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Ares V Launch Vehicle National Aeronautics and Space Administration Lunar Program Industry Briefing: Ares V Overview Steve Cook Manager, Ares Projects Office www.nasa.gov Ares Projects Overview ♦ Deliver crew and cargo for missions to International Space Station (ISS), the Moon and beyond ♦ Continuing progress toward design, component testing, and early flight testing ♦ Ares I Crew Launch Vehicle • Carries 6 crew to ISS, 4 to Moon • First flight test scheduled in 2009 • Initial Operational Capability in 2015 ♦ Ares V Cargo Launch Vehicle • Launches Earth Departure Stage (EDS), Altair and Orion to Low Earth Orbit for lunar missions • Largest launch vehicle ever designed • Ongoing concept design work leading into detailed development work starting in 2011 • First flight test planned in 2018 National Aeronautics and Space Administration 2 Ares V Cargo Launch Vehicle Heavy Lift for Science and Exploration ♦ Key transportation system for exploration beyond Low Earth Orbit • Offers unique payload capabilities opening new doors to human exploration on the Moon and beyond • Designed for routine crew and cargo transportation to the Moon − EDS + Altair to LEO − EDS + Altair + Orion to TLI • Considered national asset creating new opportunities for science, national security and space business • Capable of transporting more than 71 metric tons to the Moon • Focal point for design and development located at MSFC with support across the Agency National Aeronautics and Space Administration 3 Building on a Foundation of Proven Technologies Launch Vehicle Comparisons 122 m (400 ft) Crew Altair 91 m Lunar (300 ft) Orion Earth Departure Lander Stage (EDS) (1 J-2X) 253.0 mT (557.7K lbm) LOX/LH2 S-IVB (1 J-2 engine) Upper Stage 108.9 mT (1 J-2X) (240.0K 137.1 mT 61 m LOX/LH (200 ft) (302.2K lbm) 2 LOX/LH 2 S-II (5 J-2 engines) 453.6 mT 5-Segment Core Stage Overall Vehicle Height, m (ft) (1,000.0K lbm) Reusable (6 RS-68 Engines) Solid Rocket 1,587.3 mT LOX/LH2 30 m Booster (3,499.5K lbm) (100 ft) S-IC (RSRB) LOX/LH2 (5 F-1) 2 5.5-Segment 1,769.0 mT RSRBs (3,900.0K lbm) LOX/RP-1 0 Space Shuttle Ares I Ares V Saturn V Height: 56.1 m (184.2 ft) Height: 99.1 m (325.0 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: 25.0 mT (55.1K lbm) to 25.5 mT (56.2K lbm) 71.1 mT (156.7K lbm) to TLI (with Ares I) 44.9 mT (99K kbm) to TLI DAC 2 TR 6 Low Earth Orbit (LEO) to LEO 118.8 mT (262K lbm) to LEO LV 51.00.48 62.8 mT (138.5K lbm) to Direct TLI National Aeronautics and Space Administration ~187.7 mT (413.8K lbm) to LEO 4 Ares V Element Heritage Upper Stage Derived Vehicle Systems J-2X Upper Stage Engine From Delta IV RS-68 Elements from First Stage RSRB (5-Segment RSRB) Ares I Ares V Delta IV 25.5 t (56.2K lbm) to 71.1 t (156.7K lbm) to TLI (with Ares I) Low Earth Orbit (LEO) 63.0 t (138.5K lbm) to Direct TLI 187.7 t (413.8K lbm) to LEO National Aeronautics and Space Administration 7603.5 ESAS to LCCR Major Events National Aeronaut ics and Space Administr ation 7405.177330. Original ESAS CY-06 Budget Detailed Cost Trade of Recommended IDAC 3 Trade Space EDS Diameter Incorporate Ares I Capability Trade to Increase SSME vs RS-68 Design Lessons Option Change from • Lunar Architecture Learned / • 6 Core Engines • Ares I / Ares V • ~$4.25B Life Cycle Cost • 45.0 mT Lander Team 1/2 (LAT) Studies 8.4m to 10m Parameters • 5.5 Segment Savings for • 20.0 mT CEV Commonality • Lunar Architecture PBAN • Ares I : 5 Seg RSRB • 5 Engine Core • No Loiter in LEO • Mission Delta V’s Team 1/2 (LAT) / J2-X instead of • Core Engine / SRB • 8.4m OML increased Studies Air-Start SSME • Increased Commonality Trades to Increase Updated • 5 SSMEs / 2J2S • Ares V: 1 J2-X with Ares I Booster Design Margins • Increase Margins From • Lunar /Mars Capability TLI Only to Earth Systems Benefits • 45.0t Lander • 30-95 Day LEO Loiter • Increase Subsystem through TLI • 20.2t CEV Assessed • Tank Assembly Mass Growth • ~6t Perf. Margin Allowance (MGA) • Loiter Penalties for 30 Tooling • 4 Day LEO Loiter Commonality Day Orbit Quantified • Ares I Common MGAs • HTPB Decision End of FY09 220 Concepts 320 Concepts 730 Concepts 460 Concepts Evaluated Evaluated Evaluated Evaluated 2005 2006 2007 2008 ESAS Ares I ATP Orion ATP Ares I SRR Orion SRR Ares I SDR Ares V MCR Complete National Aeronautics and Space Administration 7603.6 Ares V Elements New LCCR Point-of-Departure (51.0.48) Gross Lift Off Mass: 3,704.5 mT (8,167.1k lbm) Integrated Stack Length: 116.2 m (381.1 ft) Altair Lunar Lander Payload Adapter J–2X Loiter Skirt Payload Solid Rocket Boosters (2) Shroud Interstage • Two recoverable 5.5-segment PBAN-fueled, steel-case boosters (derived from current Ares I First Stage) Earth Departure Stage (EDS) • Option for new design • One Saturn-derived J–2X LOX/LH2 engine (expendable) • 10-m (33-ft) diameter stage • Aluminum-Lithium (Al-Li) tanks • Composite structures, Instrument Unit and Interstage RS–68B • Primary Ares V avionics system Core Stage Engines • Six Delta IV-derived RS–68B (6) LOX/LH2 engines (expendable) • 10-m (33-ft) diameter stage • Composite structures • Aluminum-Lithium (Al-Li) tanks 9/25/08National Aeronautics and Space Administration 7603.7 Ares V Technology Needs ETDP Technology Prioritization Process (TPP) Ares V Technology Priorities 1. Large Composite Manufacturing Nose Cone/Forward Skirt Loaded Motor 2. HTPB Propellant 3. Long Term CFM Ares Value Stream 4. Composite Damage Tolerance/Detection Key Technology Areas 5. EDS State Determination & Abort Composites 6. Composite Joining Technology Cryo Fluid Management 7. Liquid Level Measurement Solids 8. Multi Layer Insulation Automation 9. Leak Detection Liquid Propulsion 10. Non Autoclave Composites Control/Separation 11. SRM Composite Metal Technology 12. Composite Dry Structure Development 13. Composite Damage Failure Detection for Abort 14. Nozzle Sensitivity to Pocketing (High Heat Flux from HTPB) 15. LH2 Tank Micro Cracking Core Stage Aft Skirt Point of Departure Shroud (Biconic) National Aeronautics and Space Administration 7603.8 Ares V Summary Schedule 2009 2010 2011 2012 2013 2014 2015 2016 2017 2018 2019 2020 Ares V FY09 FY10 FY11 FY12 FY13 FY14 FY15 FY16 FY17 FY18 FY19 FY20 SRR Level I/II Milestones 6-10 SRR PDR CDR DCR Altair Milestones (for reference only) Altair 1 Altair 2 Altair 3 Altair 4 ATP PRR SRR SDR PDR CDR DCR Phase 1 Ares V-Y Ares V Project Milestones 6-9 7-11 3-12 12-10 Phase 023-14 12-16 STUDY DEFINITION CoDR DESIGN System Engineering and DEVELOPMENT STUDY OPERATIONS Integration RAC 1 RAC 2 RAC 3 RAC 4 DAC 1 RR PDR CDR Core Stage Core Stage Engine (RS-68B) RR PDR CDR Booster RR PDR CDR Earth Departure Stage RR PDR CDR RR PDR CDR Earth Departure Stage Engine RR PDR Payload Shroud CDR RR PDR Instrument Unit CDR MPTA CDR SRR SDR PDR CS MPTA Systems Testing EDS IGVT National Aeronautics and Space Administration 7603.9 Ares V Profile 51.00.48 Recommended POD (Lunar Sortie) Time Altitude Event EDS Engine Cutoff (sec) (km) Time = 806.0 sec Sub-Orbital Burn Duration = 502.9 sec Liftoff 0.0 0.0 Injected Weight = 187.7 mT Orbital Altitude = 240.8 km circ @ 29.0° Maximum Dynamic Pressure 78.8 14.4 SRB Separation 121.6 36.4 Shroud Separation 295.0 126.9 Core Stage Separation Main Engine Cutoff 303.1 133.3 & EDS Ignition EDS TLI Burn Time = 303.1 sec Orbital Altitude = 185.2 km circ @ 29.0º EDS Ignition 303.1 133.3 Burn Duration = 424.9 sec EDS Engine Cutoff 806.0 243.5 EDS TLI Burn Duration 424.9 TBD LSAM/CEV LSAM/CEV Separation TBD TBD Separation Shroud Separation Time = 295.0 sec SRB Separation Time = 121.6 sec EDS Disposal Liftoff CEV Rendez. & Dock w/EDS Time - Assumed Up to 4 Days Time = +1 sec Orbital Altitude Assumed to Degrade to 185.2 km Thrust-to-Weight Ratio = 1.36 GLOM =3,704.5 mT Launch SRB Core Stage Impact Splashdown National Aeronautics and Space Administration 7603.10 Payload Utilization Ares V as a National Asset ♦ Ares V offers the largest payload capability than all other existing launch vehicles • Over 40% more lift capability than Saturn V • 3-5 times for volume than most other launch systems ♦ These unique capabilities open new worlds and create unmatched opportunities • Human exploration • Science • Space Business ♦ Ares V is actively engaged with external organizations during this early concept phase to ensure its utilization for other missions • National Security • Astronomy and Solar System Science National Aeronautics and Space Administration 7603.11 Our Achievements ♦ Programmatic Milestones • Completed Ares I System Requirements Review (SRR) – Jan 2007 • Awarded contracts for Ares I First Stage, J-2X Engine, Upper Stage and Instrument Unit • Completed Ares I System Definition Review (SDR) – Oct 2007 • Completed Ares V Mission Concept Review (MCR) – Jun 2008 • Completed Constellation Lunar Capability Concept Review (LCCR) – Jun 2008 • Released Ares V Request For Information (RFI) and evaluating responses – Aug 2008 • Completion of Ares I Preliminary Design Review (PDR) – Sep 2008 ♦ Technical Accomplishments • Ares I Drogue Chute Drop Test – July 2008 • Ares I First Stage Separation and Re-entry Wind Tunnel Tests • J-2X Injector and Power Pack Tests • A-3 Test Stand Construction for J-2X Engine at Stennis Space Center • MSFC Dynamic Test Stand 4550 Refurbishment for Ares I and Ares V Integrated Vehicle Ground Vibration Testing • Established Ares V
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