The impact time and angle constrained terminal guidance laws against a maneuvering target are usually designed under the assumption that the magnitude of the missile's velocity can be controlled, rather than a missile with uncontrollable speed because it is difficult to adjust the time-to-go due to the maneuver of the target. The main objective of this work is to propose a new guidance law to access the ability of hitting a maneuvering target at the desired impact time and terminal angle under the assumption that the magnitude of the missile's velocity is uncontrollable. In the design, the linearized relative kinematic equations are constructed, then used in the design of optimal guidance law with terminal angle constraint. The analytical formula of the time-to-go estimation is obtained based on the optimal guidance law, which is used to design a bias term to meet the impact time constraint. Numerical simulations are conducted for different engagement scenarios to verify effectiveness of the design.

中文翻译：

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时间和角度约束下机动目标的次优制导律

针对机动目标的撞击时间和角度约束末制导律通常是在导弹速度大小可以控制的假设下设计的，而不是在速度不可控的情况下设计的，因为由于飞行时间难以调整，到目标的机动。这项工作的主要目标是提出一种新的制导律，以在导弹速度大小不可控的假设下，获得以所需的撞击时间和终端角度击中机动目标的能力。设计中，构造了线性化相对运动方程，并将其用于带有终端角约束的最优制导律的设计。基于最优制导律得到了剩余飞行时间估计的解析公式，并用于设计偏差项以满足撞击时间约束。针对不同的交战场景进行数值模拟，以验证设计的有效性。