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   推进剂 在 航空航天科学与工程 分类中 的翻译结果: 查询用时:1.897秒
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推进剂     
相关语句
  propellant
    Study on Primary Combustion of Boron-based Fuel-rich Propellant
    含硼富燃推进剂一次燃烧研究
短句来源
    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
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    A Simplified Model for the Design of Hypergolic Liquid Propellant Rocket Engine Combustors
    自燃推进剂液体火箭发动机燃烧室设计简化模型
短句来源
    Some Applications of the Numerical Computation Method to the Transient Calculation of Liquid Propellant Rocket Engine
    数值计算方法在液体推进剂火箭发动机瞬变过程计算中的若干应用
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    A STUDY FOR THE PROPELLANT EFFICIENCY OF ION ENGINE
    离子发动机推进剂效率的研究
短句来源
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  propellants
    Researches on Combustion and Processes of High Boron Content Boron-Based Fuel-Rich Solid Propellants
    高含硼富燃固体推进剂工艺和燃烧性能研究
短句来源
    The Flame Temperature Distribution Measurement of Solid Propellants
    固体推进剂火焰温度分布测量
短句来源
    A COMMENT ON THE PLATEAU COMBUSTION MECHANISM OF THE DOUBLE-BASE PROPELLANTS
    评双基推进剂平台燃烧机理
短句来源
    PRESSURE-COUPLED RESPONSE FUNCTION OF SOLID PROPELLANTS INCLUDING THOSE WITH NEGATIVE PRESSURE-EXPONENTS
    含负压力指数固体推进剂的压力响应函数
短句来源
    An Optimisation Design of Energy Characteristic of Solid Propellants
    固体推进剂能量特性优化设计
短句来源
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  propellent
    A Review of Ap Composite Solid Propellent Steady Combustion Models
    Ap复合固体推进剂稳态燃烧模型综述
短句来源
    Separation and Determination of Extractable Organic Components in NEPE Propellent
    NEPE推进剂中可提取有机组分的分离测定
短句来源
    Calculation of Fluid Resistance in Design of Propellent Management Device of Surface Tension Tanks
    表面张力贮箱推进剂管理装置流阻的计算
短句来源
    It is discovered that rare earth compounds added into silicone substrate can certainly increase bonding strength between RTV Silicone rubber and HMX-CMDB propellant or Al-RDX-CMDB propellent coated with the primer, and the failure mode of shear samples is cohesive failure of silicone rubber itself.
    发现稀土化合物确实能提高硅橡胶与刷涂底漆的HMX—CMDB推进剂或Al—RDX—CMDB推进剂之间的粘接强度,并且硅橡胶与HMX—CMDB推进剂粘接的剪切破坏形式为硅橡胶本身的内聚破坏。
短句来源
    The separation and detemination of the extrctable organic components (HMX, C2 and NG+BTTN) in NEPE propellent are investigated. NEPE propellant samples were soaked in the purified THF for 24h; then, heat and stir the solution in 50℃ for 5 h.
    研究了NEPE推进剂中可提取有机组分(HMX,C2和NG+BTIN)的分离和测定方法.试样用THF浸泡24h后,在50℃搅拌5h.提取液采用正相高效液相色谱(NPHPLC)分离、测定HMX,C2和混合酯.HMX,C2和NG+BTTN测定的相对标准偏差分别为0.31%,1.20%和2.19%.
短句来源
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  rocket propellant
    THEORETICAL AND EXPERIMENTAL STUDIES FOR LIQUID ROCKET PROPELLANT EXPLOSION
    液体推进剂爆炸理论与实验研究
短句来源
    Unsymmetrical dimethylhydrazine (UDMH) is the main fuel of liquid rocket propellant. Stress is always laid on the pollution of UDMH to water.
    偏二甲肼(UDMH)是液体推进剂的主体燃料,其对水体的污染一直倍受重视。
短句来源
    The Quantitative Safety Analysis of Conventional Liquid Rocket Propellant Operation
    常规液体推进剂作业安全性研究
短句来源
    Application of Electrochemical Gas Sensor on Detection of Liquid Rocket Propellant
    控制电位电解型气体传感器在液体推进剂检测中的应用
短句来源
    Based on CT experimental results of HTPB composite solid rocket propellant and under the assumption of single type of microcrack,the concentration degree and area of internal defects are quantitatively analyzed,the mathematic model and measurement method of damage are established.
    本文通过HTPB复合固体推进剂断面层的计算机层析识别(Computerized Tomography 简称CT) 实验结果分析,并在微裂纹类型单一的假设条件下定量分析了材料内部微裂纹分布的密集程度和微裂纹面积的大小,建立了HTPB 复合固体推进剂损伤的CT 数学识别模型和方法。
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  propellant
Analysis and operational results show that the control system can meet all technical requirements for high energy composite solid propellant manufacturing.
      
Comprehensive Substantiation of the Structure and Parameters of a Power-Propellant System for a Spacecraft
      
The conceptual and methodological principles, as well as some results of the comprehensive substantiation of a technical approach at early stages of design of power-propellant systems (PPS), are presented.
      
The time of turn is minimized, as well as the functional having a meaning of the propellant consumption.
      
The estimations of the propellant consumption for a realization of the programmed turn are made.
      
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  propellants
An experimental method for determination of critical conditions of condensation of metal propellants of electric jet engines (EJEs) on the surfaces of materials of spacecraft thermoregulating covers is presented.
      
Mechanism of combustion of fire-extinguishing propellants based on potassium nitrate
      
A study is made of one-dimensional nonstationary problems of the combustion and detonation of aerosuspensions of unitary fuels or propellants, which contain the oxidant as well as the combustible material (gunpowder, high explosives).
      
The temperature of attainable superheating of rocket propellants is also calculated by the theory of homogeneous nucleation.
      
It is demonstrated that the employed kinetic model of thermochemical processes provides an adequate description of the available experimental data on the rate of combustion of AP- and PBR-based solid propellants.
      
更多          
  propellent
It is verified that the constitutive model with damage proposed can more accurately estimate the stress response of a class of viscoelastic particle-reinforced composite, such as solid propellent, than the constitutive model without damage.
      
The rheological behaviour of plastic propellent in rocket motor situations is simulated in an experimental technique.
      
In this a differential gas pressure is applied across a plug of propellent in a rigid tube so as to deform it in an approximately telescopic shear fashion.
      
The rheological properties of plastic propellent have been examined by means of a technique in which gas pressures are used to stress a plug of propellent pressed into a rigid tube.
      
The application of these superposed results to predict propellent behaviour is discussed.
      
更多          
  rocket propellant
The detection of defects and the characterization of solid rocket propellant were thus possible.
      
We have considered the electrodynamic effects on small Al2O3 spherules dumped into the Earth's magnetosphere in large quantities during solid rocket propellant burns.
      
TG studies of a composite solid rocket propellant based on HTPB-binder
      
The reasons for substantially nonstationary modes of operation of this system are considered, and a simplified model that approximates the phenomena of nonstationary combustion of a solid rocket propellant is proposed.
      
The paper presents estimates of the dynamic characteristics of unsteady combustion of a solid rocket propellant in a combustion chamber with in pressure is varied automatically by a specified program.
      
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