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   propulsive device 在 航空航天科学与工程 分类中 的翻译结果: 查询用时:0.051秒
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propulsive device
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  推进装置
    Microwave Plasma Thruster (MPT) is a new studying type electro-thermal propulsive device.
    微波等离子推力器(Microwave Plasma Thruster—MPT)是一种新型的在研电热推进装置
短句来源
    Pulse Detonation Engine (PDE) is a high-powered propulsive device which hasattracted great attention from the Department of Defense in China as a new concept atthe present time.
    脉冲爆震发动机(PDE)是一种新概念、高性能的推进装置,目前已受到我国国防部门的高度重视。
短句来源
    Pulse detonation rocket engine (PDRE) is a new concept of propulsive device which takes fuel and oxidizer, utilizes high temperature and pressure gas produced by pulsed detonation wave to generate thrust.
    脉冲爆震火箭发动机是一种自带燃料和氧化剂,利用脉冲式爆震波产生高温、高压燃气来产生推力的新概念推进装置
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    Pulse detonation engine (PDE) is a new concept of propulsive engine which uses high temperature and pressure gas produced by intermittent or pulsant detonation wave to generate thrust. PDE has many desirable advantages, including high thermal dynamic cycle efficiency, low specific fuel consumption, high thrust/weight and specific impulse, simple configuration, and will become propulsive device of aviation and spaceflight aerocraft in 21st century.
    脉冲爆震发动机是一种利用间歇式或脉冲式爆震波产生的高温、高压燃气来产生推力的新概念发动机,这种发动机具有循环热效率高、燃料消耗率低、推重比高、比冲大、结构简单等优点,将成为21世纪新型的航空航天飞行器的动力装置。
短句来源
    Scramjet is the perfect propulsive device to hypersonic vehicle, and is a hot issue in current hypersonic technology area.
    超燃冲压发动机是高超声速飞行器理想的动力装置,是当前高超声速技术领域的研究热点。
短句来源
    Pulse detonation engine (PDE) is a new concept of propulsive engine which uses high temperature and pressure gas produced by intermittent or pulsant detonation wave to generate thrust. PDE has many desirable advantages, including high thermal dynamic cycle efficiency, low specific fuel consumption, high thrustlweight and specific impulse, simple configuration, and will become propulsive device of aviation and spaceflight aerocraft in 21st century.
    脉冲爆震发动机是一种利用间歇式或脉冲式爆震波产生的高温、高压燃气来产生推力的新概念发动机,这种发动机具有循环热效率高、燃料消耗率低、推重比高、比冲大、结构简单等优点,将成为21世纪新型的航空航天飞行器的动力装置。
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  propulsive device
Use of propellers as a propulsive device has a history over 00 years.
      


Microwave plasma thruster (MPT) is a new type of electro-thermal propulsive device. We are the first in China to study MPT. Our MPT consists of a microwave generator, a gas storing and supplying system, a resonant cavity and an accelerating nozzle. When the microwave discharge breaks down the gas in the resonant cavity, free-floating plasma is generated. Then the plasma exhausts from nozzle to produce thrust. The key parameters in designing a small MPT suitable for space application are the geometric parameters...

Microwave plasma thruster (MPT) is a new type of electro-thermal propulsive device. We are the first in China to study MPT. Our MPT consists of a microwave generator, a gas storing and supplying system, a resonant cavity and an accelerating nozzle. When the microwave discharge breaks down the gas in the resonant cavity, free-floating plasma is generated. Then the plasma exhausts from nozzle to produce thrust. The key parameters in designing a small MPT suitable for space application are the geometric parameters and electromagnetic distribution parameters of the small cylindrical cavity. In order to obtain these parameters, we use the finite-difference time-domain (FDTD) method to solve the Maxwell equations, use the finite-volume method to solve the N-S equations; and use the single temperature local thermal equilibrium model to solve plasma equations the numerical simulation of the coupling flow field of microwave plasma within resonant cavity was discussed under the condition of different frequencies and the same resonant model. The results of numerical simulation are as follows: 1) When the resonant model is fixed, the size of MPT will decrease with the increase of the microwave frequency. 2) When the pressure in the cavity is fixed, the flow rate of gas, the microwave power and the throat of nozzle of MPT will all decrease with the decrease of the size of MPT, and the thrust of MPT is also decreased. 3) The distribution of the temperature, the pressure and the electronic density in resonant cavity will be invariable when the resonant model is fixed and the resonant frequency is different. These results can be used for miniaturization of MPT.

为了获得微波等离子推力器(MPT)圆柱形谐振腔小型化的设计参数,采用时域有限差分法(FDTD)求解Maxwell方程、有限体积法求解N-S方程、单温度局域热平衡模型求解等离子体数密度、温度等参数的全数值方法,对MPT圆柱形谐振腔在不同微波频率、相同谐振模式情况下的微波等离子体耦合流场进行了数值模拟计算。计算结果表明,提高微波频率可缩小圆柱形谐振腔尺寸。圆柱形谐振腔小型化后,在腔内压强一定的情况下,相应地工质气体的流量减小、消耗的微波功率减小,喷管喉径也减小、从而MPT的推力也减小,且不同微波频率、相同谐振模式情况下,腔内等离子体区温度、压强、电子数密度的变化规律相同。这些结论为今后MPT的小型化设计提供了理论依据。

 
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