三维非线性变结构寻的制导律

High precision 3-D nonlinear variable structure guidance law for homing missile

建立了球坐标系内的三维导弹与目标相对运动模型,基于零化导弹与目标的视线角速度设计了非线性三维变结构鲁棒末制导律。该制导律考虑了更一般的拦截情况,不依赖于碰撞线附近线性化的假设,克服了剩余时间的估计误差对制导精度的不利影响。仿真结果表明,该制导律对于目标做复杂的大机动逃逸运动,仍然能够取得较好的脱靶量。

Three-dimensional relative motion model of missile and target is established, it considers the target's acceleration as the input disturbance and then derives the strongly robust adaptive guidance law based on zeroing normal speed of LOS (line-of-sight). 3-D nonlinear variable structure guidance law for homing missile based on zeroing speed of LOS angle is presented in this paper, the adaptive law can estimate the uncertain boundary of target's maneuvering acceleration. The more general combat environment is considered in the algorithm, so it is depended on the hypothesis of the linearization near collision course, and overcomes the influence that the estimation error of the surplus time brings to the guidance precision. The simulating results indicate that the guidance law exhibits strong robustness properties against disturbances from target's maneuvers. The guidance algorithm is very simple and never needs the boundary of the acceleration of target, so it is more convenient for comprehension and practical implementation.