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SpaceSpace TransportationTransportation AtlasAtlas VV // AuxiliaryAuxiliary PayloadPayload OverviewOverview LockheedLockheed MartinMartin SpaceSpace SystemsSystems CompanyCompany JimJim EnglandEngland (303)(303) 977-0861977-0861 ProgramProgram Manager,Manager, AtlasAtlas GovernmentGovernment ProgramsPrograms BusinessBusiness DevelDevelopmentopment andand AdvancedAdvanced ProgramsPrograms 33 AugustAugust 20062006 1 Video – Take a Ride 2 ReliableReliable && VersatileVersatile LaunchLaunch VehicleVehicle FamilyFamily RReettiirreedd RReettiirreedd Atlas I AC-69 RReettiirreedd Jul 1990 Atlas II AC-102 RReettiirreedd 8/11 Dec 1991 Atlas IIA 10/10 AC-105 RReettiirreedd Jun 1992 • Consecutive Successful Atlas CentaurAtlas Flights: IIAS 79 Retired • First Flight Successes: 823/23 of 8 AC-108 Retired • Mission Success: 100% Atlas II, IIA, IIAS,Dec 1993 IIIA, IIIB, and V Families Atlas IIIA First Flight • Retired Variants: A, B, C, D, E, F, G, H,30/30 I, II, IIA, IIAS,AC-201 IIIA, IIIB May 2000 Atlas IIIB X/Y AC-204 2/2 X Successes / Y FlightsFeb 2002 Atlas V-400 AV-001 4/4 Mission Success: One Launch at a Time 4/4 Aug 2002 Atlas V-500 AV-003 4/4 Jul 2003 3/3 3 RecentRecent AtlasAtlas // CentaurCentaur EvolutionEvolution Atlas I / II Family Atlas III Family Atlas V Family dd dd iirree iirree eett eett RR RR 5-m PLF 30 GSO Kit 26 Single Avionics Engine Common Upgrade 22 Centaur Centaur 3.8-m 18 Common LO2 Core Tank Booster Stretch 14 10 Liquid SRBs Strap-ons RD-180 SRBs 6 Engine Atlas I Atlas IIAS Atlas IIIA Atlas IIIB Atlas V Atlas V Atlas V 407 km (220 nm) Circ. Capability (mT) 2 Atlas II (SEC) (DEC) (400 Series) (500 Series) (HLV) Atlas IIA (0–3 SRBs) (0–5 SRBs) 7/90 12/93 5/00 2/02 8/02 7/03 2012+ DemonstratedDemonstrated LowLow--riskrisk ContinuousContinuous ImprovementImprovement 4 AtlasAtlas VV CommonCommon ElementsElements 4.2-meter Common Centaur 5.4-meter PLF Contraves PLF (LPF, EPF, XPF) (68, 77, 87) RL10A-4-2 Single or Dual Engines Common Core Booster™ Solid Rocket Booster (SRB) Common Propulsion Atlas V 400 (0-3 SRBs) HLV Atlas 500 (0-5 SRBs) RD-180 Engine 5 AtlasAtlas VV ConfigurationConfiguration SummarySummary Atlas V Launch Vehicle Family Vehicle Naming Convention: Atlas V xyz 1st Digit = x = PLF Diameter (meters) 2nd Digit = y = No. of SRBs (0 to 5) 3rd Digit = z = No. of Centaur Engines (1 or 2) Vehicle 400 500 Heavy Series: PLF 4.2 Meter 5.4 Meter 5.5 Meter Diameter LPF Short (68’) Long (87’) EPF Med (77’) XEPF Long (87’) No. of 0 thru 3 0 thru 5 2 LRBs Strap-Ons SRBs SRBs No. Centaur 1 or 2 1 or 2 1 or 2 Engines The Atlas V Launch Vehicle Family Provides: • Modular, Common Element Design • 4 & 5 Meter Payload Fairings • Standard Payload Interfaces 400 500 HLV • Standard Kits for GSO 6 AtlasAtlas VV ConfigurationsConfigurations 401401 411411 421421 431431 501501 511511 521521 531531 541541 551551 HLVHLV 3 3 --- 3 --- --- 3 3 --- 3 --- 3 3 Flights:Flights: 401,401, 401,401, 521,521, 521,521, 431,431, 401,401, 551,551, 411411…….. 7 AtlasAtlas VV LaunchLaunch HistoryHistory AV-001 Perigee Apogee/C3 AV-002 AV-003 AV-005 AV-004 AV-007 AV-010 AV-001 AV-002 AV-003 Aug 21, 2002 May 13, 2003 Jul 17, 2003 1σ2σ3σ AV-005 AV-004 AV-007 Outer Circle Dec 17, 2004 Mar 11, 2005 Aug 12, 2005 Represents 3σ Accuracy Requirement Argument Inclination of Perigee AV-010 AV-008 Jan 19, 2006 20 Jan 2006 EightEight Missions:Missions: 100%100% MissionMission SuccessSuccess 8 AV-010AV-010 // PlutoPluto NewNew HorizonsHorizons LaunchLaunch • January 19, 2006 • NASA Pluto New Horizons Spacecraft • First 551 configuration • First Block 2 Avionics • First Block B SRB • Nuclear certification required • Nominal flight profile • Injection conditions well within 1 sigma – C3, RLA, DLA FastestFastest SatelliteSatellite VehicleVehicle EverEver LaunchedLaunched 9 AV-010AV-010 Pluto:Pluto: ViewView fromfrom thethe flameflame bucketbucket 10 Video – Pluto NH 11 SecondarySecondary PayloadPayload CarriersCarriers –– 2006 2006 12 PreviousPrevious AtlasAtlas SecondarySecondary MissionsMissions 13 AtlasAtlas VV SecondarySecondary PayloadPayload CapabilitiesCapabilities • Internal Payload Carrier (IPC) – Capability to Support Large Secondary Payloads – Flight Scheduled on STP-1 (Dec 2006) – Flight Scheduled on LRO (Oct 2008) – All EELV and Commercial Mission As Available (DMSP, NPOESS, GPS) • eXternal Payload Carrier (XPC) IPC – Supports Suborbital Flight Test Requirements • Others Carriers in Development – Type-C Carrier (TCC) – Aft bulkhead Carrier (ABC) – Upper Stage Payload Carrier (USPC) – Dual Payload Carrier (DPC) ESPA XPC MultipleMultiple AtlasAtlas SecondarySecondary LaunchLaunch OptionsOptions 14 STP-1STP-1 withwith anan IPCIPC •• TheThe NovemberNovember 20062006 STP-1STP-1 MissionMission toto demonstratedemonstrate smallsmall satellitesatellite capabilitycapability 15 GPSGPS IIFIIF withwith anan IPCIPC • Performance Margin > 1500 lbs – IPC stack height shown is 53” – Max 106” IPC stack height possible • Approx Weights of Bare Structure: – ESPA: 350 lbs – C-29: 100-175 lbs depending on wall thickness GPS II Aux SC ESPA 30” Cube Up to 6 53” C-29 16 AtlasAtlas VV IPCIPC StackStack OptionsOptions B1194 PSR B1194 PSR B1194 PSR C-26 C-26 C-24 ESPA D1666 PSR C-24 D1666 PSR C-29 C-29 C-29 Option 1: Baseline Option 2: w/ ESPA Option 3: Stack Separation No Separation SP No Separation SP Separation SP 54” Dia x 60” Ht 54”Diax 60”Ht 48” Dia x 60” Ht B1194 PSR B1194 PSR B1194 PSR ESPA D1666 PSR D1666 PSR D1666 PSR D1666 PSR D1666 PSR C-24 D1666 PSR ESPA C-29 C-29 C-29 Option 4: Stack Sep w/ ESPA Option 5: Stack Separation Option 6: Stack Sep w/ ESPA Separation SP Separation SP Separation SP 48” Dia x 60” Ht 48” Dia x 60” Ht 48”Diax 60”Ht 17 SecondarySecondary CapabilityCapability AddressesAddresses TechnologyTechnology MaturityMaturity • Effective Space Acquisition System Block 1 Block 2 Block 3 requires continuous technology Production development and demonstration – which in turn requires routine, low cost access to space System Block 2 Block3 Block 4 Development • USG manifests 6-8 NSS payloads per year Block 3 Block 4 Block 5 – Excess performance Technology Development available (GPS, DMSP, NPOESS, etc) Secondary – Opportunity for 6 to 12 Payloads secondary payloads per year Science & Block 4 Block 5 Block 6 Technology SecondarySecondary PayloadsPayloads EnableEnable BlockBlock AcquisitionAcquisition 18 AtlasAtlas SecondarySecondary ManifestManifest CapabilityCapability CY2006 CY2007 CY2008 CY2009 CY2010 CY2011 Launch Pad 1st 2nd 1st 2nd 1st 2nd 1st 2nd 1st 2nd 1st 2nd J M M J S N J M M J S N J M M J S N J M M J S N J M M J S N J M M J S N CCAFS GPS IIF-6 GPS IIF-8 GPS IIF-12 401 401 401 NROL-30 SBIRS G-1 AV009/401 401 LC-41 19 Jan Reserved 2 Pluto 501 AV010/551 3 LRO AEHF-1 401 STP-2 531 401 STTR-1 GPS IIF-7 401 401 20 Apr ASTRA 1KR NROL-24 AV008/411 GPS IIF-3 3 Reserved 1 401 401 AV012/501 AEHF-3 531 MUOS-2 541 12 Oct SBIRS G-2 STP-1 WGS F3 401 AV013/401 521 GPS IIF-4 MSL 401 541 MUOS-1 541 NROL-33 * 401 GPS IIF-2 WGS F1 SDO NROL-38 521 401 WGS F4 401 401 521 VAFB 15 Nov NROL-28 DMSP-18 NROL-41 NROL-39 NROL-45 SLC-3E AV006/411 401 501 501 501 * Launch Under Review Secondary Opportunity Secondary Payload Successfully Launched Atlas V Atlas V 3 LEGEND 400 500 19 BusinessBusiness ModelModel forfor EELVEELV SecondarySecondary PayloadsPayloads • Identify specific missions to routinely fly secondary payloads (GPS- IIF, DMSP, etc.) • Define standard interface (volume, weight, LV services, CG, etc.) – Mass simulators to maintain primary spacecraft schedule – Plug and play swap-ability – Technically and programmatically transparent to primary SV • Business Model implementation – USG to direct their SV programs to include secondary payloads – USG to fund the non-recurring secondary mission capability –cost based – Individual secondary payload flights for $1-2M per slot – cost based DisruptiveDisruptive CapabilityCapability forfor SpacecraftSpacecraft DemonstrationDemonstration 20.
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