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Please use this identifier to cite or link to this item: http://ntour.ntou.edu.tw:8080/ir/handle/987654321/28454

Title: Derivation of the Optimal Guidance Law for Space Vehicle Based on a DAE Approach
Authors: Wang H. S.;Jhu Wei-Lun;YUNG C. F.
Contributors: NTOU:Department of Electrical Engineering
國立臺灣海洋大學:電機工程學系
Date: 2010-07
Issue Date: 2011-10-21T02:37:37Z
Publisher: World Multi-Conference on Systemics, Cybernetics and Informatics, Orlando, Florida, USA
Abstract: abstract:In the simulation of space vehicles, we often encounter the trajectory prescribed path control (TPPC) problems. That is, we usually append a set of path constraints to the equations of motion for describing the shape of the trajectory. To describe the TPPC problem, the concept of the differential-algebraic equation (DAE) system is usually adopted. In this paper, the optimal guidance law for aircraft 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).
Relation: pp.407-412
URI: http://ntour.ntou.edu.tw/handle/987654321/28454
Appears in Collections:[電機工程學系] 演講及研討會

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