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Cryogenic LH 2 Storage

Cryogenic LH 2 Storage. Steve Feuerborn 15 February 2005 Thermal Control Subsystem Thermal Control Engineer, CAD Specialist, Thermal-Communications Liaison, Heat Pipe Specialist, Cryogenics Specialist. Working Design. Tank Dimensions: D=9.5m, H=19.5m Surface Area=865m 2

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Cryogenic LH 2 Storage

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  1. Cryogenic LH2 Storage Steve Feuerborn 15 February 2005 Thermal Control Subsystem Thermal Control Engineer, CAD Specialist, Thermal-Communications Liaison, Heat Pipe Specialist, Cryogenics Specialist

  2. Working Design • Tank Dimensions: D=9.5m, H=19.5m • Surface Area=865m2 • 100 Layer MLI (~2”) • “Zero-Boiloff” System • 15 kW TRW-derivative Cryo-Cooler • Propellant Mixer • Integrated Tank Radiators

  3. System Parameters • Insulation Mass: 2100 kg • Cryo-cooler Mass (includes radiators): 1500 kg • Cryo-cooler Power:16 kWe • Total ZBO Mass: 3600 kg • Passive Boiloff Loss: ~40000 kg • Estimated Propellant Losses: • Engine Cooldown(~3%): 2400 kg • Residual(~1%): 800 kg • Boiloff(~1%): 800 kg

  4. Sizing Code • % Steve Feuerborn • % AAE 450 • % ZBO Thermal Control Sizing Code • % Inputs • Tank_Diameter=9.5; % (m) • Tank_Height=19.5; % (m) • q=100; % (Wt) Worst case heating loads • % Empirical Sizing Factors - derived from sources (1) and (2) • MLI_Area_Density=2.4; % (kg/m2) • Cryo_Mass_Ratio=15; % (kg/Wt) • Cryo_Power_Ratio=0.16; % (kWe/Wt) • % Calculated Values • Surface_Area=4*pi*(Tank_Diameter/2)^2+pi*Tank_Diameter*Tank_Height; % (m2) • % Final Values • Total_MLI_Mass=Surface_Area*MLI_Area_Density % (kg) • Total_Cryo_Masss=q*Cryo_Mass_Ratio % (kg) • Total_Cryo_Power=q*Cryo_Power_Ratio % (kWe) • %(1) Beke et al. “Nuclear Thermal Rocket/Vehicle Design Options for Future NASA Missions to the Moon and Mars.” AIAA-1993-4170 • %(2) Zubrin, Robert. “The Use of Dual Mode Nuclear Thermal Rocket Engines to Support Space Exploration Missions.” AIAA-1991-3406

  5. Sources • (1) Beke et al. “Nuclear Thermal Rocket/Vehicle Design Options for Future NASA Missions to the Moon and Mars.” AIAA-1993-4170 • (2) Zubrin, Robert. “The Use of Dual Mode Nuclear Thermal Rocket Engines to Support Space Exploration Missions.” AIAA-1991-3406 • (3) Kittel, Peter. Plachta, David. “An Updated Zero Boil-Off Cryogenic Propellant Storage Analysis Applied to Upper Stages or Depots in an LEO Environment.” AIAA-2002-3589

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