详细计算分析了地球扁率对最优轨道的影响。
The changes of optimal trajectory caused by Earth's oblateness are computed.
首先介绍最优轨道对参数的连续依赖性和优化算法的算法模型的收敛性理论。
First, the the ory of continuous dependence of the optimal trajectory on the parameters and the theory of convergence about optimization algorithm model are introduced.
研究了一种应用非线性规化求解有限推力作用下异面最优轨道转移问题的方法。
A method of applying nonlinear program to solve nonplanar optimal orbital transfer under finite thrust is studied.
对一台实际的欠驱动机器人实现了最优轨道生成，并进行了动作实验，取得了较好效果。
The effectiveness of the method is confirmed by an experiment with a real under actuated robot.
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.
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.
本文通过建立航天器在空间作战的拦截模型，根据运动学的理论来设计航天器空间作战最优拦截轨道。
In this paper, the intercept model of the spacecraft in space warfare was built and the optimization orbit was designed based on the theories of kinematics.
为实现高效的轨道不平顺养护维修，建立最优养护维修计划模型和采用大型养路机械进行作业是十分重要的。
In order to realize efficient maintenance of track irregularity, it is necessary to establish the optimized maintenance plan model and adopt large scale machineries to maintain railway tracks.
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.
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.
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.
与现有一些结果相比，这里提出的方法计算简单，而且适用于一般共面椭圆轨道情况，并保证全局最优性。
Comparedwith the existing results, this method is simpler in computation and valid for the case of elliptical orbits with global optimality guaranteed.
一般状态空间中的平均样本轨道最优性问题。
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.
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.
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.
本文用两次冲量法给出了沿双共切椭圆轨道实现从一圆轨道向另一圆轨道转移的最优方案，并考虑到地球扁率造成的轨道摄动。
The optimal scheme is given for the dual-tangential transfer between two circular orbits by dual impulse method. The orbit perturbation as a result of the Earth's flattening is considered.
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.
由于在小波降噪中不同的阈值适应的信号特征不同，采用多种小波阈值对城市轨道交通牵引供电系统谐波信号进行降噪，并从中选择了最优的降噪阈值，达到对信号的优化处理。
Due to different wavelet threshold fit for different characteristic of signal, various wavelet de-noise threshold was used to decline the harmonics of signal and the best threshold was chosen.
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.
研究了标称飞行轨道最优交会点选取，交会时间与发射时间计算等问题。
The ideal rendezvous time, launch time and rendezvous point in space were studied.
因此快速生成最优轨迹对保障亚轨道飞行器任务的完成至关重要。
Therefore, it is very important for its mission completion to generate an optimal trajectory.
本文从分析不同隧道掘进机的施工单元入手，建立了不同隧道掘进机类型的隧道工程的轨道施工运输方案最优化模型。
This paper from analysis of each construction node for different TBMs, establishes different optimized models of rail transportation proposal during tunnelling by different types of TBMs.
研究了伪光谱方法在空间飞行器有限推力轨道转移最优化问题中的应用。
The problem of rapid Lunar soft-landing trajectory optimization by using a Legendre pseudospectral method was studied in this paper.
研究了伪光谱方法在空间飞行器有限推力轨道转移最优化问题中的应用。
The problem of rapid Lunar soft-landing trajectory optimization by using a Legendre pseudospectral method was studied in this paper.
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