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微重力火箭
相关语句
  micro-gravity rocket
     Aerodynamic heating calculation of micro-gravity rocket
     微重力火箭气动加热计算
短句来源
  “微重力火箭”译为未确定词的双语例句
     On the Problems of Gyration Reduction etc in Microgravity Rocket Design
     微重力火箭设计中减旋方案等问题
短句来源
     The gyration reduction proposals, calculations of the flight loads, airdynamic heating and rocket wall temperature in microgravity rocket system design are discussed.
     讨论了一种微重力火箭总体设计中减旋方案、飞行载荷、气动加热与壁温计算等几个关键问题。
短句来源
     With total length of 6000mm and launch weight of 1100kg, the TY 3 Microgravity Rocket can carry 50kg payloads to reach 220km above,and provide microgravity levels of 10 -4 g for about 360s. The rocket performed the flight test successfully on Oct. 20,2000, and a more advanced microgravity rocket system is under design.
     TY-3微重力火箭总长 6 0 0 0 mm,起飞质量 1 1 0 0 kg,有效载荷 5 0 kg,最大飞行高度 2 2 0 km,能提供 1 0 - 4 g约 36 0 s时间的微重力试验条件 ,该火箭已于 2 0 0 0年 1 0月飞行试验成功 ,而且一种更先进的微重力火箭系统正在设计中。
短句来源
  相似匹配句对
     Aerodynamic heating calculation of micro-gravity rocket
     微重力火箭气动加热计算
短句来源
     On the Problems of Gyration Reduction etc in Microgravity Rocket Design
     微重力火箭设计中减旋方案等问题
短句来源
     SPACE MICROGRAVITY RESOURCE
     空间微重力资源
短句来源
     Space Microgravity Experiment
     空间微重力试验
短句来源
     ON THE ORIGIN OF ROCKETS
     论火箭的起源
短句来源
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The gyration reduction proposals, calculations of the flight loads, airdynamic heating and rocket wall temperature in microgravity rocket system design are discussed. Proceeding from the actual situation of the rocket, a practical measure for passive gyration reduction installing a contrarotating tail fins and auxiliary gyration reduction device is put forward. And the relation between the gyration reduction and dynamic stability is analyzed. The flight loads and dynamic heating of the rocket during flight...

The gyration reduction proposals, calculations of the flight loads, airdynamic heating and rocket wall temperature in microgravity rocket system design are discussed. Proceeding from the actual situation of the rocket, a practical measure for passive gyration reduction installing a contrarotating tail fins and auxiliary gyration reduction device is put forward. And the relation between the gyration reduction and dynamic stability is analyzed. The flight loads and dynamic heating of the rocket during flight in a high supersonic velocity are also analyzed and calculated.

讨论了一种微重力火箭总体设计中减旋方案、飞行载荷、气动加热与壁温计算等几个关键问题。结合该火箭的具体特点,提出了一种简单实用的被动式减旋措施,即,安装反旋尾翼及辅助减旋机构,并分析了减旋与动稳定性的关系。对超高音速火箭的飞行载荷和气动热进行了分析计算。

With total length of 6000mm and launch weight of 1100kg, the TY 3 Microgravity Rocket can carry 50kg payloads to reach 220km above,and provide microgravity levels of 10 -4 g for about 360s. The rocket performed the flight test successfully on Oct. 20,2000, and a more advanced microgravity rocket system is under design.

TY-3微重力火箭总长 6 0 0 0 mm,起飞质量 1 1 0 0 kg,有效载荷 5 0 kg,最大飞行高度 2 2 0 km,能提供 1 0 - 4 g约 36 0 s时间的微重力试验条件 ,该火箭已于 2 0 0 0年 1 0月飞行试验成功 ,而且一种更先进的微重力火箭系统正在设计中。

The heat flux density and temperature on each character surface of microgravity rocket under the ultrasonic state, whose aerodynamic configuration is the combination rotating body of curve , are calculated and analyzed by the aerodynamic heating calculation method and equation of hemispherecolumn(cone) and sweepback wing.The temperature distribution within the structure of rocket is calculated by using the heat transfer model of onedimension plate and differential method.The effective design methods and...

The heat flux density and temperature on each character surface of microgravity rocket under the ultrasonic state, whose aerodynamic configuration is the combination rotating body of curve , are calculated and analyzed by the aerodynamic heating calculation method and equation of hemispherecolumn(cone) and sweepback wing.The temperature distribution within the structure of rocket is calculated by using the heat transfer model of onedimension plate and differential method.The effective design methods and credible basis for the structure and heat shield of rocket are provided.

针对气动外形为曲线、锥(柱)旋转组合体的微重力火箭,采用半球 柱(锥)和后掠翼的气矾加热计算方法及公式,分析计算了超高音速飞行状态下微重力火箭各特征表面上的热流及温度,并用一元平板传热模型和差分方法计算了箭体结构内部的温度分布,为箭体结构及热防护提供了有效的设计方法和可靠依据。

 
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