多高超声速导弹协同末制导律及可行初始位置域研究

Aiming at the problem that multi-hypersonic missiles can realize saturation attack to the target with a specified impact angle,a terminal guidance law with constraints of impact angle and impact time was proposed,and the feasible initial position domain of terminal guidance of missiles was studied. A relative motion model of missiles in the three-dimensional space was established. The vertical and lateral guidance command was used to realize the impact angle control and the impact time control respectively,and a three-dimensional cooperative terminal guidance law was formed. Adopting the law,the constraints of final velocity and available overload of missiles were considered,and the initial position of terminal guidance of missiles was taken as a design variable,and the difference between the actual impact time and the ideal impact time was taken as the performance index function,and an optimization model was established. The model was solved to obtain one-dimensional and two-dimensional feasible initial position domains of terminal guidance of missiles. Simulation results show that the three-dimensional cooperative guidance law can make multiple-missiles hit the target at the designated impact time with the required impact angle,and the position domain solving-method can be used to obtain the feasible initial position domains for each missile under given constraints.