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Two-stage reusable launch system utilizing a winged core vehicle and glideback boostersA near-term technology launch system is described in which Space Shuttle main engines are used on a manned orbiter and also on twin strap-on unmanned boosters. The orbiter has a circular body and clipped delta wings. The twin strap-on boosters have a circular body and deployable oblique wings for a glideback recovery. The dry and gross weights of the system, capable of delivering 70klb of cargo to orbit, are compared with a similar system with hydrocarbon-fueled boosters and with the current Shuttle.
Document ID
19890017507
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Macconochie, Ian O. (NASA Langley Research Center Hampton, VA, United States)
Martin, James A. (NASA Langley Research Center Hampton, VA, United States)
Wood, James S. (NASA Langley Research Center Hampton, VA, United States)
Duquette, Miles O. (Joint Inst. for Advancement of Flight Sciences Washington, DC., United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1989
Subject Category
Space Transportation
Report/Patent Number
NAS 1.15:101513
NASA-TM-101513
Accession Number
89N26878
Funding Number(s)
PROJECT: RTOP 506-49-11-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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