Three-dimensional guidance and control for missile

In order to ensure hit target as well as trajectory constraint, the design method based on differential geometry and eigenstructure assignment theory is presented to solve the problem of missile's three-dimensional integrated guidance and control. With a view to coupling between guidance loop and control loop, and coupling between longitudinal channel and lateral channel, and three-dimensional relative geometry relation between missile and target, the integrated guidance and control model was presented. According to this model, the feedback linearization method of integrated guidance and control was given using by differential geometry theory. The design method was given based on the eigenstructure assignment theory to ensure anticipant performance of system. Simulation results show that miss distance is less than 0.5 m, and trajectory inclination angle more than 83.5°, and angle of trajectory rotation is less than 5.5°. Therefore this integrated guidance and control method can implement efficiently hitting target as well as ensure attack constraint.