Spaceflight, Inc. General Payload Users...

Spaceflight,Inc.PayloadUsersGuide

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Spaceflight, Inc. General Payload Users Guide

1505WestlakeAvenueNorth,Suite600Seattle,WA98109

Telephone:+1(866)342-9934Web:www.spaceflight.com


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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’sGuideiscurrentlyunderrevisionandexpectedtobereleasedin2018,providingupdatesonexpandedcapabilityandserviceofferingsnowavailablethroughSpaceflight.ThecurrentlyavailabledocumentisforreferenceonlyanddoesnotguaranteecompatibilityacrossLaunchVehiclesorridesharestructures.SignupforSpaceflight’smailinglisttobenotifiedwhenthenextrevisionisreleased.


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TableofContents1 Introduction...........................................................................................................................9

1.1 DocumentOverview........................................................................................................................9

1.2 SpaceflightOverview.......................................................................................................................9

1.3 HardwareOverview......................................................................................................................11

1.4 MissionManagementOverview...................................................................................................12

2 SecondaryPayloadIntegrationandHostingProducts........................................................14

2.1 SHERPA..........................................................................................................................................15

2.2 SHERPA400/1000/2200................................................................................................................15

2.3 MiniSHERPA...................................................................................................................................17

3 SecondaryPayloadInterfaceAdapters................................................................................18

3.1 Directly-MountedPayloadtoESPARingPortInterfaceAdapter..................................................19

3.2 RPAMountingInterfaceDefinition...............................................................................................22

3.3 VPAMountingInterfaceDefinition..................................................Error!Bookmarknotdefined.

3.4 DPAMountingInterface................................................................................................................27

4 CubeSatRequirementsandDispensers...............................................................................29

4.1 GeneralCubeSatRequirements....................................................................................................29

4.2 ISISISIPODDispensers...................................................................................................................31

4.3 PlanetarySystemsCorp.CanisterizedSatelliteDispenser............................................................32

4.4 CubeSatdeploymentfromtheInternationalSpaceStation.........................................................32

5 SecondaryPayloadSeparationDevices...............................................................................34

5.1 MarkIIMotorizedLightband.........................................................................................................34

6 AnalysesCoordinatedwithLSP...........................................................................................36

6.1 TrajectoryAnalysis........................................................................................................................36


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6.2 CoupledLoadsAnalysis.................................................................................................................36

6.3 RFCompatibilityAnalysis..............................................................................................................36

6.4 ThermalAnalysis...........................................................................................................................37

6.5 SeparationTimingandRe-contactAnalysis..................................................................................37

6.6 RangeSafetyAnalysis....................................................................................................................37

6.7 Post-flightDataAnalysis................................................................................................................37

6.8 Documentation.............................................................................................................................37

7 AnalysisofAdherencetoOtherRequirements...................................................................40

7.1 CommonEnvironments.................................................................................................................40

7.2 PayloadDesignandConstructionConstraints..............................................................................45

7.3 PayloadSafetyandHazards..........................................................................................................46

7.4 ElectricalandDataInterfaces........................................................................................................47

8 FinalIntegrationandLaunchOperations............................................................................48

8.1 PayloadTransportation.................................................................................................................48

8.2 SecondarypayloadproviderInvolvementduringIntegration......................................................48

8.3 IntegrationandHandoff................................................................................................................48

AppendixA:AcronymsandAbbreviations.................................................................................................50

AppendixB SecondaryPayloadQuestionnaireTemplate......................................................................51


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ListofFigures

Figure1-1Spaceflightisresponsiblefortheinterfacebetweenallsecondarypayloads..........................10

Figure2-1SHERPAwithAdapters..............................................................................................................14

Figure2-2Delta-VCapabilities...................................................................................................................16

Figure2-3PropulsiveSHERPACapabilities.................................................................................................17

Figure2-4MiniSHERPADelta-VCapabilities..............................................................................................18

Figure3-1SHERPAwithInterfaceAdapters...............................................................................................19

Figure3-2Directly-MountedPayload-ExplodedView.............................................................................20

Figure3-3BoltHolePatternforDirectlyMountedPayload......................................................................21

Figure3-4VolumeConstraints(5.2mfairingbaselined)............................................................................22

Figure3-5RadialPayloadAdapterSecondaryPayloadCoordinateSystem..............................................23

Figure3-6Boltholepatternforradialportadapter..................................................................................24

Figure3-7VolumeConstraints(5.2mfairingbaselined)............................................................................25

Figure3-8PrimaryCoordinateSystemontheVPABack-plateandSecondaryCoordinateSystem(right).......................................................................................................................Error!Bookmarknotdefined.

Figure3-9VPAmechanicalinterfacewithdimensionsininches[mm].....................................................26

Figure3-10AllowableStaticPayloadEnvelopewithintheDeployableShroudwithdimensionsininches[mm]...........................................................................................................................................................27

Figure3-11DPASystem.............................................................................................................................27

Figure0-1ISIPOD3UCubeSatDispenser...................................................................................................31

Figure0-2NanoRacksCubeSatDeployer...................................................................................................32

Figure0-3NanoRacksElectricalInhibitDiagram........................................................................................33

Figure5-1MarkIIMotorizedLightbandManufacturedbyPlanetarySystemsCorporation(8-inch)........34

Figure7-1MaximumPredictedAcousticEnvironment..............................................................................41

Figure7-2SecondaryPayloadGeneralizedRandomVibrationEnvironment............................................42


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Figure7-3MaximumPredictedElectromagneticEnvironmentduringPadOperationsandLaunch.........43

Figure7-4MaximumPayloadFairing(PLF)TemperatureSeenbythePayload........................................44

Figure7-5NarrowbandRadiatedE-fieldLimits.........................................................................................46

Figure7-6BroadbandRadiationLimits......................................................................................................46


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ListofTables

Table1-1StandardMissionIntegrationProcess.......................................................................................12

Table2-1PropulsiveSHERPATechnicalDetails.........................................................................................15

Table2-2MiniSHERPACapabilities............................................................................................................17

Table3-1AllowableSpacecraftWetMassperInterfaceAdapter.............................................................19

Table3-2DirectlyMountedPayloadMassProperties...............................................................................20

Table3-3RadiallyMountedPayloadMassProperties...............................................................................23

Table3-4VerticallyMountedPayloadMassProperties............................................................................26

Table3-5VerticallyMountedPayloadMassProperties............................................................................28

Table5-1MarkIILightbandOptions..........................................................................................................34

Table6-1RequiredMission-SpecificDeliverables.....................................................................................39

Table7-1MaximumPredictedAcousticEnvironment...............................................................................41

Table7-2SecondaryPayloadGeneralizedRandomVibrationEnvironment.............................................42

Table7-3MaximumPredictedElectromagneticEnvironmentduringPadOperationsandLaunch..........43

Table7-4Payloadenvironmentsduringgroundprocessing......................................................................44

Table7-5MaximumPLFTemperatureseenbythePayload......................................................................44


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1 Introduction

1.1 DocumentOverview

ThisSpaceflightPayloadUsersGuide(SPUG)ispublishedbySpaceflight,Inc.toprovidegeneralinformationtopayloaddeveloperswhomwilllaunchtheirpayloadorspacecraftusingSpaceflight’sintegrationservices.Itincludesdescriptionsonthevariousflightsupporthardware,interfaces,capabilities,launchenvironments,policiesandtoplevelprocessesSpaceflightusestomanifestyourpayloadanddeliveryoutoyourmissionorbit.FurtherinformationmaybeobtainedbycontactingSpaceflightdirectlythroughwww.spaceflight.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.spaceflight.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

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,howeverthelaunchopportunitiesmaybemorelimitedandultimatelytheacceptanceofthepayloadissubjecttoapprovalbytheLaunchServicesProviderandSpaceflight.

Multiple Secondary Payload OperatorsMultiple Secondary

Payload OperatorsMultiple Secondary Payload Operators

Launch Service Providers

Primary Payload Operator

Multiple Secondary Payload Operators


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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.

Spaceflightphysicallyintegratestheselectedhardwareintoonediscretepayload,theintegratedpayloadstack,forlaunch.Formoredetailsonhowthefinalintegrationandlaunchoperationswork,pleaseseeSection8.


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1.4 MissionManagementOverview

Spaceflightprovidesfullintegrationservicesforeachpayload.Theseservicesincludeengineeringanalysis,documentationsupportforthelaunchvehicleenvironments,interfacecontroldocumentation,andrangesafety.Thegeneralmissionmanagementprocessfora24monthtimelineissummarizedinTable1-1.

Table1-1StandardMissionIntegrationProcess

MilestoneDate Purpose SpaceflightDeliverables SecondarySpacecraftproviderDeliverables

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

• Customerinitiatesprocesswithapplicablenationaladministrationforlicensingforspacecraft(e.g.FCC,NOAAasapplicable)

• UpdatedPayloadCADmodel(ifapplicable)

• UpdatedPayloadFEM(ifapplicable)

• PayloadThermalModel• UpdatedPayloadMass• CompletedMSPSP• Spacecraftlaunchsite

operationsplan


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MilestoneDate Purpose SpaceflightDeliverables SecondarySpacecraftproviderDeliverables

SystemReadinessReviewLaunch-3months

Verifiesthatallpeople,parts,andpaperarereadyfortheshipmentofthePayloadtotheLaunchSiteandreadytobeginLaunchSiteactivities

• Updatedmissionanalysesresults(ifapplicable)

• Finalintegrationschedule• Finallaunchoperationsplan• Alistoffacilitiesandservices

availableforPayloadcheckout

• VerificationofPayloadcompliancetoICDrequirements(i.e.qualificationreport)

• UpdatestoCADmodel,FEM,thermalmodel,andMSPSP(ifapplicable)

• Verificationofallnecessarylicensing

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-likestructureshowninFigure2-1SHERPAwithAdapters.TheVPAaccommodatesboth20.32cm(8in)and38.10cm(15in)payloadseparationsystems.MoredetailsaboutthesesystemsisavailableinSection3.


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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.


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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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.

• Spaceflightwillnotlaunchanysatellitethathasnotprovidedevidenceofhavingmetthenecessaryregulatoryrequirements.

o Spacecraftprovidersshallprovideevidenceofthefollowing:§ Allnecessarylicensingrequiredtotransport,communicatewith,operate,

launchand/ordeploythespacecraftfromtheapplicablenationaladministrationsandregulatoryauthoritiesthatgovernthescopeoftheirmission(e.g.FCC)orawaiverfromagivenagency,asappropriate.ThisevidenceshallbeprovidedinEnglish,andbeaccompaniedbyaCustomerattestationthatthedocumentationprovidedistrueandcorrect.

§ OrbitaldebriscompliancewithNPR8715.6§ Approvalsnecessaryforanyearthimagingviaproperauthority(e.g.NOAA).

• ThesatelliteproviderisresponsibletocompleteallnecessarytestingandshallprovideatestplantoSpaceflightperdeliveryscheduledocumentedinthisdocumentorpertheSOW/ICD.

o Requiredtesting:§ Randomvibration§ Thermalvacuumbake-out§ Shocktesting

Therearemultipleresourcesavailabletopayloadprovidersinregardtotheregulatoryprocessandtestingthatshouldbereferenced.Wehaveincludedresourceswefindhelpfulbelow.Notethatthislistisnotexhaustiveandisforreferenceonly.Theapplicablewebsiteforyourspecificspacecraftoperationsmaynotbeincluded.

• AmateurRadioInformation–www.iaru.org• FCCAmateurRadioInformation–www.arrl.org/part-97-amateur-radio• NASADebrisAnalysisTool–http://orbitaldebris.jsc.nasa.gov.mitigate/das.html• ForcommonU.S.GovernmentdocumentssuchasAFSPCMAN,MilitaryStandardsandothersuch

documentsvisit–http://everyspec.com• FCCOfficeofEngineeringandTechnology-https://www.fcc.gov/engineering-%26-technology• FCCInternationalBureauSatelliteDivision-https://www.fcc.gov/general/international-bureau-satellite-

division• FCC-GuidanceonObtainingLicensingforSmallSatellites-https://www.fcc.gov/document/guidance-

obtaining-licenses-small-satellites• NOAA-CommercialRemoteSensingRegulatoryAffairs-

https://www.nesdis.noaa.gov/CRSRA/licenseHome.html• UnitedNations–OfficeforOuterSpaceAffairs–ResourcesandReferenceMaterialforStatesand

Organizations-http://www.unoosa.org/oosa/en/spaceobjectregister/resources/index.html• UnitedNations–CollectionofNationalSpaceLaw-

http://www.unoosa.org/oosa/en/ourwork/spacelaw/nationalspacelaw/index.html• ITU–FilingProceduresforSmallSatellites-https://www.itu.int/en/ITU-

R/space/Pages/supportSmallSat.aspx


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4.2 ISISISIPODDispensers

ISISLaunchServicesprovidesavarietyofCubeSatdispensersforsmallspacecraft.TheISIPOD(pronounced“easy-pod”)isalaunchadapterforpico-andnanosatellitesthatadherestotheCubeSatinterfacestandarddefinedbytheCubeSatDesignSpecification.Spaceflightutilizesthe3UISIPODtodeploydedicated3UCubeSatsaswellas1Uand2UCubeSatswhichsharetheISIPODvolume.TheISIPOD3UdispenserisshowninFigure0-1.

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.


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4.3 PlanetarySystemsCorp.CanisterizedSatelliteDispenser

ThePlanetarySystemsCorporationCanisterizedSatelliteDispenser(CSD)isareliable,testable,andcost-effectivedeploymentmechanismforsmallsecondaryortertiarypayloads.Itfullyencapsulatesthepayloadduringlaunchandthusprovidesmissionassuranceforboththeprimarypayloadandlaunchvehicle.Allexternalsurfacesareelectricallyconductivechem-filmaluminumalloy.

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:


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4.4.1 ElectricalInhibits

CubeSatdesignshallincludethree(3)inhibitswitcheswiththree(3)correspondingdeploymentswitches.Groundchargeshallnotenergizethesatellitesystems(load).AnexamplecircuitdiagramisshowninFigure0-3.

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.

8

SpacecraftLicensingthelicenses,permits,clearances,authorizations,andapprovalsnecessaryforapartytocarryoutitsdutiesandobligationsundertheAgreement.ForaCustomerthisincludes,withoutlimitation,alllicenses,permits,clearances,authorizations,andapprovalsnecessaryto(a)transportthesatellitetotheintegrationfacility;(b)communicatewiththesatellitewhileinorbit;(c)operatethesatellitewhileinorbit;and(d)launchand/ororbitaldeploymentofthesatellite.Suchlicensesmayinclude,butarenotlimitedto:(i)obtainingallnecessarylicensesfromtheFederalCommunicationsCommission(“FCC”)oryourapplicablenationaladministration/agency;and(ii)theNationalOceanicandAtmosphericAdministration(“NOAA”)(ifapplicable).


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7 AnalysisofAdherencetoOtherRequirements

7.1 CommonEnvironments

Thefollowingsectionscontainbaselineenvironmentsbaseduponcommonlaunchvehicles.TheseenvironmentsrepresentaconservativeapproachtothesatellitedesignandshouldnotbeusedtodeterminetheabsolutecompatibilitywithlaunchopportunitiesthatSpaceflighthasavailable.Spaceflightunderstandsthatdesigningtooverlyconservativeenvironmentsimposesthepossibilityofgreatermassandoverallcosttothepayloadprovider,andweencourageearlyengagementwithSpaceflightforanyoftheenvironmentswithinthisdocumentthatposeasignificantissueorconcern.Also,theGeneralEnvironmentalVerificationStandard(GEVS,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.InorderforSpaceflighttoproceedwiththelaunchofthesatellite,allnecessarylicensingrequiredtotransport,communicatewith,operate,launchandordeploythesatellite,fromtheapplicablenationaladministrationsandregulatoryauthoritiesthatgovernthescopeoftheirmission(e.g.FCC)orawaiverfromagivenagency,asappropriate,mustbeprovided.ThisevidenceshallbeprovidedinEnglish,andbeaccompaniedbyaCustomercertificationthatthedocumentationprovidedistrueandcorrect.


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Theintegrationprocesstakesplaceinacontrolledfacilitynearthelaunchsite.Thepayloadintegrationactivityandsystemlevelteststakebetweentwoandfourweekstocomplete.PriortohandofftotheLSP,SpaceflightwillconductaseriesofcontinuitychecksensuringtheproperfunctioningofSpaceflightsystems.AmissionsimulationwillalsobeconductedatthattimetotestSpaceflighthardwareandsecondarypayloadseparationsystems,andtoverifythemissiondeploymenttimeline.

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

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