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Orbital transfer vehicle advanced expander cycle engine point design studyA detailed computer model of the expander cycle engine system steady-state operation was developed. Payload performance data for the expander cycle engine for 100K pounds and 65K pounds Space Shuttle missions were examined to establish peak payload thrusts. It was found that peak payload for the 100K pound gross weight single engine case occurred at nearly 15,000 pounds thrust for both engine mixture ratios of 6:1 and 7:1. Peak payload at engine mixture ratio of 6:1 was 4 percent greater than at 7:1 mixture ratio. The two engine configuration peak paYloads occurred at engine thrust below 7,500 pounds (extrapolated) and were lower than single engine payloads. For the 65K pound gross weight mission, peak payloads for the single engine configuration occurred at nearly 10,000 pounds for both mixture ratios. Mixture ratio of 7:1 payloads were 5 percent lower than 6:1 payloads. Two engine configuration payloads occurred at engine thrusts considerably below 10K pounds.
Document ID
19790025079
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Martinez, A.
(Rockwell International Corp. Canoga Park, CA, United States)
Date Acquired
September 3, 2013
Publication Date
October 12, 1979
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NASA-CR-161318
BMPR-1
ASR79-109
Accession Number
79N33250
Funding Number(s)
CONTRACT_GRANT: NAS8-33568
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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