Design Of Multi-missile Cooperative Guidance Law With Attack Angle Constraint

With the development of the form of war, and antimissile system are becomingmore and more perfect, which leads to the increasing difficulty of defense of singlemissile. Besides, in modern warfare’s, the demands of coordinating military operationsamong multi-branch armed forces are also increased. Therefore, multiple cooperatingmissile attacks better meet the requirements of modern informationization militaryoperation. By sharing information, communicating with each other and some othermeasures, multiple missiles could form more effective operating modes, which arecomplementary in function, collocated in direction and coordinated between differentplatforms. Multiple cooperating missile attacks not only greatly improves defense butalso has the advantage of being of tactical stealth and promoting electronic warfare. Inorder to meet the requirements of precisely striking targets, some restrictive conditionssuch as satisfying the expected attacking angles need to be added on the basis ofmultiple cooperating missile attacks. This thesis makes a deep research in multi-angleconstraints collaborative missile guidance law.Firstly, the relative motion model between missile and target has been analyzedand the research contents as well as the technical specifications which should be methave been made clear. Besides, the advantages and limitations of traditional guidancelaw has been discussed and simulated. What’s more, some basic knowledge of slidingmode variable structure control has been introduced and the design has been decided toinclude sliding mode variable structure control.Secondly, a single missile with the limitations of impact time and attacking anglehas been researched. Two modes of control, one of them satisfying the attacking time,the other satisfying the attacking angle, have been respectively designed. A shiftingstrategy has been designed to meet the two binding conditions in order to consideringboth the impact time and attacking angle during the fly of missile.Finally, the mode of guidance law of one missile has been extended to that of multimissiles. In order to realize the requirement of intercommunication between missiles,we make the estimate of missiles remaining time as the amount of interaction; deduce aunified value as all missiles’ attack time and finally realize autonomous negotiation andcoordinated operations between the shells. In addition, in order to combat maneuveringtargets, we use the disturbance observer to observe and estimate system unknowns, andadjust the guidance law form. The simulation results show that the designed guidance law can not only accurately hit the maneuvering targets, but also satisfy the constraints,which prove the effectiveness of the designed guidance law.