Research On The Separation And Formation Of Multi-interceptors

Multi-interceptors technology can effectively deal with the air threat ofprecision-guided weapons, solve the problems of multi-objective and false targets, havethe advantage of mature technology, low cost and high success rate. So it developsrapidly with the worldwide concern. This thesis studies the attitude control method, thestability analysis in separation and the formation flying control in the midcourseguidance.After the missile flies to a predetermined point, the interceptors are released frompods. The centroid and attitude equation of interceptor are built for the design andanalysis, then describe the separation process and give out the judgment of the collisionof interceptors. Firstly the decoupled linear time-invariant equations are set up based onthe separation mathematical model with the “coefficient freezing” and “small deviationlinear” approaches, then design the proportion-differential and lead-lag attitude controllaws using classical control theory. In order to deal with three-channel coupling andnonlinear, a new attitude control law is obtained based on backstepping method.Simulation results prove the new attitude control law is superior to the others in controlquality and separation performance.Secondly, the analysis of stability, speed and wind disturbance provide a theoreticalbasis for the design of separation process. Stability analysis involves the static stabilityof interceptor before commencement of the grid rudder, the initial perturbation angularvelocity, the expand time and the expand time error of grid rudder, etc. The influence onthe separation performance is also discussed. The speed analysis mainly involves theregulation time of interceptor varying with the static stability after commencement ofthe grid rudder. The Mach number and angle of attack varies with the presence ofinterfering wind, leading to the changes of aerodynamic parameters, so the influence ofwind is discussed.Finally, the midcourse guidance law and formation control command formulti-interceptors are designed. In order to improve effectiveness and reduce costs, theauxiliary and the main interceptors constitutes the formation flying to the intercept point.The midcourse guidance law and stability control system for main interceptor aredesigned. The formation tracking instruction is proved based on the state equation oftracking error. The simulation shows the validity of the tracking instruction.