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Closed-Loop Endoatmospheric Ascent GuidanceThis paper will present a complete formulation of the optimal control problem for atmospheric ascent of rocket powered launch vehicles subject to usual load constraints and final condition constraints. We shall demonstrate that the classical finite difference method for two-point-boundary-value-problems (TPBVP) is suited for solving the ascent trajectory optimization problem in real time, therefore closed-loop optimal endoatmospheric ascent guidance becomes feasible. Numerical simulations with a the vehicle data of a reusable launch vehicle will be provided.
Document ID
20030000638
Acquisition Source
Marshall Space Flight Center
Document Type
Preprint (Draft being sent to journal)
Authors
Lu, Ping
(Iowa State Univ. of Science and Technology Ames, IA United States)
Sun, Hongsheng
(Iowa State Univ. of Science and Technology Ames, IA United States)
Jackson, Scott
Date Acquired
September 7, 2013
Publication Date
January 1, 2002
Subject Category
Launch Vehicles And Launch Operations
Meeting Information
Meeting: 2002 AIAA GN and C Conference
Location: Monterey, CA
Country: United States
Start Date: August 5, 2002
End Date: August 8, 2002
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
CONTRACT_GRANT: NAS8-01105
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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