This 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.
Closed-Loop Endoatmospheric Ascent Guidance
2002 AIAA GN and C Conference ; 2002 ; Monterey, CA, United States
2002-01-01
Preprint
No indication
English
Closed-Loop Endoatmospheric Ascent Guidance
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