Abstract
A trajectory tracking guidance law is designed based on feedback linearization theory and optimal control theory, aiming at the influence of external random disturbance on target trajectory. Six-degree-of-freedom model of target missile is built by Simulink. The influence of different interference on target trajectory is analyzed, and the main control variables affecting target trajectory are given. Then the motion model is simplified to the longitudinal plane, and the simplified non-linear equations of target missile motion are obtained by force analysis. Then, according to the definition and necessary and sufficient conditions of feedback linearization theory, the precise linearized motion equation of target missile is derived in detail. Finally, the trajectory tracking guidance instructions are designed by using the linear quadratic optimal control method, and are compared with the tracking guidance laws based on the small perturbation method and the solidification coefficient method. The results show that the trajectory tracking guidance law designed in this paper can well correct the interference received by the target missile in flight and has high tracking accuracy.
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