Numerical solutions of multi-phase optimal control problems are considered, where a phase is defined as a subinterval in which the right-hand sides of the differential equations are continuous. At the phase boundaries, the state, control, and design vectors may have jumps; in addition, the dimension of these vectors as well as the dimension of the right-hand sides may change. Two direct methods for solving such problems are presented : a multiple-shooting approach and a collocation method. Both methods avoid the adjoint differential equations. By these transcriptions, the optimal control problem is converted into a nonlinear programming problem (NLP), which is solved using standard sequential quadratic programming (SQP) algorithms. The methods are applied to determine optimal ascent and reentry trajectories of a two-stage-to-orbit vehicle. Both methods are embedded into an advanced user interface which allows a user to edit most of the necessary input in a simple way. This utility is described briefly.
Description
Multi-Phase Trajectory Optimization Methods with Applications to Hypersonic Vehicles | SpringerLink
%0 Book Section
%1 Jänsch1994
%A Jänsch, C.
%A Schnepper, K.
%A Well, K. H.
%B Applied Mathematics in Aerospace Science and Engineering
%C Boston, MA
%D 1994
%E Miele, Angelo
%E Salvetti, Attilio
%I Springer US
%K ifr
%P 133--164
%R 10.1007/978-1-4757-9259-1_8
%T Multi-Phase Trajectory Optimization Methods with Applications to Hypersonic Vehicles
%U https://doi.org/10.1007/978-1-4757-9259-1_8
%X Numerical solutions of multi-phase optimal control problems are considered, where a phase is defined as a subinterval in which the right-hand sides of the differential equations are continuous. At the phase boundaries, the state, control, and design vectors may have jumps; in addition, the dimension of these vectors as well as the dimension of the right-hand sides may change. Two direct methods for solving such problems are presented : a multiple-shooting approach and a collocation method. Both methods avoid the adjoint differential equations. By these transcriptions, the optimal control problem is converted into a nonlinear programming problem (NLP), which is solved using standard sequential quadratic programming (SQP) algorithms. The methods are applied to determine optimal ascent and reentry trajectories of a two-stage-to-orbit vehicle. Both methods are embedded into an advanced user interface which allows a user to edit most of the necessary input in a simple way. This utility is described briefly.
%@ 978-1-4757-9259-1
@inbook{Jänsch1994,
abstract = {Numerical solutions of multi-phase optimal control problems are considered, where a phase is defined as a subinterval in which the right-hand sides of the differential equations are continuous. At the phase boundaries, the state, control, and design vectors may have jumps; in addition, the dimension of these vectors as well as the dimension of the right-hand sides may change. Two direct methods for solving such problems are presented : a multiple-shooting approach and a collocation method. Both methods avoid the adjoint differential equations. By these transcriptions, the optimal control problem is converted into a nonlinear programming problem (NLP), which is solved using standard sequential quadratic programming (SQP) algorithms. The methods are applied to determine optimal ascent and reentry trajectories of a two-stage-to-orbit vehicle. Both methods are embedded into an advanced user interface which allows a user to edit most of the necessary input in a simple way. This utility is described briefly.},
added-at = {2021-02-13T16:18:10.000+0100},
address = {Boston, MA},
author = {J{\"a}nsch, C. and Schnepper, K. and Well, K. H.},
biburl = {https://puma.ub.uni-stuttgart.de/bibtex/2cf889faf46246db16bbe1b17034c0158/janolucak},
booktitle = {Applied Mathematics in Aerospace Science and Engineering},
description = {Multi-Phase Trajectory Optimization Methods with Applications to Hypersonic Vehicles | SpringerLink},
doi = {10.1007/978-1-4757-9259-1_8},
editor = {Miele, Angelo and Salvetti, Attilio},
interhash = {e9a10f3cfd95501bd18e36efac460964},
intrahash = {cf889faf46246db16bbe1b17034c0158},
isbn = {978-1-4757-9259-1},
keywords = {ifr},
pages = {133--164},
publisher = {Springer US},
timestamp = {2021-02-13T15:18:10.000+0100},
title = {Multi-Phase Trajectory Optimization Methods with Applications to Hypersonic Vehicles},
url = {https://doi.org/10.1007/978-1-4757-9259-1_8},
year = 1994
}
