A Guidance Information Fusion Method for Suppressing Low-frequency Swing of Missile Terminal Guidance Section

Abstract

The invention discloses a guidance information fusion method for suppressing the low-frequency swing of the projectile body in the terminal guidance section of a missile. The specific steps are: building a guidance information fusion platform; a projectile visual line-of-sight turn rate module A determining the projectile based on radar measurement information and inertial navigation measurement information. Visual line-of-sight rate; the projectile-eye line-of-sight rate module B determines the projectile-eye line-of-sight rate based on the seeker measurement information; the projectile-eye line-of-sight rate fusion module determines the projectile-eye line-of-sight rate for calculating the overload command; the overload command module determines overload instruction. The present invention can solve the problem of the low-frequency swing of the projectile body in the terminal guidance section caused by the multipath effect, and make up for the deficiencies of the existing methods. The line-of-sight rate decreases with the projectile-to-target distance from part to all to form the overload command, reducing the impact of the overload command oscillation on the projectile attitude.

Description

technical field [0001] The invention relates to a guidance information fusion method of a missile, in particular to a guidance information fusion method for suppressing the low-frequency swing of the projectile body in the terminal guidance section of the missile. Background technique [0002] When a missile intercepts an ultra-low-altitude target, due to the multipath effect, the detection and tracking performance of the seeker is significantly reduced. The multipath effect is the strongest in the early stage when the mid-guidance is transferred to the terminal guidance, which makes the low-frequency oscillation of the deviation of the line-of-sight angle of the projectile output by the seeker the strongest. In the existing method, once the intermediate guidance is transferred to the final guidance, the deviation of the sight angle output by the seeker is all used to form the overload command. The overload command is proportional to the angular deviation signal output by t...

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to provide a guidance information fusion method that suppresses the low-frequency swing of the missile body in the terminal guidance section, and solve the problem of low-frequency swing of the missile body in the terminal guidance section caused by multipath effects

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