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Orbit on demand - Will cost determine best design?Eleven design concepts for vertical (V) and horizontal (H) take-off launch-on-demand manned orbital vehicles are discussed. Attention is given to up to three stages, Mach numbers (sub-, 2, or 3), expendable boosters, drop tanks (DT), and storable (S) or cryogenic fuels. All the concepts feature lifting bodies with circular cross-section and most have a 7 ft diam, 15 ft long payload bay as well as a crew compartment. Expendable elements impose higher costs and in some cases reduce all-azimuth launch capabilities. Single-stage vehicles simplify the logistics whether in H or V configuration. A two-stage H vehicle offers launch offset for the desired orbital plane before firing the rocket engines after take-off and subsonic acceleration. A two-stage fully reusable V form has the second lowest weight of the vehicles studied and an all-azimuth launch capability. Better definition of the prospective mission requirements is needed before choosing among the alternatives.
Document ID
19850042638
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Macconochie, J. O.
(NASA Langley Research Center Hampton, VA, United States)
Mackley, E. A.
(NASA Langley Research Center Hampton, VA, United States)
Morris, S. J.
(NASA Langley Research Center Hampton, VA, United States)
Phillips, W. P.
(NASA Langley Research Center Hampton, VA, United States)
Breiner, C. A.
(NASA Langley Research Center Hampton, VA, United States)
Scotti, S. J.
(Kentron International, Inc. Hampton, VA, United States)
Date Acquired
August 12, 2013
Publication Date
February 1, 1985
Publication Information
Publication: Aerospace America
Volume: 23
ISSN: 0740-722X
Subject Category
Spacecraft Design, Testing And Performance
Accession Number
85A24789
Distribution Limits
Public
Copyright
Other

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