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Ares V Overview

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Ares V Overview Ares V Overview Phil Sumrall NASA Marshall Space Flight Center Ares Projects Advanced Planning Manager February 26, 2008 Agenda • Ares V Gross TLI Capability Requirements – Crewed Missions – Cargo Missions • Ares V Vehicle Architecture • Ares V Trade Space • Ares V Reference Vehicle Configuration • Ares V Shroud Design • Summary Schedule • Forward Work 2 Ares V Gross TLI Capability Requirement: Crewed Outpost Lander Mission Metric (mT) English (lbm) • Earth to Orbit Derived Performance Requirement Orion 20.2 44,500 – = Lander + L2MR + L3MR Lander (Crew)* 45.9 101,192 – > 45 t (CARD) Level II Margin 4.0 8,818 • TLI Derived Performance Level III Margin 5.0 11,023 Requirement Total TLI Capability 75.1 165,567 – = Lander + Orion + L2MR + Total ETO Capability 54.9 121,034 L3MR *Includes Lander Adapter – > 67 t (CARD) • ETO Mission Destination: 130 nmi, 29 degrees • Loiter Duration 4 days (CARD TBD) • TLI Maneuver Starting Conditions: 100 nmi, 29 degrees • TLI delta-V = 3175 m/s + Gravity Loss 3 Ares V Gross TLI Capability Requirement: Cargo Outpost Lander Mission Metric (mT) English (lbm) • Earth to Orbit Derived Performance Requirement Lander (Cargo)* 54.5 120,152 – = Lander + L2MR + L3MR Level II Margin 4.0 8,818 – > 54.6 t (CARD) Level III Margin 5.0 11,023 • TLI Derived Performance Total TLI Capability 63.5t 139,994 Requirement Total ETO Capability 63.5t 139,994 – = Lander + L2MR + L3MR *Includes Lander Adapter – > 54.6 t (CARD) • ETO Mission Destination: Phasing Orbit • Loiter Duration: None (no loiter capability on EDS) Note: Saturn V TLI Payload Capability was 48.6t (Apollo 17 - CM/SM/ LM/SLA), Ares V Earth-to-TLI requirement exceeds Saturn V Capability by 31% 4 Ares V Vehicle Architecture Stack Integration Altair • 3.4 M kg (7.4M lb) gross liftoff weight Lunar Lander • 110 m (360 ft) in length Payload J–2X Shroud Loiter Skirt Interstage Solid Rocket Boosters (2) • Two recoverable 5-segment PBAN-fueled boosters (derived Earth Departure Stage (EDS) from current Ares I first stage • 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 • Primary Ares V avionics system Core Stage • Five Delta IV-derived RS–68 LOX/LH2 engines (expendable) • 10 m (33-ft) diameter stage RS–68 5 Ares V Trade Space (4-day Loiter, 29° Inclination, 130nmi Insertion, 100nmi TLI Departure) Core Standard Core Opt. Core Length / Booster W/ 5 RS-68 # Core Engines Common Ares V Vehicle Features • Composite dry structures 51.0.39 51.0.46 5 Segment • Core, EDS, and Shroud PBAN 63.6t +5.0t 68.6t • Metallic Cryo tanks (Core & EDS) Steel Case -2.5t +2.5t • RS-68 (108%) Reusable Engines: 6 • 414.2 sec, 797K lbf @ Vac + + Spacers: 1 6 6 • Shroud: 10m diameter, 9.7m barrel . 1 1 length, 8.8m usable diameter 51.0.40 51.0.47 t t 5 Segment HTPB 69.7t +5.0t 74.7t Composite Case +3.6t +8.6t Expendable Engines: 6 LCCR Study Reference LCCR Study Upgrade - - Spacers: 1 3 2 . 6 3 Ares V Spacer Results 51.0.41 t t 51.0.48 5.5 Segment 74.0 PBAN 67.4t +3.7t 71.1t 72.0 Steel Case +1.3t +5.0t 70.0 ) t ( Reusable 68.0 Engines: 6 d 5 Core Engines a o l y 66.0 6 Core Engines Spacers: 0 a p 7 Core Engines I L 64.0 T Current Ground Rules and Assumptions 62.0 – TLI Payload Requirement: 75.1t 60.0 • Lander (45.9t) + Orion (20.2t) + L2 Margin (4t) + L3 Margin (5t) 58.0 0 1 2 Note: L2/L3 Margin (green) is remaining capability above Lander/Adapter Number of Half Segment Spacers Mass. Performance (blue) is TLI Payload in conjunction with Ares I. 6 Ares V Reference Vehicle Configuration (51.0.39 Vehicle) EDS Stage 4 day LEO loiter GLOW 7,440,326 lbf Propellants LOX/LH2 Payload Envelope L x D 25.3 ft x 30.0 ft Shroud Jettison Mass 19,388 lbm Usable Propellant 516,953 lbm 71.1' Propellant Offload 0.0 % Stage liftoff pmf 0.8808 Launch Dry Mass 50,144 lbm Booster (each) TLI Burnout Mass 55,287 lbm Propellants PBAN (262-07 Trace) Suborbital Burn Propellant 310,000 lbm Overboard Propellant 1,390,548 lbm Pre-TLI Jettison Mass 6,895 lbm Stage pmf 0.8628 LEO FPR 7,804 lbm 73.8' Burnout Mass 221,175 lbm # Engines / Type 1 / J-2X # Boosters / Type 2 / 5 Segment SRM Engine Thrust (100%) 294,000 lbf / 238,000 lbf @ Vac Booster Thrust (@ 1.0 sec) 3,571,974 lbf @ Vac Engine Isp (100%) 448.0 sec / 449.0 sec @ Vac Booster Isp (@ 1.0 sec) 272.8 sec @ Vac Mission Power Level 100.0 % / 81.0 % Burn Time 125.9 sec Suborbital Burn Time 472.4 sec 33.0' TLI Burn Time 390.4 sec 360.5' Core Stage Propellants LOX/LH2 Usable Propellant 3,164,794 lbm Propellant Offload 0.0 % Stage pmf 0.9052 Delivery Orbit1.5 Launch TLI Dry Mass 296,952 lbm LEO Delivery130 nmi circular @ 29.0° Burnout Mass 331,411 lbm TLI Payload from 100 nmi140,177 lbm (63.6 t) 215. # Engines / Type 5 / RS-68 CEV Mass 44,500 lbm (20.2 t) 6' Engine Thrust (108%) 702,055 lbf @ SL 797,000 lbf @ Vac LSAM Mass 95,677 lbm (43.4 t) 179.2' Engine Isp (108%) 360.8 sec @ SL 414.2 sec @ Vac Insertion Altitude131.6 nmi Mission Power Level 108.0 % T/W @ Liftoff + 1 sec1.34 Core Burn Time 328.9 sec Max Dynamic Pressure623 psf Max g’s Ascent Burn3.90 g T/W @ SRB Separation1.32 T/W Second Stage0.43 Interstage Core/EDS T/W @ TLI Ignition0.58 Dry Mass 18,672 lbm 7 Summary Schedule 2009 2010 2011 2012 2013 2014 2015 2016 2017 2018 2019 2020 FY09 FY10 FY11 FY12 FY13 FY14 FY15 FY16 FY17 FY18 FY19 FY20 MCR ATP SRR SDR PDR CDR D C R LSAM 1 LSAM 3 Ares V Milestones Ares V-Y LSAM 2 LSAM 4 Design Analysis DAC-1 Requirements DAC-2 Preliminary Design Validation DAC-3 Final Design Validation Ground Vibration Testing ATP Planning/Test Preparation/Buildup MSFC TS 4550 available Facility Mods Ground Vibration Testing (MSFC TS 4550) Model Correlation/Analysis/Teardown GVT DCR Data Drop Core Stage ATP SRR PDR CDR DCR Core Stage Milestones Core Stage Engine (RS-68B) ATP PDR CDR DCR Design / Development Testing MPTA (SSC) LSAM 1 LSAM 3 Engines Fab/Test/Ship Ares V-Y LSAM 2 LSAM 4 Core Stage Fab and Delivery ATP Facility Design F a c i l i t y M o d s C h e c k o u t Michoud Facility Modifications Fab CS GVT Test Article and CS MPTA Ship to GVT (MSFC) SSC B-2 available Facility Mods CS MPTA Testing (SSC B-2) LSAM 1 LSAM 3 Core Stage Fab/Test/Ship Ares V-Y LSAM 2 LSAM 4 Booster ATP Design Empty RSRM to GVT (MSFC) RSRM GVT Test Articles Fab/Test/Ship Inert RSRM to GVT (MSFC) LSAM 1 LSAM 3 Booster Fab/Test/Ship Ares V-Y LSAM 2 LSAM 4 Payload Shroud ATP SRR PDR CDR DCR Design / Development Payload Shroud GVT Test Article Fab/Test/Ship Ship to GVT (MSFC) Payload Shroud Separation/Vibration/Thermal Testing at GRC LSAM 1 LSAM 3 Shroud Fab/Test/Ship Ares V-Y LSAM 2 LSAM 4 Earth Departure Stage ATP Design / Development MSFC TS 4670 available Test Stand Facility Mods EDS MPTA Testing (MSFC TS 4670) ATP Facility Design Facility M o d s Checkout Michoud Facility Modifications ATP Long Lead Ship to MPTA (SSC) Ship to GVT (MSFC) Fabricate EDS GVT Test Article and EDS MPTA LSAM 1 LSAM 3 Earth Departure Stage Fab/Test/Ship Ares V-Y LSAM 2 LSAM 4 EDS Engine (J-2X) ATP Long Lead Ship to EDS Fabricate GVT EDS Engine Simulator & EDS Engine MPTA LSAM 1 LSAM 3 Earth Departure Stage Engine Fab/Test/Ship Note: Al Design Rev iew dates are Board dates Ares V-Y LSAM 2 LSAM 4 8 Forward Work • Support to LCCR architecture and requirements analysis - June LCCR • Integrated Vehicle and Core Stage detailed study - Feb- July • EDS detailed trade studies and design concepts - July 07-Oct 08 • Wind tunnel testing - April • Ares I avionics extensibility assessment to Ares V Earth Departure Stage Instrument Unit - Jan-Oct. 9.
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