Study On Guidance And Control Problems For Air To Air Missile

As a core part of missile systems, guidance and control system determines theperformance of the missile. In the background of the terminal intercept of long-range airto air missile，the dissertation designs guidance and control system which meets theperformance requirements of the missile. Main research is listed as follows:Establish and analyze missile dynamical model. This paper describes the use andtransformation of the coordinate system and establishes the six degrees of freedom forthe missile, and analyzes the trajectory characteristics and missile characteristics. Theresult demonstrates that the designed parameters of the missile are reasonable, andprovides the basis for the follow-up work.Design missile terminal guidance law. Considering the missile would attacks highmaneuvering targets, the dissertation designs two guidance laws: proportional guidancelaw with the line of sight angular acceleration compensation and variable structureguidance law which has strong robustness against uncertainties. Simulation results showthat the proportional guidance law can quickly track the acceleration of maneuveringtarget, variable structure guidance law can emerge smooth command acceleration whichrange is small. These two guidance laws can get better guidance result for highmaneuvering targets with a certain project application value.Design ADRC attitude controller. The missile control system model is nonlinearand strong coupling, also with model uncertainties, the dissertation uses ADRCtechnology design ADRC controller, and use extended state observer to estimate andcompensate the disturbance of the system. The simulation results show that thecontroller has good control precision and dynamic quality.Integrated guidance and control design. A guidance and control full state couplingmodel is established, which links rudder angle directly to the information of relativemovement, and target acceleration information is treated as the bounded uncertainties ofsystem, and an integrated inversion controller is designed. The simulation results showthat compared with the traditional means which designs guidance system and controlsystem separately, integrated guidance and control design is more advantageous, whichcan not only reduce the required overload of the missile than traditional designs method,but also avoid states losing stability when the missile approach the target, and moresuitable for attacking high maneuvering target.