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低温推进剂
相关语句
  cryogenic propellant
     Study on Characteristics of Cryogenic Propellant in Pipeline Transportation System
     低温推进剂管道输送系统特性研究
短句来源
     Experimental Study and Theoretical Analysis Method Investigation on Natural Circulation Precooling of Cryogenic Propellant Rocket Engine System
     低温推进剂火箭发动机循环预冷实验和分析方法研究
短句来源
     A NOVEL METHOD OF CALCULATING THE DENSITY AND TEMPERATURE OF CRYOGENIC PROPELLANT ROCKET ENGINE PUMP EXIT
     低温推进剂火箭发动机泵出口密度、温度计算的一种新方法
短句来源
     Computation of cryogenic propellant discharge under zero gravity conditions
     失重条件下低温推进剂排放计算
短句来源
     The Insulation Experiment of Cryogenic Propellant Pipe
     低温推进剂输送管绝热试验研究
短句来源
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  cryogenic propellant rocket engine
     A NOVEL METHOD OF CALCULATING THE DENSITY AND TEMPERATURE OF CRYOGENIC PROPELLANT ROCKET ENGINE PUMP EXIT
     低温推进剂火箭发动机泵出口密度、温度计算的一种新方法
短句来源
     Experimental Study and Theoretical Analysis Method Investigation on Natural Circulation Precooling of Cryogenic Propellant Rocket Engine System
     低温推进剂火箭发动机循环预冷实验和分析方法研究
短句来源
  “低温推进剂”译为未确定词的双语例句
     The Study of Circulating Chilldown Methods of Cryogenic Rocket Engine
     低温推进剂火箭发动机循环预冷方法研究
短句来源
     The results were showed that the insulated effect of CO2 vacuum layer was better than polyurethane foamed plastic but difficulty in engineering.
     结果表明:聚氨酯发泡塑料具有一定的绝热效果,CO2冷凝真空绝热层的绝热效果更好,但CO2冷凝真空绝热的工艺实施较难。 工程上低温推进剂输送管可采用聚氨酯发泡塑料进行绝热。
短句来源
     2. Numerical Simulation and Analysis on Liquid Propellant Pressurization Transportation System Cryogenic liquid propellant pressurization transportation system has been numerically simulated with Computational Fluid Dynamics and numerical computation tool.
     3.低温推进剂增压输送系统的试验研究 参考试验设计要求,以及数值模拟的结论,搭建并完善了低温液体推进剂增压输送系统的模拟试验装置。 以液氮为模拟推进剂,以含不同组份的二氧化碳和水的氮气为模拟增压气体,进行了液氧煤油火箭的液氧箱自生增压试验研究。
短句来源
     The thermal conductivity of polyurethane foamed plastic and CO2 condensation vacuum insulation layer we tested by calorimetry method respectedly in this paper.
     用量热法分别测试了低温推进剂输送管聚氨酯发泡塑料绝热层和CO2冷凝真空绝热层的热导率。
短句来源
     Digital Signal Processing System Design of Low-temperature Propellant Level Based on DSP
     基于DSP的低温推进剂加注液位检测和信号处理系统设计
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  cryogenic propellant
Applicability of CFRP materials to the cryogenic propellant tank for reusable launch vehicle (RLV)
      
It is essential to utilize carbon fiber reinforced plastics (CFRP) for main structural materials of cryogenic propellant tanks in order to realize the drastic weight reduction needed for efficient reusable space transportation systems.
      
Cryogenic properties of different types of CFRPs are experimentally evaluated to survey the basic applicability of different material systems to the cryogenic propellant tanks for future reusable launch vehicles.
      
The results indicate that matrix cracks may be one of the major critical issues when current material systems are applied to cryogenic propellant tanks.
      
Gas permeability through damage networks in composite laminates is the key issue for the applicability of high-performance composites to the cryogenic propellant tanks of space launch vehicles.
      
更多          
  cryogenic propellants
Length scales provide some understanding of the injection of cryogenic propellants in rocket chambers on mixing efficiency, which translates to burning efficiency and performance.
      
A Helmholtz resonance technique was employed as an effective technique for measuring volumes of cryogenic propellants in orbit.
      
Even with the best insulation, cryogenic propellants are difficult to keep for long periods of time and will boil away.
      
For example, spacecraft using cryogenic propellants must use significant thermal hardware to isolate the tanks.
      
However, the transfer of cryogenic propellants introduces other complexities and potential hazards that require careful examination.
      
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This paper discusses the application prospect of liquid propellants used in Chinese strategic missiles and space launch vehicles. Taking account of the specific conditions of China, the author briefly describes the development and main research subjects of normal and cryogenic propellant loading techniques.

本文讨论了液体推进剂在我国战略导弹与航天运载器上应用的前景,结合我国的具体情况对常规推进剂和低温推进剂加注技术的发展及主要研究课题作了简要的论述。

By means of the analysis of the results from lots of ground testsand flight of the third stage of a low temperature propellant launch vehi-cle,this article has concluded sotne factocs to affect the temperature oflow temperature propellant as well as their responsible control methods,and made a scene of the new type of pressurization system and tempera- ture control technology.

通过对低温火箭三子级地面试验和多次飞行试验的分析及国外有关资料的报导,总结出影响低温推进剂温度的相关因素及控制方法,对新型的增压系统及温控技术进行了展望。

The two level distributed control system for cryogenic propellant loading is introduced,taking the Lox loading control system for example.The emphasis is put on description of the structure principle,basic functions,and design features of the system.Its technique of control,checkout and network management techniques are explained in detail.

以液氧加注控制系统为例,介绍液体运载火箭低温推进剂加注控制所采用的两级分布式系统。着重于描述液氧加注控制系统的结构原理、基本功能、设计特,并详细阐明了控制、检测及网络管理技术。

 
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