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固体推进剂     
相关语句
  solid propellant
     A STUDY ON IGNITION OF SOLID PROPELLANT BY C0_2 LASER
     C0_2激光点燃固体推进剂的研究
短句来源
     EXPERIMENTAL STUDY ON 10KW SOLID PROPELLANT COMBUSTION DRIVEN CW-CO 2 GASDYNAMIC LASER
     10kW连续波固体推进剂燃烧驱动CO_2气动激光实验研究
短句来源
     Measurement of small-signal gain on solid propellant combustion driven CO_2 gasdynamic laser
     固体推进剂燃烧驱动CO_2气动激光小信号增益测量
短句来源
     Determination of Hydroxyl Values of Solid Propellant Reinforcing Agent IS211
     固体推进剂增强剂IS211的羟值测定
短句来源
     Calculation and Experiment of Small-signal Gain on Solid Propellant Combustion Driven CO_2 Gasdynamic Laser
     固体推进剂燃烧驱动的CO_2气动激光器小信号增益的计算与实验研究
短句来源
更多       
  solid propellants
     Flame Temperature Distribution Measurement of Solid Propellants
     用相对强度法测量固体推进剂火焰温度分布
短句来源
     The catalysis of four TMOs (CuO,Fe 2O 3,Co 2O 3 and Cr 2O 3) and their six TMO mixtures (mass ratio:1∶1) on the combustion properties of AP/HTPB and AP/Al/HTPB composite solid propellants was investigated systematically.
     系统地考察了4种TMO催化剂(CuO、Fe2O3、Co2O3和Cr2O3)及其等质量比(1∶1)的6种TMO复合催化剂对AP/HTPB和AP/Al/HTPB两类复合固体推进剂燃烧性能的影响。
短句来源
     Research and Development Trends of Solid Propellants Abroad in the 21st Century
     21世纪国外固体推进剂的研究与发展趋势
短句来源
     Afterwards,oxidant prescription in solid propellants is designed adopted layout resolution inExcel based on energic demands of NEPE ( Nitrate Ester Plasticized Polyether )propellants(HMX:CL-20:AP:Al:FPM2602=60:10:19:8:3), specific impulse and the volumeof explosion of composite materials are validated at the same time.
     然后,以 NEPE(Nitrate Ester Plasticized Polyether)推进剂的能量为依据,采用 Excel 中的规划求解进行了固体推进剂中氧化剂配方的设计(HMX:CL-20:AP:Al:FPM2602=60:10:19:8:3),并对该配方的比冲、爆容进行了验证。
短句来源
     A Study on the Compatibility of 1,3,3-Trinitroazetidine with Some Common Stabilizing Agents of solid Propellants
     1,3,3-三硝基氮杂环丁烷与固体推进剂常用安定剂的相容性研究
更多       
  solid 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
     The basic concepts and main varieties of thermoplastic elastomers (TPEs) are outlined in the paper and advantages of TPEs over thermoset elastomers and the feasibility of TPEs as solid rocket propellant binders are analyzed in details. The basic requirements for TPEs used in solid propellants and applications of meet and enersetic TPFs to solld propellant formulations are reviewed.
     概述了热塑性弹性体(TPEs)的基本概念和种类,分析了TPEs的优点和在固体推进剂中应用的可能性,指出了固体推进剂对TPEs的基本要求,综述了惰性TPEs和合能TPEs在固体推进剂配方中的应用研究。
短句来源
     This paper did some research on numerical simulation about the structure of solid rocket propellant, based on the mechanical problem during the designing process and stockpile process of solid rocket propellant .
     本论文以固体火箭发动机在设计和贮存使用过程中所常见的力学问题为研究背景,对固体推进剂材料的特性结构的数值仿真作了多侧面的研究。
短句来源
     The calculatin for equilibrium ingredients of solid rocket propellant burning products was performed using the gradient method and Monte Carlo method.
     应用梯度法和MonteCarlo方法对固体推进剂燃烧产物平衡组分进行了计算。
短句来源
     Development in the Preparation of Nano-scale Combustion Catalysts Used in Solid Rocket Propellant
     固体推进剂用纳米燃烧催化剂制备研究新进展
短句来源
更多       
  solid 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
     A new type thermoplastic polyurethane elastomer for using as binder in solid propellent were prepared with melt prepolymerization method based on ethylene oxide tetrahydrofuran random copolyehter,isophorone diisocyanate and 1,4 butanediol.
     基于端羟环氧乙烷 -四氢呋喃无规共聚醚、异佛尔酮二异氰酸酯以及 1,4-丁二醇 ,采用熔融二步法合成了一系列新型的用于固体推进剂的热塑性聚氨酯弹性体。
短句来源

 

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  solid propellant
Analysis and operational results show that the control system can meet all technical requirements for high energy composite solid propellant manufacturing.
      
Quasi-One-Dimensional Model of Combustion of Sandwich Heterogeneous Solid Propellant
      
This model includes the heat- and mass-transfer and kinetic-gasdynamic processes in the gas phase above the surface of burning solid propellant, as well as the heat-transfer processes in solid material.
      
The problem of the thermal stability of the base subsystem of components of a composite solid propellant with respect to the introduction of heat-absorbing agents, inhibitors, and burning rate catalysts was considered.
      
Numerical computations have been carried out in an inert simulator of solid propellant rocket motor with the aid of a standard k-ω turbulence model.
      
更多          
  solid propellants
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.
      
The use of fractal for prediction of burning rate of composite solid propellants
      
By using the fractal geometry it is possible to calculate the actual AP (Ammonium Perchlorate) surface area and oxidizer-binder interface fractal dimension in the prediction of burning rate of composite solid propellants.
      
The starting characteristics of thermodynamic undersea vehicle systems are determined by the geometry, size and combustion area of solid propellants, which directly effect liquid propellant pipeline design.
      
It is necessary to establish accurate burning models for solid propellants.
      
更多          
  solid 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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