reentry trajectory

Optimization Design of Reentry Trajectory for Maneuverable Warhead Based on Genetic Algorithms

基于遗传算法的机动弹头再入段弹道优化设计

The model of reentry trajectory is established and the angle of attack is regarded as control variable.

首先建立了高超声速导弹再入段弹道模型，并将攻角作为控制变量。

Improving Design of Reentry Vehicle Trajectory Optimization Using Direct Collocation Method

基于直接配点法的再入轨迹优化设计

Task of designing reentry trajectory of manned spacecraft is to make standard reentry trajectory and laws of guidance and control according to requirement of task.

载人飞船返回再入轨道设计的主要任务是确定出标准返回轨道和再入制导规律。

Maneuver reentry trajectory optimization with inner state constraints

具有内点状态约束的机动再入弹道优化设计

The flight laws, characteristics and point precision of spiral reentry trajectory were studied by simulating calculation.

通过仿真计算,研究了螺旋再入弹道的飞行规律 、 特点以及落点精度等问题.

Three-dimensional reentry trajectory 10:00 am on Track 3.

三维再入大气层轨迹上午10点钟三轨道。

Near real-time optimization for reentry trajectory of RLV

可重复使用运载器再入轨迹次实时优化

Shall I make some more sandwiches? three-dimensional reentry trajectory

我再做一些三明治好吗？三维再入大气层轨迹

Taking the minimum control energy reentry trajectory with fixed terminal time and the minimum total heat load reentry trajectory as examples, some key problems such as parameterized method were discussed in detail.

以终端时间固定的空间最小控制能量再入轨迹和终端时间自由的平面最小热载再入轨迹为例，详细讨论了遗传算法用于再入轨迹优化设计所需要解决的一些关键问题。

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.

Research on Modeling and Dynamic Simulation of Unmanned Aerospace Vehicle Reentry Trajectory Optimization for Manned Deep Space Exploration

空天无人飞行器的建模及其动态仿真研究载人航天器深空飞行返回再入轨迹优化

Reentry Trajectory Optimization for Manned Deep Space Exploration

载人航天器深空飞行返回再入轨迹优化

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。

In transition phase followed braking phase, a standard reentry trajectory is computed and stored using landing point prediction guidance method ( LPPGM).

该方法融合了落点预报制导方法和基准弹道制导方法的长处。

The present paper discusses the adjustable ability and design method of a standard spacecraft reentry trajectory.

本文研究载人飞船三自由度标准返回轨道的设计方法.