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   engine 在 航空航天科学与工程 分类中 的翻译结果: 查询用时:0.195秒
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engine
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  发动机
    The Method Investigation of 3D Measurement, Visual Re-construction and Recognition Applied in Engine Fault Images
    发动机故障图像的三维测量、视觉重建与识别方法研究
短句来源
    The Research of Engine Wear Faults Diagnosis Based on Debris Analysis and Data Fusion
    基于磨粒分析和信息融合的发动机磨损故障诊断技术研究
短句来源
    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
    Research on Airframe/Engine Integration Issues and Multidisciplinary Design Optimization Methods for Airbreathing Hypersonic Vehicle
    高超声速飞行器机体/发动机一体化及总体多学科设计优化方法研究
短句来源
    Studies on the Method of Reliability Growth Test Evaluation for Liquid Rocket Engine
    液体火箭发动机可靠性增长试验评定方法研究
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  引擎
    Research and Application on Measure and Keep Engine Rotational Speeds of the Airship with Double Engines
    双引擎飞艇发动机转速测量与保持的研究和应用
短句来源
    Study of the Engine Fault Diagnosis Method Based on Wavelet Transformation
    基于小波变换的引擎故障诊断方法研究
短句来源
    Finally,a emulational diagnosis system is devised by means of VC++ transferring MATLAB engine.
    最后采用VC++调用MATLAB引擎的方法进行了仿真诊断系统的设计。
短句来源
    This thesis expounded the modeling technology of 3D objects in computer animation simulation and the method of using OpenGL engine in Visual C++ environment, recommended correlative programming technology of the platform.
    最后本文系统阐述了计算机动画仿真中的对象建模技术和Visual C++环境下用OpenGL引擎实现三维动画的方法,并介绍了平台的相关编程技术;
短句来源
    By the methodology of separating the math model and geometry model of unmanned helicopter, a geometry model is singly built and is processed with our 3D engine and customized math model.
    本文中采用直升机的几何模型与数学模型分开的方法,单独建立几何模型,利用开发的三维渲染引擎并结合自定义的数学模型进行渲染和控制。
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  “engine”译为未确定词的双语例句
    VIBRATION SPECTRUM ANALYSIS OF A TURBOPROP ENGINE IN STARTING PROCESS
    发动机起动过程的振动谱分析
短句来源
    Ablation Calculation of Carbon/Carbon Composite Throat Liner in Aluminumized Solid Propellant Engine
    碳/碳复合材料喉衬的烧蚀计算
短句来源
    Advances in Solid Rocket-Ramjet Engine
    固体火箭-冲压发动机的研究进展
短句来源
    The Performance Calculation and Parameter Analysis of Fan-Ramjet Engine
    风扇冲压发动机性能计算及参数分析
短句来源
    Optimum Design of Scramjet Engine
    超音速燃烧冲压发动机最佳设计参数
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  engine
The efficient Fourier transform also makes possible the efficient calculation of convolution over SO(3) which has been used as the analytic engine for some new approaches to searching 3D databases (Funkhouser et al., ACM Trans.
      
Design and characteristics of electric supercharger for diesel engine acceleration by additional rapid air injection
      
Research results indicate that the electric supercharger can respond rapidly with the great flux, and it is independent of the operating conditions of a diesel engine.
      
Influence of temperature on cam-tappet lubrication in an internal combustion engine
      
The transient thermo-elastohydrodynamic (TEHL) lubrication simulation and isothermal elastohydrodynamic (EHL) simulation were performed on the exhausting camtappet friction pair of an internal combustion engine.
      
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A simplified model for the disign of hypergolic liquid propellant rocket engine combustors is presented.In contrast with Priem's basic model,the effects of decomposition reaction of fuel,secondary atomization of droplets and non-uniformity of mixture ratio and flow flux in the cross-section of the chamber on the combustion efficiency have been considered.All equations required for the calculation of combustion efficiency are derived and the computer program is given.As an example of the application of...

A simplified model for the disign of hypergolic liquid propellant rocket engine combustors is presented.In contrast with Priem's basic model,the effects of decomposition reaction of fuel,secondary atomization of droplets and non-uniformity of mixture ratio and flow flux in the cross-section of the chamber on the combustion efficiency have been considered.All equations required for the calculation of combustion efficiency are derived and the computer program is given.As an example of the application of this method,the combustion efficiency of “C” engine is calculated.Comparison of calculated Combustion efficiencies with experimental results shows satisfactory agreement with errors within 1-5%.Curves of total vaporization rate of fuel and vaporization rate per unit length as functions of the axial distance of combustor for given rocket engine are also presented.These curves show that the effects of decomposition reaction,secondary atomization of droplets and drop size distribution on vaporization rate are very substantial.Finally, the conditions,under which this model can be used,are discussed

本文提出了一个自燃推进剂液体火箭发动机燃烧室设计简化模型。与 Priem 基本模型不同,本文考虑了燃料分解反应,液滴二次雾化以及燃烧室截面上混合比和流强的不均匀性对燃烧效率的影响。文中导出了计算所需的全部公式,提出了计算程序。应用本方法计算了 C 发动机的燃烧效率。计算效率与试验结果相当符合,其误差在1~5%以内。文中还给出了燃料总蒸发速率和单位长度上的蒸发速率随该发动机燃烧室轴向距离变化的曲线。曲线表明,分解反应,液滴二次雾化和液滴尺寸分布对蒸发速率的影响很大。最后讨论了本模型使用的条件。

This paper is a phase report of study for the subject “Throtting Cavita- tion Venturi.”The design methods involved and preliminary theoretical analysis having been discussed in other papers,this report puts emphasis on the discussion of the following points:the maximum absolute error δ and maximum relative error ξ within the operating range of the throttling cavitation venturi, the relationships between the main parameters,test specimens,equipments and results,two phase gas-liquid flow in the cavitation venturi...

This paper is a phase report of study for the subject “Throtting Cavita- tion Venturi.”The design methods involved and preliminary theoretical analysis having been discussed in other papers,this report puts emphasis on the discussion of the following points:the maximum absolute error δ and maximum relative error ξ within the operating range of the throttling cavitation venturi, the relationships between the main parameters,test specimens,equipments and results,two phase gas-liquid flow in the cavitation venturi and the bubble dynumic characteristics under the condition of small amplitude. This paper may be utilized as a reference for those who are engaged in the development of variable-thrust liquid propellant rocket engine and liquid venturi flowmeters.

本文是“流量可调汽蚀文氏管”研究课题的阶段研究报告,因有关的设计方法及初步理论分析已在专门的文章中讨论了,故本篇重点讨论如下几个问题:流量可调汽蚀文氏管工作范围内的最大绝对误差δ,最大相对误差ξ,各主要参数间的关系,试验件,试验设备及试验结果,汽蚀文氏管中的气——液二相流及小振幅情况下的气泡动态特性等。本文可供研制变推力液体燃料火箭发动机及文氏管液体流量计有关人员参考。

A Computer program of the hot starting and shutdown transients of a simple pressurized liquid bipropellant rocket engine is given,based upon the idea and basic equations provided by W.T.Webber etal.and mainly applying priem's combnstion model and feeding system distribution para- meter model.The hot starting and shutdown transients are calculated on 441B-Ⅲ digital computer and the elementary results arc obtained.

本文依据 W.T.Webber 等人提供的思路和基本方程,基本采用了 Priem 的燃烧模型和管路系统分布参数模型,为简单的挤压式双元液体推进剂火箭发动机热启动——关车瞬变工作过程编写了计算机程序,并在441B—Ⅲ型电子计算机上进行了计算,得出了初步的结果。

 
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