aerodynamic heating

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

气动加热问题是高超声速飞行器TPS（Thermal Protection System，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。

These hypervelocity within the atmosphere and are subjected to enormous heating as well as aerodynamic loads.

这类弹丸在大气中高速飞行,并受到剧烈的气动加热及空气动力负荷的作用.

Using engineering estimating method, one stead aerodynamic heating of high speed missile was calculated.

采用工程估算方法, 计算了近程高速弹头的非定常气动加热.

Hence, it was necessary to devise a heat shield to protect it against this intense aerodynamic heating.

因此，有必要制做一个隔热板，以防止这种强烈的气动力加热。

Flying aerodynamic heating makes great effect on the reliability of nose fuze.

飞行气动热对弹头引信可靠性影响极大.

aircrafts or reusable space vehicles will encounter severe aerodynamic heating when flying at supersonic speed.

飞机或可重复使用航天器在高超声速飞行时将面临严重的气动加热问题。

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

TY-3探空火箭突起物气动加热计算

In this thesis, the aerodynamic heating methods of hypersonic projectile are presented.

本论文进行了高超声速弹丸的气动热研究.

Characteristics analysis of high-speed aerocraft optical dome in aerodynamic heating environment

波导循环器波导环行器气动热环境下高速飞行器光学头罩特性分析