A midcourse guidance law for missiles with Thrust Vector Control

Author

Yeh, Fu-Kuang ; Chien, Hsiuan-Hau ; Fu, Li-Chen

Author_Institution

Dept. of Electr. Eng., Nat. Taiwan Univ., Taipei, Taiwan

Volume

3

fYear

2001

fDate

2001

Firstpage

2357

Abstract

A nonlinear missile guidance controller with Thrust Vector Control (TVC) inputs for the interception of a theater ballistic missile is presented. In this paper, the midcourse phase of the missile is investigated, during which many non-ideal conditions must be considered, such as variation of the inertia of the missile and existence of the aerodynamic force, and an effect controller is designed to take into account the properties of TVC. Specifically, a 3 DOF optimal midcourse guidance law is designed to minimize the control effort and the distance between the missile and the target. The asymptotic stability of the overall system is proved by Lyapunov theory. Extensive simulations are conducted to validate the effectiveness of the proposed guidance law for TVC

Keywords

Lyapunov methods; asymptotic stability; ballistics; missile control; missile guidance; nonlinear control systems; Lyapunov theory; aerodynamic force; asymptotic stability; midcourse guidance law; missiles with thrust vector control; nonlinear missile guidance controller; simulations; theater ballistic missile; Acceleration; Computer science; Equations; Missiles; Optimal control; Propulsion; Quaternions; Sliding mode control; Space vehicles; Torque;

fLanguage

English

Publisher

ieee

Conference_Titel

American Control Conference, 2001. Proceedings of the 2001

Conference_Location

Arlington, VA

ISSN

0743-1619

Print_ISBN

0-7803-6495-3

Type

conf

DOI

10.1109/ACC.2001.946104

Filename

946104