DOCSLIB.ORG

Ares V Overview ESMD Technology Exchange Conference

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
Ares V Overview ESMD Technology Exchange Conference National Aeronautics and Space Administration AArreess VV OOvveerrvviieeww EESSMMDD TTeecchhnnoollooggyy EExxcchhaannggee CCoonnffeerreennccee November 2007 www.nasa.gov Ares Projects Office Phil Sumrall Contents ! Vehicle & Requirements Overview ! Value Streaming Process ! Technology Challenges ! Apollo Technology Development ! Conclusions National Aeronautics and Space Administration 7368.2 National Aeronautics and Space Administration VVeehhiiccllee && RReeqquuiirreemmeennttss OOvveerrvviieeww www.nasa.gov Reference Ares V Overview Ares V (CaLV) Payload Fairing Earth Departure Stage (EDS) Core Stage (CS) Reusable Solid Rocket Booster (RSRB) National Aeronautics and Space Administration 7368.4 Ares V Ascent Profile EDS Engine Cutoff Core Stage Time = 767.2 sec 5 x RS-68 Sub-Orbital Burn Duration = 441.9 sec Injected Weight = 359,287 lbm 414.2 sec. Isp, 106.0% Power Lead Shroud Separation Orbital Altitude = 120 nmi circ @ 28.5° 33.0 ft (10.0 m) Diameter Time = 335.5 sec Altitude = 422.7 kft EDS Heating Rate = 0.1 BTU/ft!-sec 1 x J2X EDS TLI Burn 448.0 sec. Isp,294 lbf Thrust EDS Ignition Orbital Altitude = 100 nmi circ @ 28.5 Time = 325.3 sec Burn Duration = 309.0 sec 27.5 ft (10.0 m) Diameter Altitude = 400.0 kft Mach = 12.49 Main Engine Cutoff Lunar Time = 325.3 sec Maximum Dynamic Pressure Lander/CEV Altitude = 400.0 kft Time = 79.5 sec Separation Altitude = 45.8 kft Mach = 12.49 Mach = 1.69 Dynamic Pressure = 637 psf SRB Separation Time = 126.6 sec Altitude = 125.0 kft Mach = 3.87 Dynamic Pressure = 85 psf EDS Disposal Core Separation Time = 325.3 sec CEV Rendez. & Dock w/EDS Liftoff Time - Assumed Up to 14 Days Time = +1 sec Orbital Altitude Assumed to Degrade to 100 nmi Thrust-to-Weight = 1.36 Launch SRB GLOW = 7,326,376 lbm Splashdown National Aeronautics and Space Administration 7368.5 Ares V Driving Requirements from CARD CARD Req’t Requirement Rationale The CaLV shall utilize twin shuttle-derived 5-segment !Draws Performance Constraints around Booster SRBs along with a core stage that employs 5 modified Selection and Core Stage Design CA0391-HQ RS-68 engines for first stage propulsion. !Boosters and Core Stage Provide ~70% of Detla V for LEO Insertion The CaLV EDS shall deliver at least 66,939 (TBR-001- !Defines TLI Payload most strenuous performance 076) kg (147,266 lbm) from Earth Rendezvous Orbit parameter CA0847-PO (ERO) to the start of the Trans-Lunar Coast (TLC) for !TLI Payload Sizes EDS crewed lunar missions. The LSAM shall have a Control Mass of 45,000 (TBR- !Defines LEO Payload for Crew Mission CA0836-PO 001-075) kg (99,180 lbm) at the time of launch for Lunar !Contribute ~2/3 Mass for TLI Payload Sortie and Lunar Outpost crew missions !TLI Payload Sizes EDS The CEV shall have a Control Mass of 20,185 (TBR-001- !Contribute ~1/3 Mass for TLI Payload CA4139-PO 159) kg (44,500 lbm) at the time of CaLV rendezvous. !TLI Payload Sizes EDS The CaLV EDS shall provide a minimum translational !Defines Delta V thus propellant Needed for Delta V CA0051-PO delta-V of 3,150 (TBR-001-258) m/s (10,335 f/s) for the !TLI Delta V Sizes EDS TLI for crewed lunar missions. The CaLV EDS shall meet its requirements after !Defines Propellant Reserves for EDS Stage CA0850-PO loitering in low Earth orbit (LEO) at least (TBD-001-975) !Major Factor in subsystem Selection and Design for days after orbit insertion for crewed lunar missions. EDS The CaLV shall deliver at least 125,000 (TBR-001-220) !Defines Mars Mission Max Payload per launch CA0282-PO kg (275,578 lbm) to a (TBD-001-072) Earth orbit for Mars !Orbit and Payload size the Ares V exploration missions. The CaLV shall launch cargo into a (TBD-001-565) Earth Further defines performance capability of Ares V CA3215-PO ! orbit for Mars missions. All Missions Lunar Requirements Mars Requirements National Aeronautics and Space Administration 7368.6 Performance Comparison ESAS CaLV to Ares V Current Reference ! Original ESAS Capability • 46.0 mt Allowable Lander Mass • 20.0 mt CEV Mass • No Loiter in LEO • TLI total "v = 10,236 ft/sec • 7.4 mt TLI performance reserve • 73.4 mt CaLV gross payload at TLI capability ! Concept refinement to reduce cost and maximize commonality between Ares I and Ares V • Core Stage " SSME derived to RS-68 • SSME Isp = 452.1 sec • RS-68 Isp = 414.7 sec " 27.5 ft. to 33 ft. diameter • RSRB " ESAS RSRB used HTPB, MEOP = 1066 psi, thrust trace optimized for CaLV " Current RSRB uses PBAN, MEOP = 1016 psi, thrust trace optimized for Ares I (53-06) • EDS " 2 J-2S+ (451.5 sec) engines to 1 J-2X engine (448 sec) • Other concept and analysis maturation • 73.1 mt CaLV gross payload at TLI capability • CxCB approval May 2006 ! CARD Requirements and Groundrules Changes- Current Baseline Reference • 14 Day Loiter Requirement Assumed (CARD TBD) • TLI total "v = 10,417 ft/sec • FPR 2.4 mt propellant (400 ft/sec) • Parking Orbit change (160 to 120 nmi) • 64.6 mt CaLV gross payload at TLI capability National Aeronautics and Space Administration 7368.7 5 RS-68 Core, 5 Seg. SRB, 1 J-2X EDS 1.5 Launch TLI – 14 Day Loiter Vehicle Concept Characteristics EDS Stage 14 day Loiter Propellants LOX/LH2 Usable Propellant 492,753 lbm GLOW 7,326,376 lbf Propellant Offload 0.0 % 72.2' Payload Envelope L x D 33.0 ft x 24.5 ft Stage pmf 0.8853 27.5' Shroud Jettison Mass 12,868 lbm Dry Mass 47,503 lbm Burnout Mass 48,735 lbm Booster (each) Suborbital Burn Mass 290,000 lbm Propellants PBAN (166-06 Trace) Pre-TLI Overboard Mass 9,757 lbm Overboard Propellant 1,380,873 lbm FPR 5,319 lbm Stage pmf 0.8558 # Engines / Type 1 / J-2X Burnout Mass 232,608 lbm Engine Thrust (100%) 294,000 lbf @ Vac 76.4' # Boosters / Type 2 / 5 Segment SRM Engine Isp (100%) 448.0 sec @ Vac Booster Thrust (@ 0.7 sec) 3,510,791 lbf @ Vac Mission Power Level 100.0 % Booster Isp (@ 0.7 sec) 267.4 sec @ Vac Stage Burn Time 751.7 sec Burn Time 126.6 sec 33.0' Delivery Orbit 1.5 Launch TLI Core Stage LEO Delivery 120 nmi circular @ 28.5° 361.9' Propellants LOX/LH2 TLI Payload from 100 nmi 142,543 lbm 64.6 MT* Usable Propellant 3,078,410 lbm Performance Reserve 8,913 lbm 4.0 MT Propellant Offload 0.0 % CEV Payload Mass 44,500 lbm 20.2 MT Stage pmf 0.9017 LSAM Payload Mass 89,130 lbm 40.4 MT Dry Mass 301,883 lbm Insertion Altitude 122.0 nmi Burnout Mass 335,684 lbm T/W @ Liftoff 1.36 # Engines / Type 5 / RS-68 Max Dynamic Pressure 637 psf 213.3' Engine Thrust (106%) 688,693 lbf @ SL 784,000 lbf @ Vac Max g’s Ascent Burn 3.86 g Engine Isp (106%) 360.8 sec @ SL 414.2 sec @ Vac T/W @ Booster Separation 1.35 176.7' Mission Power Level 106.0 % T/W Second Stage 0.44 Core Burn Time 325.3 sec T/W @ TLI Ignition 0.75 Delivery Orbit Interstage Core/EDS LEO Payload @ 120 nmi 283,913 lbm 128.8 MT Dry Mass 17,847 lbm Single Launch Lunar Direct 119,521 lbm 54.2 MT * LEO delivery orbit is 120 nmi circ @ 28.5°, assumes orbital decay to 100 nmi during 14 day loiter for CEV rendezvous and dock prior to TLI burn National Aeronautics and Space Administration 7368.8 Ongoing Requirements’ Trade Studies ! Teams are continuing to assess the requirements, balancing the Lunar Lander trade space with the Areas V trade space. • Continual assessment will occur through SRRs • Changes in diameters are being assessed ! Ares V capabilities will adjust with some of the Ares I design refinements • Commonality of some propulsion components ! Trade study to assess Ares I Launch Before Areas V • Possible reduction of loiter time from 14 days to 4 National Aeronautics and Space Administration 7368.9 National Aeronautics and Space Administration VVaalluuee SSttrreeaammiinngg PPrroocceessss www.nasa.gov Ares Capabilities Value Stream ! Abbreviated process with 2 objectives 1. Identify development needs not met with current capabilities 2. Formulate capability/technology development to meet defined capabilities ! Two phases to the process ! Phase 1: Identify development needs not met with current capabilities • Input from system designers, chief engineers, lead system engineers, etc. • Simple survey questions to identify needs " From your point of view describe the key technical challenges in designing to meet your requirements. If we could overcome the challenges what capability/technology would allow us to significantly improve margins or push the requirement further? • Examples • Mass of subsystem • Reliability of subsystem • Number of maintenance items • Thermal capability • Specific material properties " Can you identify any worthwhile technologies that could address your technical challenges? ! Input evaluated and prioritized by a Technology Review Panel ! Phase 2: Formulate Technology Projects • Align Technology development with the specific design team needs National Aeronautics and Space Administration 7368.11 APO Technology Priority Groups ! Composites ! Cryogenic Fluid Management ! Solids ! Automation ! Liquid Propulsion ! Control/Separation National Aeronautics and Space Administration 7368.12 Ares Project Office Major Prioritized Technology Needs 1. Large Composite Manufacturing 2. HTPB Propellant 3. Long-term Cryogenic Storage 4. Composite damage tolerance/detection 5. EDS state determination/abort 5. Composite joining technology 7. Liquid Level Measurement 8. Multi-layer Insulation 9. Leak detection 10.Non autoclave composites 10.SRM composite metal technology 12.Develop composite dry structures 13.Composite damage failure detection for abort and damage identification 14.Composite Nozzle NDE 15.Nozzle sensitivity to pocketing/ ply lifting using HTPB with higher heat flux 16.TVC architecture development to minimize operations (EHA Ares I upgrade)
Load more

Recommended publications
  • The New Vision for Space Exploration
    Constellation The New Vision for Space Exploration Dale Thomas NASA Constellation Program October 2008 The Constellation Program was born from the Constellation’sNASA Authorization Beginnings Act of 2005 which stated…. The Administrator shall establish a program to develop a sustained human presence on the moon, including a robust precursor program to promote exploration, science, commerce and U.S. preeminence in space, and as a stepping stone to future exploration of Mars and other destinations. CONSTELLATION PROJECTS Initial Capability Lunar Capability Orion Altair Ares I Ares V Mission Operations EVA Ground Operations Lunar Surface EVA EXPLORATION ROADMAP 0506 07 08 09 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 LunarLunar OutpostOutpost BuildupBuildup ExplorationExploration andand ScienceScience LunarLunar RoboticsRobotics MissionsMissions CommercialCommercial OrbitalOrbital Transportation ServicesServices forfor ISSISS AresAres II andand OrionOrion DevelopmentDevelopment AltairAltair Lunar LanderLander Development AresAres VV and EarthEarth DepartureDeparture Stage SurfaceSurface SystemsSystems DevelopmentDevelopment ORION: NEXT GENERATION PILOTED SPACECRAFT Human access to Low Earth Orbit … … to the Moon and Mars ORION PROJECT: CREW EXPLORATION VEHICLE Orion will support both space station and moon missions Launch Abort System Orion will support both space stationDesigned and moonto operate missions for up to 210 days in Earth or lunar Designedorbit to operate for up to 210 days in Earth or lunar orbit Designed for lunar
    [Show full text]
  • Annual Report
    The 2008 Annual Report of the International Space Exploration Coordination Group Released March 2009 International Space Exploration Coordination Group (ISECG) – Annual Report:2008 THIS PAGE INTENTIONALLY BLANK 1 International Space Exploration Coordination Group (ISECG) – Annual Report:2008 CONTENTS Introduction …………………………………………………………………………… 4 Part 1: The Role of the ISECG 1.1 Overview …………………………………………………………………………. 6 1.2 Working Groups of the ISECG …………………………………………………… 7 1.2.1 Enhancement of Public Engagement …………………………………………… 7 1.2.2 Establishment of Relationships with Existing International Working Groups …. 7 1.2.3 The International Space Exploration Coordination Tool (INTERSECT) ……. 8 1.2.4 The Space Exploration Interface Standards Working Group (ISWG) ………….. 8 1.2.5 Mapping the Space Exploration Journey ………………………………………... 8 Part 2: Current and Near-Term Activities of ISECG Members 2.1 Low Earth Orbit (LEO) …………………………………………………………… 10 2.1.1 The International Space Station (ISS) …………………………………………… 10 2.1.2 Emerging Government Capabilities …………………………………………….. 10 2.1.3 Emerging Commercial Providers ……………………………………………….. 11 2.2 Beyond LEO – The Moon and Mars ……………………………………………….. 11 2.2.1 Moon ……………………………………………………………………………… 11 2.2.2 Mars ………………………………………………………………………………. 12 Part 3: Progress in 2008 towards Opportunities for Integrated and Collaborative Space Exploration 3.1 Robotic Network Science – The International Lunar Network ……………………… 16 3.2 Joint Development for Robotic Exploration – Mars Sample Return ………………………… 17 3.3 Collaborative
    [Show full text]
  • FY10 Agency Mission Planning Model Acronyms
    Version 6-11-09 Mission Data Sources Science Mission Directorate (SMD) submit; 5-4-09 Exploration Systems Mission Directorate (ESMD) submit; 6-11-09 Space Operations Mission Directorate (SOMD) submit; 5-27-09 Aeronautics Research Mission Directorate (ARMD) response; 5-28-09 Mission Acronyms & Definitions Mission Directorate Altair-x Lunar descent stage aka: LSAM = Lunar Surface Access Module (x-mission #) ESMD Ares 1 Crew Launch Vehicle (aka CLV) ESMD Ares V Cargo Launch Vehicle (aka CaLV) ESMD Astro-H SXS Instrument (Explorer Program Mission of Opportunity) [JAXA launch] SMD X-Air Estimated number of Aircraft Earth Science Flights SMD X-Bal Estimated number of Scientific Balloon Flights SMD BARREL Balloon Array for RBSP Relativistic Electron Losses (Two balloon campaigns of 20 flights each) SMD CaLV Cargo Launch Vehicle (aka CaLV) ESMD Chndraayn1 Discovery MoO instrument to be flown on Indian satellite Chandraayan [ELV launch] SMD CLARREO Climate Absolute Radiance and Reflectivity Observatory (see ESDS-x below) SMD CLV Crew Launch Vehicle (aka Ares I) ESMD COR-Lx Cosmic Origins Program Large class mission (x-mission #) (Flagship missions to be defined by Decadal Survey) SMD COR-Mx Cosmic Origins Program Medium class mission (x-mission #) SMD dB decibels ARMD DESDynl Deformation, Ecosystem Structure and Dynamics of Ice (see ESDS-x below) SMD Disc-xx Discovery Mission (xx- mission #) SMD ESDS-x Earth Science Decadal Survey Mission (x- mission #) Likely CLARREO and DESDynI first, order TBD SMD EX-xx Explorer mission (class undefined: Could
    [Show full text]
  • Ares V Cargo Launch Vehicle
    National Aeronautics and Space Administration Constellation Program: America’s Fleet of Next-Generation Launch Vehicles The Ares V Cargo Launch Vehicle Planning and early design are under way for hard- NASA’s Constellation Program to carry human ware, propulsion systems and associated techno- explorers back to the moon, and then onward to logies for NASA’s Ares V cargo launch vehicle — the Mars and other destinations in the solar system. “heavy lifter” of America’s next-generation space fleet. The Ares V effort includes multiple hardware and Ares V will serve as NASA’s primary vessel for safe, propulsion element teams at NASA centers and facts reliable delivery of large-scale hardware to space — contractor organizations around the nation, and is from the lunar landing craft and materials for estab- led by the Ares Projects Office at NASA’s Marshall lishing a moon base, to food, fresh water and other Space Flight Center in Huntsville, Ala. These teams staples needed to extend a human presence beyond rely on nearly a half century of NASA spaceflight Earth orbit. experience and aerospace technology advances. Together, they are developing new vehicle hard- Under the goals of NASA’s exploration mission, ware and flight systems and matur ing technologies Ares V is a vital part of the cost-effective space evolved from powerful, proven Saturn rocket and transportation infrastructure being developed by space shuttle propulsion elements and knowledge. NASA Concept image of Ares V in Earth orbit. (NASA MSFC) The versatile, heavy-lifting Ares V is a two-stage, vertically- stacked launch vehicle. It can carry nearly 414,000 pounds (188 metric tons) to low-Earth orbit.
    [Show full text]
  • NASA Launch Services Manifest
    Launch Options - Future Options • Constellation Architecture • Commercial Alternatives – SpaceX – Orbital Sciences • EELV Options • DIRECT • Side-Mount Shuttle Derived • Space (or “Senate”) Launch System • Recent Developments © 2012 David L. Akin - All rights reserved http://spacecraft.ssl.umd.edu U N I V E R S I T Y O F U.S. Future Launch Options MARYLAND 1 ENAE 791 - Launch and Entry Vehicle Design Attribution • Slides shown are from the public record of the deliberations of the Augustine Commission (2009) • Full presentation packages available at http:// www.nasa.gov/ofces/hsf/meetings/index.html U N I V E R S I T Y O F U.S. Future Launch Options MARYLAND 2 ENAE 791 - Launch and Entry Vehicle Design Review of Human Spaceflight Plans Constellation Overview June 17, 2009 Doug Cooke www.nasa.gov Jeff Hanley Constellation Architecture Earth Departure Stage Altair Lunar Lander Orion Ares I Crew Exploration Crew Launch Vehicle Vehicle Ares V Cargo Launch Vehicle Constellation is an Integrated Architecture National Aeronautics and Space Administration 2 Key Exploration Objectives 1. Replace Space Shuttle capability, with Shuttle retirement in 2010 2. To ensure sustainability, development and operations costs must be minimized 3. Develop systems to serve as building blocks for human exploration of the solar system using the Moon as a test bed 4. Design future human spaceflight systems to be significantly safer than heritage systems 5. Provide crew transport to ISS by 2015, to the lunar surface for extended durations by 2020, and to Mars by TBD 6. Separate crew from cargo delivery to orbit 7. Maintain and grow existing national aerospace supplier base 8.
    [Show full text]
  • ASTROPHYSICS from the MOON Jack Burns
    ASTROPHYSICS FROM THE MOON Jack Burns LUNAR Lead Scientists: Center for Astrophysics & Space Astronomy J. Burns, Principal Investigator University of Colorado at Boulder E. Hallman, U. Colorado J. Lazio, NRL J. Hewitt, MIT C. Carilli, NRAO T. Murphy, UCSD D. Currie, U. Maryland S. Merkowitz, GSFC J. Kasper, CfA R. MacDowall, GSFC and D. Duncan (E/PO) J. Darling J. Stocke JILA Astrophysics Lunch Seminar September 26, 2008 National Space Exploration Policy, Authorized by Congress • Complete the International Space Station • Safely fly the Space Shuttle until 2010 • Develop and fly the Crew Exploration Vehicle (Orion) no later than 2014 • Return to the Moon no later than 2020 • Extend human presence across the solar system and beyond • Implement a sustained and affordable human and robotic program • Develop supporting innovative technologies, knowledge, and infrastructures • Promote international and commercial participation in exploration NASA Authorization Act of 2005 TheThe AdministratorAdministrator shallshall establishestablish aa programprogram toto developdevelop aa sustainedsustained humanhuman presencepresence onon thethe Moon,Moon, includingincluding aa robustrobust precursorprecursor programprogram toto promotepromote exploration,exploration, science,science, commercecommerce andand U.S.U.S. preeminencepreeminence inin space,space, andand asas aa steppingstepping stonestone toto futurefuture explorationexploration ofof MarsMars andand otherother destinations.destinations. ComponentsComponents of the Constellation of Program Program Constellation EarthEarth DepartureDeparture OrionOrion -- StageStage CrewCrew ExplorationExploration VehicleVehicle AresAres VV -- HeavyHeavy LiftLift LaunchLaunch VehicleVehicle LunarLunar LanderLander AresAres II -- CrewCrew LaunchLaunch VehicleVehicle Exploring the Cosmos From the Moon Comments from NRC Study (2007) • “Extraordinary radio-quiet of lunar farside” would be a “powerful tool to investigate the Dark Ages of the Universe … in highly redshifted signals from neutral hydrogen”.
    [Show full text]
  • Ares V Cargo Launch Vehicle
    National Aeronautics and Space Administration Constellation Program: America's Fleet of Next-Generation Launch Vehicles The Ares V Cargo Launch Vehicle Planning and early design are under way for being developed by NASA’s Constellation hardware, propulsion systems and associated Program to carry human explorers back to technologies for NASA’s Ares V cargo launch the moon, and then onward to Mars and other vehicle — the “heavy lifter” of America’s next- destinations in the solar system. generation space fleet. facts The Ares V effort includes multiple project Ares V will serve as NASA’s primary vessel for element teams at NASA centers and contract safe, reliable delivery of resources to space organizations around the nation, and is led — from large-scale hardware and materials by the Exploration Launch Projects Office for establishing a permanent moon base, to at NASA’s Marshall Space Flight Center in food, fresh water and other staples needed to Huntsville, Ala. These teams rely on nearly a extend a human presence beyond Earth orbit. half a century of NASA spaceflight experience and aerospace technology advances. Together, Under the goals of the Vision for Space they are developing new vehicle hardware Exploration, Ares V is a vital part of the cost- and flight systems and maturing technologies effective space transportation infrastructure evolved from powerful, reliable Apollo-era and space shuttle propulsion elements. NASA Concept image of Ares V in Earth orbit. (NASA/MSFC) www.nasa.gov The versatile, heavy-lifting Ares V is a two-stage, vertically stacked launch system. The launch vehicle can carry about 287,000 pounds to low Earth orbit and 143,000 pounds to the moon.
    [Show full text]
  • Ares V Cargo Launch Vehicle Will Work in Tandem with the Ares I Crew Launch Vehicle to Deliver the Power to Explore the Moon and Beyond
    National Aeronautics and Space Administration The Ares V Cargo Launch Vehicle will work in tandem with the Ares I Crew Launch Vehicle to deliver the power to explore the Moon and beyond. www.nasa.gov NASA’s Ares Projects — Ares V Cargo Launch Vehicle The Ares V will provide unprecedented capability to explore orbit by the Ares I. Orion will dock with Altair, and the Earth the Moon and establish a permanent outpost there in the Departure Stage will ignite again to send the coupled space- next decade. NASA is designing the Ares V to send more craft to the Moon. Once the astronauts arrive in lunar orbit, than 40 percent more mass to the Moon than the Apollo-era they will check out systems, transfer to Altair, and descend Saturn V rocket. That increase in payload mass, as well as to the Moon, while Orion remains in orbit. On the Moon, astro- Payload Shroud an increase in volume, will open the door to exciting new nauts will explore the terrain and conduct experiments. After (Exploded view) possibilities for exploration, science, and discovery. completing their mission, the crewmembers will return in Altair to lunar orbit and dock with Orion for the return to Earth. Altair Lunar Lander Ares V will work in tandem with the Ares I crew launch vehicle. By separating the crew and cargo rockets while sharing similar With a capability of sending more than 156,000 pounds to the Earth Departure propulsion elements — and by building on proven hardware Moon, the Ares V also is expected to be used in a fully auto- Stage while using modern engineering practices — NASA is building mated mode to deliver habitats, rovers, scientific equipment, LOX/LH2 One J-2X Engine a safe, reliable, cost-efficient transportation system for explo- and other supplies to the lunar outpost.
    [Show full text]
  • The First Human Asteroid Mission: Target Selection and Conceptual Mission Design
    The First Human Asteroid Mission: Target Selection and Conceptual Mission Design Daniel Zimmerman,∗ Sam Wagner,∗ and Bong Wiey Asteroid Deflection Research Center - Iowa State University, Ames, IA 50011-2271 President Obama has recently declared that NASA will pursue a crewed mission to an asteroid by 2025. This paper identifies the optimum target candidates of near-Earth objects (NEOs) for a first crewed mission between 2018 and 2030. Target asteroids in the NEO database with orbital elements that meet predetermined requirements are analyzed for mission design. System architectures are then proposed to meet the require- ments for five designated NEO candidates. Additional technology which can be applied to crewed NEO mis- sions in the future is also discussed, and a previous NEO target selection study is analyzed. Although some development of heavy launch vehicles is still required for the first NEO mission, design examples show that a first mission can be achieved by 2025. The Ares V and the Orion CEV are used as the baseline system architecture for this study. Nomenclature a Semi-major Axis (AU) AU Astronomical Unit BOM Burnout Mass CEV Crew Exploration Vehicle e Eccentricity EDS Earth Departure Stage EOR Earth Orbit Rendezvous H Absolute Magnitude i Inclination (deg) Isp Specific Impulse (s) ISS International Space Station JPL Jet Propulsion Laboratory LEO Low-Earth Orbit LH2 Liquid Hydrogen LOX Liquid Oxygen MWe Megawatt Electrical MT Metric Ton NASA National Aeronautics and Space Administration NEO Near-Earth Object OT V Orbital Transfer Vehicle RSRM Reusable Solid Rocket Motor SSME Space Shuttle Main Engine T LI Trans Lunar Injection V ASIMR Variable Specific Impulse Magnetoplasma Rocket ∆V Velocity Change (km/s) ∗Graduate Research Assistant, Dept.
    [Show full text]
  • Administrator Griffin's Testimony
    HOLD FOR RELEASE UNTIL PRESENTED BY WITNESS February 27, 2008 Statement of Michael D. Griffin Administrator National Aeronautics and Space Administration before the Subcommittee on Space, Aeronautics and Related Sciences Committee on Commerce, Science and Transportation United States Senate Mr. Chairman and Members of the Subcommittee, thank you for the opportunity to appear today to discuss the President’s FY 2009 budget request for NASA. The President’s budget request for NASA is $17.6 billion, a 2.9 percent increase over the net budget authority enacted for 2008, along with a steady, five-year runout commensurate with inflation. This increase demonstrates the President’s commitment to funding the balanced priorities he set forth for the Agency in space exploration, Earth and space science, and aeronautics research. We are making steady progress in achieving these goals. I ask for your continued support as you consider the President’s FY 2009 budget request for NASA. When I testified before this Subcommittee last year, I spoke about the Administration’s balanced priorities for our Nation’s civil space and aeronautics research goals as set forth by the NASA Authorization Act of 2005 (P.L. 109-155) and the Vision for Space Exploration. NASA’s mandate is clear, and the NASA Authorization Act of 2005, as well as the level of funding appropriated to NASA in FY 2008, tells me that Congress broadly endorses the balanced set of programs the Agency has put forward in this era of limited budget growth. I have said this in other forums, but it warrants repeating here: at present funding levels, NASA’s budget is sufficient to support a variety of excellent space programs, but it cannot support all of the potential programs we could execute.
    [Show full text]
  • Rocketry Index a “Catalog” of All the Hobby Rockets
    and Present The Rocketry Index A “Catalog” of all the hobby rockets... ever! (or at least as many as I could manage!) Compiled and Edited by John A. Lee OSL Revision: 13.01 Contents Introductory Materials............................................................... 43 What Is “The Rocketry Index?”........................................................43 What Gets Included With the Rockets ..............................................45 What Gets Included With the Companies .........................................47 Company Information .................................................................................... 47 Company Statement ....................................................................................... 47 Rocketeers’ Views of the Companies.............................................................. 47 Master Lists ................................................................................................... 47 Family Groups...................................................................................49 Patriarchal Families ...................................................................................... 49 Always Ready Rocketry Families ..................................................................... 50 ARR Basic Blues Family .................................................................................................... 50 Art Applewhite Families ................................................................................... 50 Applewhite Cinco Family .................................................................................................
    [Show full text]
  • Suggested Outline of Annual Report
    The 2008 Annual Report of the International Space Exploration Coordination Group Released March 2009 1 International Space Exploration Coordination Group Annual Report: 2008 Introduction This second Annual Report of the International Space Exploration Coordination Group (ISECG) and its sub-working groups provides highlights of their activities during the past twelve-months including the progress of its Workplan, work ahead, the major space exploration accomplishments of its members including future opportunities, and progress in implementing the Themes described in The Global Exploration Strategy: The Framework for Coordination. In addition, this ISECG Annual Report, as with the 2007 edition, provides an opportunity for agencies to update the international community on their individual space exploration plans – this information will be found in the Annex. The Annual Report is intended to keep all exploration stakeholders, including other exploration related coordination groups, better informed of the ISECG's work and progress implementing the Global Exploration Strategy Framework document. Efficient, beneficial and public supported Space Exploration can only be accomplished as an international endeavour involving a diverse stakeholder community comprising; space agencies and their policy/funding governments, industry, scientific institutions, academia, and non-profit groups. The ISECG is facilitating this dialogue and understanding. 2 Part 1 The Role of the ISECG 1.1 Overview The International Space Exploration Coordination Group (ISECG) was born out of The Global Exploration Strategy: The Framework for Coordination (GES or Framework Document) that was prepared by fourteen space agencies1 and published in May 2007. The GES elaborates a vision for the peaceful robotic and human space exploration, including a common set of key space exploration themes, focusing on destinations within the Solar System where humans may one day live and work.
    [Show full text]