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Rapid near-optimal aerospace plane trajectory generation and guidanceProblems associated with onboard trajectory optimization, propulsion system cycle selection, and the synthesis of guidance laws are addressed for ascent to low earth orbit of an airbreathing, single-stage-to-orbit vehicle. A multicycle propulsion system is assumed that incorporates turbojet, ramjet, scramjet, and rocket engines. An energy state approximation is applied to a singularly perturbed, four-state dynamic model for flight of a point mass over a spherical nonrotating earth. An algorithm is then derived for generating both the fuel-optimal climb profile and the guidance commands required to follow that profile. In particular, analytic switching conditions are derived that, under appropriate assumptions, efficiently govern optimal transition from one propulsion cycle to another. The algorithm proves to be computationally efficient and suitable for real-time implementation. The paper concludes with the presentation of representative numerical results that illustrate the nature of the fuel-optimal climb paths and the tracking performance of the guidance algorithm.
Document ID
19920035988
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Corban, J. E.
(Guided Systems Technologies Atlanta, GA, United States)
Calise, A. J.
(Georgia Inst. of Tech. Atlanta, GA, United States)
Flandro, G. A.
(Georgia Institute of Technology Atlanta, United States)
Date Acquired
August 15, 2013
Publication Date
December 1, 1991
Publication Information
Publication: Journal of Guidance, Control, and Dynamics
Volume: 14
ISSN: 0731-5090
Subject Category
Spacecraft Design, Testing And Performance
Accession Number
92A18612
Funding Number(s)
CONTRACT_GRANT: NAG1-922
Distribution Limits
Public
Copyright
Other

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