Strong tracking terminal guidance method

Abstract

The invention provides a strong tracking terminal guidance control method in order to realize terminal guidance control over a missile interception target. According to the main design idea of the guidance control method, a missile-target sight angle changing in real time serves as a tracking control target, the track angle of an interception missile is controlled to rapidly track the missile-target sight angle, and therefore the purpose of strong tracking of the missile interception target is achieved. In order to realize the interception target, a controlled missile-target tracking error system is established, a coupled PI terminal guidance law is designed accordingly, the robust stability and disturbance rejection robustness of a missile-target tracking control system are theoretically analyzed, a simulation result not only verifies the rationality of the theoretical analysis, but also indicates that the coupled PI terminal guidance control method has strong tracking capability of enabling the interception missile to quickly track the target, and therefore the method has important scientific significance and application value in the field of terminal guidance control.

Description

technical field [0001] The invention relates to a terminal guidance control method, in particular to a strong tracking terminal guidance control method. Background technique [0002] The use of precision-guided weapons to accurately and quickly intercept targets is the main combat method in present and future wars. The design of the terminal guidance law not only requires the missile to hit the target with a small amount of miss, but also requires the missile to hit the target at a specific attack angle in order to maximize the damage effect on the combat target. The guidance laws widely used in recent years mainly include optimal control guidance law, differential game guidance law, control guidance law and sliding mode control guidance law. In modern warfare, when the high-speed flying missile hits the target, the time left for the terminal guidance is often only a few tens of seconds, which urgently requires that the line of sight (LOS) angular rate of the missile can be...

AI Technical Summary

Problems solved by technology

However, at the end of the missile guidance terminal, when the relative distance r→0, the LOS angular acceleration will be caused The singularity of the situation increases the difficulty of control, making the design of the guidance law very complicated, and can only sacrifice the index of hitting the target at zero distance.

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