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推进剂     
相关语句
  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
    A Model for Erosive Burning of Solid Propellant Based on Statistical Theory of Turbulent Flame
    根据紊流火焰统计理论所建立的固体推进剂侵蚀燃烧模型
短句来源
    AN INVESTIGATION ON APPLICATION OF 30-60μm COARSE ALUMINIUM (SPHERICAL, ASPHERICAL)POWDER IN HTPB PROPELLANT
    30~60μm粗铝粉(球形、非球形)在丁羟推进剂中使用研究
短句来源
    EXPERIMENTAL RESEARCH ON CRACK GROWTH BEHAVIOR IN HTPB COMPOSITE PROPELLANT
    国产HTPB复合推进剂裂纹扩展特性的实验研究
短句来源
    BIFURCATION STUDY OF THE IGNITION OF HAN-BASED LIQUID PROPELLANT LP1846
    液体推进剂LP1846点火的分歧分析
短句来源
更多       
  propellants
    Measurement of the Glass Transition Temperature for Composite Solid Propellants
    复合固体推进剂玻璃转化温度的测定
短句来源
    ON MODELS FOR THE PLATEAU COMBUSTION OF DB-AND NITRAMINE CMDB PROPELLANTS
    双基和硝胺改性双基推进剂平台燃烧模型的研究
短句来源
    Advanced Solid Rocket Propellants Containing Oxetane Binder
    含氧杂环丁烷粘合剂的先进固体推进剂
短句来源
    MECHANICAL MODEL OF MESOPHASE IN COMPOSITE SOLID PROPELLANTS
    复合固体推进剂过渡相(中间相)力学模型
短句来源
    Thermal-Mechanical Coupling Analysis and Application in Solid Propellants Grains
    固体推进剂药柱热-机耦合分析及应用
短句来源
更多       
  propellent
    An Application of Fracture Mechanics to the Safety Evaluation of Rocket Propellent Tank
    断裂力学在推进剂贮箱安全评定中的应用
短句来源
    The experimental system includes a vacuum simulation section, power supply section, propellent feed section, parameter measurement section and an arcjet.
    实验系统包括真空模拟系统 ,供电系统 ,推进剂供给系统 ,参数测量系统和发动机本体 .
短句来源
    In vacuum environment, the performances of the arcjet were tested under several conditions with argon as the propellent.
    在真空环境下 ,用氩作推进剂 ,得到了不同工况下发动机的性能参数 .
短句来源
    The experimental system includes a vacuum simulation section, power supply section, propellent feed section, parameter measurement section and an arcjet.
    试验系统包括真空模拟系统 ,供电系统 ,推进剂供给系统 ,参数测量系统和发动机本体。
短句来源
    In vacuum environment, the performances of the arcjet were tested under several conditions with argon as the propellent.
    在真空环境下 ,用氩为推进剂 ,得到了不同工况下发动机的性能参数。
短句来源
  rocket propellant
    On Burning Rate Measurement System of Solid Rocket Propellant in a Closed Burner
    密闭燃烧器法固体推进剂燃速测试系统
短句来源
    Solid rocket propellant is a kind of high-energy material. Therefore, the propellant is easy to combustion and detonation.
    固体推进剂是一种高含能材料,具有燃烧和爆炸的危险性。
短句来源
    A burning rate measurement system of solid rocket propellant in a closed burner is designed,in-cluding its hardware and software,especially the addition of data base management system to the software which enables it not only to query and report the experiment data, but also to have some intelligence, this may assist people to recognize the propellant burning rate.
    就密闭燃烧器法测试系统部分的硬件、软件进行了全面统一的设计 ,尤其是在软件部分引入了数据库管理系统 ,不仅使该软件能查询实验相关的数据 ,还使该软件具备了一定的智能 ,可以辅助识别推进剂燃速。
短句来源
    The atomization mechanism of hypergolic rocket propellant and decomposition combustion at high pressure and turbulence burning of premixed reactant flow field are considered .
    数值仿真模型中考虑了自燃推进剂雾化机理、高压分解燃烧和预混反应流湍流燃烧等。
短句来源

 

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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.
      
更多          
  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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