A new design method for trajectory shaping guidance laws with the impact angle constraint is proposed in this study. The basic idea is that the multiplier introduced to combine the equations for the terminal constraints is used to shape a flight trajectory as desired. To this end, the general form of impact angle control guidance (IACG) is first derived as a function of an arbitrary constraint-combining multiplier using the optimal control. We reveal that the constraint-combining multiplier satisfying the kinematics can be expressed as a function of state variables. From this result, the constraint-combining multiplier to achieve a desired trajectory can be obtained. Accordingly, when the desired trajectory is designed to satisfy the terminal constraints, the proposed method directly can provide a closed form of IACG laws that can achieve the desired trajectory. The potential significance of the proposed result is that various trajectory shaping IACG laws that can cope with various guidance goals can be readily determined compared to existing approaches. In this study, several examples are shown to validate the proposed method. The results also indicate that previous IACG laws belong to the subset of the proposed result. Finally, the characteristics of the proposed guidance laws are analyzed through numerical simulations.

提出了一种新的具有冲击角约束的弹道制导律设计方法。基本思想是，引入用于组合终端约束方程的乘数可根据需要来塑造飞行轨迹。为此，首先使用最佳控制将冲击角控制制导（IACG）的一般形式作为任意约束组合乘数的函数进行推导。我们揭示了满足运动学的约束组合乘子可以表示为状态变量的函数。从该结果，可以获得实现期望轨迹的约束组合乘数。因此，当期望的轨迹被设计为满足终端约束时，所提出的方法可以直接提供闭环形式的IACG定律，该定律可以实现所需的轨迹。提出的结果的潜在意义是，与现有方法相比，可以轻松确定可以应对各种制导目标的各种轨迹整形IACG法则。在这项研究中，显示了几个例子来验证所提出的方法。结果还表明，以前的IACG法律属于建议结果的子集。最后，通过数值模拟分析了提出的制导律的特点。列举了几个例子来验证所提出的方法。结果还表明，以前的IACG法律属于建议结果的子集。最后，通过数值模拟分析了提出的制导律的特点。列举了几个例子来验证所提出的方法。结果还表明，以前的IACG法律属于建议结果的子集。最后，通过数值模拟分析了提出的制导律的特点。