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A real-time guidance algorithm for aerospace plane optimal ascent to low earth orbitProblems of onboard trajectory optimization and synthesis of suitable guidance laws for ascent to low Earth orbit of an air-breathing, single-stage-to-orbit vehicle are addressed. A multimode propulsion system is assumed which incorporates turbojet, ramjet, Scramjet, and rocket engines. An algorithm for generating fuel-optimal climb profiles is presented. This algorithm results from the application of the minimum principle to a low-order dynamic model that includes angle-of-attack effects and the normal component of thrust. Maximum dynamic pressure and maximum aerodynamic heating rate constraints are considered. Switching conditions are derived which, under appropriate assumptions, govern optimal transition from one propulsion mode to another. A nonlinear transformation technique is employed to derived a feedback controller for tracking the computed trajectory. Numerical results illustrate the nature of the resulting fuel-optimal climb paths.
Document ID
19890066714
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Calise, A. J.
(Georgia Inst. of Tech. Atlanta, GA, United States)
Flandro, G. A.
(Georgia Institute of Technology Atlanta, United States)
Corban, J. E.
(Georgia Inst. of Tech. Atlanta, GA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1989
Subject Category
Launch Vehicles And Space Vehicles
Meeting Information
Meeting: 1989 American Control Conference
Location: Pittsburgh, PA
Country: United States
Start Date: June 21, 1989
End Date: June 23, 1989
Accession Number
89A54085
Funding Number(s)
CONTRACT_GRANT: NAG1-784
Distribution Limits
Public
Copyright
Other

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