Trajectory optimization is a key technology of hypersonic glide vehicle.
轨迹优化是高超声速滑翔式飞行器关键技术之一。
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 direct shooting method solving finite thrust trajectory optimization is studied.
研究了求解有限推力轨迹优化问题的直接打靶方法。
A method was proposed for the trajectory optimization of prompt reentry strike vehicle.
提出了有动力再入打击飞行器的航迹优化方法。
It was found that they have the same shortcomings for trajectory optimization in tactical flight.
比较了这几种方法的特点，同时总结了它们应用于战术飞行轨迹优化时共同存在的问题。
In the fourth part, trajectory optimization of painting robot for complex curved surfaces is studied.
第四部分研究了复杂曲面上喷涂机器人喷枪轨迹优化问题。
Therefore, the direct collocation method is a viable approach to the reentry vehicle trajectory optimization problem.
因此，直接配点法对于再入轨迹优化问题的求解是可行的。
Therefore, the direct collocation method is a viable approach to lunar probe soft landing trajectory optimization problem.
因此，直接配点法对于再入轨迹优化问题的求解是可行的。
Trajectory optimization is one of the key factors in scheme planning of the new type of hypersonic gliding reentry vehicles.
轨迹优化是新型高超声速滑翔式再入飞行器方案设计的关键技术之一。
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 gradient projection algorithms are constructed for the real-time computation of trajectory optimization, and the concrete steps of the algorithms are also given.
为了轨道优化的实时计算，构造了一类梯度投影下降算法，并且给出实际应用的具体步骤。
This approach for GTO launch trajectory optimization has been testified with predominant performance index, and has great engineering value in launch vehicle system design.
算例分析结果表明所提出的GTO发射轨道优化设计策略的优良性能，在运载火箭总体设计中有良好的应用价值。
Three kinds of trajectory optimization methods including Indirect method, Hybrid method and Gauss pseudospectral method, as well as solving thoughts were given in this paper.
本文给出三种求解轨道优化设计问题的方法（间接法、混合法和高斯伪谱方法）及求解思路。
It is introduced that the application of optimum process theory to flight trajectory optimization. In this paper, it has studied the method of dealing with changing parameter.
主要介绍了应用最优过程理论计算飞机最优飞行轨迹的数学模型和计算方法。
The system parameter design combining with the trajectory optimization design can efficiently improve the whole design performance of launch vehicle during its preliminary design.
在运载火箭概念设计阶段，总体参数的确定结合轨迹优化设计能最大程度地提高设计性能。
The results of calculation and simulation indicate that application of the discrete method for problem of trajectory optimization can avoid the problem of initial value sensitivity.
仿真计算结果表明这种离散化的方法应用于此轨道优化问题可以避免传统轨道优化方法对初值敏感的问题。
As an example, maximum trajectory optimization was applied on a two-stage ballistic missile, and a comparison of original and optimal trajectories was presented with figures and tables.
对某型二级弹道式导弹进行了最大射程弹道优化，并将得到的最大射程弹道与原弹道进行了比较分析。
An iteration method is presented to solve the optimization function for approximating the rotation transformation part of the pseudo moving frame at any position of the motion trajectory.
采用迭代法求解该优化方程来逼近运动轨迹任意处伪活动标架的旋转变换矩阵。
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.
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。
In this dissertation, low energy trajectory design and optimization for collinear libration point missions is studied.
本文对共线平动点任务节能轨道设计与优化进行了研究。
Design and optimization of homing trajectory is essential for accurate aerial delivery of parafoil system.
归航轨迹的设计和优化对实现翼伞系统的精确空投至关重要。
Some real-time computation problems for the optimization of air defence missile trajectory are presented, and the quasi-Newton methods are used to compute the initial optimization trajectory.
提出防空导弹轨道优化的一些实时计算问题，并且应用拟牛顿法计算初始优化轨道。
First, the optimization model of interplanetary low-thrust trajectory was established using modified equinoctial elements.
首先，基于归一化的改进春分点根数建立了星际小推力转移轨道的优化模型；
The optimization and management of movement trajectories, such as inflection point, can make the machine with faster speed , more steady condition , higher efficiency and flying trajectory movement.
对拐点等多种运动轨迹的优化处理可以使机器的运动性能速度更快、状态更稳、效率更高，实 现可飞行轨迹运动。
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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