助手标题  
全文文献 工具书 数字 学术定义 翻译助手 学术趋势 更多
查询帮助
意见反馈
   火箭 在 航空航天科学与工程 分类中 的翻译结果: 查询用时:1.846秒
图标索引 在分类学科中查询
所有学科
航空航天科学与工程
动力工程
武器工业与军事技术
气象学
数学
力学
自动化技术
计算机软件及计算机应用
电信技术
更多类别查询

图标索引 历史查询
 

火箭     
相关语句
  rocket
    Studies on Theory and Strategy of Intelligent Fault Diagnosis for Liquid-Propellant Rocket Engine
    液体火箭发动机智能故障诊断理论与策略研究
短句来源
    Investigation on Performance and Influence Factors of Rocket Ejector Mode of RBCC
    RBCC引射火箭模态性能与影响因素研究
短句来源
    Optimization Design for Cost of Solid Rocket Motors
    固体火箭发动机面向成本优化设计
短句来源
    Fuzzy Reliability Analysis for a Flanged Connection System of Rocket Motors
    火箭发动机法兰连接系统模糊可靠性分析
短句来源
    Research on Working Process of the 85% H_2O_2-PE Hybrid Rocket Motor
    85%H_2O_2-PE固液火箭发动机工作过程研究
短句来源
更多       
  propellant rocket
    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
    Computer Calculation of the Hot Starting and Shutdown Transients of Liquid Propellant Rocket Engine
    液体火箭发动机热启动及关车过程计算机计算
短句来源
    Theoretical Calculation of the Thrust Chamber Radiation Cooling in a Liguid Propellant Rocket Engine and the Influence of Design Parameters on Equilibrium Heat Flux and Wall Temperature
    液体火箭发动机推力室辐射冷却的理论计算及主要设计参数对平衡热流强和平衡室壁温度的影响
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
短句来源
    ONE-DIMENSIONAL TWO-PHASE CONSTANT LAG FLOW IN COMBUSTION CHAMBER OF SOLID PROPELLANT ROCKET MOTORS
    固体火箭发动机燃烧室一维两相常滞后流动
短句来源
更多       
  rockets
    AERODYNAMIC DESIGN OF INTERSTAGE AND THE EFFECTS OF PLUME INDUCED FLOW SEPARATION ON AERODYNAMICS OF ROCKETS
    级间段气动设计及羽流诱导 分离对火箭气动特性的影响
短句来源
    Research on Launching Technology for Heavy Pilotless Aircraft with Double Booster Rockets
    大型无人机双发火箭助推发射技术的研究
短句来源
    A Study of the Synchronism of Double Solid Boosting Rockets Applied to UAV
    无人机双发固体火箭助推器同步性研究
短句来源
    An Improved Method for Conceptual Design of Multi-stage Solid Rockets Based on Depleted Shutdown
    一种对基于耗尽关机多级固体火箭概念设计的改进方法(英文)
短句来源
    A nonlinear model on the simulation of pogo vibrations in liquid rockets
    液体火箭Pogo振动蓄压器非线性仿真研究
短句来源
更多       
  rocket motors
    Optimization Design for Cost of Solid Rocket Motors
    固体火箭发动机面向成本优化设计
短句来源
    Fuzzy Reliability Analysis for a Flanged Connection System of Rocket Motors
    火箭发动机法兰连接系统模糊可靠性分析
短句来源
    ONE-DIMENSIONAL TWO-PHASE CONSTANT LAG FLOW IN COMBUSTION CHAMBER OF SOLID PROPELLANT ROCKET MOTORS
    固体火箭发动机燃烧室一维两相常滞后流动
短句来源
    ONE-DIMENSIONAL TWO-PHASE FLOW IN COMBUSTION CHAMBER OF SOLID PROPELLANT ROCKET MOTORS
    固体火箭发动机燃烧室中的一维两相流动
短句来源
    INTEGRAL PERFORMANCE OPTIMUM DESIGN FOR MULTISTAGE SOLID PROPELLANT ROCKET MOTORS
    多级固体火箭发动机总体优化设计
短句来源
更多       

 

查询“火箭”译词为其他词的双语例句

 

查询“火箭”译词为用户自定义的双语例句

    我想查看译文中含有:的双语例句
例句
为了更好的帮助您理解掌握查询词或其译词在地道英语中的实际用法,我们为您准备了出自英文原文的大量英语例句,供您参考。
  rocket
Microbiological Degradation of Asymmetric Dimethylhydrazine, a Toxic Rocket Fuel Ingredient
      
The possibility of microbiological cleaning of water and soil polluted with asymmetric dimethylhydrazine (ADMH), a highly toxic ingredient of rocket fuel (IRF), was studied.
      
Consideration was given to the controlled solid bodies such as aircraft, rocket, and so on moving in the aerodynamic medium.
      
Peculiarities of Estimating the Aircraft Performance Characteristics of the Rocket-and-Space Facilities under Conditions of Fuzz
      
The method is based on the results of measurements of the state parameters and geophysical conditions of the employment of the rocket-and-space facilities under conditions of uncertainty of the a priori data on measurement errors.
      
更多          
  propellant rocket
Monte Carlo simulation algorithms are given which are intended for the calculation of the spectral emissivity of jets of combustion products of solid-propellant rocket motors (SRM).
      
The Outflow of a Two-Phase Gas-Liquid Mixture from the Mixing Head of a Gas Generator when Starting a Liquid-Propellant Rocket E
      
This paper deals with the problems of mathematical simulation of the start-up of a liquid-propellant rocket engine (LPRE), which are associated with two-phase flows in the mixing heads (MH) of combustors and gas generators.
      
The instability of the working process in the combustion chamber of a solid-propellant rocket engine
      
Heat transfer in the thrust chamber is of great importance in the design of liquid propellant rocket engines.
      
更多          
  rockets
Ions with a Mass Number of Two in Mass-Spectrometric Experiments aboard Rockets and Satellites
      
Results of the calculation of the structure of relaxation shock waves in gas suspensions of the solid fuel of rockets are given in [8].
      
The mass-energy and specific characteristics of the propulsive jet discharges of rockets were factorized.
      
Variations in the electron density in the midlatitude ionospheric D region during launches and flights of different-type rockets at various distances from the launching site have been experimentally studied using partial reflections.
      
Coning motion stability of wrap around fin rockets
      
更多          
  rocket motors
The operation of rocket motors is often accompanied by the development of powerful secondary vortices in the combustion chamber [1-3], The superposition of the secondary vortices on the main flow leads to the formation of a cellular flow structure.
      
Monte Carlo simulation algorithms are given which are intended for the calculation of the spectral emissivity of jets of combustion products of solid-propellant rocket motors (SRM).
      
For technological reasons many high-performance solid rocket motors are made from segmented propellant grains with non-uniform port geometry.
      
This research demonstrated that hybrid rockets offer a safe, reliable upper stage option that is a versatile, cost-effective alternative to solid rocket motors.
      
Comprehension of wall-injection flow in a channel in the presence of different geometric discontinuities is necessary as part of the general investigations concerning combustion instabilities of solid propellant rocket motors.
      
更多          
  其他


点击这里查询相关文摘
图标索引 相关查询

 


 
CNKI小工具
在英文学术搜索中查有关火箭的内容
在知识搜索中查有关火箭的内容
在数字搜索中查有关火箭的内容
在概念知识元中查有关火箭的内容
在学术趋势中查有关火箭的内容
 
 

CNKI主页设CNKI翻译助手为主页 | 收藏CNKI翻译助手 | 广告服务 | 英文学术搜索
版权图标  2008 CNKI-中国知网
京ICP证040431号 互联网出版许可证 新出网证(京)字008号
北京市公安局海淀分局 备案号:110 1081725
版权图标 2008中国知网(cnki) 中国学术期刊(光盘版)电子杂志社