Novel Guidance Law and Autopilot Designs for Intercepting Missiles and Launch Rockets with TVC and DCS
Date Issued
2004
Date
2004
Author(s)
Cheng, Chia-Hao
DOI
en-US
Abstract
The control of flight vehicles has been an important topic ever
since the range of activities of human beings was extended from
the earth to the universe. The decision part in an airframe:
guidance law (GL) and autopilot are being discussed, and the
intercepting missiles and launch rockets are the two plants we are interested in. In this thesis, we advocate a wingless airframe in order to reduce the nonlinear effect from the aerodynamics as much as possible. We propose a robust autopilot system based on thrust vector control (TVC) and divert control system (DCS) in order to extend the maneuvering range of an airframe from the place with aerodynamic influence to the place without. Besides, two new missile GLs and one original rocket GL are presented. The missile GLs utilize the optimal control theory, feedback linearization technique, and Lyapunov analysis, whereas the rocket GL employs the differential geometry and sliding mode control. In addition, the design methodology of parameters of the integrated guidance/autopilot (G/A) systems is suggested with technical proofs. Various simulations including aerodynamic model were finally demonstrated to verify the feasibility of the integrated G/A systems of missiles and rockets.
Subjects
導引法則
運載火箭
自動駕駛儀
側噴流控制
滑動模式
最佳化理論
推力向量控制
微分幾何學
李亞普諾夫
攔截飛彈
DCS
Intercepting Missiles
Autopilot
Guidance Law
Launch Rockets
TVC
Optimal Theory
Sliding Mode
Differential Geometry
Lyapunov
Type
thesis
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