基于运动伪装理论和冲击角约束的拦截导弹末端制导律

An improved motion camouflage guidance law considering impact angle constraint is developed for interceptor missiles intercepting maneuvering targets with unknown acceleration in three-dimensional scenarios. The relative motion equation is derived in the sight rotation coordinate system based on spatial position relationships. Interception conditions are established through motion camouflage characteristics，leading to the formulation of a terminal guidance law incorporating impact angle constraints. A finite-time extended state observer is designed to address the challenge of unmeasurable target maneuver information，enabling accurate estimation of target acceleration and mitigating the impact of unknown maneuvers on interception accuracy. The simulation results show that the proposed guidance law can hit the target faster and more accurately with the desired impact angle under the premise of smaller overload and line-of-sight rotation rate, which proves the effectiveness and superiority of the algorithm.