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Ares V and RS-68B Ares V and RS-68B Steve Creech, NASA MSFC Jim Taylor, NASA MSFC Lt. Col. Scott Bellamy, AFSPC Fritz Kuck, Pratt & Whitney Rocketdyne JANNAF Liquid Propulsion Subcommittee (LPS) JANNAF LPS Technical Steering Group RS-68/-68A/-68B Specialist Session 8-12 December 2008 Orlando, Florida ARES V and RS-68B Abstract Ares V is the heavy lift vehicle NASA is designing for 05 06 07 08 09 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25… lunar and other space missions. It has significantly more ExplorationExploration andand ScienceScience LunarLunar RoboticsRobotics MissionsMissions LunarLunar OutpostOutpost BuildupBuildup lift capability than the Saturn V vehicle used for the Research and Technology DevelopmentDevelopment on ISS Apollo missions to the moon. Ares V is powered by two Commercial Orbital Transportation Services for ISS recoverable 5.5 segment solid rocket boosters and six RS-68B engines on the core stage. The upper stage, SpaceSpace ShuttleShuttle OperationsOperations SSPSSP TransitionTransition designated as the Earth Departure Stage, is powered by a Ares I and OrionOrion Development Operations CapabilityCapability Development single J-2X engine. This paper provides an overview of (EVA(EVA Systems,Systems, GroundGround Operations,Operations, MissionMission Operations)Operations) Ares I-X Orion andand Ares I Production andand Operation Test Flight the Ares V vehicle and the RS-68B engine, an upgrade April 2009 to the Pratt & Whitney Rocketdyne RS-68 engine Altair Development developed for the Delta IV vehicle. Ares VV && EarthEarth Departure Stage SurfaceSurface SystemsSystems DevelopmentDevelopment 032408 Constellation Program Figure 2. NASA’s Exploration Roadmap The Constellation Program includes the Ares I & V launch vehicles, the Orion crew exploration vehicle, the Ares V Altair lunar lander and their associated missions. Ares I launches the Orion and its crew, and Ares V launches The Ares V is built upon a foundation of proven the earth departure stage (EDS) and Altair with the technologies from the Space Shuttle, Ares I and Saturn crew’s supplies. The Ares V earth departure stage and V vehicles as shown in Figure 3. The reusable solid the Orion vehicle rendezvous and mate in earth orbit, rocket motors are derived from the Space Shuttle and and the EDS propels the vehicles to the moon or other Ares I boosters. The core stage tank includes destination. The Constellation Program vehicles are technologies from the Space Shuttle program but will be depicted in Figure 1. built to the larger 33 foot diameter used on the Saturn V tanks. The J-2X engine, that powers the earth departure stage, has restart capability and will be a variant of the Ares I upper stage engine that was derived from the J-2 Earth engine that powered the Saturn V S-II and S-IVB stages. Departure Stage Building on a Foundation of Proven Technologies Launch Vehicle Comparisons 122 m (400 ft) Orion Crew Exploration Ares V Crew Ares V Vehicle Altair Cargo Launch Vehicle 91 m Lunar (300 ft) Orion Earth Departure Lander Stage (EDS) (1 J-2X) Altair 253.0 mT (557.7K lbm) LOX/LH2 S-IVB Lunar (1 J-2 engine) Upper Stage 108.9 mT Lander (1 J-2X) Lander (240.0K 137.0 mT 61 m LOX/LH (200 ft) (302K lbm) 2 LOX/LH 2 S-II (5 J-2 engines) 453.6 mT 5-Segment Core Stage Overall Vehicle Height, m m (ft) Height, Vehicle Overall (1,000.0K lbm) Reusable (6 RS-68 Engines) Ares I Solid Rocket 1,587.3 mT LOX/LH2 30 m Booster (3,499.5K lbm) Crew Launch (100 ft) S-IC (RSRB) LOX/LH2 Vehicle (5 F-1) 2 5.5-Segment 1,769.0 mT RSRBs (3,900.0K lbm) LOX/RP-1 Figure 1. Constellation Program Vehicles 0 Space Shuttle Ares I Ares V Saturn V Height: 56.1 m (184.2 ft) Height: 99.1 m (325 ft) Height: 116.2 m (381.1 ft) Height: 110.9 m (364 ft) Gross Liftoff Mass: Gross Liftoff Mass: Gross Liftoff Mass: Gross Liftoff Mass: 2,041.1 mT (4,500.0K lbm) 927.1 mT (2,044.0K lbm) 3,704.5 mT (8,167.1K lbm) 2,948.4 mT (6,500K lbm) Payload Capability: Payload Capability: Payload Capability: Payload Capability: Ares I and Orion are currently in full scale development 25.0 mT (55.1K lbm) to 25.5 mT (56.2K lbm) 44.9 mT (99K kbm) to TLI Low Earth Orbit (LEO) to LEO 71.1 mT (156.7K lbm) to TLI (with Ares I) 118.8 mT (262K lbm) to LEO DAC 2 TR 6 62.8 mT (138.5K lbm) to Direct TLI with first operational flight scheduled for spring of LV 51.00.48 ~187.7 mT (413.8K lbm) to LEO 2014. The Ares I project has completed preliminary Figure 3. Ares V Technical Foundation design (PDR), while the Orion project will conduct PDR in mid 2009. Ares V is currently in systems The versatile, heavy-lift Ares V is a two-stage, vertically architectural definition study phase, and full scale stacked launch vehicle that is capable of delivering development is planned to start in October 2010 with 414,000 pounds (188 metric tons) to low-Earth orbit. test flights beginning in 2018. NASA’s Exploration Working together with the Ares I crew launch vehicle, roadmap is shown in Figure 2. the Ares V can send nearly 157,000 pounds (71 metric tons) to the moon. The Ares V payload capability is 2 approximately 50 percent greater than the Saturn V. of tank size, as well as solid booster and RS-68 engine Payload capabilities to various orbits along with the design and performance options. Figure 6 shows some payload envelop information are shown in Figure 4. of the preliminary study results and opportunities for payload margin. The vehicle design has several specific practical limits and constraints. For example, the height of the door in the Vertical Assembly Building (VAB) at the Kennedy Space Center limits the height of the Ares 21.7 m (71.1 ft) V. Additionally, the diameter of 10 meters is considered 10 m (33 ft) ♦ Payload capabilities a practical limit due to fabrication and shipping • LEO (130 x 130 nmi @ 29 deg) ~150 mT 23.2 m (76.2 ft) capabilities. Also, the standard RSRM segment length • GTO (130 x 19323 nmi @ 29 deg) ~75 mT • GEO (19323 x 19323 @ 0 deg) ~40 mT combined with a structural requirement for the 10 m • GEO (19323 x 19323 @ 0 deg) ~40 mT (33 ft) 116.2 m (381.1 ft) attachment point of the RSRB to be between the core ♦ Payload envelop stage hydrogen and oxygen tanks, and, Michoud • 8.8 m diameter 71.3 m • 8.8 m diameter Assembly Facility building limitations constrain the (233.8 ft) 58.7 m • 9.7 m barrel length (192.6 ft) length of the core stage. • 700 m3 approximate volume Ares V LCCR Trade Space NOTE: These are MEAN numbers March-June 2008 Core Standard Core Opt. Core Length + Common Design Booster + 5 RS-68B Engines 6 RS-68B Engines Features 51.00.39 +5.0 mT 51.00.46 Spacers: 1 Composite Dry Structures Figure 4. Ares V Capabilities for Other Missions 5 Segment for Core Stage, EDS & PBAN 68.6 mT Shroud Steel Case 63.6 mT 60.2 mT Reusable Metallic Cryo Tanks for Core +6.1 mT +6.1 Ares V is composed of several elements as shown in +6.1 mT Stage & EDS 51.00.40 +5.0 mT 51.00.47 Spacers: 1 5 Segment RS-68B Performance: I = 414.2 sec HTPB sp Figure 5. The first stage includes the two recoverable Thrust = 797k lb @ vac Composite Case 69.7 mT 74.7 mT f Expendable 61.5 mT 66.3 mT 5.5-segment PBAN-fueled boosters that are derived J-2X Performance: -3.6 mT -3.6 -2.3 mT -2.3 Isp = 448.0 sec 51.00.41 +3.7 mT 51.00.48 Spacers: 0 from the 4 –segment Shuttle SRB and 5-segment Ares I 5.5 Segment Thrust = 294k lbf @ vac PBAN Steel Case 71.1 mT Shroud Dimensions: first stage boosters designed and manufactured by ATK. 67.4 mT Reusable 63.0 mT Barrel Dia. = 10 m Usable Dia. = 8.8 m The core stage includes six RS-68B engines derived Barrel Length = 9.7 m Initial LCCR Study Reference Alternative New POD from the Pratt & Whitney Rocketdyne RS-68 engine Recommend for New POD ♦ Current Ground Rules and Assumptions 1.5 Launch TLI Capability Cargo TLI Capability • 4-day loiter/29 degree,130nmi insertion/100nmi TLI departure used on the United Launch Alliance Delta IV vehicle. • TLI Payload Goal: 75.1 mT The 71.3 meter long core stage has composite structures − Lander (45.0 mT) + Orion (20.2 mT) + Margin ♦ Note: Performance (light blue) is TLI payload in conjunction with Ares I and includes aluminum-lithium tanks that are 10 meters National Aeronautics and Space Administration 7557_AresV_Overview.1 in diameter. The earth departure stage includes an Figure 6. Ares V Trade Study interstage, loiter skirt, aluminum-lithium tanks, composite structure, instrument unit with the primary One of the early vehicle studies planned for the new 6- Ares V avionics system. Other elements of the Ares V engine baseline is analysis of the base heating. The two include the payload shroud and Altair lunar lander. RSRB and six RS-68B engines with their turbine exhaust ducted above the nozzle exit plane create a significant thermal environment. Various engine layout schemes are being studied as shown in Figures 7 and 8.
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