Performance investigation of control and guidance system for a spinning flight vehicle with dithering canard

In this paper, control and guidance system of a spinning flight vehicle with a single plane of dithering canard control fins are investigated. Decreasing the number of actuators, lowering the vehicle weight, and reducing the final cost are outcomes of applying two canard controls; however, the control system will become complicated due to guidance system interaction. Producing asymmetric force and torque in yaw direction is the result of this interaction. Dithering canard is proposed for proper control of this spinning vehicle. Dithering canard adjusts its deflection with respect to the roll attitude of the flight vehicle. In this paper, a method is proposed for control and guidance of this spinning vehicle with dithering canard. This method is investigated in a six DOF flight simulation in presence of IR seeker, autopilot, gyro, actuators. Appropriate simulation results in various flight situations verify the proper performance of this new control method.