針對具高機動性自動駕駛系統之攔截飛彈控制器設計
Other Title
Novel Control Design for Intercepting Missiles with Highly Maneuverable Autopilot System
Date Issued
2006
Abstract
In this thesis, we propose a highly maneuverable autopilot system based on multiple Thrust Vector Control (TVC) mechanisms 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. The strategy of the cooperation of multiple TVC mechanisms and DCS is discussed in detail. The decision part in missiles: guidance law (GL) and autopilot is presented. The GL is designed with dynamic sliding mode control in order to eliminate the chattering phenomenon caused by sliding mode control and to minimize the distance between the missile and the target without the estimation of interception time. The autopilot controller based on quaternion representation is designed using backstepping control technique to execute the attitude command. The stability of the integrated guidance/autopilot (G/A) system is analyzed by Lyapunov stability theory. In addition, we advocate a wingless missile to reduce the nonlinear effect from the aerodynamics as much as possible. Extensive simulations including aerodynamic model are finally demonstrated to verify the validity of the proposed integrated G/A systems of missiles incorporating the highly maneuverable inputs. Furthermore, we compare the performance of the simulations with that from the previous works of our research group.
Subjects
背向步進控制
動態順滑模態
推力向量控制
側噴流控制系統
李奧普諾夫定理
backstepping control
dynamic sliding mode control
Thrust Vector Control
Divert Control System
Lyapunov stability theory
Type
thesis
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