Finite time speed tracking guidance law design method

Abstract

The invention discloses a finite time speed tracking guidance law design method. The method comprises the following steps: step 1, establishing a mathematical model of a guidance system; 2, designinga finite time speed tracking guidance law; 3, defining a design parameter adjustment method; and step 4, testing the performance of the guidance law. According to the method, a speed tracking guidancelaw is designed based on a finite time control theory, it is theoretically guaranteed that the speed tracking error angle of the missile converges to zero within finite time, and therefore it is guaranteed that the missile accurately hits a target. The fractional power term is introduced into the guidance law designed by the invention, and the guidance law can have better anti-interference capability according to an existing finite time control theory research result.

Description

technical field [0001] The invention belongs to the field of aerospace, and relates to a speed tracking guidance law design method based on finite time control theory, in particular to a speed tracking guidance law that can theoretically ensure that the speed tracking error angle of a missile converges to zero within a limited time design method. Background technique [0002] Velocity-seeking guidance is a guidance method widely used by many low-cost guided weapons. The basic principle is to make the missile speed direction point to the target direction, that is, make the missile speed tracking error angle (that is, the angle between the speed direction and the line of sight direction) be zero, so as to achieve precise strikes on the target. The traditional speed tracking guidance command is generally formed according to the ratio of the speed tracking error angle. This method cannot guarantee the convergence of the missile speed tracking error angle to zero theoretically. ...

AI Technical Summary

Problems solved by technology

The traditional speed tracking guidance command is generally formed according to the ratio of the speed tracking error angle. This method cannot guarantee the convergence of the missile speed tracking error angle to zero theoretically.

In recent years, some speed tracking guidance laws based on Lyapunov's asymptotic stability theory have also appeared, but these results can only guarantee that the missile speed tracking error angle asymptotically converges to zero theoretically (that is, the convergence time is infinite)

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