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发动机点火    
相关语句
  engine ignition
    MICROCOMPUTER DIAGNOSIS SYSTEM FOR AUTOMOTIVE ENGINE IGNITION SYSTEM
    汽车发动机点火系的微机诊断系统
短句来源
    Features of Rotary Engine Ignition System on MAZDA RX 7 Car and Its Fault Removal
    马自达 RX-7 型轿车转子发动机点火系特点及故障排除
短句来源
    Developing a Fault Diagnosis Expert System for Automobile Engine Ignition Systems
    汽车发动机点火系统故障诊断专家系统的研究开发
短句来源
    Development of a Fault Diagnosis Expert System for Automobile Engine Ignition Systems
    汽车发动机点火系统故障诊断专家系统的开发
短句来源
    Testing Analysis of Engine Ignition System Transient Voltage
    发动机点火系统瞬变电压的测试分析
短句来源
更多       
  engine ignition
    MICROCOMPUTER DIAGNOSIS SYSTEM FOR AUTOMOTIVE ENGINE IGNITION SYSTEM
    汽车发动机点火系的微机诊断系统
短句来源
    Features of Rotary Engine Ignition System on MAZDA RX 7 Car and Its Fault Removal
    马自达 RX-7 型轿车转子发动机点火系特点及故障排除
短句来源
    Developing a Fault Diagnosis Expert System for Automobile Engine Ignition Systems
    汽车发动机点火系统故障诊断专家系统的研究开发
短句来源
    Development of a Fault Diagnosis Expert System for Automobile Engine Ignition Systems
    汽车发动机点火系统故障诊断专家系统的开发
短句来源
    Testing Analysis of Engine Ignition System Transient Voltage
    发动机点火系统瞬变电压的测试分析
短句来源
更多       
  engine start
    Research on Fault Online Detect of UAV Engine Start and Pull Up Circuit
    无人机发动机点火停车电路故障在线检测研究
短句来源
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  engine ignition
Figure 2 illustrates a sponge device used for engine ignition in a typical propellant tank.
      
Ignition systems require gas free delivery during engine ignition while propellant is settling over the tank outlet.
      
Initial data analysis showed that the countdown, engine ignition and initial phase of flight were normal.
      
Investigation of deflagration to detonation transition for application to pulse detonation engine ignition systems.
      
In contrast, in quasihorizontal launch mode the center of the front dome is submerged at engine ignition.
      
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The 300mm diameter solid Propellant rocket motor employs a composite propellant end burning grain. The effective burning time was 42 seconds and the thrust was 720kg. For the motor operating reliability, the motor utilizes a large number of nonmetal materials for thermal protecion of the case and the nozzle, for the lining of the grain, and for the motor assembly seal. The motor repeated firing tests proved that the performance of the materials was good, the design of the structures was reasonable, the technological...

The 300mm diameter solid Propellant rocket motor employs a composite propellant end burning grain. The effective burning time was 42 seconds and the thrust was 720kg. For the motor operating reliability, the motor utilizes a large number of nonmetal materials for thermal protecion of the case and the nozzle, for the lining of the grain, and for the motor assembly seal. The motor repeated firing tests proved that the performance of the materials was good, the design of the structures was reasonable, the technological method was reliable, and all the design criteriaw ere met. This paper discusses the design rationale, the structural features, theperformance, the results of the motor firing test, and the major technical problems of these nonmetal material components.

直径300毫米的固体推进剂火箭发动机采用了复合推进剂端燃药柱。有效燃烧时间42秒,推力720公斤。为保证发动机可靠地工作,发动机采用了大量的非金属材料用于壳体及喷管的热防护、药柱的包覆和发动机装配的密封。多次发动机点火试验证明这些料材的性能良好,结构设计合理,工艺措施可靠,符合设计要求。本文论述了这些非金属材料部件的设计思想,结构特点、性能、点火试验结果以及主要技术问题。

The ignition of combustible gas stream by electric spark discharge was considered both theoretically and experimentally. By treating the spark as a linear heat source and applying the boundary layer assumptions, the development of the reaction zone was calculated. By adopting the ignition criterion based on the behaviour of the reaction zone development, the critical ignition condition was determined and discussed. The process of ignition was experimentally followed photographic inspections. Comparing with the...

The ignition of combustible gas stream by electric spark discharge was considered both theoretically and experimentally. By treating the spark as a linear heat source and applying the boundary layer assumptions, the development of the reaction zone was calculated. By adopting the ignition criterion based on the behaviour of the reaction zone development, the critical ignition condition was determined and discussed. The process of ignition was experimentally followed photographic inspections. Comparing with the computed reaction zone development, it shows that this sort of treatment do describes the essential feature of the ignition process. In addition, the influence of the spark energy, the gas stream speed and the electrode distance on the lean ignition limit of the gasoline-air mixtures by an automobile ignition coil was determined.

对电火花引燃可燃气流的问题进行了理论分析和实验研究。将电火花看作是可燃气流中的一个线热源,运用边界层方程,考察反应区的发展,以其能否扩展开去作为引燃的判据,分析讨论了着火临界条件,导出了点火能和流速等参数之间的关系。实验中拍摄了不同条件下火焰发展的面貌,与数值计算得到的反应区发展相比较,表明这种模型确是在一定程度上反映了电火花引燃可燃气流的实际情况。此外,利用汽车发动机点火系统测试了电火花能量、来流速度、电极距离等因素对汽油-空气预混气的着火稀限的影响。

According to the mock fire rendering that fired in June and July, 1981,made by an electronic computer it is firmly believed that the initialperturbation is a decisive one of all the factors that influence the firingconcentration of ×× rocket, and the over high rotating speed of the rocketand the gas jet, especially that of the engine rotating the rocket, are thedecisive ones of all the factors that influence the initial perturbation inthe paper. To improve the firing concentration of ×× rocket, the proposals...

According to the mock fire rendering that fired in June and July, 1981,made by an electronic computer it is firmly believed that the initialperturbation is a decisive one of all the factors that influence the firingconcentration of ×× rocket, and the over high rotating speed of the rocketand the gas jet, especially that of the engine rotating the rocket, are thedecisive ones of all the factors that influence the initial perturbation inthe paper. To improve the firing concentration of ×× rocket, the proposals to laysteel plats on the rocket launcher for weakening the force of the gas jet, toslow down rotating speed of the rocket (for example, to reduce by half) andto postpone the ignition of the engine rotating the rocket are put forward andproved in the paper. In a broad sense, this paper also discussed the influence of the rotationof a rocket on the length of critical section of the eccentric of motive forceof the rocket. The conclusion has come to that the length approaches to a halfof its trajectory wave length i. e. equals to the critical section of initialperturbation when the rotating speed is comparatively high.

××火箭的研制经历了二十余年的漫长历程,射击密集度曾长期不过关。我们通过电子数字计算机模拟发射,重现了1981年6~7月发射试验,且确定了各种情况下的特征系数,为分析计算××火箭的方向密集度提供了方便。 本文认定影响××火箭密集度的决定性因素是起始扰动,而影响起始扰动的主要因素是燃气流特别是旋转发动机的燃气流作用力。为了提高××火箭的密集度,重申了在定向器上铺钢板以减小燃气流作用力的意见;提出了降低现有炮口转速(例如折半)和推迟旋转发动机点火的建议,对此作了定量论证。 本文还在一般意义上探讨了弹体自转对推力偏心临界段的影响问题,指出当自转速度较高时,推力偏心临界段长度趋近于半个弹道波长,即趋于与起始扰动临界段长度相等。

 
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