A time-coordinated guidance method for multiple missiles with collision angle constraints

Abstract

The invention discloses a multi-missile time cooperative guidance method with collision angle constraints, which establishes a new missile and target dynamic equation in a reference coordinate system and designs a guidance law with terminal collision angle constraints based on optimal control theory; The error between the flight time and the expected remaining flight time is used as the sliding mode surface, so that the remaining flight time of the missile tends to the expected remaining flight time, and the time-controllable guidance law is designed based on the sliding mode control theory; then the terminal collision angle controllable The switching strategy of the guidance law and the time-controllable guidance law enables the missile to hit the target at the desired time and angle; establish a multi-missile time-coordinated communication network, and design coordination variables based on the two-layer cooperative guidance architecture to make the remaining flight time of the missile tend to be consistent , so that each missile hits the target at the same time at the desired collision angle. A true multi-missile time coordination has been realized.

Description

technical field [0001] The invention belongs to the technical field of missile guidance, and in particular relates to a multi-missile time cooperative guidance method with collision angle constraints. Background technique [0002] With the continuous development of anti-missile technology in various countries, a single missile can no longer complete the combat tasks of penetration and interception. The coordinated guidance law strategy in which multiple missiles carry out saturation attacks on the same target at the same time can effectively improve the battlefield survivability and interception success rate of missiles. At present, most of the research on coordinated guidance at home and abroad focuses on time coordination, and time coordination guidance strategies can be divided into the following two types: [0003] 1) Set the expected flight time in advance, control the collision time of each missile independently, and launch all missiles at the same time, then each mis...

AI Technical Summary

Problems solved by technology

However, the first collaborative strategy in the prior art mainly studies the guidance law with controllable collision time for a single target, and then sets the same flight time for each missile to hit the target at the same time. There is no communication between the missiles. Coordination in the true sense; while the second guidance strategy in the prior art is mainly based on the multi-agent coordination theory to design the guidance law. Although the mutual communication between the missiles has been realized in this way, it is assumed that the acceleration of the missile speed and direction is controllable. Missiles with solid rocket motors are not suitable

In addition, there are few studies in the prior art that consider both the end collision angle constraint and the multi-missile time coordination

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