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   propulsion systems 在 航空航天科学与工程 分类中 的翻译结果: 查询用时:0.008秒
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propulsion systems
相关语句
  推进系统
    The Test Equipment of Aircrew Escape Propulsion Systems
    乘员救生推进系统的试验设备
短句来源
    EVOLUTION OF HEALTH MONITORING TECHNIQUE OF LIQUID R0CKET PROPULSION SYSTEMS
    液体火箭推进系统健康监控技术的演变
短句来源
    WAVELET ANALYSIS AND ITS APPLICATION IN HEALTH MONITORING OF PROPULSION SYSTEMS
    小波分析及其在推进系统健康监控中的应用
短句来源
    DEVELOPMENT ON SOFTWARE OF MANAGEMENT AND FAULT DIAGNOSIS OF PROPULSION SYSTEMS
    卫星推进系统在轨管理和故障诊断软件的开发
短句来源
    AN ANALYSIS ON ENERGY UTILIZATION OF JET PROPULSION SYSTEMS
    喷气推进系统的用能分析
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  “propulsion systems”译为未确定词的双语例句
    New Concept Propulsion Systems and Their Application Prospect
    新概念推进技术及其应用前景
短句来源
    The development of dual-mode chemical propulsion systems
    双模式化学推进技术发展研究
短句来源
    Rocket Based Combined Cycle (RBCC) will be one of the promising propulsion systems for single stage to orbit vehicle, and has extensively application foreground in both military and civil usage. Ejectorjet is the alternative power of RBCC during low-speed operation.
    火箭基组合循环发动机(RBCC:Rocket Based Combined Cycle)是单级入轨最有潜力的动力方案之一,具有广泛的军事和民用航天应用前景,受到世界各国航天界的瞩目。
短句来源
    Infrared sources of jet propulsion systems were analyzed and their suppression techniques were discussed in this paper.
    本文分析喷气动力装置的红外辐射源,并讨论抑制红外辐射的技术途径.
短句来源
    It might be seen from the developing work in AFRPL and the articles published in AIAA/DGLR/ISASS 18th IEPC and 19 th IEPC that the developing of nonconventional propulsion systems is not only a conceptual conceiving now, but also a number of applications in space destined to occur in the next 10 to 15 years.
    从美国“空军火箭推进实验室”(AFRPL)的发展工作以及国际电推进会议的论文可以看到,非常规推进的发展早已经不是方案设想,大约在未来的10~15年内,即将在一系列空间任务中付诸实现.
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  propulsion systems
Mechanical and propulsion systems prognostics: U.S.
      
High-cycle fatigue (HCF), involving the premature initiation and/or rapid propagation of cracks to failure due to high-frequency cyclic loading, remains a principal cause of failures in gas-turbine propulsion systems.
      
This requires a further development of current diesel and gasoline engines as well as a careful look to alternatives like fuel cell systems or hybrid propulsion systems.
      
Increasing shortage on energy resources as well as future emission legislation development increase the pressure to develop more efficient, environmentally friendly propulsion systems for vehicles.
      
An analysis is made of the optimum motion for three possible propulsion systems: limited exit velocity, limited power, and limited thrust.
      
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Simplification of the mathematical model for a marine gas turbine propulsion system is studied by modal analysis,and selection of remained state variables in the order-reduced model

木文结合航机改装的舰用燃气轮机系统,在较详细的高阶非线性模型的基础上进行了系统的模态分析和灵敏度分析,进而探讨了燃气轮机作为控制对象时反馈变量的选择和高阶模型的简化方法。这方法为这类系统的控制器设计时数学模型的处理提供了有价值的参考。

Electrical rocket engine is a new type of space propulsion system. It has the advantages of high impulse and longevity and is particularly suitable for long-life satellites and space stations in future.The sorts, elementary theory, latest development and future prospects are introduced in this paper.

电火箭发动机是一种新型的空间推进装置.它的优点是比冲高和寿命长,因此特别适用于未来的长寿命卫星和空间站.本文介绍了现有电火箭发动机的种类、基本原理、现状和发展方向.

Axial-flow compressor developed for advanced propulsion system tends to possess large mass flow, large. loading and high efficiency. As a result, three-dimensional flow effects have significant influence on the performance of the compressor cascade, and thus it is difficult to model the flow occurring in a real compressor cascade passage with plane cascade experiments, especially in tip and root regions. The authors investigate a varying-geometry converging cascade passage whose geometric shape is similar...

Axial-flow compressor developed for advanced propulsion system tends to possess large mass flow, large. loading and high efficiency. As a result, three-dimensional flow effects have significant influence on the performance of the compressor cascade, and thus it is difficult to model the flow occurring in a real compressor cascade passage with plane cascade experiments, especially in tip and root regions. The authors investigate a varying-geometry converging cascade passage whose geometric shape is similar to that of a real compressor. Experiments show that, in such a cascade, air-flow can be deflected at lower velocity, and then accelerated, and thus, the boundary layer on the side wall becomes thinner, and the width of wake small, all of which bring a lower total pres- sure loss. By adopting the theory of compressible turbulent boundary layer, utilizing some characteristic parameters such as momentum thickness, form factor, energy factor and other combined parameters, and then assuming the flow model with simple-power velocity distribution in the wake behind the cascade, a simplified equation for calculating total pressure loss coefficient, static pressure ratio, and diffusion factor of high subsonic converging cascade is derived. The basic equation derived may be used for predicting the performance parameters of inlet guide vane and stator of the compressor for both design condition and off-design condition. In this paper, based on the assumption of a model with simple-power velocity distribution in the wake behind the cascade, a correlation equation, relating "n" to intake flow condition, cascade geometric parameters and characteristic parameters in the wake behind the cascade, is also derived. Therefore, we can estimate the value of "n" by means of the above equation, thus making experiments unnecessary. According to these basic equations, the total pressure losses, static pressure ratio and diffusion factor for the given compressor cascade with converging passage under various conditions are calculated and found to be in fairly good agreement with experimental data.

本文对变几何收敛通道中扩压叶栅的主要性能参数(总压损失系数ω、增压比π、扩散因子D)进行了初步理论分析研究,推导出高亚音速范围内该类型叶栅的几何参数、气流参数、尾迹附面层特性参数与叶栅主要性能参数的关联方程,并在亚音速范围内,将采用上述方程得到的计算值同实验值进行了比较,表明两者吻合较好,从而为压气机叶栅设计时选取主要参数提供了依据。

 
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