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Hybrid Propulsion Technology Program, phase 1. Volume 1: Executive summaryThe study program was contracted to evaluate concepts of hybrid propulsion, select the most optimum, and prepare a conceptual design package. Further, this study required preparation of a technology definition package to identify hybrid propulsion enabling technologies and planning to acquire that technology in Phase 2 and demonstrate that technology in Phase 3. Researchers evaluated two design philosophies for Hybrid Rocket Booster (HRB) selection. The first is an ASRM modified hybrid wherein as many components/designs as possible were used from the present Advanced Solid Rocket Motor (ASRM) design. The second was an entirely new hybrid optimized booster using ASRM criteria as a point of departure, i.e., diameter, thrust time curve, launch facilities, and external tank attach points. Researchers selected the new design based on the logic of optimizing a hybrid booster to provide NASA with a next generation vehicle in lieu of an interim advancement over the ASRM. The enabling technologies for hybrid propulsion are applicable to either and vehicle design may be selected at a downstream point (Phase 3) at NASA's discretion. The completion of these studies resulted in ranking the various concepts of boosters from the RSRM to a turbopump fed (TF) hybrid. The scoring resulting from the Figure of Merit (FOM) scoring system clearly shows a natural growth path where the turbopump fed solid liquid staged combustion hybrid provides maximized payload and the highest safety, reliability, and low life cycle costing.
Document ID
19910001741
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Date Acquired
September 6, 2013
Publication Date
October 23, 1989
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NASA-CR-183950
NAS 1.26:183950
Accession Number
91N11054
Funding Number(s)
CONTRACT_GRANT: NAS8-37775
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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