激光末端制导武器系统中，激光照射指示器出射激光的束散角是一个重要的参数。
In laser control and guide system, diverging Angle of laser beam is an important parameter.
根据激光末端制导的工作原理，分析了激光照射指示器的性能指标，提出了各性能指标的数字化检测方法。
According to the principle of laser terminal guidance, some important performances of laser radiation indicator are analyzed and the numeralization test method is introduced.
同时采用最优制导律设计与理想速度曲线相结合的方法，设计了能同时保证末端制导精度及速度方向、大小的制导律。
Furthermore, a guidance law is proposed by using a combination of optimal guidance law design with ideal velocity curve approach.
多次数值打靶仿真表明，提出的预测制导方法对高超声速飞行器末端制导初始条件误差以及导航误差影响具有较强的鲁棒性。
Numerical simulation of multiple target practice shows that the presented predictive guidance method for hypersonic craft strong robustness on initial conditions and navigation errors.
根据机载布撒器的工作特点，设计了一种满足其作战要求的具有末端角度约束的制导律，并分析了工程实用性。
According to the performance of airborne dispenser, a guidance law with angle constraint which meets the requirements of it is designed, and its project feasibility is analyzed.
在这一背景下，本文研究了带末端攻击角度约束的制导方法设计和制导控制一体化方法设计问题。
In this paper, the missile guidance with terminal impact Angle constraint and integrated guidance and control design for missile with terminal impact constraint were researched.
在这一背景下，本文研究了带末端攻击角度约束的制导方法设计和制导控制一体化方法设计问题。
In this paper, the missile guidance with terminal impact Angle constraint and integrated guidance and control design for missile with terminal impact constraint were researched.
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