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Lunar Capability Concept Review (LCCR)

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Lunar Capability Concept Review (LCCR) Lunar Capability Concept Review (LCCR) Transportation Systems Only June 18 – 20, 2008 Report to the PSS LCCR Agenda Date Time Topic Presenter June 18 8:00 – 8:15 am Welcome / Introduction Hanley / Muirhead 8:15 – 9:00 am 01: LCCR Overview Knotts 9:00 – 9:15 am 02: Lunar Requirements Summary Knotts 9:15 – 10:00 am 03: CxAT_Lunar Study Process Joosten 10:00 – 11:00 am 04: LSS Concepts Culbert 11:00 – 11:30 am Lunch 11:30 am – 2:00 pm 05: Altair System Hansen / Connolly 2:00 – 4:30 pm 06: Ares V System Creech 4:30 – 5:30 pm 07: Ground Operations Quinn June 19 8:00 – 8:30 pm 08: Ares V and Altair Margins Strategies and Basis Muirhead 8:30 – 10:30 am 09: Integrated Performance and Mission Design Martinez 10:30 am – 12:30 pm 10: Strategic Analysis Falker 12:30 – 1:00 pm Lunch 1:00 – 3:00 pm 11: HLR POD Architecture Drake 3:00 – 5:00 pm 12: LCCR Product Summary and Forward Plan Parkinson 5:00 – 5:30 pm 13: Architecture Summary and Next Steps Muirhead June 20 8:00 – 9:00 am 14: MCR Wrap-up – Altair Hansen / Graham 9:00 – 10:00 am 15: MCR Wrap-up – Ares V Creech 10:00 – 10:30 am 16: LCCR Success Criteria Review Knotts 10:30 – 11:00 am Summary / Conclusions Hanley 11:00 – 11:30 am Board Discussion June 18 - 20, 2008 Section 00: LCCR Agenda Page 2 Components of Program Constellation Earth Departure Stage Crew Exploration Vehicle Heavy Lift Launch Vehicle Lunar Crew Launch Lander Vehicle June 18 - 20, 2008 Section 05: Altair System Page 3 Typical Lunar Reference Mission MOON Vehicles are not to scale. Ascent Stage 100 km Lander Performs LOI Expended Low Lunar Orbit Earth Departure Stage Expended Service Low Module Earth Expended Orbit CEV Direct Entry EDS, Lander Land Landing EARTH June 18 - 20, 2008 Section 05: Altair System Page 4 Background VSE Global VSE Exploration Strategy ESASESAS LAT1LAT1 LAT2LAT2 CxAT Lunar June 18 - 20, 2008 Section 03: CxAT_Lunar Study Process Page 5 LCCR Scope ♦ LCCR will define a Point of Departure (POD)* transportation architecture for the CxP Lunar Capability including capabilities to: • Deliver and return crew to the surface of the moon for short durations, i.e. Human Lunar Return (HLR) • Enable establishment of a lunar outpost ♦ This review focuses on the conceptual designs and key driving requirements for Ares V and Altair (crewed and cargo) ♦ This review assumes the capabilities of Ares I and Orion for the lunar missions ♦ This review will show how the POD transportation architecture, including EVA and Ground Ops, supports a range of mission campaigns and possible surface architecture solutions • Specific Lunar Surface Systems definition is not part of this review *This is a POD transportation architecture and NOT the final baseline June 18 - 20, 2008 Section 01: LCCR Overview Page 6 CxP L2 Lunar Design Reference Missions • DRM 1 : Lunar Sortie Crew DRM − This mission lands anywhere on the Moon, uses only on-board consumables, and leaves within ~1 week. This mission enables exploration of high-interest science sites, scouting of Lunar Outpost locations, technology development objectives, and the capability to perform EVAs. • DRM 2 : Uncrewed Cargo Lander DRM − Used to support an Outpost, help build one, or merely preposition assets for a subsequent Sortie Lander, this uncrewed mission lands anywhere on the Moon, and has enough resources to sustain itself until a component of the Lunar Surface Systems takes over. • DRM 3 : Visiting Lunar Outpost Expedition DRM − Analogous to an assembly flight to ISS, this mission lands at the site of a complete Outpost or one under construction, and allows crewmembers to extend their stay by using assets of the Outpost rather than only what is carried onboard their Lander. • DRM 4 : Resident Lunar Outpost Expedition DRM − Realizing one of the goals of US Space Policy, this mission allows a sustained human presence on the surface of the Moon, since it follows a single crew of four to the surface, transitions them to a habitat at an Outpost, and gets them back to Earth after transitioning over to a replacement crew. • DRM 5 : Outpost Remote DRM − This mission is separated in function from the other DRMs by focusing only on those Lunar Surface Systems which need to operate without human intervention, either because humans are not present to operate them, or the task is more easily performed in an autonomous or automatic manner. June 18 - 20, 2008 Section 02: LCCR Requirements Summary Page 7 Building on a Foundation of Proven Technologies - Launch Vehicle Comparisons - 122 m (400 ft) PPBE Submit (51.0.39) Crew Altair 91 m Lunar (300 ft) Orion Earth Departure Lander Stage (EDS) (1 J–2X) 234.5 t (517.0k lbm) LOX/LH S-IVB 2 (1 J–2 engine) Upper Stage 108.9 t (1 J–2X) (240.0k lbm) 61 m 137.1 t (200 ft) LOX/LH2 (302.2k lbm) LOX/LH 2 S-II (5 J–2 engines) Core Stage 453.6 t 5-Segment Overall Vehicle Height, m (ft) (5 RS–68B Engines) (1,000.0k lb ) Reusable m 1,435.5 t LOX/LH Solid Rocket (3,164.8k lb ) 2 30 m Booster m (100 ft) LOX/LH (RSRB) 2 S-IC (5 F–1) 2 5-Segment 1,769.0 t RSRBs (3,900.0k lbm) LOX/RP-1 0 Space Shuttle Ares I Ares V Saturn V Height: 56 m (184 ft) Height: 99 m (325 ft) Height: 110 m (361 ft) Height: 111 m (364 ft) Gross Liftoff Mass: Gross Liftoff Mass: Gross Liftoff Mass: Gross Liftoff Mass: 3,374.9 t (7,440.3k lbm) 2,041.2 t (4,500.0k lbm) 927.1 t (2,043.9k lbm) 2,948.4 t (6,500.0k lbm) Payload Capability: Payload Capability: Payload Capability: Payload Capability: 63.6 t (140.2k lb ) to TLI (with Ares I) 25.0 t (55.1k lbm) 25.6 t (56.5k lbm) m 44.9 t (99.0k lbm) to TLI 55.6 t (122.6k lb ) to Direct TLI to Low Earth Orbit (LEO) to LEO m 118.8 t (262.0k lbm) to LEO DAC 2 TR 5 143.4 t (316.1k lbm) to LEO June 18 - 20, 2008 Section 06: Ares V System Page 8 Ares V Trade Space Common Design Features Core Standard Core Opt. Core Length / Booster W/ 5 RS-68 6 Core Engines Composite Dry Structures for Core Stage, EDS & 51.0.39 +5.0 t 51.0.46 Spacers: 1 Shroud 5 Segment PBAN Metallic Cryo Tanks for Core Steel Case Stage & EDS Reusable 63.6 t 68.6 t +6.1 t t +6.1 +6.1 t t +6.1 RS-68B Performance: 51.0.40 +5.0 t 51.0.47 Spacers: 1 Isp = 414.2 sec 5 Segment Thrust = 797k lbf @ vac HTPB Composite Case J-2X Performance: Expendable 69.7 t 74.7 t Isp = 448.0 sec -2.3 t t -2.3 -3.6 t t -3.6 Thrust = 294k lbf @ vac 51.0.41 +3.7 t 51.0.48 Spacers: 0 5.5 Segment Shroud Dimensions: PBAN Barrel Dia. = 10 m Steel Case Usable Dia. = 8.8 m Reusable 67.4 t 71.1 t Barrel Length = 9.7 m LCCR Initial Reference 1.5 Launch TLI Capability June 18 - 20, 2008 Section 03: CxAT_Lunar Study Process Page 9 Recommendations ♦ Approach • Applied Margins/Reserves Methodology to Altair & Ares V (net loss of architecture “performance”) • Developed higher fidelity mission analysis techniques (net gain of architecture “performance") ♦ Result • Lunar Architecture still requires ~12% additional performance Higher performance Ares V Cargo • Optimized options required Crew • Altair prop loading and Optimized Altair Wet Mass loiter requirements Delta-V determined Altair Wet Mass Post-LOI Loiter Time June 18 - 20, 2008 Section 03: CxAT_Lunar Study Process Page 10 Recommended New Point of Departure - Vehicle 51.0.48 - ♦ Vehicle 51.0.48 recommended • 6 Engine Core, 5.5 Segment PBAN Steel Case 21.7 m 10 m Booster • Provides Architecture Closure with Margin 23.2 m ♦ Recommend Maintaining Vehicle 51.0.47 with Composite HTPB Booster as Ares V Option • Final Decision on Ares V Booster at Constellation Lunar SRR (2010) 10 m 116.2 m • Additional Performance Capability if needed for Margin or requirements • Allows for competitive acquisition environment for 71.3 m booster 58.7 m ♦ Near Term Plan to Maintain Booster Options • Fund key technology areas: composite cases, HTPB propellant characterization • Competitive Phase 1 Industry Studies NOTE: These are MEAN numbers June 18 - 20, 2008 Section 06: Ares V System Page 11 Summary ♦ Ares V Initial 2008 Capability (51.0.39) exceeds Saturn Capability by ~30% ♦ Ares V LCCR analysis focused on meeting lunar requirements and developing margin ♦ Ares V is sensitive to Loiter, Attitude, Power, and Altitude requirements in addition to payload performance ♦ Recommended new POD Ares V can meet current HLR requirements with ~6 t of Margin • Additional budget required (~$1.7BRY) for the 5.5 Segment PBAN Booster and 6 Engine Core • Plan to maintain new composite HTPB booster as an option ♦ Additional analysis required to determine Ares V PLOM and PLOC contributions for CARD recommendations June 18 - 20, 2008 Section 06: Ares V System Page 12 Altair Lunar Lander ♦ 4 crew to and from the surface • Seven days on the surface • Lunar outpost crew rotation ♦ Global access capability ♦ Anytime return to Earth ♦ Capability to land 14 to 17 metric tons of dedicated cargo ♦ Airlock for surface activities ♦ Descent stage: • Liquid oxygen / liquid hydrogen propulsion ♦ Ascent stage: • Hypergolic Propellants or Liquid oxygen/methane June 18 - 20, 2008 Section 05: Altair System Page 13 Configuration Variants Sortie Variant Outpost Variant 45,000 kg 45,000 kg Descent Module Descent Module Ascent Module Ascent Module Airlock Avionics Power Mass Available for Payload Structures and Mechanisms Manager's Reserve Propulsion Thermal Control Life Support Cargo Variant Other 53,600 kg Non-Propellant Fluids Descent Module Cargo on Upper Deck Propellant Sortie Mission Lander June 18 - 20, 2008 Section 05: Altair System Page 14 Design Approach ♦ Project examined the multitude of concepts developed in the post-ESAS era, took lessons learned and began to develop a real design.
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