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 designed maneuver reentry trajectory can meet the demands of attitude, heat flux and velocity for the warhead.
所设计的再入机动弹道能满足机动弹头对姿态、热流和速度的要求。
In view of the particularity for maneuver warhead reentry trajectory and the guidance method, key techniques in attitude control system design are analyzed.
针对机动弹头再入弹道和制导方式的特殊性，分析了激光末制导机动弹头姿控系统设计的关键技术。
The paper has brought out functions of the reentry trajectory of TBM in case of the predigest model of atmosphere and solved them by the Runge-Kutta method.
文中在简化的大气模型下建立TBM的再入段方程，并采用龙格-库塔法来求解，通过仿真，可以看出模型符合仿真需要。
So maneuver reentry trajectory design problem was transferred into the more complex optimum control problem with terminal constraints and inner state constraints.
这就增加了内点约束，从而使机动再入弹道设计问题成为具有内点约束和终端约束更复杂的最优控制问题。
A new analytic solution of the ballistic missiles reentry trajectory is presented by considering some more actual factors on the basis of the existing analytic solution.
在现有再入段解析方法的基础上，考虑更为贴近实际的条件因素，求得一组新的弹道导弹再入弹道解析解。
The mathematical model of reentry maneuvering trajectory is established. The fitting expression of aerodynamic coefficient function on velocity, attack of Angle and altitude is presented.
建立了再入机动弹道数学模型，给出了气动力系数为速度、迎角、高度的函数拟合式，进行了最佳再入机动弹道设计和仿真计算。
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。
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。
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 optimal design of the trajectory for the standard twice reentry of mooncraft under the conditions of the trajectory endpoint set and multiply objective constraints in this paper.
对登月飞船在指定轨道终点及多约束条件下两次再入轨道的优化设计进行了研究。
Baced on the properties of elliptical trajectory, the reentry conditions of the vehicles, spherical geometry, and the fixed-point theorem, an algorithm for the ideal trajectory is proposed.
根据飞行器椭圆弹道的性质、飞行器再入条件、球面几何和不动点原理给出了理想弹道的计算算法。
The nominal trajectory-based techniques include the methods to compute the reentry flight corridor, the reference trajectory and the track law of the reference trajectory.
标准轨道法。 给出了再入走廊的计算方法，阐述了参考阻力加速度-速度剖面的规划和跟踪问题。
For reentry capsules of spacecraft, making up the trajectory in black-out area is a key link of aerodynamic analysis from flight test data.
对于飞船返回舱，黑障区弹道再现是再人飞行试验气动分析工作的重要环节。
This paper deals with the problem of determining the aerodynamic shape of a reentry vehicle with minimum total trajectory heat transfer.
本文研究确定再入飞行器的最小总加热量气动外形问题。
The physical causation of the optimal trajectory and the corresponding angleofattack profile are presented. It is a good reference for schematic trajectory design for gliding type reentry vehicles.
分析了沿最优轨迹飞行的物理原因和基本迎角控制规律，可为滑翔式再入飞行器的最优轨迹方案设计提供依据。
The flight test data of some a reentry capsule are analyzed. The results validate the developed mathematical model and algorithm of trajectory reconstruction.
对某飞船返回舱的飞行试验数据进行了计算和分析，结果证实了弹道重建数学模型的正确性和算法的可行性。
The flight test data of some a reentry capsule are analyzed. The results validate the developed mathematical model and algorithm of trajectory reconstruction.
对某飞船返回舱的飞行试验数据进行了计算和分析，结果证实了弹道重建数学模型的正确性和算法的可行性。
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