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A guidance-motivated sensitivity analysis of an aero-assisted boost vehicleA simple model of an aero-assisted booster is used to examine the contributions of propulsion system type, aerodynamic lift and flight trajectory to the efficiency with which payloads can be placed into low earth orbit. The higher propulsive efficiency of ramjet and scramjet propulsion has the potential of increasing the payload mass ratio significantly. The contributions of turbojet propulsion and aerodynamic lift are less significant. The additional complexity involved in using aerodynamic propulsion and lift requires dealing with a more comprehensive set of design variables than for rocket boosters. The approach taken is to derive a set of sensitivity functions which relate booster performance to the design variables. The problems of optimum mixing of aerodynamic lift with thrust and determining the optimal boost trajectory is treated. The potential payload capacity of a horizontal take-off air-breathing boost vehicle is examined. The optimization problem which considers propulsive efficiency, aerodynamic configuration, and control and guidance issues is discussed.
Document ID
19860062708
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Taylor, L. W.
(NASA Langley Research Center Hampton, VA, United States)
Gracey, C.
(NASA Langley Research Center Hampton, VA, United States)
Armstrong, C. D.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1986
Subject Category
Launch Vehicles And Space Vehicles
Report/Patent Number
AIAA PAPER 86-2103
Accession Number
86A47446
Distribution Limits
Public
Copyright
Other

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