Dynamic inverse control of feedback linearization in ballistic correction based on nose cone swinging

Abstract

It is a complicated nonlinear controlling problem to conduct a two-dimensional trajectory correction of rockets. By establishing the aerodynamic correction force mathematical model of rockets on nose cone swinging, the linear control is realized by the dynamic inverse nonlinear controlling theory and the three-time-scale separation method. The control ability and the simulation results are also tested and verified. The results show that the output responses of system track the expected curve well and the error is controlled in a given margin. The maximum correction is about ±314 m in the lengthwise direction and ±1 212 m in the crosswise direction from the moment of 5 s to the drop-point time when the angle of fire is 55°. Thus, based on the dynamic inverse control of feedback linearization, the trajectory correction capability of nose cone swinging can satisfy the requirements of two-dimensional ballistic correction, and the validity and effectiveness of the method are proved.

Keywords

nose cone swinging / two-dimensional ballistic correction / feedback linearization / dynamic inverse control / three-timescale separation method

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