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Study Task for Determining the Effects of Boost-Phase Environments on Densified Propellants Thermal Conditions for Expendable Launch VehiclesA thermodynamic study has been conducted that investigated the effects of the boost-phase environment on densified propellant thermal conditions for expendable launch vehicles. Two thermodynamic models were developed and utilized to bound the expected thermodynamic conditions inside the cryogenic liquid hydrogen and oxygen propellant tanks of an Atlas IIAS/Centaur launch vehicle during the initial phases of flight. The ideal isentropic compression model was developed to predict minimum pressurant gas requirements. The thermal equilibrium model was developed to predict the maximum pressurant gas requirements. The models were modified to simulate the required flight tank pressure profiles through ramp pressurization, liquid expulsion, and tank venting. The transient parameters investigated were: liquid temperature, liquid level, and pressurant gas consumption. Several mission scenarios were analyzed using the thermodynamic models, and the results indicate that flying an Atlas IIAS launch vehicle with densified propellants is feasible and beneficial but may require some minor changes to the vehicle.
Document ID
20020061304
Acquisition Source
Glenn Research Center
Document Type
Contractor Report (CR)
Authors
Haberbusch, Mark S.
(Sierra Lobo, Inc. Freemont, OH United States)
Meyer, Michael L.
Date Acquired
September 7, 2013
Publication Date
April 1, 2002
Subject Category
Propellants And Fuels
Report/Patent Number
NAS 1.26:210808
E-12715
NASA/CR-2002-210808
Funding Number(s)
CONTRACT_GRANT: NASA Order C-73676-J
PROJECT: RTOP 721-20-00
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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