterfacecontroldocument.
4.1 GeneralCubeSatRequirements
• SatelliteshallbeincompliancewithAFSPCMAN91-710o Propulsionsystems,ifaccepted,shallbedesigned,integratedandtestedinaccordance
withVolume3.Additionally,activationofpropulsionshallhave3inhibits.o HazardousmaterialshallbeincompliancewithVolume3
• CubeSatsshallnotcreateanyadditionalspacedebris• CubeSatsshouldconsiderusinganidentificationdeviceforuseingroundtracking• CubeSatsshallusematerialsthathaveaTotalMassLossof≤1.0%andaCollectedVolatile
CondensableMaterialof≤0.1%.o Thesearestandardsgenerallysetbypayloadsthataresensitivetoout-gassingand
SpaceflightwillverifythattheCubeSathasmetthisthroughpayloadprovidertesting.• CubeSatdimensionsanddispenserinterfacesaredependentonthedispenserusedonthe
mission.• Thegeneralrequirementsfortheelectricalsystemarecenteredontheconceptofmakingthe
systemsafe.o CubeSatshallbelaunchedinapoweroffstateo Poweroffstateshallbemaintainedthroughoutanyshorttermstorage,integration
operations(otherthanthoserequiredforsystemcheckoutifrequired),andonceinthedispenser.Thisisgenerallyaccomplishedthroughtheuseofarailmounteddeploymentswitchwhichwhileactivatedallpoweredfunctionsaredisconnectedfromthepowersupplysystem.
o Ifthedeploymentswitchistoggled,itshallresettot=0.• SpaceflightdiscouragesCubeSatpayloadsfromrequiringanycheckouts,batterychargingorRF
testingoncethesatelliteisdeliveredtotheintegrationsite.Shouldtherebearequirementtodoso,Spaceflightwillconsidertherequestonamission-by-missionbasisasanon-standardservice.
• Thesatelliteshallinhibitinadvertentradiofrequency(RF)transmissionthroughtheuseofthreeinhibits.Shouldthepayloadproviderdecidenottousethreeinhibitsotherschemeswillbeconsidered,howevertheuseofatimerisnotconsideredaninhibit.
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• Satellitedeployablesystems(solarpanels,antennasandothernon-separatingitems)shallnotdeployfor15minutesaftertheyhavebeendeployed.
• Satelliteshallnottransmitsignalsanyearlierthan30minutespostseparation.Thiscan,andmostlikely,willbemodifiedonamission-by-missionbasisdependingonthemissionconstraints.Payloadprovidersshouldnotconsidertransmittinganysoonerthanthe30minuteswithoutpriordiscussionswithSpaceflight.
• Spaceflightwillnotlaunchanysatellitethathasnotorcannotprovideevidenceofhavingmettheproperregulatoryrequirements.
o Payloadprovidersshallprovideevidenceofthefollowing:§ Licensinginaccordancewiththeircountry’sauthorityfortheuseofradio
frequency(ies).Amateurfrequencyisacceptable.§ OrbitaldebrisiscompliantwithNPR8715.6§ Approvalsnecessaryforanyearthimagingviaproperauthority.
• ThepayloadproviderisresponsibletocompleteallnecessarytestingandshallprovideatestplantoSpaceflightperdeliveryscheduledocumentedinthisdocumentorpertheSOW/ICD.
o Requiredtesting:§ Randomvibration§ Thermalvacuumbake-out§ Shocktesting
Therearemultipleresourcesavailabletopayloadprovidersinregardstotheregulatoryandtestingthatshouldbereferenced.Belowisalistofwebsites.Spaceflightprovidessupporttopayloadprovidersinallareasasneeded.
• AmateurRadioInformation–www.iaru.org• FCCAmateurRadioInformation–www.arrl.org/part-97-amateur-radio• NASADebrisAnalysisTool–http://orbitaldebris.jsc.nasa.gov.mitigate/das.html• RemoteSensingLicensing–www.nesdis.noaa.gov/CRSRA/licenseHome.html• ForcommonU.S.GovernmentdocumentssuchasAFSPCMAN,MilitaryStandardsandother
suchdocumentsvisit–http://everyspec.com
4.2 ISISISIPODDispensers
ISISLaunchServicesprovidesavarietyofCubeSatdispensersforsmallspacecraft.TheISIPOD(pronounced“easy-pod”)isalaunchadapterforpico-andnanosatellitesthatadherestotheCubeSatinterfacestandarddefinedbytheCubeSatDesignSpecification.Spaceflightutilizesthe3UISIPODtodeploydedicated3UCubeSatsaswellas1Uand2UCubeSatswhichsharetheISIPODvolume.TheISIPOD3UdispenserisshowninFigure0-1.
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Figure0-1ISIPOD3UCubeSatDispenser
TheCubeSatisinsertedintothe3UISIPODalongthePODlongaxis.Itisconstrainedbyfourhardenedanodizedaluminumguiderails,fourpolyoxymethylene(POM)feetonthespring-loadedpusherplate,andtwospring-loadedPOMrailslocatedonthedoor.Withthedoorclosed,thespringsinthePOMrailslocatedonthedoorsuppresschatteringorrattlingoftheCubeSatduringlaunch.TheguiderailsensurethatminimumtipoffratesareimpartedtotheCubeSatpayloadupondeployment.TheCubesat(s)arecompletelyenclosedbytheISIPODtoensurethesafetyofotherpayloads.Withthegroundingbolt,theISIPODisdesignedtobeaFaradaycagetosatisfyEMI/EMCstandards.Uponreceiptofthedeploymentcommand,theISIPODdoorreleasemechanismactivatesreleasingthedoor,andthespring-loadedpusherplatepushestheCubeSat(s)outoftheISIPOD.TheISIPODmainspringimparts1-2m/sseparationvelocityinmostconfigurations.
SpaceflightSystemshassignedanagreementwithInnovativeSolutioninSpace(ISIS)oftheNetherlandstomanufacturetheISIPOD,brandedtheEZPOD,intheUnitedStates.
• ISIPODCubeSatDeployerBrochure(PDF)http://www.isispace.nl/brochures/ISIS_ISIPOD_Brochure_v.7.11.pdf
ToaccommodatelargerCubeSatconfigurations,Spaceflightoffersboth6Uand12Ucontainerizednanosatellitedispensers.ContactSpaceflightformoreinformation.
4.3 PlanetarySystemsCorp.CanisterizedSatelliteDispenser
ThePlanetarySystemsCorporationCanisterizedSatelliteDispenser(CSD)isareliable,testable,andcost-effectivedeploymentmechanismforsmallsecondaryortertiarypayloads.Itfullyencapsulatesthepayloadduringlaunchandthusprovidesmissionassuranceforboththeprimarypayloadandlaunchvehicle.Allexternalsurfacesareelectricallyconductivechem-filmaluminumalloy.
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TheCSDiseasytouseandoperate.TheactofclosingtheCSDdoorautomaticallypreloadsthepayloadtabs,andtherearenopyrotechnics.ThedoorinitiatorisaDCbrushmotorwithsubstantialflightheritage.TheCSDcanbecycledinamatterofsecondswithoutconsumables.
• PlanetarySystemsCorporationPayloadforContainerizedSatelliteDispenser(CSD)SpecificationSheetfor3U,6U,and12U(PDF)http://www.planetarysystemscorp.com/#!__downloads
4.4 CubeSatdeploymentfromtheInternationalSpaceStation
SpaceflightworkswithourmissionpartnerstoprovidedeploymentfromtheInternationalSpaceStation(ISS).TherequirementstodeployfromtheISSincludesection4.1ofthisdocumentaswellassections4.4.1and4.4.2.Thisdeploymentconfigurationhasminimallaunchloads(Figure4-5).Deploymentspeedsrangefrom0.5m/sto1.5m/s.
Figure0-2NanoRacksCubeSatDeployer
CubeSatsdeployedthroughtheNanoRacksCubeSatDeployer(NRCSD)mustmeetcertainrequirements,inordertomeetthesafetystandardsoftheISS.Theserequirementsinclude:
4.4.1 ElectricalInhibits
CubeSatdesignshallincludethree(3)inhibitswitcheswiththree(3)correspondingdeploymentswitches.Groundchargeshallnotenergizethesatellitesystems(load).AnexamplecircuitdiagramisshowninFigure0-3.
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Figure0-3NanoRacksElectricalInhibitDiagram
4.4.2 Batteries
Batteriesmustmaintainchargeforaminimumof6months.BatteriesrequireadditionaltestingforNASAsafetycertification.
TestingproceduresandrequirementsaredetailedinJSC-20793Rev.BCrewedSpaceVehicleBatterySafetyRequirements.
ContactSpaceflightforadditionalinformation.
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5 SecondaryPayloadSeparationDevices
5.1 MarkIIMotorizedLightband
PlanetarySystemsprovidesarangeofcontainerizedandcircularringsatellitedispensers.TheMarkIIMotorizedLightbandisaspace-vehicleseparationsystem,showninFigure5-1.Itgeneratesarelativelylowshockatseparation,anditisnon-pyrotechnicandthereforegeneratesnodebris.Itismotordriven,whicheliminatestheneedforrefurbishmentorconsumableinitiators.Thesystemisdeliveredwithseparationsprings,switches,andconnectorswithintheassemblythatdoesnotrequireadditionalbrackets.Finally,ithasbeenflightprovenover30times.
Figure5-1MarkIIMotorizedLightbandManufacturedbyPlanetarySystemsCorporation(8-inch)
Toaccommodateavarietyofpayloads,theMarkIILightbandisproducedinmultiplediameters,rangingfrom8inchto38inch.Table5-1showstheLightbanddiametricaloptionswithassociatedmass.Themassoftheseparationsystemisnotchargedtocustomer,forexamplea150kgwitha381mmseparationsystemthathasamassof2.63kgischargedatthepriceof150kg.
Table5-1MarkIILightbandOptions
Diameter(in) Diameter(mm) Mass(lb) Mass(kg)8.000 203 3.28 1.4911.732 298 4.62 2.1013.000 330 5.03 2.2815.000 381 5.79 2.6318.250 464 6.88 3.1219.848 504 7.24 3.2823.250 591 8.44 3.8324.000 610 8.95 4.0631.600 803 12.38 5.6238.810 986 15.08 6.84
• PlanetarySystemsCorporationUserManualforMarkIIMotorizedLightband(PDF)
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http://www.planetarysystemscorp.com/#!__downloads
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6 AnalysesCoordinatedwithLSP
6.1 TrajectoryAnalysis
Trajectoryanalysisisperformedearlyinthemissionplanningprocess.EarlyanalysiswillusetherequirementssubmittedwiththePayloadQuestionnaire,andisprimarilyusedtodiscoverpotentialissuesandunderstandsecondarypayloadmanifestingopportunities.Lateranalyseswillprovideinformationonpayloadsequencingandorbitdispersions,aswellasanyrange-imposedrestrictionsforenvironmentalorsafetyconcerns.InthecasewhereSpaceflighthasmanifestedtheintegratedpayloadstackwithaprimarypayload,theprimarypayloadmissionrequirementswillalwaystakeprecedence,andwillnotbeaffectedbysecondarypayloadrequirements.ForthosemissionswhereSpaceflighthasprocuredtheentirelaunchcapacity,thetrajectorywillbeinaccordancewithapre-determinedorbitorwithCo-leadcustomers.
6.2 CoupledLoadsAnalysis
Spaceflightdevelopsafiniteelementmodeloftheintegratedpayloadstacktoprovideinputtothelaunchvehiclecombinedcoupledloadsanalysis(CLA).TwoCLAsareconducted,theinitialanalysisfollowedbyafinalverification.Theseanalysesareusedtodeterminepotentialdynamicenvelopeexceedancesandinformthepayloadprovideraboutdesignconcernsrelatedtothelaunchdynamicenvironment.Tofacilitatetheseanalyses,eachmanifestedsecondarypayload(withtheexceptionofCubeSats)providerisexpectedtoprovideaNASTRANfiniteelementmodel.Thescheduleincludessufficienttimetoupdatemodelsandupdatethecoupledloadsanalysisiftherearesignificantchangesinthemodelsorenvironments.
TypicallaunchvehicleeventssimulatedintheCLAincludeliftoff,air-loads,enginerestarts,andenginecut-off.Notalleventsmaybeanalyzedifflightexperienceorclassanalysesshowthemtobebenignevents.CLAoutputwillincludemaximumaccelerationsandinterfaceloadsatselectednodesofthespacecraft.
6.3 RFCompatibilityAnalysis
ThelaunchvehicleproviderwillperformaRadioFrequency(RF)compatibilityanalysistoverifythatallRFsourcesidentifiedatthelaunchsiteorusedtosupportthemissionarecompatiblewiththelaunchvehicleandgroundtelemetryandtrackingsystems.Systemstobeanalyzedincludeanytelemetry,tracking,andflightterminationsystems.Areportwilldetailallfindings,includingsystemlinkrequirements,andwillincludeanyinterferenceissueswithsecondarypayloadRFsystems.Allsecondarypayloadsaretobeoffpriortodeployment;however,thesecondarypayloadproviderisexpectedtoensurethatRFsensitivecomponentsandmaterialsarenotaffectedbylaunchvehicleRFsources.TheICDcontainsatablewithallknownemittersforthepayloadprovidertoassess.Spaceflightuses
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proceduralconstraints(coordinatedRFtransmittingifrequiredandthefactthatallpayloadsarepoweredoff)aswellasverificationofharnessdesigntoensureEMI/EMCrequirementsaremet.
6.4 ThermalAnalysis
Athermalanalysiswillbeconducted,takingintoaccountenvironmentsimposedontheprimaryandsecondarypayloadsduringgroundoperationsfollowingencapsulationupuntilthesecondarypayloadisseparatedfromthelaunchvehicle.Accordingly,eachsecondarypayloadprovider(withtheexceptionofCubeSats)isexpectedtoprovideathermalmathmodelandgeometricmathmodel.Complexityofthethermalmodelrequiredmayvary,dependingonthesizeofthespacecraftandthefidelityofthethermalinterfacesrequired.
6.5 SeparationTimingandRe-contactAnalysis
Spaceflightdevelopsamissiontimelinebasedonmultiplefactorsandcharacteristicsofeachofthepayloads.Spaceflightusesacombinationofmissionrequirements,separationsystemspecifications,payloadmass,andothervariablesthatcontributetothere-contactpossibility.TheSeparationTimingandRe-contactanalysiswilldetermineminimumrelativevelocitiesrequiredforpayloaddeployment.Itwillalsoensurethatthepayloadsdonotre-contactthelaunchvehicleupperstageoreachotherafterdeployment.
6.6 RangeSafetyAnalysis
EachpayloadisresponsibleforensuringthattheyareincompliancewiththeapplicableAFSPCMAN91-710requirements.Spaceflighthastheultimateresponsibilityfortheintegratedpayloadstackandreliesontheinputsfromeachpayload.Thisisprimarilyaccomplishedthrougheachpayloadprovider’sMissileSystempre-LaunchSafetyPackage(MSPSP)aswellasAFSPCMAN91-710tailoringinputsasapplicable.SpaceflightprovidesanMSPSPtemplateandsupportthroughouttherangesafetyanalysisprocess.
6.7 Post-flightDataAnalysis
Followinglaunchcompletion,thelaunchvehicleproviderwillperformapost-flightanalysistoverifylaunchvehicleperformancefromflightdata.Thepost-flightanalysiswillincludeanassessmentofinjectionaccuracyandspacecraftseparationattitudes.Theanalysismayalsoincludepayloadenvironmentaldata,includingtemperature,pressure,shock,acoustic,orotherdatadependingonsensoruseandextentofinstrumentation.ThisdatawillbeavailabletosecondarypayloadSecondarypayloadprovidersforverificationactivities.
6.8 Documentation
Documentationwillberequiredfromsecondarypayloadprovidersinatimelyfashion,aslistedinTable1-1.Thesedocumentsrepresentthegeneraltypesofnecessarycommunicationbetweenthesecondarypayload,thesecondarypayloadintegrator,theprimarypayloadprovider,thelaunchvehicleprovider,andvarioussupportagenciesassociatedwiththelaunch.Spaceflightwillinterfacewithasinglepoint-of-
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contact(POC)assignedbythesecondarypayload,throughwhomalldatawillberouted.Specificdocumentationneedswillbeprovidedonceasecondarypayloadismanifestedonparticularmission.
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Table6-1RequiredMission-SpecificDeliverablesItem# Description
1
PayloadQuestionnaire(SeeAppendixB)Thespacecraftquestionnaireisthefirststepinthesecondarypayloadmanifestprocess.Itshouldincludetheinitialsecondarypayloadrequirements,orbitrequirements,interfacedetails,massproperties,preliminarydrawings,etc.Anyspecialfairingrequirementsshouldbespecifiedinthequestionnaireandupdatedthroughthemissionintegrationprocess.
2 SpacecraftFiniteElementModelAspacecraftFEMisrequiredforeachsecondarypayloadtobeusedincoupledloadsanalysis.
3SpacecraftThermalModelAspacecraftthermalmodelisrequiredforeachsecondarypayloadtobeusedinanintegratedthermalanalysis
4VerificationofICDComplianceEachsecondarypayloadisrequiredtodocumentthetestplanandprovidetestresults(e.g.,staticloads,vibration,acoustics,shock)forthespacecraft.
5
SpacecraftCADModelAllsecondarypayloadsarerequiredtosubmitdrawingsshowingtheconfiguration,shape,anddimensionsoftheirsatellite.Internaldetailsaregenerallynotrequiredinthedrawings/CADmodels.Eachsecondarypayloadisrequiredtoreporttheirrespectivespacecraftmassproperties.Thevaluesshouldincludethenominalvaluesand3σuncertainties.
6
MissileSystemPre-launchSafetyPackage(MSPSP)TheMSPSPisadatapackagethatprovidesdetailedtechnicaldataonallhazardousitemsincludingdrawings,schematics,RFRadiation,andassemblyandhandlingprocedures.MorespecificsontheMSPSPcanbefoundintheAFSPCMAN91-710.
7SpacecraftLaunchOperationsPlanEachsecondarypayloadmustspecifyanyhandlingconstraints,environmentalconstraints,personnelrequirements,equipmentrequirements,etc.fortheirsatellite.
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7 AnalysisofAdherencetoOtherRequirements
7.1 CommonEnvironments
Thefollowingsectionscontainbaselineenvironmentsbaseduponcommonlaunchvehicles.TheseenvironmentsrepresentaconservativeapproachtothesatellitedesignandshouldnotbeusedtodeterminetheabsolutecompatibilitywithlaunchopportunitiesthatSpaceflighthasavailable.Spaceflightunderstandsthatdesigningtooverlyconservativeenvironmentsimposesthepossibilityofgreatermassandoverallcosttothepayloadprovider,andweencourageearlyengagementwithSpaceflightforanyoftheenvironmentswithinthisdocumentthatposeasignificantissueorconcern.Also,theGeneralEnvironmentalVerificationStandard(GEBS,GSFC-STD-7000)aswellasMIL-STD-1540areagreatresourcefordesigningwhenthespecificlaunchopportunityhasnotyetbeendefined.
Spaceflightusesaphilosophyofgraduallyreducingthemarginappliedtoenvironmentsasthemissionprogresses.Duringtheinitialplanning,Spaceflightrecommendsusingthisdocumentorthetwopreviouslymentioned.Thisrepresentsthehighestamountofmarginoruncertaintyappliedtothevalues.Withthereleaseoftheinitialinterfacecontroldocumentamorerefinedmaximumpredictedenvironmentisprovided,howeverthereisstillalevelofuncertaintyappliedanddependsonthematurityofthelaunchsystemand/ortheintegratedpayloadstack.Thefinalmaximumpredictedenvironmentsareprovidedafterthelaunchvehiclemissioncriticaldesignreview.
7.1.1 Quasi-StaticLoading
Maximumpredictedquasi-staticloadsforminisatellitesareexpectedtobe≤10gappliednon-simultaneouslyineachorthogonalaxis.
Maximumpredictedquasi-staticloadsforCubeSatsareexpectedtobe<20gappliednon-simultaneouslyineachorthogonalaxis.
Actualloads,accelerations,anddeflectionsareafunctionofthelaunchvehicle,primarypayload,andothersecondarypayloaddynamicstructuralproperties.Theseareaccuratelydeterminedviacoupledloadsanalysis(CLA).
7.1.2 SineVibration
ThesinevibrationenvironmentisbasedonaCLAperformedbythelaunchvehicleproviderwhenthefullmanifestislockeddown.TheresultsfromCLAareusedtoderivearesponsespectrumofthevibrationlevelsatthesecondarypayloadinterface.Foragivenmodaldampingvalue,asmoothedenvelopeofpeakresponsesiscreated,whichisthenusedtoproduceasinevibrationinputcurve.
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7.1.3 AcousticEnvironment
ThemaximumpredictedacousticenvironmentisshowninFigure7-1.Spacecraftwithlargeflatsurfacesaresusceptibletoacousticenvironments.Acoustictestingisrecommendedforanyspacecraftwithstructuralcomponentssusceptibletoexcitationbyacousticenvironments.
Figure7-1MaximumPredictedAcousticEnvironment
Table7-1showsthemaximumpredictedacousticenvironmentinsideapayloadfairing.
Table7-1MaximumPredictedAcousticEnvironment
OctaveCenterFrequency(Hz)
MaximumPredictedAcousticEnvironment(OASP=139.6dB)
31.5 128.063 131.0125 135.2250 133.6500 130.31000 126.02000 120.04000 116.0
Thisisthemaximumpredictedenvironmentanddoesnotincludemarginforqualificationoracceptancetesting.Fortestfactorsanddurations,consultGSFC-STD-7000Table2.2-2.
7.1.4 RandomVibration
GeneralizedrandomvibrationqualificationandacceptancelevelenvironmentsareshowninFigure7-2forapayloadhavingamasslessthan22.7kg(50lb).
128131
135.2133.6
130.3
126
120
116115
120
125
130
135
140
10 100 1000 10000
FlightLimitLevels(dB)
Frequency(Hz)
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Figure7-2SecondaryPayloadGeneralizedRandomVibrationEnvironment
Table7-2showsthegeneralizedrandomvibrationenvironmentforapayloadwithmasslessthan22.7kg(50lb).
Table7-2SecondaryPayloadGeneralizedRandomVibrationEnvironment
Frequency(Hz)
GeneralizedRandomVibrationEnvironment
22.7kg(50lb)orless(g2/Hz)Qualification Acceptance
20 0.026 0.01350 0.16 0.08800 0.16 0.082000 0.026 0.013GRMS 14.1 10.0
7.1.5 ElectromagneticInterference/CompatibilityEnvironment
ThemaximumpredictedelectromagneticenvironmentisshowninFigure7-3.ThesecondarypayloadproviderisexpectedtoensurethatspacecraftmaterialsandcomponentsarenotsusceptibletoRFenvironmentgiveninFigure7-3.
0.01
0.1
1
10 100 1000
ASD(g2
/Hz )
Frequency(Hz)
QualificationAcceptance
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Figure7-3MaximumPredictedElectromagneticEnvironmentduringPadOperationsandLaunch
Table7-3showsthemaximumpredictedelectromagneticenvironmentduringpadoperationsandlaunch.
Table7-3MaximumPredictedElectromagneticEnvironmentduringPadOperationsandLaunchFreq(MHz) EFieldLimit(dBμV/m)
30 901609.9 901610 1401626 1401626.1 902199.5 902200 1502300 1502300.5 905754.9 905755 1635775 1635775.1 9010000 9018000 40
7.1.6 PressureandVenting
Thepressuredecayrateinsidethepayloadfairingislessthan6.2kPa/s(0.899psi/sec).
SelectedCubeSatdispensersareexpectedtobedesignedtomaintaininteriorpressurewithin6.9kPa(1psi)oftheinternalpayloadfairingpressure.
30
50
70
90
110
130
150
170
10 100 1000 10000 100000
EFieldLimit(dBμ
V/m)
Frequency(MHz)
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7.1.7 Temperature,Cleanliness,andHandling
Thetemperature,humidity,andaircleanlinessduringgroundoperationsaregiveninTable7-4.
Table7-4Payloadenvironmentsduringgroundprocessing
SHERPAPayloadProcessingFacility(PPF)duringIntegrationProcesses
LSPPPFduringIntegrationProcesses
EncapsulatedinPayloadFairing
DuringtransportfromPPF
On-padEncapsulated
Temperature21°C±5.0°C(70°F±8.8°F)
21°C±2.9°C(70°F±5°F)
21°C±2.9°C(70°F±5°F)
21°C±2.9°C(70°F±5°F)
between10°–29.4°C±2.9°C(50°F–85°F±5°F)
Humidity 50%±15% 50%±5% 50%±5% 50%±5%anysettingbetween20%and50%±5%
Cleanliness Class100,000 Class10,000 Class10,000 Class10,000 Class5,000
Amaximuminnerpayloadfairingwalltemperatureseenbythepayload,withemissivity0.9,isgiveninFigure7-4andTable7-5.
Figure7-4MaximumPayloadFairing(PLF)TemperatureSeenbythePayload
Table7-5MaximumPLFTemperatureseenbythePayload
TimeSinceLaunch(sec) Temperature(°C)0 48.9
100 93.3250 93.3
405060708090
100
0 50 100 150 200 250 300
Tempe
rature(degC)
TimeSinceLiftoff(Seconds)
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7.2 PayloadDesignandConstructionConstraints
7.2.1 PartsSelection
TheSecondaryPayloadisexpectedtousematerialsthatcomplywithNASA-STD-6016,StandardMaterialsandProcessesRequirementsforSpacecraft.
TheSecondaryPayloadisexpectedtousematerialsthatwhenexposedtoavacuumenvironmentwillnotexceedatotalmasslossof1.0%andvolatilecondensablematterof0.1%whentestedperASTME-595oranequivalentmethod.
7.2.2 Processes
TheSecondaryPayloadisexpectedtobemaintainedincleanassemblyareasmeetingaclass100,000cleanlinessspecificationasaminimumduringgroundprocessingandpayloadintegrationIAWUS-FED-STD209E.
TheSecondaryPayloadisexpectedtobehandledonlywithcleanglovesaftertestinginpreparationforandduringgroundprocessingandpayloadintegration.
TheSecondaryPayloadsurfacesareexpectedtobemaintainedvisiblycleanunderblacklightinspection,pertheIEST-STD-CC1246Dlevel300Aasaminimumduringgroundprocessingandpayloadintegration.
7.2.3 Venting
AllenclosedvolumesoftheSecondaryPayloadareexpectedtohavethecapabilitytomaintaininteriorpressurewithin6.9kPa(1psi)oftheexternalpressurewheninanenclosedconfigurationandwhensubjectedtothelaunchventingenvironment.
7.2.4 ElectromagneticInterference/Compatibility
TheSecondaryPayloadisexpectedtoinhibitwirelesstransmissionuntildeployedfromtheSHERPAorlaunchvehicle.
LaunchServiceProvidersexpectthesecondarypayloadtomaintainnarrowbandradiationemissionswithinthelevelsshowninFigure7-5whileinanactivestateincloseproximitytothelaunchvehicleupperstage.
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Figure7-5NarrowbandRadiatedE-fieldLimits
TheSecondaryPayloadisexpectedtomaintainbroadbandradiationemissionswithinthelevelsshowninFigure7-6whileinanactivestatewithincloseproximitytothelaunchvehicleupperstage.
Figure7-6BroadbandRadiationLimits
7.2.5 SpaceDebris
SecondarypayloadareexpectedtocomplywiththeNationalSpacePolicyrequirementforspacedebris,whichstatesthatsmallsatellitesinLEOshouldre-entertheatmospherewithin25yearsfromlaunch.
7.3 PayloadSafetyandHazards
SecondarypayloadprovidersareexpectedtoprovideaPayloadQuestionnaire(PQ)priortocontractsigningthatdescribesanypotentialhazardsassociatedwiththeirspacecraft.APQtemplateisprovidedinAppendixB.
14kHz,114
1GHz,114
1GHz,160 18GHz,160
100
110
120
130
140
150
160
170
1.00E+04 1.00E+05 1.00E+06 1.00E+07 1.00E+08 1.00E+09 1.00E+10 1.00E+11
EFieldLimit(dBμ
V/meter)
Frequency(Hz)
14kHz,134 30MHz,134
30MHz,128
1GHz,128
120
125
130
135
140
1.00E+04 1.00E+05 1.00E+06 1.00E+07 1.00E+08 1.00E+09
dBμV
/meter/M
Hz
Frequency(Hz)
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SecondarypayloadprovidersareexpectedtoprovideaMissileSystemPre-launchSafetyPackage(MSPSP)atL-9monthsthatincludesdetailedtechnicaldataonallhazardousitemsincludingdrawings,schematics,andassemblyandhandlingprocedures.AnMSPSPtemplatewillbeprovidedbySpaceflightaftercontractsigningandidentificationofthelaunchvehicle.
Thisdocumentationisrequiredbythelaunchserviceprovideraspartofobtaininglaunchapprovalsbytherange.HazardsaresubjecttoapprovalbySpaceflight.
7.3.1 HandlingSafety
Secondarypayloaddesignisexpectedtobecompatiblewithoperationsthatplacethepayloadinhorizontalaswellasverticalattitudesduringgroundhandlingandintegration.Accesstothesecondarypayloadmaybelimitedfollowingintegrationintothelaunchvehiclefairing,dependingonthelevelofaccessthathasbeencontracted.
7.3.2 PressurizedSystems
Designandverificationofsecondarypayloadpressurizedsystemsandcomponentsareexpectedtobeinaccordancewithaerospaceindustryguidelinesandmustprecludeinadvertentoperation.Thedesignisexpectedtoprotectpersonnelandhardwarefromdamageduetopressuresystemfailurebeforelaunch,andprotectthelaunchsystemandprimarypayloadfrompressuresystemfailureduringflight.Documentationofanypressurizedsystemsdesignandsafetyverificationwillberequiredofthesecondarypayloadcontractortosupportregulatoryagencyapprovals.
7.3.3 Actuated/EnergeticSystems
Secondarypayloadactuationandotherenergeticsystemsforspacecraftpropulsion,separation,andmechanicalsystemsareexpectedtobedesignedinaccordancewithaerospaceindustryguidelines,andmustprecludeinadvertentoperationwhensubjectedtotheenvironmentsmentionedinthisguideduringpre-launchandlaunchoperations.Documentationofanyactuationandotherenergeticsystemsdesignandsafetyverificationwillberequiredofthesecondarypayloadcontractortosupportregulatoryagencyapprovals.
7.4 ElectricalandDataInterfacesSecondarypayloadsareexpectedtobepoweredoffduringlaunch.NoelectricalsignalsaresentfromtheSHERPAtothepayloads,exceptthedeploymentcommandtotheseparationdevice.
Forminisatelliteandnanosatellitepayloads,theSHERPAprovidesredundantpayloadseparationsignalspertheseparationdeviceuser’smanual.
Separationstatusisnotsupplieddirectlytothepayload.
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8 FinalIntegrationandLaunchOperationsThissectiondefinesthefourstandardpayloadinterfacesofferedbytheSHERPA:directintegrationtotheSHERPARadialPortInterface(RPI),RadialPortAdapter(RPA)mounting,VerticalPayloadAdapter(VPA)mounting,andDualPortAdapter(DPA)mounting.
8.1 PayloadTransportation
ThesecondarypayloadproviderisexpectedtoarrangefortransportofthespacecraftfromthesecondarypayloadproviderfacilitytotheSpaceflightPayloadProcessingFacility.UponpayloadarrivalatthePayloadProcessingFacility,thesecondarypayloadproviderisexpectedtohavearepresentativeperformaposttransportationinspectionpriortohandofftoSpaceflightforpayloadintegrationactivities.Followingintegrationactivities,SpaceflightwillarrangefortransportofthefullyintegratedSpaceflightpayloadadaptertotheLSPpayloadprocessingfacilityforintegrationtothelaunchvehicle.
8.2 SecondarypayloadproviderInvolvementduringIntegration
Secondarypayloadproviderinvolvementintheintegrationactivityisgenerallyafunctionofthesecondarypayloadcomplexity.Levelsofaccessduringpayloadintegrationcanbenegotiated.Forpicosatellitesandnanosatelliteshavingminimalcomplexity,nosecondarypayloadproviderinvolvementisexpectedafterdelivery.Spaceflightwillconducttheintegrationactivity,andtesttheseparationcircuitcontinuity.
Formicrosatellitesandminisatelliteshavinggreatercomplexity,secondarypayloadpersonnelareexpectedtobepresenttoobserveintegrationtotheSpaceflightpayloadadapter.Generallyforthesetypesofpayloads,Spaceflightperformstheintegrationactivityundersecondarypayloadproviderobservation.UsingsecondarypayloadproviderprovidedGSE,thesecondarypayloadprovidermayrunhealthstatuschecksandconductbatterycharginguntillastaccess.
Forhostedpayloads,thesecondarypayloadproviderisexpectedtobeheavilyinvolvedinpayloadintegrationandSpaceflightpayloadadaptertesting,toincludeend-to-endfunctionaltestingandmissionsimulation.
8.3 IntegrationandHandoff
SpaceflightmustreceivesecondarypayloadsattheSpaceflightpayloadprocessingfacilityapproximately6weekspriortolaunchtoallowenoughtimeforpayloadadapterintegration,test,anddeliverytothelaunchvehicleproviderfacility.
Theintegrationprocesstakesplaceinacontrolledfacilitynearthelaunchsite.Thepayloadintegrationactivityandsystemlevelteststakebetweentwoandfourweekstocomplete.PriortohandofftotheLSP,SpaceflightwillconductaseriesofcontinuitychecksensuringtheproperfunctioningofSpaceflightsystems.AmissionsimulationwillalsobeconductedatthattimetotestSpaceflighthardwareandsecondarypayloadseparationsystems,andtoverifythemissiondeploymenttimeline.
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OncetheSpaceflightsecondarypayloadadapterisfullyintegratedandtested,thesystemishandedofftotheLSPfortheremainderoftheintegrationprocess.Nominally,thisisthelastaccesstosecondarypayloads.However,insomecasesbatterychargingcanbeaccommodateduntilpayloadfairingencapsulation.
Thefully-populatedSpaceflightsecondarypayloadadapteristhenmatedwiththeprimesatellite,andthenthepayloadstackismatedwiththelaunchvehicleupperstage.Finallythepayloadisencapsulatedwithinapayloadfairing.Uponcompletionoftheintegrationprocess,thelaunchvehicleismovedtothepadanderectedforlaunch.LaunchreadinessapprovalisreceivedviaaLaunchReadinessReview(LRR)held24hoursbeforelaunch.FromSpaceflightsecondarypayloadadapterhandofftolaunchtakesapproximatelyten(10)days.
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AppendixA:AcronymsandAbbreviations
ATP AuthoritytoProceedCCAM ContaminationandCollisionAvoidanceManeuverCLA CoupledLoadsAnalysisEELV EvolvedExpendableLaunchVehicleEGSE ElectricalGroundSupportEquipmentEMC ElectromagneticCompatibilityEMI ElectromagneticInterferenceESPA EELVSecondaryPayloadAdapterFRR FlightReadinessReviewGEVS GeneralEnvironmentalVerificationSpecificationICD InterfaceControlDocumentISS InternationalSpaceStationITAR InternationalTrafficinArmsRegulationsLRR LaunchReadinessReviewLSP LaunchServicesProviderMPE MaximumPredictedEnvironmentPLF PayloadFairingPOC PointofContactPPF PayloadProcessingFacilityRF RadioFrequencySIP StandardInterfacePlaneSHERPA SpaceflightSecondaryPayloadSystemSSIP SecondaryPayloadInterfacePlaneSPUG SecondaryPayloadUsersGuideTAA TechnicalAssistanceAgreement
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AppendixB SecondaryPayloadQuestionnaireTemplateThePayloadQuestionnaireistypicallyprovidedtothesecondarypayloadproviderpriortoContractSigning.Inputstothisdocumentflowintothedraftpayload-specificInterfaceControlDocumentasrequirements.Thereforeleavemarginwherenecessary,andclearlymarkfieldswheredatastillneedstobedeterminedorreviewed.ExplanationandrationaleareextremelyhelpfulindraftingtheICD.ThefollowinginformationshouldbecontainedwithinthecompletedPayloadQuestionnaire.Pleaseincludeunitswhereapplicable.
1. PayloadName/Title/Acronym2. Payloadclass(e.g.ESPA,1Ucubesat,etc.)3. Payloadownerandoperator4. Payloadpoints-of-contactandcontactinformation5. Spacecraft(maximum)massandfirstfundamentalfrequency6. Dimensionedthree-viewdrawingofspacecraftshowingtheoutermoldlineofthesatellitein
stowedconfiguration(includecoordinatesystem)7. Centerofgravity(CG)location8. Momentofinertia(MOI)tensorofthespacecraftinitsstowedconfiguration9. Maximumspacecraftvolumeenvelope10. Imageofspacecrafton-orbit(operational)surfaceconfiguration11. Desiredorbitalparametersforparking,transfer,andfinalorbits,includingacceptablebounds12. DesiredseparationL+timeandattitudeandacceptablebounds13. Descriptionofanyplannedorrequiredprocessingatthelaunchsitepriortoencapsulation14. Desiredcleanlinesslevelduringpayloadintegrationoperations15. Descriptionoflevelofspacecraftaccessrequiredduringspacecraftintegration16. Descriptionofintegrationhandlingrequirements(includinggroundhandlingloadlimitations)17. Descriptionoflaunchloadlimitationsalongpayloadaxes18. Descriptionofpowerrequirementsduringspacecraftintegration19. Descriptionofanysafetyissuesassociatedwiththespacecraft(includingmaterialsorhanding
operationsthatmightbeconsideredhazardous)20. Descriptionofanypropulsionsystemstobeusedonthespacecraft.21. Descriptionofanypressurevesselstobeusedonthespacecraft.22. Descriptionofthespacecraftpowersystem(e.g.typesofbatteries,solarcells,etc.)23. DescriptionofanyRFsystemstobeusedonthespacecraft.DetaileachRFtransmitteror
receiver,itsfunction,frequency,sensitivity,poweroutput,andbandwidth24. PlannedtimingofRFinitializationfollowingpayloadseparation25. Typeofseparationmechanism(includingconfigurationofinhibitswitchesandseparation
connectors)26. Descriptionofanysecurityrequirements27. High-leveldescriptionofintendedpayloadoperationsduringpayloadlifetime28. Othercomments