气动加热

长时间气动加热飞行器的隔热机理

Insulation Mechanism of Spacecraft With Long Time Aero-Heating

气动加热问题是高超声速飞行器TPS（ThermalProtectionSystem，热防护系统）设计的关键，数值模拟是研究气动加热问题的重要手段，对气动热数值模拟进行研究具有重要的意义。

Aerodynamic heating problems are the key to the design of hypersonic vehicle TPS ( Thermal Protection System ) .

气动加热再次明确了设计要求&它由镍铬铁合金“因科镍X”制造。

Aerodynamic heating again defined its design requirements , and it was built of the nickel alloy Inconel X.

TVD格式与高超音速气动加热数值模拟

TVD scheme and numerical simulation of aerodynamic heating in hypersonic flows

提出一种高速飞行器瞬态气动加热控制系统中传感器的快速、高精度ET转换方法。

A high speed and accurate E T translation method of sensor for transient aerodynamic heating control system of high speed flight vehicle is proposed .

TY-3探空火箭突起物气动加热计算

Calculation of aerodynamic heating for the protuberances on TY-3 sounding rocket

该技术主要是运用CCD摄像机与计算机组成的图像采集与处理系统，利用涂料发生相变的颜色变化信息，测定高超声速流场中模型表面气动加热的特性参数和热流分布情况。

Using the color changing information of phase change paint , this technique mainly applies an image capturing and processing system which consists of a CCD video camera and a computer to measure the characteristic parameter and the heat transfer rate of model surface in hypersonic flow .

根据美国先进空天飞行器X-38的再入轨迹，计算襟翼结构在再入过程中的气动加热问题。

According to the re-entry orbit of American advanced re-entry space vehicle X-38 , the heat flux of the body flap aroused by aerodynamic heating during the re-entry time was simulated .

座舱蒙皮外表面气动加热的物理仿真研究

Physical simulation of aerodynamic heating on outside surfaces of cabin skins

气动加热对红外成像的影响试验研究

Experiment Research on the Aerodynamic Heating Effect on the Infrared Imaging

飞行器持续气动加热的耦合性分析

An Analysis of Coupling Feature in Continuing Gasdynamic Heating over Flight Vehicles

我国的一种返回式卫星发射时未设整流罩，星体直接受到气动加热。

This paper discusses the problem of aerodynamics heat of non-fairinged satellite .

气动加热与结构温度场耦合分析平台研发技术

Development of the platform for analysis coupling aeroheating and structural temperature field

气动加热下高温陶瓷材料内的瞬态耦合换热

Transient coupled heat transfer in high temperature ceramics submitted to aerodynamic heating

含灰气体平板气动加热实验研究

The study of heat transfer on a flat plate in dust gas

再入弹头的气动加热及热响应分析

Aerodynamic Heat and the Thermal Response of Reentry Missile

气动加热参数辨识在型号设计中的应用

Parameter Identification of Pneumatic Heating in Missile Design

高速火箭弹的气动加热计算

Aerodynamic Heating Calculation of the High Velocity Rocket

气动加热是可重复使用高超声速空天飞行器研究的关键问题之一。

Aerothermal is one of the key problems in research of hypersonic reusable aerospace shuttles .

ZrB2-SiC和C/C复合材料高超声速气动加热与热应力分析

Aerodynamic Heating and Thermal Stress Analysis of ZrB_2-SiC and C / C Composites in Hypersonic Flows

微重力火箭气动加热计算

Aerodynamic heating calculation of micro-gravity rocket

高超声速飞行器在大气层内飞行时，结构表面受到强烈的气动加热作用。

The structure surface is under strong influence of aerodynamic heating when hypersonic aerocraft flies in aerosphere .

这些结果能够定性地反映出耦合性在气动加热问题上的影响。

The results can , at least qualitatively , depict the coupling effects on gasdynamic heating process .

气动加热与结构热传递耦合问题在航天和工程应用领域非常重要。

The coupling problems of aeroheating and solid heat penetration are very important to aerospace and engineering applications .

超高速弹箭存在的气动加热烧蚀现象会严重影响其外弹道特性。

The phenomenon of aerodynamic heating and ablation for hypervelocity projectues seriously affects the characteristics of the exterior ballistics .

地球轨道再人飞行器最小气动加热外形优化设计

The optimization design of earth orbit reentry vehicle configurations for minimum aerodynamic heat transfer numerical calculation of separation flow over severely indented blunt body

高温效应严重地影响了飞行器的气动加热、俯仰力矩特性和通讯传输。

High temperature effects have an important influence on the aerodynamic heating , the pitching moment characteristics and the communications of re-entry flight vehicles .

在超音速飞行器的设计中，由于气动加热效应相当剧烈，考虑热效应的壁板颤振问题成为一个不可忽视的气动弹性问题。

Because of the drastic aerodynamic heating effect , panel flutter analysis considering thermal effects becomes an emerging problem in the design process of supersonic aircraft .

根据单点或多点测温，应用最小二乘及最佳摄动法，确定气动加热面边界热流密度。

The method to estimate boundary heating flux according to the observation ( single point or multipoint ), is given with least squares and perturbation methods ;

同时，飞行器在飞行过程中，摩擦引起的气动加热会导致飞行器的结构参数发生缓慢时变，这也给飞行器的模态识别带来了一定困难。

When the aero craft is working , the aerodynamic heating will make the dynamic parameter changed slowly . This also brings difficulties to the modal identifying work .