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推进剂     
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  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
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     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
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  propellants
     An Investigation on Synergistic Effect of CaCO 3 Untrafine Particles and M 2O 3 on the Combustion of AP/Al/HTPB Propellants
     超细 CaCO_3 与金属氧化物 M_2O_3 对 Al/AP/HTPB 推进剂燃烧的催化协同效应研究
短句来源
     Analysis on Specific Impulse Efficiencies of Reduced Smoke HTPB/AP/RDX/Al Propellants
     少烟HTPB/AP/RDX/Al推进剂比冲效率分析
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     Study on Burning Rate Inhibitors of HTPB/AP/Al Propellants
     HTPB/AP/Al复合推进剂燃速降速剂研究
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     Synthesis of Nanometer PbO,Bi_2O_3 and Their Effect on Burning Properties of Solid Propellants
     纳米PbO和Bi_2O_3粉的制备及对推进剂燃烧性能的影响
短句来源
     The B, B2O3 and BN content in the combustion draff of coating boron-based propellants has been changed from 37.54:1:3.97 to 3.11:1:0.09;
     含包覆硼推进剂燃烧残渣中B、B_2O_3与BN中B元素的摩尔比由包覆前的37.54:1:3.97变为3.11:1:0.09;
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
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     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
     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
     Experimental Study of Structural Strength and Residual Life for Missile Propellent Tanks
     导弹推进剂贮箱结构强度及剩余寿命实验研究
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     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。
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  rocket propellant
     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。
短句来源
     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 operating process of liquid apogee engine (N2O4/MMH) thrust chamber is studied. By applying the SIMPLE algorithm with staggered grid, the numerical model is established. The atomization mechanism and decomposition combustion of hypergolic rocket propellant are considered in the model.
     研究了远地点发动机(N2O4/MMH)的推力室工作过程,考虑了自燃推进剂的雾化、蒸发以及化学反应流动过程,采用交错网格系统的SIMPLE算法,得到了不同边区冷却流量对推力室的内流场和燃烧效率的影响结果,数值计算的结果与理论分析相符合,为推力室工作过程的稳定性分析提供了重要参考。
短句来源
     Unsymmetrical dimethylhydrazine (1,1-dimethylhydrazine, UDMH) and dinitrogen tetroxide (N2O4) are highly volatile and reactive compounds used primarily as a liquid rocket propellant.
     偏二甲基肼(UDMH)和四氧化二氮(N_2O_4)是常用的火箭液体推进剂。 在火箭发射现场UDMH-N_2O_4的泄漏事故可造成工作人员吸入性急性肺损伤(ALI)甚至急性呼吸窘迫综合征(ARDS)。
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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.
      
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  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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