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Inputs on HPM EPS, SEP Stage Block II configuration, and comments on 10/2 presentation package

Inputs on HPM EPS, SEP Stage Block II configuration, and comments on 10/2 presentation package. Tim Sarver-Verhey 10/1/2001. HPM Power System - Update. Power system performance & characteristics. CTM Power System - Update. Power system performance & characteristics.

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Inputs on HPM EPS, SEP Stage Block II configuration, and comments on 10/2 presentation package

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  1. Inputs on HPM EPS, SEP Stage Block II configuration, and comments on 10/2 presentation package Tim Sarver-Verhey 10/1/2001

  2. HPM Power System - Update • Power system performance & characteristics GRC/TRSV

  3. CTM Power System - Update • Power system performance & characteristics GRC/TRSV

  4. SEP Stage - Orbit Transfer Performance • Transfer from ISS orbit to 320,000 km @ 19.5 ° • Assumed low-thrust spiral • Inclination change performed throughout spiral • Total Vehicle Mass • 59.7 MT • 36.3 MT fixed payload assumed (31.1 Chem load + 5.2 MT HPM dry mass) • 16.3 MT for return trip: SEP Stage + Empty HPM • Propellant Mass • 12.2 MT for out-bound • Trip Time • 272 days out-bound GRC/TRSV

  5. SEP Stage - System Summary • Thrusters • 9 Gridded ion engines required • 1 spare included • PPUs on deployed palette • PV Arrays • 2 Square rigger wings employed • Array area = 2700 m2 • Power produced = 450 kW • Assume 5 kW for system power • Power density = 167 W/m2 • Arrays fixed on base palette • HPM/Base to fly solar inertial • Articulated Boom • 20 m coilable main boom section • 2 rigid segments to extend thruster reach • SEP System • “Dry” Mass = 11.2 MT • Includes 2 MT of xenon on-board Mass Breakdown GRC/TRSV

  6. SEP Stage - Detailed Mass Breakdown Radiator area: 30.2 m2 Radiator area: 24.6 m2 GRC/TRSV

  7. Subsystem • Calculated Mass (kg) • Navigation/Attitude Control • 12 • Command/Control/Comm • 42 • Thermal • 234 • Power • 305 • Propellant Management • 1,089 • Structures • 1314 • Shielding • 943 • Calculated Dry Mass • 3939 • Dry Mass Margin • 165 • Dry Mass Target Mass • 4,104 Hybrid Propellant Module (HPM) Mass & Technology Summary • HPM Advanced Technology Requirements • Integrated Flywheel Energy Storage System • - Combination energy storage and attitude control • Advanced Triple Junction Crystalline Solar Cells • >30% efficiency • Zero Boil-Off System • - Cryogenic propellant storage system (up to 10 years of storage without boil-off) • Integrated Primary Multifunction Structure & Meteoroid and Orbital Debris Shield • - Non-metallic hybrids to maximize radiation protection • Autonomous Operations including Rendezvous and Docking • On-Orbit Cryogenic Fluid Transfer • Lightweight Composite Cryogenic Propellant Storage Tanks • Graphitic Foams and Syntactic Metal Foams • Carbon-Carbon Composite Radiators GRC/TRSV

  8. Technologies Currently Used in CTV Advanced Triple Junction Crystalline Solar Cells Provide >500 W/kg (blanket) >30% efficiency or Integrated Primary Multifunction Structure & Meteoroid and Orbital Debris Shield Non-metallic hybrids to maximize radiation protection Autonomous Operations including Rendezvous and Docking Lightweight Composite Cryogenic Storage Tanks Graphitic Foams and Syntactic Metal Foams Carbon-Carbon Composite Radiators Advanced ECLSS CO2 Removal System Crew Transfer Vehicle (CTV)Mass & Technology Summary 5.5m Graphic deleted Mass of Full (CTV) =5282 kg GRC/TRSV

  9. Solar Electric Propulsion Module (SEP) Mass & Technology Summary • Photovoltaic Arrays: 2 square-rigger style wings (rad hard as possible) • Thin film cells, Array area = 2700 m2, Power produced = 450 kW • Thrusters: 8 Gridded Ion Engines, operating at 50 kW • Xenon, 3,300 s Isp, 2.0 N thrust per engine, 15 khours lifetime (Minimum) • Articulated boom for thrust vectoring • Base Palette containing • Extra Xenon for free-flying operation • Arrays mounts • Power processing • Reaction Control system • Attitude Control system • HPM docking & Fluid Transfer interfaces Mass of Full (SEP) =11,000 kg (includes 2000 KG of Xenon) GRC/TRSV

  10. Overall Technology Summary • Key Technologies • Integrated flywheel energy storage system • Advanced triple junction crystalline solar cells • Zero Boil-Off (ZBO) system • Integrated primary multifunction structure, radiation & meteoroid and orbital debris shielding • Autonomous operations including rendezvous and docking • On-orbit cryogenic fluid transfer • Lightweight cryogenic propellant tanks • Graphitic foams and syntactic metal foams • Carbon-carbon composite radiators • High performance, high cycle life LH2/LOX main engine • Integrated GH2/GOX Reaction Control System (RCS) • Advanced ECLSS CO2 removal system • Large deployable thin film arrays • Gridded ion engines • HPM CTV CTM SEP • 3-axis control possible 3-axis control 3-axis control • > 40% eff > 40% eff > 40% eff 20% eff • Multistage NA NA NA • Also provides Also provides Also provides Yes • thermal radiation thermal • Insulation shielding insulation • MANS/AFF MANS/AFF MANS/AFF MANS/AFF • LH2/LO2/XenonNA LH2/LO2/Xenon Xenon/GH2/GO2 • Composite NA Aluminum Composite • YES YES YES YES • YES YES YES YES • NA NA 50-100 Starts NA • 0.995 reliability • NA NA Yes YES • NA YES NA NA • NA NA NA167W/m**2, rad res’t. • NA NA NA Hi-power, >15kh life GRC/TRSV

  11. Summary & Forward Work • The HPM concept in the OASIS framework could reduce costs and enhance mission robustness across a wide spectrum of future space activities. • Economic sensitivities for NASA and commercial applications have indicated that inexpensive launch of propellant on the order of $1000/kg is the threshold for making a space based transportation infrastructure viable. • Solar Electric Propulsion technologies (high performance, radiation resistant arrays, long-lived high performance gridded ion engines, large deployable systems) present significant technology development challenges, which can be achieved with sufficient resources.Pat: folks here aren’t too comfortable having SEP called out as tall pole (yet again), in particular since many other elements of this program are little more than paper studies (launch vehicles and their costs, Gateway/OASIS, light-weight cryo-tanks, etc.) Can this statement be further revised so that SEP doesn’t appear to be the lone ‘bad guy’ for this mission? • Follow-on activities under RASC have been proposed for FY02: • Refined commercial and DOD applications • Increased detail assessments for other supporting concepts (SEP, CTM, CTV, etc) • Applications beyond the Earth-Moon system GRC/TRSV

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