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AAE450 Senior Spacecraft Design Catherine Frey Week 2: January 25 th, 2007 Propulsion Team Leader Liquid Propellant Tank Sizing.

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Presentation on theme: "AAE450 Senior Spacecraft Design Catherine Frey Week 2: January 25 th, 2007 Propulsion Team Leader Liquid Propellant Tank Sizing."— Presentation transcript:

1 AAE450 Senior Spacecraft Design Catherine Frey Week 2: January 25 th, 2007 Propulsion Team Leader Liquid Propellant Tank Sizing

2 AAE450 Senior Spacecraft Design Liquid Propellant Masses LOX/LH 2 –vehicles carrying crew –launching from Mars 5.00 O/F mixture ratio VehicleLOX MassLH 2 Mass TC3908 kg782 kg ET102499 kg20500 kg MT313626 kg62725 kg MLV3789000 kg757800 kg

3 AAE450 Senior Spacecraft Design Liquid Propellant Volumes LOX 16x denser than LH 2 VehicleLOX Tank Volume LH 2 Tank Volume TC3.40 m 3 11.03 m 3 ET89.2 m 3 289.1 m 3 MT273.0 m 3 884.7 m 3 MLV3298 m 3 10688 m 3

4 AAE450 Senior Spacecraft Design Liquid Propellant Mass Calculations LOX density 1 : 1149 kg/m 3 LH 2 density 1 : 70.9 kg/m 3 Optimum O/F ratio 4 : 6.00 O/F ratio used 3 : 5.00 LH 2 mass calculated –m LH2 =(m prop )(1+O/F) LOX mass calculated –m LOX =(O/F)(m LH2 )

5 AAE450 Senior Spacecraft Design Liquid Propellant Volume Calculations LOX density 1 : 1149 kg/m 3 LH 2 density 1 : 70.9 kg/m 3 Optimum O/F ratio 4 : 6.00 O/F ratio used 3 : 5.00 LOX volume calculated –v Lox = m LOX /ρ LOX LH 2 volume calculated –v LH2 = m LH2 /ρ LH2

6 AAE450 Senior Spacecraft Design All Liquid Propellant Vehicles Vehiclem prop (kg)m LOX (kg)v LOX (m 3 )m LH2 (kg)v LOX (m 3 ) TC4690.23908.53.40781.711.03 MT376350.6313625.5272.9662725.1884.7 MT/SR337417.8281181.5244.7256236.3793.18 ET122998.3102498.689.2120499.7289.14 aE355408.0296173.3257.7759234.7835.47 dM (HMO to HEO) 526391.2438659.3381.7787731.91237.4

7 AAE450 Senior Spacecraft Design All Liquid Propellant Vehicles Vehiclem prop (kg)m LOX (kg)v LOX (m 3 )m LH2 (kg)v LOX (m 3 ) dM (HMO to ES) 67187.255989.348.7311197.9157.94 aM (HEO to HMO) 626663.9522219.9454.5104444.01473.12 aM (HEO to HMO) 280101.2233417.7203.1546683.5658.44 dE (HEO to HMO) 1213400.01011166.7880.04202233.32852.37 dE (HEO to HMO) 801187.6667656.3581.08133531.31883.37 MLV (MS to HMO) 4546800.03789000.03297.65757800.010688.29

8 AAE450 Senior Spacecraft Design References 1 Gordon, Sanford, and Bonnie J. McBride. Scientific and Technical Information Office. NASA. Computer Program for Calculation of Complex Chemical Equilibrium Compositions, Rocket Performance, Incident and Reflected Shocks, and Chapman-Jouget Detonations. Washington, D.C., 1971. 2 Landau, Damon F. Strategies for the Sustained Human Exploration of Mars. Diss. Purdue Univ., 2006. 3 Larson, Wiley J., and Linda K. Pranke, eds. Human Spaceflight: Mission Analysis and Design. The McGraw-Hill Companies, Inc. 783-784. 4 Wade, Mark. "LOX/LH2." Encyclopedia Astronautica. Astronautix. 23 Jan. 2007.

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