Research On The Control Method Of Hypersonic Glider Cluster Formation

Hypersonic glide missile is a new type of combined missile,it has the advantages of long range,fast flight speed,large lift-to-drag ratio,and strong maneuverability,so it can effectively penetrate the defense and achieve the precise attack on the target.At the same time,the coordinated operation of missile cluster has good robustness and concealment,and can improve the penetration ability of the missile.Therefore,the combination of the above two factors can give full play to their advantages and solve the problem of how to improve the cooperative combat capability of glide cluster.This paper mainly studies the guidance and control of glider missile,mainly from the formation control of balanced glide segment,the design of multi-constraint terminal guidance law of subduction segment,and the co-guidance of multiple gliders.Firstly,aiming at the formation control problem of gliding aircraft,a formation control method considering aerodynamic characteristics is designed.Through the linearization,relative motion equations who considering the aerodynamic characteristics are obtained.The kinematics control quantity of relative distance by using the method of Terminal sliding mode control,and then the quantity is transformed into dynamic control equation constraints to get further simplified relative motion equation.There is a single input multiple output(SIMO)underactuated system in the end.Using decoupling sliding mode control method for the formation,the low Angle,azimuth Angle are under effective control.The simulation shows that the glider can form a stable formation eventually.Then a 3d terminal guidance method based on real-time update of parameters is proposed for multi-constraint terminal guidance in subduction section.In this method,the three-dimensional motion is decomposed into horizontal and vertical planes,the optimal trajectory is calculated in real time to obtain the Angle command satisfying the terminal constraint,and the time is controlled by controlling the change of track Angle in the front section of the longitudinal plane.The applicability and robustness of the method are verified by numerical simulation.Finally,to solve the problem of co-guidance of multiple gliding projectiles,the final guidance law considering multi-constraint conditions is used to realize the co-guidance in the form of open loop.At the same time,a closed loop co-guidance method is proposed based on the "collar-slave" collaborative architecture,and its stability is verified by simulation.