Then, through solving the slow time-scale problem by optimal control theory, the optimal reduced-order reference trajectory is obtained.
然后，应用最优控制理论得出慢时间尺度上的解，并将其作为降维后的最优参考轨迹；
Trajectory correction projectile; Sensitivity function; Identification; Optimal control; Actuator.
弹道修正弹；灵敏度函数；辨识；最优控制；舵机。
The control of the trajectory is the core technique in horizontal well technique, while trajectory design and optimal design are the two key techniques.
井眼轨迹控制是侧钻水平井技术的核心，而轨道设计与优化设计又是轨道控制技术的两大关键技术之一。
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。
It provides a better solution to the problem of industrial robot's time optimal trajectory planning and control under the nonlinear kinematical constraints.
它为工业机器人在非线性运动学约束条件下的时间最优轨迹规划及控制问题提供了一种较好的解决方案。
An optimal preview control method of trajectory tracking performance index function based on trajectory error area in digital optimal preview control is investigated.
研究在数字最优预见控制中以面积误差作为评价函数的轨迹跟踪最优预见控制方法。
A nonlinear optimal control model for designing three-dimensional trajectory of horizontal well was established.
针对三维水平井井眼轨道设计问题，建立了一个非线性最优控制模型。
Optimal control of tactical maneuver for a high-performance aircraft is investigated in flight trajectory.
应用轨迹优化方法研究了高性能战斗机机动动作的最优控制问题。
Spacecraft reentry trajectory optimization is a kind of optimal control problem.
飞行器再入轨迹优化是一类最优控制问题。
The trajectory problem was cast as the optimal control problem and Pontriaghin Maximum Principle was used to obtain first order necessary condition.
我们将此弹道问题转化成最优控制问题，通过极大值原理得到最优弹道的一阶必要条件。
The optimal glide trajectory and control system of combined guidance munition were studied.
研究了制导炮弹最优滑翔弹道与控制问题。
Firstly the optimal control problem of minimum-time strike trajectory was translated into two-point-boundary-value problem by using Pontryagin maximum principle.
首先，利用庞特里亚金极大值原理将时间最短打击轨道的最优控制问题转化为两点边值问题。
The optimization methods for launch trajectory of low earth orbit are discussed, and the optimal control problems are converted into parameter optimization problems by multiple parameterized methods.
确定了近地轨道的发射轨道优化设计方法 ，采用多重参数化法将轨迹最优控制问题转化为参数优化问题。
The optimization methods for launch trajectory of low earth orbit are discussed, and the optimal control problems are converted into parameter optimization problems by multiple parameterized methods.
确定了近地轨道的发射轨道优化设计方法 ，采用多重参数化法将轨迹最优控制问题转化为参数优化问题。
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