Research On Combined Control System For An Atmospheric Interceptor Controlled By Lateral/Aerodynamic Forces

The actical missile requires the lateral/aerodynamic forces combined controltechnology to improve the maneuvering capability and response speed of endo-atmosphereinterceptor missile as the solo aerodynamic force cannot control the interceptor missilestrike with high maneuvering target accurately due to the high combat airspace and highmobility requirements. In this paper, the attitude combined control problems ofendo-atmosphere interceptor missile with the lateral force/aerodynamic combined controlare studied deeply.The model of impulse thruster for attitude control is established based on the workingcharacteristics of impulse thruster for attitude control, and on this basis the dynamics andkinematics model of interceptor missile with the lateral/aerodynamic forces combinedcontrol is set up. In addition, the motion equation of pitch, yaw and roll channels includinglateral force, which makes the foundation of lateral/aerodynamic forces combined controlsystem design and analysis, is given out.Typical aerodynamic shape missile engineering calculations of the aerodynamiccoefficients is studied. With the aid of MATLAB this calculation method is realized, and theusefulness and accuracy of the engineering calculation method is verified by aerodynamiccoefficients calculation of typical cases. Meanwhile, ignition logic of impulse thruster forattitude control is researched according to the structure layout of the impulse thruster forattitude control. The ignition logic based on the vector synthesis is designed, and thesimulation experiments of the ignition logic are carried out.As for interceptor missile with lateral/aerodynamic forces combined control, attitudecontrol system design methods based on the classical control theory and based on slidingmode variable structure control theory are proposed respectively by making the pitchchannel stabilization loop as the research targets. Based on the frequency domain method inclassical control theory, the aerodynamic control loop and the lateral force control loopwhich contains the aerodynamic control loop, are designed, and the direct force discretecontrol system is obtained by discretization, to realize the lateral/aerodynamic forcescombined control. What’s more, the discrete characteristics of direct force control systemand the continuity of aerodynamic control are analysed，and based on the sliding modevariable structure control theory, the lateral/aerodynamic forces combined control system isdesigned by using lateral force to follow the switching control. According to the proposed lateral/aerodynamic forces combined control system designmethod the simulation and comparative analysis of the designed control system is carriedout in the case of the aerodynamic coefficients perturbation on one characteristic point. Thesimulation results show that the effectiveness of the combined control systems designedbased on the classical control theory and based on sliding mode variable structure controltheory.