Crew Exploration Lander for Ganymede, Callisto, and training 6-person crew 3.4 day transits 180 days in lunar orbit Three LM1s (for redundancy ... ROV – (Surface) Rover Vehicle RTQ

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Text of Crew Exploration Lander for Ganymede, Callisto, and training 6-person crew 3.4 day transits 180 days...

  • SSD LM1 Moon LanderSlide 1 of 18 Slides

    Mark G. Benton, Sr.8/3/2009 10:53 PM

    2009 Mark G. Benton, Sr.All Rights Reserved

    Mark G. Benton, Sr., The Boeing CompanyMark G. Benton, Sr., The Boeing CompanyAIAA 2009 Joint Propulsion ConferenceAIAA 2009 Joint Propulsion Conference

    August 3 August 3 -- 5, 2009, Denver, Colorado5, 2009, Denver, Colorado

    Crew Exploration Lander for Ganymede, Crew Exploration Lander for Ganymede, Callisto, and EarthCallisto, and Earths Moon s Moon -- Vehicle Vehicle

    System DesignSystem Design (AIAA(AIAA--20092009--5179)5179)

    Spaceship DiscoverySlide 1 of 18 Slides

    AIAA 2009 Joint Propulsion Conference8/3/2009 10:53 PM

    2009 Mark G. Benton, Sr.All Rights Reserved

  • SSD LM1 Moon LanderSlide 2 of 18 Slides

    Mark G. Benton, Sr.8/3/2009 10:53 PM

    2009 Mark G. Benton, Sr.All Rights Reserved

    Spaceship Discovery Spaceship Discovery ArchitectureArchitecturefor Human Solar System Explorationfor Human Solar System Exploration

    Spaceship DiscoveryConceptual vehicle architectureModular spacecraft, assembled

    in Earth parking orbitNumber of drop tanks tailored

    to mission V requirementsBi-modal NTR engines

    High Isp propulsion (950 s) High elec. power (200 kw)

    Crew protective systems Artificial gravity Radiation shielding High degree of redundancy

    Design Reference Missions *DRM 1: MoonDRMs 2 / 3: MarsDRMs 5 / 6: Callisto / Ganymede

    Launch, Assembly, DepartureModular 50 MT subassemblies

    (33.0 m L x 8.4 m dia.) launched Assembled in 556 km (300 nmi)

    altitude, circular Earth orbitSystems checked out and

    propellant tanks topped offMission crew arrivesEscape to solar transfer ellipse

    * Note: DRM 4 exploration mission to asteroid Ceres reserved for future work

    Crew Module (CM)

    Service Module (SM)

    Main LH2Propellant Core Tank (CT) (4 pl)

    Engineering Module (EM)

    Main LH2Propellant Drop Tank (DT) (12 pl)

    Deployable Solar / Thermal Shade (2 pl)

    Side View Cutaway Key Features

    Side View Main Ship

    Closed Brayton Cycle (CBC) Electrical Gen. System (3 places)

    5-Port Docking Module (DM)

    Very Low Boil off System (VLBOS) (Cryo. Retention)

    Ganymede, Callisto, Earths Moon Lander Module LM1(DRMs 1, 5, 6)

    Mars Lander Modules LM2, LM3 (DRMs 2, 3)

    Reentry Module (RM)

    Bimodal Nuclear Thermal Rocket (NTR) Engine (3 pl)

    Abort Propulsion System (APS) Main Engine

    Artificial Gravity (AG) Centrifuge

    Galactic Cosmic Ray (GCR) & Solar Particle Event (SPE) Biological Shield (LH2 & H2O)

    Gimbaled High Gain Antenna (2 pl)

  • SSD LM1 Moon LanderSlide 3 of 18 Slides

    Mark G. Benton, Sr.8/3/2009 10:53 PM

    2009 Mark G. Benton, Sr.All Rights Reserved

    Spaceship Discovery Spaceship Discovery Details ofDetails ofDRMs 1, 5, and 6 Exploration MissionsDRMs 1, 5, and 6 Exploration Missions

    DRM 1 Earths Moon Flight test SSD Flight test LM1 landersCrew training 6-person crew 3.4 day transits 180 days in lunar orbit Three LM1s (for redundancy) 30 day duration per lander

    DRM 5 Callisto Four person crew Four year total durationOne year, 9 month transits 183 day wait time at JupiterCapture into 185 km circular

    Callisto parking orbit Three LM1s (for redundancy) 30 day duration per lander

    DRM 6 GanymedeCrew, duration, transits, wait

    time at Jupiter same as DRM 5Capture into 185 km circular

    Ganymede parking orbit Three LM1s (for redundancy)

    b. DRMs 5 or 6 Outbound Transit to Jovian System and Insertion into Callisto or Ganymede Orbit

    a. DRMs 5 or 6 Assembly in Earth Parking Orbit in Preparation for Trans-Jupiter Injection

    c. DRMs 5 or 6 In Orbit around Callisto or Ganymede, Ready for Landing MissionsDRM 1 Trans-Lunar Injection, Outbound Transit, Lunar Orbit Insertion, and Ready for Landing Missions

    d. DRMs 5 or 6 Trans-Earth Injection, Inbound Transit, and Earth Trajectory InjectionDRM 1 Trans-Earth Injection, Inbound Transit, and Earth Orbit Insertion

  • SSD LM1 Moon LanderSlide 4 of 18 Slides

    Mark G. Benton, Sr.8/3/2009 10:53 PM

    2009 Mark G. Benton, Sr.All Rights Reserved

    LM1 Design RequirementsLM1 Design Requirementsand Mission Flight Performanceand Mission Flight Performance

    Target Planetary Body Ganymede Callisto Moon

    Planetary ParametersRadius at Surface (km) 2,631 2,410 1,738Equatorial Rotation (m/s) 26.7 10.5 4.6Gravitational Parameter (km3/s2) 9,887 7,179 4,903Gravity at Surface (m/s2) 1.428 1.237 1.62Circ. Parking Orbit ParametersParking Orbit Radius (km) 2,816 2,596 1,923Parking Orbit Altitude (km) 185.4 185.4 185.4Orbital Velocity (m/s) 1,874 1,663 1,597Descent ParametersV for Transfer Burn 1 (m/s) 221 203 197 Periapsis Altitude (PDI) (km) 15.2 15.2 15.2 Inertial Velocity at PDI (m/s) 1,968 1,749 1,711Relative Velocity at PDI (m/s) 1,941 1,739 1,706True Anomaly at Landing (deg) 11.9 10.4 13.9 Ascent ParametersRelative Vel. at Burnout (m/s) 1,938 1,707 1,628Rel. Vel. at 185 km Alt. (m/s) 1,876 1,663 1,600V for Circulariz. Burn 2 (m/s) 335 265 258Ascent True Anomaly (deg) 37.7 38 32.31 Includes 25 m/s maneuvering, 5 degree decent plane change, and 1% flight performance reserve.2 Includes 100 m/s maneuvering, 5 deg. ascent plane change, launch from +30 degree inclination, and 1% flight performance reserve.

    Temperature Ranges (C):Ganymede -179 to -130Callisto -196 to -116Moon -180 to +130

    Descent to Surface *

    Powered Descent Initiation (PDI) Point

    Descent Transfer Orbit

    Descent Transfer Burn

    - True Anomaly, PDI to Landing

    Landing Point

    Ascent to Orbit *

    Parking Orbit

    Launch Point

    Orbit Circularization Burn

    - True Anomaly, Launch to Circularization Burn

    * Note: Drawings Not to Scale

  • SSD LM1 Moon LanderSlide 5 of 18 Slides

    Mark G. Benton, Sr.8/3/2009 10:53 PM

    2009 Mark G. Benton, Sr.All Rights Reserved

    LM1 Design Data LM1 Design Data Configuration Elevation ViewsConfiguration Elevation Views

    Abbreviations and AcronymsAS Ascent StageBSW Biological Shield WaterCOM Communications Equip.DS Descent StageECS Equipment Cooling Sys. FAE Fixed Ascent Engine FDK Flight DeckGDE Gimballed Descent Eng. GNC Guidance, Nav., ControlHAB Crew Habitat LGR Landing Gear LSS Life Support SystemME Main EngineMMH Mono-Methyl HydrazineMPS Main Propulsion SystemNTO Nitrogen Tetroxide OML Outer MoldlinePRP PropellantPRS PressurizationRCS Reaction Control SystemROV (Surface) Rover VehicleRTQ RCS Thruster QuadSCR SupercriticalVDM Vehicle Drive MotorVDW Vehicle Drive Wheel

    GDE (8 pl)

    AS ECS/LSS Bay

    DS BSW Tanks (8 pl)

    Deploy w/ Pyros, Spring & Gravity Assist

    45-Deg. Cutaway (LGR Stowed)

    + 0.6 m Stroke, & + 0.6 mLeveling Strut

    DS Thrust Cylinder Structure Pri. Struc.

    Independent Suspension VDM & VDW (8 pl)

    45-Deg. Cutaway (LGR Depl.)

    SSD-LM1-v2

    Tunnel to Air Lock in DS

    DS Cargo Bay

    FDK & HABCrew Cabin

    DS MPS LO2 Tank

    DS Air Lock

    DS MPS LH2 Tank

    Side View Cutaway

    Reflective Thermal Foil

    AS MPS NTO Tk. (2 pl)

    DS Fuel Cell /LSS SCR LO2Tks. (2 pl)

    DS Fuel Cell /LSS SCR LH2Tks. (2 pl)

    Fuel Cell(4 pl)

    Front View Cutaway

    AS RCS NTO Tk. (4 pl)

    AS FAE (8 pl)

    AS MPS MMH Tk. (2 pl)

    AS RCS MMH Tk. (4 pl)

    LSS SCR LO2 Tk. (2 pl)

    ECS/LSS H2O Tk. (2 pl)

    DS MPS LO2 Tank

    DS MPS & BSW PRS Tks (4 pl)

  • SSD LM1 Moon LanderSlide 6 of 18 Slides

    Mark G. Benton, Sr.8/3/2009 10:53 PM

    2009 Mark G. Benton, Sr.All Rights Reserved

    LM1 Design Data LM1 Design Data Configuration Cross Section ViewsConfiguration Cross Section Views

    Design Features Two-way trans: orbit surfaceAbort to orbit during descentSingle engine-out redundancy FDK, HAB, ROV functionalityRadiation shielding for HAB Insulation for extreme tempsCrew: 2 (3 for rescue)Payload: 500 / 125 kg (DS/AS)Endurance:30 / 7 d (DS/AS) LM1 Total Masses

    21.97 MT (Ganymede) 19.62 MT (Callisto) 20.12 MT (Earths Moon)

    Descent Section (DS) LH2 LO2 MPS propellants (8) gimballed, 12.2 kN main eng.

    (throttleable 100% - 30%)Power: LH2 / LO2 fuel cellsAirlock and cargo bay

    Ascent Section (AS)MMH NTO MPS propellants (8) fixed 3.3 kN main eng.MMH NTO RCS propellantsPower: Solar Arrays / Batts.

    DS RCS NTO Tk. (4 pl)

    RCS PRS Tank (2 pl)

    DS MPS NTO Tk. (2 pl)

    Crew HAB Incl. Sleep, Food Prep., & Hygiene Facilities

    MPS PRS Tank (4 pl)

    DS RCS MMH Tk. (2 pl)

    RTQ (4 pl)

    FAE(8 pl)

    Tunnel to Airlock in DS

    AS Lower Level

    LSS SCR LO2Tanks (2 pl)

    Tunnel to Airlock in DS

    AS Upper Level

    DS MPS LH2 Tank

    Cargo Bay

    DS-AS PyroSep. Bolts(6 pl)

    DS Surface Access Door Pair (2 pl)

    DS Fuel Cell/ LSS SCR LH2Tank(2 pl)

    Airlock in DS

    Insulated Fuel Cell Bay (2 pl)

    DS Upper Level (LGR Stowed)

    Air Lock

    Cargo Bay

    Fuel Cell(4 pl)

    Fuel Cell / LSS SCR LO2 Tks.(2 pl)

    GDE(8 pl)

    DS Lower Level (LGR Depl.)

    Crew Bunk(2 pl)

    MPS and RCS Tank Bay (2 pl)

    LSS H2O Tks (2 pl)

    FDK w/ (2) Large Windows

    Batteries

    GNC & COM Bay

    DS MPS MMH Tk. (2 pl)

    DS MPS & BSW PRS Tks (4 pl)

    DS BSW Tanks (8 pl)

    SSD-LM1-v2

  • SSD LM1 Moon LanderSlide 7 of 18 Slides

    Mark G. Benton, Sr.8/3/2009 10:53 PM

    2009 Mark G. Benton, Sr.All Rights Reserved

    Moon Landing Mission Description Moon Landing Mission Description Launch, Assembly, Transit, & DeorbitLaunch, Assemb