Programming maneuvering flight guidance scheme about reentry vehicle is presented in this paper.
文提出一种关于再入飞行器程序机动飞行的制导方案。
An optimal guidance law for reentry vehicle with high altitude maneuvering on downward phase is studied.
研究了在降弧段进行高空机动的再入飞行器最优制导律。
High temperature chemical non equilibrium phenomena have a great effect on the flow field around a reentry vehicle.
高温非平衡化学反应对高超声速再入飞行器绕流流场的气动热特性有较大影响。
In this paper, plasma wake flow of hypersonic reentry vehicle and radar scattering characteristics have been studied.
对再入飞行器等离子体尾迹及其雷达散射特性进行了分析、研究和大量的计算。
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 novel guidance law is devised for developing the guidance technology of optimal glide of a hypersonic reentry vehicle.
针对高超声速再入飞行器最远距离滑翔制导关键技术，设计了一种新型制导律。
This paper gives the method that is effective in decreasing the roll Angle and roll rate in roll channel of the reentry vehicle.
针对再入飞行器滚动通道产生较大的滚动角及滚动角速率，给出了一种能够有效地减小滚动角和滚动角速率的方法。
A predictive guidance method for reentry vehicle in the case of attacking the stationary target on the surface is also investigated.
论文最后研究了预测制导方法在高速再入飞行器攻击地面固定目标任务中的应用问题。
This paper researches into reentry vehicle impact errors which result from the roll velocity changes by use of rotor dynamic theory.
用转子动力学理论研究了再入航天器滚速变化引起的落点误差。
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。
Variable bend tail concept may be one of the possible approaches for satisfying the maneuvering requirement of hypersonic reentry vehicle.
可变弯尾飞行器的气动方案是高超声速机动的潜在可行方案。
Firstly, the state variables of the reentry vehicle are decomposed into two sub-systems of different time scales using the singular perturbation theory.
首先，利用奇异摄动理论对再入飞行器状态变量进行两个时间尺度的划分，将系统状态方程分解成两个低维子系统。
The guidance method satisfies terminal angular constraint as reentry vehicle hitting target, but also ensures minimum loss of maneuvering velocity for reentry vehicle.
该方法利用最优控制理论的思想方法，不仅使飞行器命中目标时满足了终端角度约束的条件，而且保证了再入飞行器机动速度损失最小。
As to the attitude stablization of reentry vehicle with parameter uncertainties, its variable structure decoupling control law is designed and simulation results are given.
讨论了其滑模面的构造方法和解耦控制条件，在姿态控制中保证了姿态跟踪期望值。
Hmmm... a double-dip reentry after an uneventful trip around the moon? Additionally, that reentry vehicle is far larger than would be launched by a sample-and-return mission.
嗯…平安无事绕月后的一个二次再入？此外，再入飞行器远远高端于发射简单的取样返回任务。
Hmmm.... A double-dip reentry after an uneventful trip around the moon? Additionally, that reentry vehicle is far larger than would be launched by a sample-and-return mission.
嗯…平安无事绕月后的一个二次再入？此外，再入飞行器远远高端于发射简单的取样返回任务。
In this paper aerodynamic characteristics of maneuvering reentry vehicle of cruciform configuration and bifurcate configuration are compared by means of the wind tunnel test results.
利用典型状态的风洞试验结果对十字布局与叉字布局再入机动飞行器的气动特性进行了分析与比较。
In this paper, system structure and software design of reentry vehicle Sir -dof semi physical simulation are introduced briefly, and corresponding simulation technical methods is discussed.
本文简要介绍了再入体六自由度控制系统半实物仿真的系统结构与软件系统设计，并探讨了相应的仿真技术途径。
Against the big error of height determination for the reentry vehicle because of the information provided by low precision geomagnetic sensor, a novel real-time prediction method is proposed.
针对于目前地磁传感器测量精度较低，将其信息直接用于飞行器再入段定高误差较大的问题，提出了一种在线预测进行定高的方法。
The paper widens the application of local method which used to be utilized in rarefied flow to the quick prediction of aerodynamic characteristics of missile-like reentry vehicle in hypersonic flow.
首先，使用局部线性方法给出模型的系数函数的初始估计； 然后使用积分方法，给出它们的积分估计； 进一步，研究这些积分估计的渐近正态性。
This astronaut photograph highlights the reentry plasma trail of one such spacecraft, the ISS Progress 42p supply vehicle (Russian designation M-10M).
这张太空影像就是显示了进步42p飞船(俄称M - 20 M飞船)，在“回归”大气层时等离子化的轨迹。
A new reentry guidance algorithm for RLV (reusable launching vehicle) is presented.
提出了一种针对可重复使用运载器的再入制导算法。
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。
The objective of this paper is to design the reentry flight control laws for the Suborbital Reusable Launch Vehicle(SRLV) based on nonlinear dynamic-inversion.
基于非线性动态逆理论，设计了亚轨道可重复使用运载器（SRLV）的再入控制律。
The opening parachute signal is required to sent on the fixed height when the vehicle reentry. The height controlled error through axis apparent acceleration can not meet the required precision.
弹道式飞行器再入时，常常要求在规定高度上发出开伞信号，过载延时控制方法误差太大，不能满足精度要求。
The second qualification flight of Ariane - 5(V502) will carry an atmospheric Reentry Demonstrator(ARD) which is a simple unmanned capsule - type vehicle.
欧洲再入大气层试验飞行器是简单的不载人座舱式飞行器。它将随“阿里安5”火箭的第二次鉴定飞行发射升空。
The second qualification flight of Ariane - 5(V502) will carry an atmospheric Reentry Demonstrator(ARD) which is a simple unmanned capsule - type vehicle.
欧洲再入大气层试验飞行器是简单的不载人座舱式飞行器。它将随“阿里安5”火箭的第二次鉴定飞行发射升空。
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