Novel Controller Design for Missiles to Intercept Maneuvering Target
Date Issued
2007
Date
2007
Author(s)
Hsueh, Ming-Hsiung
DOI
en-US
Abstract
The decision part in missiles: guidance law and autopilot system is presented in this thesis. The guidance law is designed with linear differential game theory in order to consider the motion of target and to minimize the distance between the missile and the target as soon as possible. The autopilot system based on quaternion representation is designed using sliding mode control method to generate the attitude command. The stability of the integrated guidance/autopilot system is proved with Lyapunov stability theory. In addition, two wingless missiles are applied in the thesis in order to reduce the nonlinear effect from the aerodynamics. Furthermore, in order to extend the operation range of missiles from endo-atmosphere to exo-atmosphere, the missiles are equipped with Thrust Vector Control (TVC) mechanisms and Divert Control System (DCS). Finally, various simulations incorporating aerodynamic model are demonstrated to verify the validity of the proposed integrated guidance/autopilot systems, and we compare the performance of the simulations with that from the previous works. Moreover, the simulation results reveal that the mission of intercepting a maneuvering target is successful.
Subjects
機動目標
線性可微分賽局
順滑模態
推力向量控制
側噴流控制系統
李奧普洛夫定理
Linear differential game theory
Sliding mode control
Thrust Vector Control
Diver Control System
Lyapunov stability theory
Maneuvering target
Type
thesis