This paper addresses the problem of maximizing the warhead effectiveness, by achieving impact at the structurally vulnerable points of the targets. The impact direction is first defined using target frame, and then a unique relation between the desired impact angles and the desired line-of-sight angles is derived. Using this relation, two nonlinear guidance strategies, based on finite-time sliding mode and optimal control methods, are proposed to achieve interception of maneuvering targets at a pre-specified desired impact orientation. Unlike most of the existing three-dimensional guidance strategies, the proposed guidance strategies are derived without decoupling nonlinear coupled engagement kinematics into two mutually orthogonal planes and performing linearization, thereby avoiding possible performance deterioration for engagement with large heading errors. The performances of proposed guidance strategies are evaluated for various engagement geometries as well as constant speed and different realistic time-varying speed pursuer models subjected to aerodynamics parameter variations, and found to be satisfactory.

本文通过对目标的结构脆弱点产生影响，解决了使弹头效能最大化的问题。首先使用目标框架定义冲击方向，然后得出所需冲击角和所需视线角之间的唯一关系。利用这种关系，提出了两种基于有限时间滑模和最优控制方法的非线性制导策略，以在预定的期望冲击方位上实现对机动目标的拦截。与大多数现有的三维制导策略不同，所提出的制导策略无需将非线性耦合啮合运动学解耦到两个相互正交的平面中并执行线性化，从而避免了大航向误差时可能导致的性能下降。针对各种接合几何形状以及恒定速度和受空气动力学参数变化影响的不同现实时变速度追踪器模型，对所提出的制导策略的性能进行了评估，结果令人满意。