Novel Control Design for Intercepting Missile with Passive Ranging System
Date Issued
2009
Date
2009
Author(s)
Huang, Po-Hsu
Abstract
This thesis presents the three main parts of the missile system: estimator/seeker, guidance Law and autopilot system. The estimator/seeker is developed with a passive ranging law by using angle-only measurements for acquiring better covert operation. The guidance law is designed with the sliding-mode theory, for minimizing the distance between the missile and the target. The autopilot system based on quaternion representation is also 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, the actuator of missile is equipped with Thrust Vector Control (TVC) and Divert Control System (DCS) in order to extend the operation range from endo-atmosphere to exo-atmosphere. Finally, various simulations incorporating aerodynamics model are presented to verify the validity of the proposal Seeker/Estimator and 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
Passive ranging
Sliding mode control
Thrust Vector Control
Diver Control System
Lyapunov stability theory
Maneuvering target
Type
thesis
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