Design Of Guidance And Control Systems For Cooperative Missiles

The performance of the modern weapon system has made a great progress with the development of technology,weapon electronic system and self-organizing network.The performance of a single missile is also increasing as well as high prices and expensive maintenance costs.At the same time,the anti-missiles systems of various countries are constantly updated and innovated,such as “Sade” and “Patriot” anti-missile systems.Therefore,in order to improve the penetration capability and campaign efficiency,the idea of multi-missiles cooperative engagement is carried out.It can complement the functions of the missiles in the group through the communications between several inexpensive and functional differently missiles,so as to enhance the overall combat capability and greatly reduce costs.This paper will take multi airto-ground missiles as the research scenario to study related research on the design of guidance and control system for missiles in a group.Firstly,on the basis of some reasonable assumptions,a six degree-of-freedom mathematical model of missile is presented by Newton-Euler method according to the well used coordinate systems.The missile target relative motion model is derived in 2D plane and 3D space,respectively.Through the derivation of the basic model of missile and the relative motion model,the foundation is laid for the proposition of the “efficient information” and the design of cooperative guidance laws.Secondly,this paper presents an offline multi-missiles cooperative midcourse guidance strategy for multi-missiles engagement scenario.The midcourse guidance problem is transformed into a two-point boundary problem through appropriate model simplification and theoretical analysis.Based on the three degree-of-freedom kinematics model of missile,a suboptimal midcourse guidance law is proposed by using the singular perturbation technique.Then,the idea of “efficient information” is proposed firstly for multi-missiles cooperative engagement scenario.It represents a kind of useful information for improving missile interception accuracy.Meanwhile,through the theoretical analysis of the “efficient information”,it can be found that the “efficient information” effective time proposed in this paper can be used to describe the missile’s ability to attack a specific stationary target.The lager the effective time is,the stronger the missile’s ability is.Based on the effective time of the “efficient information”,this paper extends the current switched gain impact angle proportion guidance method,and gives the quantitative relationship between the effective time and the desired impact angle constraint.In addition,a new collisionavoidance cooperative guidance law is proposed by combining the effective time and the artificial potential field method.It can not only ensure that the missile hit the target accurately,but also carry out certain collision avoidance,which is more suitable for the future cooperative attack mission in complex battlefield environments.What’s more,for the attitude-oriented control model of missile,a sliding mode controller and a disturbance observer are used to design the autopilot,which solves the influence owing to matched/mismatched disturbance of the attitude control system.Based on the Lyapunov theory,it is proved that the attitude tracking error is bounded in the presence of disturbances.Finally,the effectiveness of the proposed multi-missiles sub-optimal midcourse guidance law,the impact angle guidance law,the cooperative anti-collision guidance law and the sliding mode controller are verified by the simulation of the whole trajectory.The simulation results are analyzed and the future development directions of the research are given.