Cooperative Guidance Control Method In Multi-missile

With the continuous development of modern missile technology,the capability of missile breakthrough has become increasingly strong,the difficulty of defense and interception of missiles has also increased.In order to make up for the deficiency of single missile,multi-missile time coordinated guidance is used to intercept at the same time,and then the interception capability is improved.This paper discusses the cooperative guidance background of multiple missiles intercepting multiple targets collaboratively,the missile's midcourse guidance and the terminal guidance are both outside the atmosphere,it can only actively consume fuel for orbit control,so fuel is very valuable,it is hoped that coordinated guidance can be achieved with the aim of achieving the goal of simultaneously intercepting multiple targets while saving fuel as much as possible.For multi-missile coordinated guidance,since the target's flight trajectory can be predicted,we can predict the position of the target at a given time and regard it as the predicted-hit-point.considering that the missile uses switch-type orbit-controlled engine,based on the idea of formation flying,it is divided into main and anxiliary missile,in the process of midcourse guidance,the main missile uses the Lambert guidance strategy,and the auxiliary missile uses the Hill guidance strategy relatived to the main missile.The two guidance strategies can control the missile's flight trajectory according to the selected predicted-hit-point and interception time,and the time to reach the predicted-hit-point is controllable.At the same time,adopting Hill guidance for auxiliary missiles is more conducive to adjust their distance from the main missile during the flight.This midcourse guidance strategy is combined with the missile's terminal guidance law(eg,the variable structure guidance law),when the target-missile relative distance enters the seeker detection distance,it is transferred to the terminal guidance mode,the flight time can be controlled and the accuracy of hit can be ensured.For the collision avoidance of missiles,this paper first proposes the principle of target allocation,and then uses the golden section method to calculate the minimum distance between two orbiting vehicles,and predicts the minimum distance between any two missiles.Reasonable target allocation principles can reduce the interference or collision between missiles to a certain extent,in the missile's flight process,in order to further ensure that the missiles have enough safe distances from each other,this paper proposes the hover control of the auxiliary missile relative to the main missile.Finally,the above algorithm and strategy are verified,which validates the effectiveness of the proposed guidance control strategy and target allocation strate gy.The accuracy of the interception of multiple targets and the consistency of the hit time are verified.