Derivation of the Optimal Guidance Law for Space Vehicle Based on a DAE
碩士 === 國立臺灣海洋大學 === 電機工程學系 === 93 === The purpose of this thesis The purpose of this thesis is two-fold: to analyze the numerical method for nonlinear differential algebraic equations (DAE's) and to solve the optimal control problem in a DAE framework. In particular, the optimal guidance law fo...
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| Format: | Others |
| Language: | en_US |
| Published: |
2005
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| Online Access: | http://ndltd.ncl.edu.tw/handle/81344031623539762221 |
| Summary: | 碩士 === 國立臺灣海洋大學 === 電機工程學系 === 93 === The purpose of this thesis The purpose of this thesis is
two-fold: to analyze the numerical method for nonlinear
differential algebraic equations (DAE's) and to solve the optimal
control problem in a DAE framework. In particular, the optimal
guidance law for air-craft dynamics is derived based on a DAE
approach. We will reformulate the problem as a Hamiltonian DAE
system. After establishing the system of aircraft dynamics, we can
derive the optimal guidance law of the system by numerical
method. The numerical method is mainly based on the backward
differential formulas (BDF).
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