Multi-missile cooperative guidance method based on output consistency

Abstract

The invention discloses a multi-missile cooperative guidance method based on output consistency. The method comprises the steps that constraint conditions of normal acceleration and field angles of all missiles are given; a linear model on which the missile status depends is built on the basis of a relative motion relationship of missiles and a target, convergence variables, line-of-sight angle rates and field angles of the linear model on which the missile status depends are selected as output variables, and a predictive control model is built according to a set prediction time domain; a performance index function is obtained on the basis of requirements of predictive control model and missile striking time cooperation; the performance index function and the constraint conditions are converted into a quadratic programming standard form; an optimal model achieving multi-missile cooperative guidance is obtained, normal acceleration of all the missiles on the present moment is obtained by means of a convex optimization method, and updated statuses of all the missiles are adopted on the next moment till all the missiles hit the target. According to the multi-missile cooperative guidance method based on the output consistency, optimal cooperative guidance on the condition that normal acceleration overload and field angles are limited can be achieved.

Description

technical field [0001] The invention belongs to the technical field of guidance, and in particular relates to a multi-projectile cooperative guidance method based on output consistency. Background technique [0002] With the continuous development of missile interception systems, the tactics of relying on a single missile to penetrate the defense and achieve strikes are gradually restricted. The method of using multiple missiles to achieve saturation attack on the same target and destroy targets with certain interception capabilities has become the main means to ensure the survivability of missiles on the battlefield and improve the success rate of strike missions. Starting from this idea, designing a cooperative guidance method that drives multiple missiles to hit the target at the same time is of great significance for the advancement of defense penetration technology. [0003] The existing coordinated guidance method for ensuring simultaneous strikes has the following pr...

AI Technical Summary

Problems solved by technology

This will easily cause the trajectory to be too curved. If the limitation of the field of view is not considered in the design of the guidance law, it will be difficult to ensure that the seeker's field of view always captures the target.

[0006] 3) Due to the limited deflection of the rudder surface of the missile, the normal acceleration of the missile is limited, resulting in a saturation nonlinearity in the input of the missile control system

[0007] 4) Designing the hit time control guidance law for a single missile, and then specifying the hit time cooperative guidance method, does not consider the missile group as a whole, and cannot achieve optimal overall performance

[0008] To sum up, the existing technology mainly designs the time-to-hit control guidance law for a single missile, instead of solving the cooperative guidance problem as a cluster problem, and does not consider various physical constraints

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