Design of omnidirectional steepest roll control law for vertical launching missile

A new type of anti-tank missile is studied, and the Magnus effect of roll-to-yaw channel in the process of turning is analyzed. Under the condition of rapid response of composite linkage servo, the theory and engineering method of vertical launching which apply to the projectile quickly and accurately complete initial segment turning and all-round flight is discussed. In this paper, the guidance control model of missile's omnidirectional launch is established, and the optimal control law of roll angle based on minimum principle is designed. Considering the constraints of the projectile and steering gear, an optimal model of the roll angle control function which is suitable for engineering practice is proposed. Simulation results show that the projectile can roll in all directions at a faster speed in accordance with the designed roll angle control law based on the time required to ensure the stability of the missile attitude, which achieves the projectile roll in the air that required to complete all-round launch and it is proved that the proposed model is effective and reliable.