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。
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.
我们将寻求最优控制和奇摄动非线性状态调节器问题的相应轨道。
We shall seek the optimal control and corresponding trajectories of the singularly perturbed nonlinear state regulator problem.
以目标轨道面倾角最大为优化性能指标，获得了升力和滚转角的最优控制规律。
The optimization performance index is to maximize the orbital plane change, and the optimal lift and bank control law are obtained.
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。
A nonlinear optimal control model for designing three-dimensional trajectory of horizontal well was established.
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。
Firstly the optimal control problem of minimum-time strike trajectory was translated into two-point-boundary-value problem by using Pontryagin maximum principle.
电动力绳系卫星的推力幅值较小且方向固定，完成轨道机动任务的周期长，其最优控制问题的求解比较困难。
Electrodynamic tethers with low thrust-to-weight ratios can only perform orbital transfers over a large number of revolutions, which poses a real challenge to short time scale optimal control methods.
针对近距离相对运动的轨道控制问题，提出用常值小推力完成最优转移的方法。
An optimal orbit maneuver method based on continuous low thrust was presented to solve relative motion control.
其次，在导引段，以脉冲控制策略为前提，分别设计了指数滑移导引律和能量最优转移轨道。
Secondly, the exponential slippage guidance method and optimal energy transfer orbit are designed respectively in the homing phase.
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.
将准最优控制理论用于轨道自主快速交会时线性二次型调节器的设计。
The hypo-optimal theory was applied on the design of linear quadratic regulator for fast and automatic orbit rendezvous in this paper.
将准最优控制理论用于轨道自主快速交会时线性二次型调节器的设计。
The hypo-optimal theory was applied on the design of linear quadratic regulator for fast and automatic orbit rendezvous in this paper.
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