基于虚拟视角约束的机动目标拦截制导方法

To enable the missile to intercept one maneuvering target with a certain terminal attack angle, a guidance method for interception of the maneuvering target with terminal virtual look angle and terminal line-of-sight angle constraints is proposed. According to the transform relationship between the motion vectors in the velocity coordinates system, the nonlinear model of relative motion in the virtual coordinates system is established. Then, the thought of polynomial guidance in the linear model is introduced into the nonlinear model creatively. Through the constraints of the terminal virtual look angle and the terminal line-of-sight angle, the solution of the polynomial virtual control variable of the distance between the missile and the target is derived. Finally, according to the transformation relation between the virtual vectors and the motion vectors, the acceleration command expression in the velocity coordinates system is obtained. Simulations under the conditions of different guidance coefficients, terminal attack angles and types of maneuvering targets are carried out to verify the method proposed. The simulation results are compared with those of the optimal guidance law of Trajectory Shaping Guidance. Simulation results show that the proposed guidance lawallows the missile to intercept the maneuvering target with a desired attack angle and the terminal virtual look angle converges to zero, which can avoid terminal command saturation.