Control System Design For Missile With Morphing Swept Wings

Variable sweep wing missile (VSWM) will play an important role in modern weaponry and military war with its long range, high mobility and good damage effects. The complexed aerodynamic characteristics and features of runing in subsonic/transonic supersonic of sound makes robust design for control system a challenging task. So the dissertation develops deep study around this practice background on model and aerodynamic analysis, trajectory optimization, G&C system design, and simulation of G&C system for VSWM.First, based on the full reference to domestic and foreign literatures, this dissertation establishes flight model of VSWM, and then the simplified control system model is delivered. The aerodynamic characteristics and dynamic response characteristics of elastomers are analyzed, which laid the foundation for subsequent work carried out in this article.Second, for solving the trajectory optimization problem of VSWM, the Particle Swarm Optimization (PSO) method, which is appropriate for solving multivariable, nonlinear and time-varying problem, is studied. The optimization results suggest that the VSWM has the capability of extend range and improve off-speed in gliding and diving trajectory.Third, the design method for guidance law of VSWM is studied. Based on optimal control theory, terminal guidance law is derived and the stability of the guiding trajectory is analyzed in detail. The middle guidance law is based on a virtual target tracking method, and the robustness of the wind disturbance is analyzed. At the end, the guidance law shifting problem is analyzed in two respects of seeker shifting and trajectory shifting problems.Fourth, according to the control features of VSWM, we take the autopilot design of longitudinal channel as an example to exam the effect of parameters tuning adaptive algorithm in designing control system parameters. The influence of wing elastic vibration to the control system is considered as interference. Finally, notch filter is adopted to eliminate the effect of wing elastic vibration.Fifth, for G&C system of VSWM may be full checked up reasonable, numerical simulation is done to analyse guide prescion by means of Mento Carlo Methods. The various interference factors that influence an accuracy of hit are analyzed, and the simulation results under standard conditions are delived.