得到了再入飞行器和模型的转捩雷诺数。
Transition Reynolds Numbers for both the reentry vehicles and the test models are obtained.
本文主要讨论再入飞行器机动弹道的设计问题。
This paper mainly discusses the design of maneuverable trajectories of re-entry vehicle.
文提出一种关于再入飞行器程序机动飞行的制导方案。
Programming maneuvering flight guidance scheme about reentry vehicle is presented in this paper.
研究了在降弧段进行高空机动的再入飞行器最优制导律。
An optimal guidance law for reentry vehicle with high altitude maneuvering on downward phase is studied.
本文研究确定再入飞行器的最小总加热量气动外形问题。
This paper deals with the problem of determining the aerodynamic shape of a reentry vehicle with minimum total trajectory heat transfer.
本文对再入飞行器几种回收方案的气动特性进行了分析和比较。
This paper presents a Review of aerodynamic characteristics for several recovery schemes of 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。
Trajectory optimization is one of the key factors in scheme planning of the new type of hypersonic gliding reentry vehicles.
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。
A novel guidance law is devised for developing the guidance technology of optimal glide of a hypersonic reentry vehicle.
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。
In this paper, plasma wake flow of hypersonic reentry vehicle and radar scattering characteristics have been studied.
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。
High temperature chemical non equilibrium phenomena have a great effect on the flow field around a reentry vehicle.
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。
A predictive guidance method for reentry vehicle in the case of attacking the stationary target on the surface is also investigated.
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。
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.
解决有限推力模型的再入飞行器初制导问题，利用传统开环控制的关机方程达不到要求的精度。
For the finite propulsion reentry guidance, the conventional closed-thruster equation based on open-loop control loses its way.
在具有控制和轨迹约束的再入制导中，提出了一种新的基于多模型预测再入飞行器纵向制导方法。
A new method based on multi-model prediction is proposed for the longitudinal guidance of re-entry vehicles with trajectory and control constraints.
载人飞船返回舱的烧蚀热防护技术研究和试验表明，碳化烧蚀材料是再入飞行器最有效的热防护层。
Investigations and experiments indicate that charring ablators provide the most efficient thermal protection shield for the re-entry vehicles.
再入飞行器气动布局优化设计是一个复杂的工程系统设计问题，通常包含若干子系统和大量的设计参数。
The optimization design of aerodynamic shape for reentry vehicles (ASRV) is a design problem of the complex engineering system, which often involves several subsystems and various parameters.
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 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.
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。
Firstly, the state variables of the reentry vehicle are decomposed into two sub-systems of different time scales using the singular perturbation theory.
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。
This paper gives the method that is effective in decreasing the roll Angle and roll rate in roll channel of the reentry vehicle.
研究了有动力通用再入飞行器的燃料最优巡航轨迹，将问题转化为求解最优稳态巡航轨迹和最优周期巡航轨迹问题。
The fuel optimal cruise trajectory of a powered common aero vehicle was analyzed. The problem was divided into determining the optimal steady-state cruise and optimal periodic cruise problems.
给出了一种新的飞行器运动数学模型和这一模型下的最优制导律以及再入飞行器发动机工作时间、过载系数和估算方法。
The optimal high altitude guidance law with reentry constraint condition is derived by using the optimal control theory, and the algorithm of time to go is also given.
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。
The guidance method satisfies terminal angular constraint as reentry vehicle hitting target, but also ensures minimum loss of maneuvering velocity for reentry vehicle.
本文运用飞行力学原理和现代控制理论，对攻击地面固定目标的飞行器的再入机动制导方法进行了研究。
In this paper, the method of reentry maneuver guidance applying to attack the ground fixed target is described by using flight dynamics principle and modern control theory.
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 aerodynamic characteristics of maneuvering reentry vehicle of cruciform configuration and bifurcate configuration are compared by means of the wind tunnel test results.
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。
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.
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。
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.
电弧等离子体风洞是一种能产生高温、高压的热源设备，用于在地面模拟航天用再入式飞行器的气动环境。
Plasma wind tunnel is equipment which can generate high-temperature and high-pressure to simulate the air environment of aerospace reentry vehicles.
飞行器再入轨迹优化是一类最优控制问题。
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。
Spacecraft reentry trajectory optimization is a kind of optimal control problem.
应用推荐