Design Of Guidance And Control System For Radar Guided Missile

As a core part of missile systems, guidance and control system determines the performance of the missile. In this paper, the guidance and control system of radar guided missile is designed and studied.The mathematics models of missile in pitching channel and roll channel are built and the non-corrected missile is analyzed according to the aerodynamic parameters processing and the shape parameters analyzing.The autopilot of each channel is designed in consideration of the drawbacks of non-corrected missile and the characteristics of axis-asymmetric missile. The pitching channel is designed with classical control theory and adaptive control theory, in addition, the roll channel is designed with classical control theory and sliding mode variable structure theory. The design results are analyzed and verified by simulation.A guidance law based on const trajectory inclination angle is applied in both climbing scheme and slide scheme based on missile range extension consideration. The gravity PN guidance law, bias proportional navigation guidance law based on terminal impact angle constraint and sliding mode variable structure guidance law with terminal impact angular constraint are all derived, simulated and analyzed in the terminal guidance stage. To ensure smooth instruction variation between different guidance stages, a handing-off guidance law is also designed.On the basis of certain guidance scheme, considering that the view field of radar seeker is too small, a scan law is designed to increase instantaneous field of view. Meanwhile, in order to eliminate the effect of shrink of searching acquisition area caused by decline of flight height, a method of radar antenna precession in elevation is proposed. Besides, the seeker angular tracking loop is designed to track target automatically.The 6-degree-of-freedom simulation program is designed, and the simulation is carried out for stationary target. In actual flight, the missile will maneuver in pitch, yaw and roll channel at the same time. Simulations show that the design methods accurately satisfies terminal position and impact angle constraint, which confirms the validity of design methods in this paper and also confirm that the autopilot designed on the basis of simplified linear model is suitable for nonlinear model.