A nonlinear constant bearing guidance and adaptive autopilot design for BTT missiles

Author

Fu, Li-Chen ; Chang, Wei-Der ; Chuang, Dung-Ming ; Kuo, Te-Son ; Wang, Tze-Chien ; Tsai, Chi-Wang

Author_Institution

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

Volume

5

fYear

1997

fDate

4-6 Jun 1997

Firstpage

2774

Abstract

This paper is an integration of two earlier results on missile guidance and autopilot (Chuang, 1993; Chang, 1995). The guidance design is a nonlinear implementation of the constant bearing guidance. The guidance command in the form of acceleration is transformed into acceptable forms for the autopilot design. This design incorporates feedforward neural networks in the structure of adaptive control. Its weighting matrices and other unknown parameters are tuned online, and the approximation error of the neural networks is compensated via the technique of sliding mode control. Stability and performance for the integrated system are also investigated

Keywords

adaptive control; control system synthesis; digital simulation; feedforward neural nets; missile guidance; neurocontrollers; nonlinear control systems; stability; variable structure systems; BTT missiles; adaptive autopilot design; approximation error; feedforward neural networks; nonlinear constant bearing guidance; sliding mode control; Acceleration; Actuators; Adaptive control; Computer science; Design engineering; Equations; Kinematics; Missiles; Neural networks; Stability;

fLanguage

English

Publisher

ieee

Conference_Titel

American Control Conference, 1997. Proceedings of the 1997

Conference_Location

Albuquerque, NM

ISSN

0743-1619

Print_ISBN

0-7803-3832-4

Type

conf

DOI

10.1109/ACC.1997.611960

Filename

611960