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Advanced transportation system studies technical area 3: Alternate propulsion system concepts. SSME upper stage useThe main objective was to determine viable methods for starting the Space Shuttle Main Engine (SSME) in an altitude environment and restarting it in an orbit environment with minimum changes in utilization of the engine system or hardware. The study concluded that the use of the SSME in an upper stage is feasible with minimal changes to the engine systems. The altitude start case requires only a change in the valve sequencing during start and reorificing of the ASI lines. Inlet pressures can be moderately low at 40 psia for the LOX and 32 psia for the H2. The orbital restart case adds the need to recirculate propellant and thermal control paint (to keep the turbomachinery inlets cold to minimize the tank pressures needed), and the need to heat two small components (to maintain acceptable mixture ratios during the early part of the start). These actions allow start anytime after approximately 120 minutes. Earlier starts (approximately one hour) are also possible but would require additional component heating for mixture ratio control during the early portion of the start sequence.
Document ID
19940012625
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Strangeland, Eric (Rockwell International Corp. Canoga Park, CA, United States)
Levak, Daniel (Rockwell International Corp. Canoga Park, CA, United States)
Date Acquired
September 6, 2013
Publication Date
April 1, 1993
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NASA-CR-193865
NAS 1.26:193865
DCN1-1-PP-02147
Accession Number
94N17098
Funding Number(s)
CONTRACT_GRANT: NAS8-39210
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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