摘要：AbstractA guidance strategy is proposed in this paper that ensures near-zero miss distance along with simultaneous control over the direction and time of impact. The line-of-sight angle between the interceptor and the target is shaped as a nonlinear polynomial function of relative range between them. This polynomial function provides the desired line-of-sight orientations to achieve the mission objectives. The coefficients of the line-of-sight polynomial are obtained by subjecting it to the boundary conditions that adhere to the desired terminal constraints. A controller is designed using the nonlinear dynamic inversion control technique to track the reference flight path directions derived using the desired line-of-sight orientations. The simulation results obtained from various numerical simulations validate the efficacy of the proposed guidance law.
