Dept. of Electr. Eng., National Taiwan Univ.LI-CHEN FUChang, Wei-DerWei-DerChangChuang, Dung-MingDung-MingChuangKuo, Te-SonTe-SonKuoWang, Tze-ChienTze-ChienWangTsai, Chi-WangChi-WangTsai2007-04-192018-07-062007-04-192018-07-061997-0607431619http://ntur.lib.ntu.edu.tw//handle/246246/2007041910031864https://www.scopus.com/inward/record.uri?eid=2-s2.0-0030652284&partnerID=40&md5=88a8d87d6eaf6d603b6e1e664ab66004This paper is an integration of two earlier results on missile guidance and autopilot. 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 on-line, 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.application/pdf383637 bytesapplication/pdfen-USAdaptive control systems; Approximation theory; Control system analysis; Error compensation; Feedforward neural networks; Missiles; Nonlinear control systems; System stability; Bank to turn missiles; Missile autopilot; Nonlinear constant bearing guidance; Electronic guidance systemsconference paper10.1109/ACC.1997.6119602-s2.0-0030652284http://ntur.lib.ntu.edu.tw/bitstream/246246/2007041910031864/1/00611960.pdf