这一过程有一个另外的好处，就是不必为火箭发动机建造一个点火系统。
This provides the added advantage of not having to build an ignition system into the rocket.
然后，火箭发动机点火启动，飞船提速达到3倍音速，升入地球的大气层上空。
Then the Enterprise's rocket motors will ignite, accelerating the ship to three times the speed of sound, taking it up over the Earth's atmosphere.
本文采用理论分析和数值仿真方法对大长径比固体火箭发动机点火瞬态过程进行了系统研究。
This dissertation integrates theoretical analysis and numerical simulation method to investigate the ignition transient process of large aspect ratio solid rocket motors.
用固体火箭发动机中常用的瞬态平衡压强法对烟火剂式点火器内弹道性能进行了理论预示，并提出热损失系数的概念。
Instantaneous equilibrium pressure method is used in this paper to analysis the internal ballistics of pyrogen-type igniters. A concept of igniter heat loss coefficient is also presented.
爆震波多管点火技术适合用于多燃烧室液体火箭发动机的同步点火。
The detonation wave ignition technique is suitable to synchronization ignition of multi-chamber liquid rocket engine.
为了实现快速短距起爆，火焰射流点火系统被尝试应用在脉冲爆震火箭发动机上。
In order to achieve a rapid initiation of detonation in a short distance, a flame jet ignition system was applied to the pulse detonation rocket engine (PDRE).
星形是固体火箭发动机常用的装药形式，而其点火瞬时过程对发动机能否正常工作起着极为重要的作用。
Its ignition transient process plays an important role in determining whether a solid rocket motor can work normally.
固体火箭发动机的点火是一个十分复杂的物理化学过程，包括三个阶段：点火延迟、火焰传播和燃烧室气体充填。
The ignition of the solid rocket motor (SRM) is a very complex physical and chemistry process, which is composed of three component phases: ignition delay, flame spreading and chamber filling.
介绍了基于故障树分析法(FTA)进行的某固体火箭发动机低温下点火延迟故障的分析过程。
The ignition delay fault of solid rocket motor happening in a low temperature based on FTA is analyzed in the paper.
为研究轻型、可靠、环保的空间站机动变轨发动机，在氢氧液体火箭发动机头部设计中引入了新型气动谐振点火技术。
To develop light, reliable, sanitary space station maneuverable orbital transfer thruster, the novel gas dynamic resonance ignition method was applied.
因此对旋转固体火箭发动机尾部点火过程的数值模拟中，需要考虑点火器生成的高温粒子对点火过程的影响。
So the hot particles produced by the igniter should be considered in the numerical simulation of the ignition of the rotating RSM with the aft-end igniter.
中国已在西北部城市西安完成最大的固体燃料火箭发动机点火测试。
China has completed the test ignition of its largest solid-fuel rocket motor in the northwest city of Xi 'an.
这是首次成功地应用于空空导弹发动机上的点火发动机，从而为后续空空导弹固体火箭发动机点火装置的设计提供了一条新的途径。
This is the first time that ignition motor which successful used for an air-to-air missile. Which provides a good method for the design of next generation ignition motor.
就像人体的情况下，行业也是这样，阀门起到非常重要的角色，无论是运输饮用水，或在火箭发动机点火控制。
Like in case of human body, in industry too, the valves play a very vital role, be it transportation of drinking water, or control of ignition in a rocket engine.
中国已在西北部城市西安完成最大的固体燃料火箭发动机点火测试。
With a diameter of three meters, the solid-fuel rocket motor ran for 100 seconds after ignition.
结合气动谐振点火器进行头部设计的氢氧变轨火箭发动机是一项新颖化学火箭推进技术，尤其适于空间站应用。
Orbit maneuver hydrogen-oxygen thruster based on gas dynamic resonance igniter is a novel chemical propulsion technology especially prospective in space station application.
中国已在西北部城市西安完成最大的固体燃料火箭发动机点火测试。
Solid-fuel rocket engines have a much larger capacity than liquid-fueled iterations.
中国已在西北部城市西安完成最大的固体燃料火箭发动机点火测试。
Solid-fuel rocket engines have a much larger capacity than liquid-fueled iterations.
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