Transcription

Small Spacecraft Mission ServiceVEGA-CUser’s ManualIssue 1 – Revision 0Sept. 2020Issued and approved by ArianespaceRoland LagierChief Technical Officer

SSMS Vega-C User’s ManualIssue 1PrefaceThe present User’s Manual is an add-on to the Vega-C User’s Manual and providesan overview of the Small Spacecraft Mission Service on Vega-C launch systemoperated by Arianespace at the Guiana Space Centre.This document contains the essential data which are necessary: To assess compatibility of Mini, Micro, Nano S/C and Cubesats Deployersmission with Vega-C launch system, To initiate the preparation of all technical and operational documentationrelated to a launch of any Small S/C either on rideshare mission or aspiggyback with main passenger.Inquiries concerning clarification or interpretation of this manual should be directedto the addresses listed below. Comments and suggestions on all aspects of thismanual are encouraged and appreciated.France HeadquartersUSA - U.S. SubsidiaryArianespaceBoulevard de l'EuropeBP 177 91006 Evry-Courcouronnes Cedex FranceTel: (33) 1 60 87 60 00Fax: (33) 1 60 87 64 59Arianespace Inc.601 13th Street N.W. Suite 710 N.Washington, DC 20005, USATel: (1) 202 628-3936Fax: (1) 202 628-3949Singapore - Asean SubsidiaryJapan - Tokyo OfficeArianespace Singapore PTE LTD# 18-09A Shenton House3 Shenton WaySingapore 068805Fax: (65) 62 23 42 68ArianespaceKasumigaseki Building, 31Fl.3-2-5 Kasumigaseki Chiyoda-kuTokyo 100-6031 JapanFax: (81) 3 3592 2768WebsiteFrench Guiana - Launch Facilitieswww.arianespace.comArianespace , Sept. 2020ArianespaceBP 80997388 Kourou Cedex French GuianaFax: (33) 5 94 33 62 66III

SSMS Vega-C User’s ManualIssue 1Configuration Control SheetIssue /Rev.Proof ofConceptIssue onVegaIssue 1Revision 0IVDateChange descriptionFeb, 2017First issue, dedicated toSSMS Proof of Concept Flighton VegaJuly, 2020Vega-C issuePrepared byApproved byC. DUPUIS AEP. LOIRE AEA. SCACCIAESAF. CARAMELLIESAC. DUPUISL. BOUAZIZArianespace , Sept. 2020

SSMS Vega-C User’s ManualIssue 1Table of contentsPrefaceConfiguration control sheetTable of contentsAcronyms, abbreviations and definitionsCHAPTER 1. INTRODUCTION1.1. PURPOSE OF THE VEGA-C SMALL S/C MISSION SERVICE USER’S MANUAL1.2. SMALL S/C CLASSIFICATION1.3. TYPE OF MISSIONS1.3.1. Rideshare missions1.3.2. Piggyback missions1.4. ARIANESPACE CARRYING SYSTEMS FOR SMALL S/C1.4.1. Introduction1.4.2. SSMS carrying system1.4.3. VESPA carrying system1.4.4. VAMPIRE 937 MPL carrying system1.5. MAIN CONDITIONS APPLICABLE TO SMALL S/C1.5.1. General1.5.2. Main conditions for rideshare missions1.5.3. Main conditions for piggyback missions1.5.4. Additional specific conditions for Cubesats Deployers1.6. PROCURING SMALL S/C LAUNCH SERVICECHAPTER 2. LAUNCH MISSION2.1. GENERAL2.2. TYPICAL MISSION PROFILE2.3. AEROTHERMAL FLUX AT FAIRING JETTISONING2.4. CONDITIONS AT SEPARATIONCHAPTER 3. SMALL S/C INTERFACES3.1. INTRODUCTION3.2. SMALL S/C REFERENCE AXES & CLOCKING3.3. SMALL S/C DIMENSIONS3.4. MECHANICAL INTERFACE3.5. ELECTRICAL INTERFACES3.5.1. General3.5.2. Umbilical links for Mini/Micro/Nano S/C3.5.3. S/C separation monitoring for Mini/Micro/Nano S/C3.5.4. Electrical continuity interface for Mini/Micro/Nano S/C3.5.5. Electrical interface for Cubesats Deployers3.6. INTERFACES VERIFICATIONS FOR MINI/MICRO/NANO S/C3.6.1. Prior to the launch campaign3.6.2. Pre-launch validation of the electrical links3.7. ON FAIRING MISSION INSIGNIACHAPTER 4. DESIGN, COMPATIBILITY VERIFICATION REQUIREMENTS &ENVIRONMENTAL CONDITIONS4.1. INTRODUCTION4.2. DESIGN REQUIREMENTSArianespace , Sept. 2020V

SSMS Vega-C User’s ManualIssue afety RequirementsSelection of Spacecraft MaterialsMass PropertiesFrequency RequirementsDesign LoadsDynamic LoadsOther loadsLine loads peaking induced by S/C4.3. COMPATIBILITY VERIFICATION REQUIREMENTS4.3.1. Verification logic4.3.2. Safety factors4.3.3. Spacecraft compatibility tests4.3.3.1. Static tests4.3.3.2. Sinusoidal vibration tests4.3.3.3. Random vibration tests4.3.3.4. Acoustic vibration tests4.3.3.5. Shock qualification4.4. THERMAL LOADS4.5. RF ENVIRONMENTCHAPTER 5. MISSION MANAGEMENT & LAUNCH CAMPAIGN ORGANISATION5.1. INTRODUCTION5.2. MISSION MANAGEMENT5.2.1. Contract organization5.2.2. Launch schedule management5.2.3. Meetings and Reviews5.3. SYSTEMS ENGINEERING SUPPORT5.3.1. Interface Management5.3.2. Mission Analysis5.3.3. Small S/C Compatibility Verification5.3.4. Post-launch Analysis5.3.5. Standard activities5.4. LAUNCH VEHICLE ADAPTATION5.5. LAUNCH CAMPAIGN5.5.1. Typical launch campaign for Mini/Micro/Nano S/C5.5.2. Typical launch campaign for Cubesats Deployer(s)5.5.3. Launch campaign overview5.5.4. Summary of launch campaign meetings and reviews5.5.5. Range Support at CSG5.5.6 Standard support service5.6. SAFETY ASSURANCE5.7. QUALITY ASSURANCE5.8. OPTIONAL SERVICESAnnex 1 – APPLICATION TO USE ARIANESPACE’S LAUNCH VEHICLE (DUA)TEMPLATEAnnex 2 – STANDARD SMALL S/C ADAPTERS2.1 PSC MLB2.2 RUAG PASAnnex 3 – DESCRIPTION of SAB AEROSPACE FACILITIES in BRNOAnnex 4 – VEGA SSMS PROOF of CONCEPT MISSION & VEGA SMALL S/CLAUNCH RECORD§1 - p6Arianespace , Sept. 2020

SSMS Vega-C User’s ManualIssue 1Acronyms, abbreviations and definitionsAAEAVUM ArianespaceAttitude & Vernier Upper Module(Vega-C last stage)BOBBT POCBreak Out BoxCombined operations readinessreviewCADCBOD-LTCVIComputer Aided DesignLow Tension Clamp Band OpeningDeviceContamination&CollisionAvoidance ManeuversCritical Design ReviewCoupled Loads AnalysisMission DirectorFrench National Space AgencyCenter of GravityCheck-Out Terminal EquipmentProgram directorPost Flight DebriefingGuiana Space CentreCentral Telemetry UnitCollected Volatile CondensableMaterialReal time flight evaluationDAMFFinal mission analysis documentDAMPPreliminary mission analysisdocumentInterface control documentApplication to use Arianespacelaunch vehiclesBBilan Technique Plan PCRALCSGCTUCVCMChef de MissionCentre National d’Etudes SpatialesChef de ProgrammeCompte-Rendu Après LancementCentre Spatial GuyanaisContrôle Visuel ImmédiatDDCIDUADocument d'Analyse de MissionFinaleDocument d'Analyse de MissionPréliminaireDocument de Contrôle d’ InterfaceDemande d'Utilisation tEquivalentIsotropicRadiatedPowerElectromagnetic CompatibilityPayload preparation complexEnsemble de Préparation desCharges UtilesEuropean Space AgencyFARFEMFMFQRFlight Acceptance ReviewFinite Element ModelFlight ModelFinal Qualification ReviewEIRPEMCEPCUFArianespace , Sept. 2020VII

SSMS Vega-C User’s ManualIssue 1GGRSGSEGeneral Range SupportGround Support EquipmentHPFHazardous Processing FacilityIATAInternational Air TransportAssociationSpecific easuring instrument laboratoryCheck out equipment roomLow Earth OrbitLaunch and Early Orbit Phase“green” Liquid MonoPropellantLaunch Service AgreementLocal Time of Ascending NodeLocal Time of Descending NodeLaunch VehicleLaunch WindowLaboratoire MesuresLaboratoire Banc de ContrôleMCIMFUMGSEMasse, Centre de gravité, InertiesMLBMLIMMHMUVMass, balances and inertiasMulti-Functional UnitMechanical Ground SupportEquipmentMotorized Light BandMulti Layer InsulationMonomethyl HydrazineVega-C User's ManualN/ANot ApplicableOASPLOverall Acoustic Sound PressureLevelOverall Check Out EquipmentLMManuel Utilisateur SD§1 - p8Payload Assembly CompositePayload Attachment FittingPayload Adapter SystemPreliminary Design ReviewProto-Flight ModelProof of ConceptCombined operations planInterleaved Spacecraft OperationsPlanSpacecraft operations planPayload Preparation Facilityparts per millionPlanetary Systems CorporationPower Spectral DensityPlan d’Opérations CombinéesPlan d’Opérations ImbriquéesPlan d’Opérations SatelliteArianespace , Sept. 2020

SSMS Vega-C User’s ManualIssue 1QQAQRQSLQuality AssuranceQualification ReviewQuasi-Static LoadRAANRight Ascension of the AscendingNodeLaunch readiness reviewRevue d’Aptitude au LancementFinal mission analysis reviewRevue d'Analyse de Mission FinalePreliminary mission analysis review Revue d'Analyse de MissionPréliminaireLaunch vehicle flight readinessRevue d’Aptitude au Vol du lanceurreviewRadio FrequencyRequest for WaiverRoot Mean Squarerevolutions per minuteSpacecraft preparation managerResponsable Préparation SatelliteSafety managerResponsable SauvegardeGround safety officerResponsable Sauvegarde SolFlight safety officerResponsable Sauvegarde SPORTSRSSSMSSSOSTMSpacecraftVega-C Launch SiteStatement Of WorkSatellite Project OperationalRequirements TablesShock Response SpectrumSmall Spacecraft Mission ServiceSun Synchronous OrbitStructural Test ModelTBCTBDTCTMTo Be ConfirmedTo Be DefinedTelecommandTelemetryUCUCIFUpper CompositeUpper CompositeFacilityUniversal TimeSite de Lancement Vega-CTUUTIntegrationVVAMPIREVEGAVega Adapter for Multiple PayloadInjection and REleaseEuropean small launcherVESPAVEga Secondary Payload AdapterArianespace , Sept. 2020Vettore EuropeoAvanzatadiGenerazioneIX

SSMS Vega-C User’s ManualIssue 1INTRODUCTION1.1Chapter 1Purpose of the Small S/C Mission Service User’s ManualArianespace has been launching Small Spacecraft since the early days of Ariane in 1980.Arianespace initiated a standardized approach with the introduction of the ASAP carryingsystem (Ariane Structure for Auxiliary Payloads). This allowed many teams worldwide togain easy and cost effective access to space for their small projects.In order to address the needs of a growing number of Small Sat projects, Arianespace isnow offering a tailored, standardized launch service for Small S/C, with regular ridesharemissions on Vega-C, in addition to some piggyback opportunities.A first “Proof of Concept” rideshare mission on Vega successfully took place on 02September 2020 with a total of 53 Small S/C.Vega-C launch system has improved capabilities compared to Vega: higher performance(60% more), larger fairing, improved versatility (3 different orbits can be targeted) and awider spectrum of payload accommodations for any S/C. This will allow embarking evenmore Small S/C at the same time and will make the life always easier to any entities thatwant to take advantage of affordable access to space.The present Small Spacecraft Mission Service User’s Manual provides information forlaunching Small S/C from 1kg up to 400 kg using the Vega-C launch system operatedfrom the Guiana Space Centre by Arianespace.The content encompasses: thethethethethetheSmall Spacecraft classification;description of the available carrying systems on Vega-C;description of the interfaces between Small Spacecraft and Launch Vehicle;requirements for Small Spacecraft design and compatibility verification andlaunch environment;mission management & launch campaign organization.Together with the Vega-C User’s Manual, the Spacecraft Processing Facility at CSG User’sManual and the Payload Safety Handbook, it gives readers the information to assess thecompatibility with the proposed standardized configurations.§1 - p10Arianespace , Sept. 2020

SSMS Vega-C User’s ManualIntroductionIssue 11.2. Small Spacecraft classificationArianespace has established the following classification for Small Spacecraft in order to providea standard launch service tailored to each class of Small S/C: Mini S/C: small satellite with a mass from 200 up to 400 Kg, Micro S/C: small satellite with a mass from 60 to 200 Kg, Nano S/C: small satellite with a mass from 30 to 60 Kg, Cubesat DeployersThe table below summarizes the Small S/C main characteristics:Mini S/CMicro S/CNano S/CCubesatDeployersMassrange400 – 200 kg200 – 60 kg60 – 30 kg35 – 10 kgMax.dimensions*H1800 Ø1500H1200 L800 W800H1000 L600 W600H600 L300 W300Interfacewith the LVMLB 24’’MLB 15 or 13’’ororPAS 610 SPAS 381 S(or H800 L500 W 600)MLB 11,732’’ or 8’’Bolted IF* NOTE1: H represents the dimension of the S/C in the direction of separation.Each class of Small S/C has been associated with some positions available on the Arianespacemultiple launch systems (SSMS carrying system, VESPA R, VAMPIRE: refer to chapter 1.4below for a detailed description).Arianespace , Sept. 2020§2 - p11

IntroductionSSMS Vega-C User’s ManualIssue 11.3. Type of missionsArianespace proposes two types of missions for Small S/C:- rideshare missions dedicated to Small S/C,- piggyback missions with main passenger.1.3.1. Rideshare missionThe rideshare missions on Vega-C take place regularly, at least one per year. The launchperiod is confirmed once Arianespace has secured a sufficient number of Customers. The maincharacteristics of the mission is defined by Arianespace taking into account the preferencesexpressed by every customer.1.3.2. Piggyback missionThe piggyback missions on Vega-C take place when extra performance and volume areavailable on an already manifested mission with Main Passenger(s). The launch period and themain characteristics of the mission are defined by the Main Passenger(s).1.4. Carrying systems for Small S/C on Vega-C1.4.1. IntroductionIn order to provide more launch opportunities for Small S/C, Arianespace, with the support ofESA, has developed several carrying systems to carry and deploy Small S/C, either forrideshare mission or in piggyback.-SSMS modular carrying system, mainly for a cluster of Small S/C of any size and mass,-VESPA R (VEga-C Secondary Payload Adapter, reinforced version of existing VESPA on Vega), for one large passenger and additional Small S/C of any size and mass,-VAMPIRE 937 MPL, for one large passenger and up to 6 Nanosatellites,The SSMS carrying system is very modular and a high number of configurations can beproposed ; some of them (with the base Hexagonal module) can be also used for piggybacktype missions.The SSMS and VESPA R systems can also be combined to offer even more positions for MiniS/C.§2 - p12Arianespace , Sept. 2020

SSMS Vega-C User’s ManualIntroductionIssue 1TYPICAL PAYLOD ASSEMBLY COMPOSITE CONFIGURATIONCARRYING SYST.TYPEThe table below summarizes the carrying systems t-3Flexi-3Flexi-4Cluster of SmallS/CSSMS&VESPA RcombinedCluster of SmallS/C with onelarge Mini S/CSSMSHex-1Hex-2One mainpassengerwith Nano S/C orCubesatsDeployersVESPA RVAMPIRE 937MPLOne mainpassengerwith Mini, Micro orNano S/COne mainpassengerwith Nano S/CTable 1.4.1a - Vega-C carrying systems capabilitiesArianespace , Sept. 2020§2 - p13

SSMS Vega-C User’s ManualIntroductionIssue 11.4.2. SSMS carrying systemThe Small Satellite Mission Service (SSMS) carrying system is a modular system designed toaddress the small satellites market by providing dedicated rideshare Small S/C missions onVega-C.The SSMS carrying structure is manufactured by SAB Aerospace and is mainly composed of:- sandwich panels with aluminum honeycomb core and with carbon fiber composite skins,- aluminum machined I/F rings,- aluminum connecting frames between the different panels and harness support parts(brackets and others).The different modules (hexagon, main deck, columns, towers, shear webs, spacers) allow toaccommodate a large number of Small S/C of various sizes and masses.SET OF SSMS MODULESHEXAGONADAPTERSMAIN DECKCENTRAL COLUMNSPACERSTOWERSSHEAR WEBSFigure 1.4.2a - SSMS carrying system modulesThe Hexagon is the base module present in every configuration.The main deck comes above the Hexagon base module and struts ensure the proper rigidity ofthe assembly.The shear webs, central column and towers module can be installed on the main deck asnecessary.For every Small S/C, the adapter comprises the separation and distancing system and the socalled spacer acts as an interface between the carrying system and the adapter. The spacercan be customized in order to raise the Small S/C or tilt the Small S/C or shift the Small S/Caxis w.r.t. the standard position/orientation.By combining all these elements, a high number of carrying system configurations can beobtained.§2 - p14Arianespace , Sept. 2020

SSMS Vega-C User’s ManualIntroductionIssue 1SSMS CARRYING SYSTEM EX-2PLAT-3FLEXI-3FLEXI-4Figure 1.4.2b - Possible SSMS carrying system versionsArianespace , Sept. 2020§2 - p15

IntroductionSSMS Vega-C User’s ManualIssue 1Figure 1.4.2c - SSMS PoC carrying system on Vega - VV16 preparation§2 - p16Arianespace , Sept. 2020

SSMS Vega-C User’s ManualIntroductionIssue 11.4.3. VESPA R carrying systemThe VESPA R carrying system is inherited from the VESPA carrying system on Vega (whichflew 3 times as of Sept. 2020).It allows to embark one large passenger in upper position, together with, in lower position, oneMini S/C or a cluster of Small S/C of various size. It is mated on the AVUM upper stage.The VESPA R is manufactured by AIRBUS DS Spain. It consists of the upper part, the boattail, the inner cone and the inner platform. It also provides the interface and separationsystem to the main passenger (Ø937 mm or Ø 1194 interface).I/F and separationsystem for mainpassengerUpper partSpringsClamp BandInner platformBoat tailI/F with AVUM Figure 1.4.3a - VESPA R configurationThe separation of the upper part of the VESPA structure is achieved by means of a Clamp Bandand 8 springs.Figure 1.4.3b - VESPA - VV10 launch campaignArianespace , Sept. 2020§2 - p17

SSMS Vega-C User’s ManualIntroductionIssue 11.4.4. VAMPIRE 937 MPL carrying systemAmongst the different so-called VAMPIRE Vega-C adapter versions for large S/C (refer to VegaC User’s Manual), the VAMPIRE 937 MPL allows to embark up to 6 Nanosatellites on 6 towers,in addition to one large Spacecraft using a Ø 937 clamp band interface.I/F and separation systemfor main passengerI/F and separationsystem for Nano S/CTowersI/F with AVUM Figure 1.4.4a - VAMPIRE 937 MPL1.5. Main conditions applicable to Small S/C1.5.1 GeneralThe standard conditions are defined in Launch Service Agreement (LSA), Terms & Conditions(T&C) and Statement of Work (SOW).This chapter briefly summarizes the main conditions in each case (rideshare mission,piggyback mission).Specific and even more simplified SOW are defined for Cubesat Deployers.1.5.2 Main conditions for rideshare missionThe following chapter describes the main conditions for a rideshare mission.Launch ScheduleThe launch period (3 months), launch slotArianespace. The launch period is notifiednumber of Customers for a given ridesharelatest 12 months in advance for Mini, Microadvance for Cubesats Deployers.§2 - p18(1 month) and launch date are defined byonce Arianespace has secured a sufficientmission. The launch period is defined at theand Nano S/C and at the latest 6 months inArianespace , Sept. 2020

SSMS Vega-C User’s ManualIntroductionIssue 1Dummy payloadA dummy payload has to be made available in case the actual Small S/C is not ready forthe launch.The dummy payload provided by the Customer must be representative of the Small S/Cin terms of mass and mechanical interface. The dummy payload must be smaller thanthe actual Small S/C volume, with no CoG offset and be compatible with the flightenvironment. No electrical interface is required.Proof of availability of the dummy will be made by the Small S/C Customer for the FlightReadiness Review (RAV) and the dummy shall be provided at the beginning of the launchcampaign.As an option, available at Customer request, Arianespace can procure the dummy.Targeted orbitThe targeted orbit is defined by Arianespace taking into account the preferencesexpressed by every Customer.Thanks to AVUM last stage re-ignition capabilities, up to three different altitudes can betargeted.Separation time and orientationThe time and attitude at S/C separation are defined by Arianespace.Small S/C status during final countdown and flightThe Small S/C shall be inert (S/C OFF, no RF emission, no status changes) during thefinal countdown and ascent phase until after the small S/C separation. The actual delayafter separation will be determined by Arianespace in the frame of the mission analysisprocess and will depend on the type of orbit and overall mission timeline.Small S/C battery chargeThe Small S/C battery operating life shall be at least 45 days after the last batterycharge, usually performed just before S/C mating on the carrying structure.Alternatively, battery trickle charges shall be possible via umbilical links.Small S/C preparation at the launch siteS/C arrival date to French Guiana shall be coordinated with Arianespace, with theobjective that all the Small S/C for a given mission were transferred the same day.The CSG facilities are shared with the other Small S/C on the same flight. This includesSpacecraft Preparation Clean Room, and when necessary, Filling hall and Lab for Checkout stations (LBC).The Small S/C shall be ready for integration on the carrying structure. Refer to chapter 5for an extensive description of the integration work flow.No access to the satellite is authorized after fairing encapsulation.Arianespace , Sept. 2020§2 - p19

IntroductionSSMS Vega-C User’s ManualIssue 11.5.3 Main conditions for piggyback missionThe following chapter describes the main conditions for a piggyback mission with a mainpassenger.Main passenger approvalFor a piggyback mission, the launch of a Small S/C is subject to the approval of the mainpassenger. The Small S/C shall be able to answer to any inquiry aiming at demonstratingtechnical and programmatic innocuousness for main passenger.Launch ScheduleThe Launch schedule is totally subordinated to the launch schedule of the mainpassenger and the Small S/C shall in no case be entitled to affect the launch schedule.The consequence is that, should the Small S/C not be ready for the launch, it will fly as itis if already mounted on the Payload Assembly Composite or, it will be replaced by adummy payload.Dummy payloadA dummy payload has to be made available in case the actual Small S/C is not ready forthe launch.The dummy payload provided by the Customer must be representative of the Small S/Cin terms of mass and mechanical interface. The dummy payload must be smaller thanthe actual Small S/C volume, with no CoG offset and be compatible with the flightenvironment. No electrical interface is required.Proof of availability of the dummy will be made by the Small S/C Customer for the FlightReadiness Review (RAV) and the dummy shall be provided at the beginning of the launchcampaign.As an option, available at Customer request, Arianespace can procure the dummy.Targeted orbitThe targeted orbit is defined by Arianespace taking into account the main passengertechnical requirements. In particular, for Sun synchronous Orbit (SSO) mission, the localtime of ascending node (LTAN) is defined by the main passenger.Thanks to AVUM last stage re-ignition capabilities, the Small S/C can be released on adifferent orbit altitude to cope as much as possible with Small S/C preferred orbit.Separation time and orientationThe separation timeline and orientation are defined by Arianespace.For Mini Auxiliary Passenger, and depending on overall mission, the customer preferredseparation conditions can be considered.Small S/C status during final countdown and flightThe Small S/C shall be inert (S/C OFF, no RF emission, no status changes) during thefinal countdown and ascent phase until after the Small S/C separation. The actual delayafter separation will be determined by Arianespace in the frame of the mission analysisprocess and will depend on the type of orbit and overall mission timeline.§2 - p20Arianespace , Sept. 2020

SSMS Vega-C User’s ManualIntroductionIssue 1Small S/C battery chargeThe Small S/C battery operating life shall be at least 45 days after the last batterycharge, usually performed just before S/C mating on the carrying structure.Alternatively, battery trickle charges shall be possible via umbilical links.Small S/C preparation at the launch siteS/C arrival date to French Guiana shall be coordinated with Arianespace, with theobjective that all the auxiliary passengers for a given mission were transferred the sameday.The CSG facilities are shared with the other Small S/C on the same flight. This includesSpacecraft Preparation Clean Room, and when necessary, Filling hall and Lab for Checkout stations (LBC).The Small S/C shall be ready the day before the start of the Combined Operations (POC)18 days before the launch date (L-18) for integration on the carrying structure.No access to the satellite is authorized after mating on the carrying structure.1.5.4 Additional specific conditions for Cubesats DeployersThe following chapter describes the main conditions for Cubesats Deployers.Preparation and integration facilityThe preparation facilities for Cubesats Deployers are located in Brno, Czech Republic,Continental Europe (refer to Annex 3 for facility description). The Deployers fullyintegrated with the Cubesats shall be ready for integration on the SSMS Hexa module atthe latest 7 weeks before launch date.Deployer procurement & Cubesats integrationAs a standard, Customer shall procure the Deployer(s) and deliver to Arianespace fullyintegrated Deployer(s) with the Cubesats already integrated inside the Deployer(s). Itmeans the management of the interfaces between the Cubesats and Deployer(s) isCustomer responsibility.As an option, available at Customer request, Arianespace with the support of ourpartners, can procure the Deployer(s) and manage Cubesats integration. For moreinformation on this option, please contact Arianespace.Deployer compatibility to Vega-C last stage avionicsThe Cubesats separation is managed either directly by the Vega-C Multi-Functional Unit(MFU) or, when necessary, by a dedicated electrical interface unit called “Sequencer” andprovided by Arianespace. Compatibility between Deployer and Vega-C last stage avionicsshall be brought by the Customer. Refer to chapter 3 for details.TransportThe Cubesats and Cubesats Deployer(s) shall be compatible with a shipment by regularcommercial airplane. Refer to chapter 5 for details.Arianespace , Sept. 2020§2 - p21

IntroductionSSMS Vega-C User’s ManualIssue 11.6. Procuring Small S/C Launch ServicesA template of the Application to Use Arianespace’s Launch Vehicle for Small Spacecraft isattached in Annex 1.Two versions are available:-Full MS Word version,-Simplified MS Excel version.It is used by Arianespace to identify the possible launch opportunities, to build the Small S/Caggregate and provide preliminary mission and pricing information. Later on, once the LaunchService Agreement (LSA) is effective, it will be used to initiate the Interface Control Document(DCI).Arianespace is committed to maintain a list of launch opportunities for Small S/C on Vega-C.The corresponding missions are mainly Sun Synchronous Orbit (SSO) and Low Earth Orbit(LEO).§2 - p22Arianespace , Sept. 2020

SSMS User’s ManualSmall S/C missionIssue 1SMALL SPACECRAFTMISSION2.1Chapter 2GeneralThe mission profile is defined by Arianespace, including:- ascent profile, number and durations of the upper stage boost phases and of the coastphases, visibility from ground stations, etc.- Small S/C separation timeline,- attitude pointing at Small S/C separation.The re-ignition capabilities of the Vega-C upper stage (so-called AVUM stage) allow typicallyto inject Small S/C on two (2) or three (3) different altitudes with a multiple AVUM boostsprofile.The customer preferred separation orientation might be considered, depending on overallmission timeline.2.2Typical mission profileThe ascent ground track for a typical SSO mission is shown here below:Figure 2.2a - Typical ground track and flight sequence for Vega-C SSO missionsArianespace , Sept. 2020§2 - p23

Small S/C missionSSMS User’s ManualIssue 1The corresponding launch sequence comprises:-2.3Solid stages ascent phase,1st AVUM boost,Coast phase,2nd AVUM boost to reach the targeted orbit,Separation of a first batch of Small Satellites (rideshare mission) or of the mainpassenger (piggyback mission),CCAM (Contamination and Collision Avoidance Maneuvers),3rd and 4th AVUM boosts to change the SSO altitude (and inclination correspondingly),Separation of a second batch of Small Satellites,CCAM maneuvers,5th and 6th AVUM boosts to change the SSO altitude (and inclination correspondingly),Separation of a third batch of Small Satellites,CCAM maneuvers,Last AVUM boost to trigger the controlled reentry of the AVUM in the Ocean.Aerothermal flux at fairing jettisoningJettisoning of the payload fairing can take place at different times depending on thepassengers aerothermal flux requirements.Typically, for SSO missions, the fairing separation takes place 5s after Z9 ignition around 270seconds from lift-off and the aerothermal flux is lower than 300 W/m2.The actual aerothermal flux at fairing jettisoning will be determined in the frame of the missionanalysis.2.4Conditions at Small S/C separationThe separation conditions (time, orientation, ) are defined by Arianespace.For Mini S/C, the customer preferred separation orientation might be considered, depending onoverall mission timeline.Separation conditions (depointing, residual angular velocities after separation) is determined inthe frame of the mission analysis. In order to counteract the effect of spacecraft nominal staticunbalance at spacecraft separation, and improve the Small S/C tip-off rates after separation,the number, position and/or energy of the springs on the adapter can be tuned.§2 - p24Arianespace , Sept. 2020

SSMS Vega-C User’s ManualIssue 1SMALL SPACECRAFTINTERFACES3.1Chapter 3IntroductionThis chapter addresses the interface requirements: volume, mechanical interfaces, electricalinterfaces, other interfaces and interface verification tests.This chapter assumes that:- for Mini/Micro/Nano S/C, the adapter

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