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   推进剂剩余量 的翻译结果: 查询用时:0.35秒
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推进剂剩余量
相关语句
  propellant residual
     SIMULATIVE TEST STUDY ABOUT THE TECHNOLOGY FOR GAUGING LIQUID PROPELLANT RESIDUAL ON SATELLITE
     卫星推进剂剩余量测量技术地面试验研究
短句来源
     A principle simulative equipment applicable to gauge liquid propellant residual on satellite is introduced briefly. This equipment is developed by a dynamic accurate measurement method named pressure stimulated by gas injection (PSGI) to simulate the propulsion subsystem of DFH 3 satellite.
     根据气体注入压力激励测量方法 ,研制了动态、高精度测量卫星液体推进剂剩余量原理样机 ,该样机以通信卫星双组元推进系统为测量对象。
短句来源
  propellant remainder
     Uniform Design Modeling of Propellant Remainder
     推进剂剩余量的均匀设计建模
短句来源
     By using uniform design's arraying experimental points,an experimental plan which simulates the amount of propellant remainder is given,a linear model about the amount of propellant remainder is built up and a good result is achieved comparing with usual simulating target experiments.
     本文主要运用均匀设计[1]的均匀分散布点方法,设计了模拟推进剂剩余量的试验方案,建立了推进剂剩余量的线性模型,并与传统的模拟打靶试验相比较,取得良好效果。
短句来源
  “推进剂剩余量”译为未确定词的双语例句
     THE TECHNICAL SCHEME FOR THE MEASUREMENT OF LIQUID PROPELLANT RESIDUE ON THE NATIONAL SATELLITE
     一种适合我国在轨卫星液体推进剂剩余量测量的技术方案
短句来源
     Residual Propellant Analysis and Calculation by Using Excel
     利用 Excel 进行推进剂剩余量的分析与计算
短句来源
     RESEARCH ON PROPELLANT REMAINING ESTIMATION IN LOW-GRAVITY
     低重力下预报推进剂剩余量的探索
短句来源
     THERMODYNAMIC MODELS OF PSGI AND THEIR USAGE FOR LIQUID PROPELLANT REMAINING MEASUREMENT ON SATELLITE
     卫星液体推进剂剩余量测量的热力学模型及其应用
短句来源
     THE THERMODYNAMIC MODELS OF PSGL FOR LIQIUD PROPELLANT REMAINING MEASUREMENT ON SATELLITE
     气体注入压力激励法测量卫星液体推进剂剩余量的热力学模型
短句来源
更多       
  相似匹配句对
     Uniform Design Modeling of Propellant Remainder
     推进剂剩余量的均匀设计建模
短句来源
     RESEARCH ON PROPELLANT REMAINING ESTIMATION IN LOW-GRAVITY
     低重力下预报推进剂剩余量的探索
短句来源
     Liner for NEPE Propellant
     NEPE推进剂包覆层
短句来源
     Temperature Control of the Low Temperature Propellant
     低温推进剂的温度控制
短句来源
     TECHNOLOGIES OF LIQUID GAUGING IN SPACE
     国外空间液体剩余量测量技术
短句来源
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  propellant residual
So a larger notch increases the amount of propellant residual attached to the vane system.
      
The propellant quantity a sponge can deliver is the propellant holding volume minus the propellant residual volume.
      
The propellant residual volume is the propellant quantity required to cover the access window sufficiently to prevent gas penetration.
      


The characteristics of modern large liquid rocket engine are summarized and analyzed in this paper.The results show that it is essential to use the high-energy non-toxic fuel (such as liquid oxygen and kerosene or liquid oxygen and liquid hydrogen) as propellant in the large liquid rocket engine.The specific impulse of engine can be increased obviously and the geometery and mass of engine can be decreased by adopting the high-pressure staged combustion feed system. The residual propellant in rocket tanks can...

The characteristics of modern large liquid rocket engine are summarized and analyzed in this paper.The results show that it is essential to use the high-energy non-toxic fuel (such as liquid oxygen and kerosene or liquid oxygen and liquid hydrogen) as propellant in the large liquid rocket engine.The specific impulse of engine can be increased obviously and the geometery and mass of engine can be decreased by adopting the high-pressure staged combustion feed system. The residual propellant in rocket tanks can be decreased by applying a propellant utilization system, and the payload of launch vehicle will increase. The pressure in rocket tanks and the pressure on the inlet of main pumps can be increased by using boost pumps, so as to ensure that the main pumps can work reliably without cavitation erosion.The high reliability, long life expectance and reusability are especially important for astronautical products.

本文对近代大型液体火箭发动机的特点进行了综述和分析.文中指出:使用高能、无毒的液氧、煤油和液氧、液氢为大型液体火箭发动机的推进剂势在必行;采用高压补燃循环系统可以明显提高发动机的比冲、减小发动机尺寸和质量;采用推进剂利用系统可以减少推进剂的剩余量,以提高运载火箭的有效载荷;使用辅助增压泵可降低贮箱压力,并提高发动机主泵的入口压力,以保证主泵在没有汽蚀的条件下可靠工作;高可靠性、长寿命和重复使用对航天产品尤为重要.

By using uniform design's arraying experimental points,an experimental plan which simulates the amount of propellant remainder is given,a linear model about the amount of propellant remainder is built up and a good result is achieved comparing with usual simulating target experiments.The greatest characteristic of the uniform design is that a general regularity can be obtained through few experiments and this is useful to development,test and assessment of strategic missile.

本文主要运用均匀设计[1]的均匀分散布点方法,设计了模拟推进剂剩余量的试验方案,建立了推进剂剩余量的线性模型,并与传统的模拟打靶试验相比较,取得良好效果。均匀设计的最大优点是,以很少的试验次数,获取一般规律性的东西,这对战略导弹的研制、试验、评定具有很好的使用价值。

he importance and peculiarity of propellant remaining estimationn in low-gravity isfirstly discussed together with a brief review of the conventional and advanced technologies.Thesoftware developed by the author for the prediction of propellant remaining in low-gravity is thenintroduced.

概述了低重力条件下预报推进系统贮箱内推进剂剩余量的意义及特点,并简单评述了目前预报推进剂剩余量的常规技术和国外的一些先进技术,同时介绍了作者目前正在编制的“低重力条件下预报推进剂剩余量的通用软件”。

 
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