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An inverse dynamics approach to trajectory optimization and guidance for an aerospace planeThe optimal ascent problem for an aerospace planes is formulated as an optimal inverse dynamic problem. Both minimum-fuel and minimax type of performance indices are considered. Some important features of the optimal trajectory and controls are used to construct a nonlinear feedback midcourse controller, which not only greatly simplifies the difficult constrained optimization problem and yields improved solutions, but is also suited for onboard implementation. Robust ascent guidance is obtained by using combination of feedback compensation and onboard generation of control through the inverse dynamics approach. Accurate orbital insertion can be achieved with near-optimal control of the rocket through inverse dynamics even in the presence of disturbances.
Document ID
19920072551
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lu, Ping
(Iowa State University of Science and Technology, Ames, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Subject Category
Astrodynamics
Report/Patent Number
AIAA PAPER 92-4331
Meeting Information
Meeting: AIAA Guidance, Navigation and Control Conference
Location: Hilton Head Island, SC
Country: United States
Start Date: August 10, 1992
End Date: August 12, 1992
Accession Number
92A55175
Funding Number(s)
CONTRACT_GRANT: NAG1-1255
Distribution Limits
Public
Copyright
Other

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