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混合火箭
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  hybrid rocket
     Experimental investigation of N_2O-PMMA lab-scale hybrid rocket motor
     N_2O-PMMA小型混合火箭发动机试验研究
短句来源
     Experimental investigation on catalytic ignition of N_2O hybrid rocket motor
     N_2O混合火箭发动机的催化点火研究
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     Study on Improving Technological Properties of Solid Fuel SQ Formulation Used in Solid-Liquid Hybrid Rocket
     固液混合火箭用固体燃料SQ型配方工艺性能改善研究
短句来源
     A pressurization test system for H2O2PE hybrid rocket motors and the hybrid rocket motor structures are presented.
     介绍了挤压式H2O2 PE固液混合火箭发动机试验系统及发动机结构特点。
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     Computation of combustion in hybrid rocket motor using a boundary layer theory
     固液混合火箭发动机燃烧的边界层计算
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  “混合火箭”译为未确定词的双语例句
     An innovative igniter based on catalytic decomposition of N2O was designed and manufactured.
     利用N2O催化分解原理,设计了一个用于启动N2O混合火箭发动机的催化点火器。
短句来源
     In a typical hybrid,the fuel is a solid and the oxidizer is a liquid.
     固液混合火箭发动机是采用液体作为氧化剂,固体作为燃料的一种典型的混合火箭发动机。
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  相似匹配句对
     THE EXPERIMENTAL STUDY OF INJECTION AND MIXING OF THE MODEL EJECTOR ROCKET
     模拟火箭引射混合特性的实验研究
短句来源
     Hybrid Library
     混合程序库
短句来源
     Experimental investigation on catalytic ignition of N_2O hybrid rocket motor
     N_2O混合火箭发动机的催化点火研究
短句来源
     Hybrid Mail
     混合邮件
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     ON THE ORIGIN OF ROCKETS
     论火箭的起源
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  hybrid rocket
This paper discusses the potential of the hybrid rocket engine as a viable and attractive mode of propulsion for both space vehicles and missiles.
      
Experimental Study of Thrust Performance of a Hybrid Rocket Motor with Various Methods of Oxidizer Injection
      
A test bench and technique for experimental investigation of thrust performance of a hybrid rocket motor are described.
      
A hybrid rocket internal ballistics code was developed to model the performance of the motor, and to perform sizing of the rocket engine.
      
By employing catalytic decomposition of HTP, auto-ignition of the solid fuel in a hybrid rocket is possible.
      
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By use of direct trajectory optimization method,the selection of overall design parameters of an anti ballistic missile for a 1?000?km range ballistic target is discussed. The following factors are taken into account in our research: the variation of parameters of the solid rocket motor,the constrains to the collision angle required by the seeker side window,the constrains to the maximum Mach number and the terminal velocity for the consideration of ablation problem,the selection of initial flight path angle...

By use of direct trajectory optimization method,the selection of overall design parameters of an anti ballistic missile for a 1?000?km range ballistic target is discussed. The following factors are taken into account in our research: the variation of parameters of the solid rocket motor,the constrains to the collision angle required by the seeker side window,the constrains to the maximum Mach number and the terminal velocity for the consideration of ablation problem,the selection of initial flight path angle and time of launch and other considerations such as the maneuver load limit and gravity compensation. It is found that a very large interceptable region can be obtained by properly selecting the design parameters and by use of the hybrid rocket motor.

应用求解非线性规划问题的直接方法,针对一种典型的目标弹道(1000km) ,对一种方案反战术弹道导弹进行了总体参数优化设计研究.研究中考虑了:发动机特性参数的变化;导引头侧窗口对交汇角的限制;烧蚀问题所引起的对最大马赫数Mamax的限制和末速的限制;导弹发射时机的选择;导弹的初始弹道角的选择;其它( 如最大过载和最大攻角的限制及重力补偿等) .研究的目的是在考虑满足各种限制的条件下,通过选择各主要参数,使拦截区最大.结果表明,通过采用混合火箭发动机方案可扩大导弹的作战空域,同时满足采用侧窗导引头所带来的限制条件.

A boundary layer numerical solution was used for the computation of combustion in hybrid rocket motor according to the boundary burning theory. Various value of mass transfer number and the oxidizer mass flux were considered in the calculation. The regression rate of the solid fuel was formulized based on the calculation. The results show good agreement with the related references and useful for further study.

针对固液混合火箭发动机典型的边界层燃烧理论,用边界层的方法对固液混合火箭发动机燃烧进行了计算,计算采用二维轴对称的层流边界层方程,化学模型采用有限速率模型。计算考虑了不同氧化剂流率,不同吹入参数的多种情况,得到了固体混合发动机边界层的温度场分布,并利用计算结果,拟合了固体燃料的燃速公式,与相关文献的比较说明计算正确,结果符合燃烧机理和流动规律,为进一步研究固液混合火箭发动机的燃烧问题打下了基础。

A pressurization test system for H2O2PE hybrid rocket motors and the hybrid rocket motor structures are presented. The method for defining the working point of the hybrid rocket motor is discussed. The best ratio of oxidizer to fuel is adjusted for high combustion efficiency and high specific impulse.The phenomenon and the mechanism of low frequency oscillation combustion are also analyzed. With the aid of concept of fuel and oxidizer combustion delaying, theoretic calculation is done for simulating coupling...

A pressurization test system for H2O2PE hybrid rocket motors and the hybrid rocket motor structures are presented. The method for defining the working point of the hybrid rocket motor is discussed. The best ratio of oxidizer to fuel is adjusted for high combustion efficiency and high specific impulse.The phenomenon and the mechanism of low frequency oscillation combustion are also analyzed. With the aid of concept of fuel and oxidizer combustion delaying, theoretic calculation is done for simulating coupling oscillation between feed system and chamber pressure. Some methods are provided for avoiding and preventing low frequency oscillation in the hybrid rocket motors

介绍了挤压式H2O2 PE固液混合火箭发动机试验系统及发动机结构特点。研究了确定固液混合火箭发动机工作点的方法,按照这种方法可以使发动机在最佳的配比附近工作,有利于提高燃烧效率和比冲。分析了固液混合火箭发动机低频耦合振荡机理和现象,利用氧化剂和燃料燃烧时滞的概念,理论上计算模拟了发动机的低频耦合振荡过程,提出了避免这种燃烧振荡的措施和方法。

 
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