When targets fly with non-maneuvering, the optimal guidance law is the proportional guidance law with a changeable factor.
当目标作非机动飞行时，最优制导律是一种变比例系数的比例制导。
For a new time-to-go algorithm, the optimal guidance law can be realized without a trajectory control engine along the lengthwise axis of the missile.
由于采用了一种新的剩余时间算法，在空间拦截弹的弹体纵轴方向无轨道控制发动机的情况下，也可以实现这种最优导引规律。
A novel guidance law is devised for developing the guidance technology of optimal glide of a hypersonic reentry vehicle.
针对高超声速再入飞行器最远距离滑翔制导关键技术，设计了一种新型制导律。
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