Research on Three-loop Autopilot for Rolling Missile Based on Linear Quadratic Optimal Control Theory

doi:10.3969/j.issn.1000-1093.2015.05.010

Abstract

Abstract: A dynamical model including cross-coupling effects of rolling missile is built. The couplings among the channels are regarded as external interference. The linear quadratic（LQR）optimal control theory is used to propose a design method of three-loop autopilot and analyze its general features. The research on the relationship between the weight coefficient matrix and the autopilot performance could assist a designer in choosing the weight coefficient matrix. The dynamical model is perceived as multiple-input multiple-output（MIMO）system, and the corresponding control system of rolling missile is designed. The results show that the three-loop autopilot using single-channel design do well in restraining the influence of couplings in rolling missile with state couplings, which has little difference from the control law derived by MIMO design. The simulation validates the correctness of the above conclusion.

Key words: control and navigation technology of aerocraft, rolling missile, three-loop autopilot, linear quadratic regulator, channel coupling

CLC Number:

TJ765.4

FAN Shi-peng， LIN De-fu， YAO Huai-jin, LU Yu-long， QI Zai-kang. Research on Three-loop Autopilot for Rolling Missile Based on Linear Quadratic Optimal Control Theory[J]. Acta Armamentarii, 2015, 36(5): 831-838.

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