AAE450 Senior Spacecraft Design Catherine Frey Week 2: January 25 th, 2007 Propulsion Team Leader Liquid Propellant Tank Sizing
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 ET kg20500 kg MT kg62725 kg MLV kg kg
AAE450 Senior Spacecraft Design Liquid Propellant Volumes LOX 16x denser than LH 2 VehicleLOX Tank Volume LH 2 Tank Volume TC3.40 m m 3 ET89.2 m m 3 MT273.0 m m 3 MLV3298 m m 3
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 )
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
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 ) TC MT MT/SR ET aE dM (HMO to HEO)
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) aM (HEO to HMO) aM (HEO to HMO) dE (HEO to HMO) dE (HEO to HMO) MLV (MS to HMO)
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., Landau, Damon F. Strategies for the Sustained Human Exploration of Mars. Diss. Purdue Univ., Larson, Wiley J., and Linda K. Pranke, eds. Human Spaceflight: Mission Analysis and Design. The McGraw-Hill Companies, Inc Wade, Mark. "LOX/LH2." Encyclopedia Astronautica. Astronautix. 23 Jan