Missile guidance method and device

Abstract

The embodiment of the invention provides a missile guidance method and device. The missile guidance method comprises the steps that according to the spatial position of an attack target and the spatial positions of all to-be-guided missiles, the coordinated attack time of all the to-be-guided missiles is obtained based on a proportional guidance method; according to the coordinated attack time andpreset terminal acceleration of all the to-be-guided missiles, a model prediction and static planning algorithm is used for the first time to obtain a set of control variables; according to the coordinated attack time, all the preset terminal acceleration and preset attack angles of all the to-be-guided missiles, the model prediction and static planning algorithm is used for the second time to guide all the to-be-guided missiles; and the control variables serve as initial control variables for using the model prediction and static planning algorithm for the second time. According to the missile guidance method and device, attack time and attack angle coordinated guidance of the multiple missiles is achieved, meanwhile, the model prediction and static planning algorithm can be rapidly converged, and the guidance efficiency and precision are improved.

Description

technical field [0001] The embodiments of the present invention belong to the technical field of aerospace weapons, and more specifically, relate to a missile guidance method and device. Background technique [0002] With the development of anti-missile technology, the living environment of missiles is getting worse and worse, and the penetration of missiles is also more difficult. For example, most modern ships are equipped with Close-In Weapon System (CIWS). [0003] Missiles generally need to use time-coordinated guidance to control the attack time in order to implement saturation attacks. In addition, when using missiles to attack targets, special attack angles can increase the lethality of warheads. Therefore, it is necessary to control the attack time and attack angle to achieve multi-missile time and angle coordinated attacks. [0004] At present, most guidance laws can only achieve attack angle coordination or only attack time coordination, and only a few guidance l...

AI Technical Summary

Problems solved by technology

[0005] In order to overcome the problem that the above-mentioned prior art cannot achieve attack time and attack angle at the same time or require longer time, or at least partly solve the above-mentioned problem, an embodiment of the present invention provides a missile guidance method and device

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