采用ANSYS软件对脉冲发动机复合壳体进行了优化设计研究。
Optimum design of the composite shell of pulse motor has been presented using ANSYS soft ware.
分析表明，通过优选脉冲发动机的结构参数和工作参数可以达到预期的弹道控制效果。
It is pointed out that the expectant trajectory control effect can be achieved by the priority selection of the structural parameter and operative parameter of impulse engine.
对五种不同燃烧室体积的脉冲发动机在小、中和大油门开度三种供油条件下测定其排放物。
The exhaust gas ingredients of pulse engines, with five different combustion chamber volumes, throttle valve at small, middle and wide opening positions respectively, are tested.
研究结果对脉冲发动机的点火起控点选择以及脉冲发动机的个数选择都有一定参考价值。
So the research is important to the selection of the fire time and number of the impulse engine and serves as theory reference.
重点讨论在快速转弯段以及快速响应过载段消耗脉冲发动机个数和系统响应时间之间的关系。
The relationship between number of required pulse motors and system response time was discussed in quick turn period and transition process.
针对弹道修正技术中应用的脉冲发动机，设计了一种用于验证发动机修正能力的动态实验方法。
Aiming at the impulse engine in the trajectory correction projectile, one dynamic experiment method is put forward to measure the correction ability of the impulse engine.
地磁传感器测量的数据不仅用于解算弹体飞行姿态，同时可通过计算给出点火脉冲发动机选择的方向基准。
The data measured by magnetic sensor can be used in calculating the flight attitude of the projectile and giving the direction benchmark of firing pulse jet.
小型固体火箭脉冲发动机具有体积小、反应时间短、结构简单、成本低廉等优点，是一种比较理想的修正执行机构。
The small solid rocket impulse engines have the advantages of small volume, short reaction time, and simple configuration, low cost, so it is a right choice.
触发叶轮随发动机转速而旋转，使得转速传感器或拾波线圈产生与发动机转速和活塞位置相对应的触发电压脉冲。
The trigger wheel rotates with engine RPMs and causes the speed sensor, or pickup oil, to produce triggering voltage pulses that correspond to engine speed and piston position.
曲柄参考点脉冲信号由一个变磁阻传感器产生，它从发动机飞轮上的突起感受信号。
The crank reference pulse originates from a variable reluctant pickup which senses a projection on the engine's flywheel.
分析了两相多循环脉冲爆震发动机工作过程中爆震室内、外壁换热特性，建立了爆震室壁温分布计算模型。
The heat transfer characteristics of the detonation chambers outer and inner wall were analyzed when the pulse detonation engine model was operated in the multi-cycle mode.
简述了脉冲爆震火箭发动机的实验系统，利用电磁阀控制煤油，氧气和隔离气体，避免了连续燃烧。
A prototype of pulse detonation rocket engine (PDRE) is introduced to solenoid valves for the control of oxygen, kerosene and isolation gas; thus continuous combustion is avoided.
对脉冲爆震发动机的混合室进行了实验研究。
The experimental study on the mixing chamber of pulse detonation engine prototype is performed.
本文首先对脉冲火箭发动机的测试系统进行组建，提出了测试系统的硬件组成方案，并对测试系统的各个应用环节加以论证。
Firstly, the pulse rocket engine test system has been built and provides hardware constitute plan and test every aspect of the application of the test.
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).
因此实际调节脉冲爆震爆震发动机应尽量采用组合的调节方式。
Therefore, combined control method should be used for controlling pulse detonation engines.
进行三个脉冲管与行波型热声发动机的配合实验，着重研究了热端气体温度、冷端温降和压力振幅的变化规律。
The experiment focuses on the temperature of the gas in the hot end heat exchanger, the temperature decline of the cold end of the pulse tube and pressure amplitude.
同时，该类研究还可为脉冲爆轰发动机(PDE)的研制提供理论基础。
Meanwhile, this study can provide theoretical basis for development pulse detonation engine (PDE).
有效的触发爆震波是脉冲爆震发动机正常工作的关键所在。
Efficient initiation of detonation waves is the key to the pulse detonation engine AB.
所以对于脉冲爆震爆震发动机应采用调节爆震频率和燃气填充相结合的控制策略。
Therefore, a cooperation method of the frequency and fuel flow should be used for pulse detonation engine control.
脉冲爆震火箭发动机是一种利用脉冲式爆震波产生高温、高压燃气发出的冲量来产生推力的新型推进系统。
A pulse detonation rocket engine (PDRE) is a new propulsion system that generates thrust by using high-temperature and high-pressure air produced by pulse detonation waves.
在涡扇发动机基础上，以脉冲爆震燃烧室代替普通加力燃烧室构成涡扇-脉冲爆震组合发动机。
Based on a turbofan engine, the afterburner is replaced with pulse detonation combustor to form a turbofan-pulse detonation hybrid engine.
在直管脉冲爆震发动机上安装不同类型的喷管，利用推力传感器测量了不同频率下发动机的瞬态推力和平均推力。
Test results from an experimental investigation of the effect of nozzle on the thrust of a straight tube pulse detonation engine are presented.
脉冲爆震发动机具有众多优点，近来受到广泛的关注和研究。
Pulse detonation engine has received much attention of late because of its several advantages compared to existent engines.
对某天然气发动机缸内压力信号、齿盘脉冲信号和上止点脉冲信号进行同步采样。
For a CNG engine, the cylinder pressure signal, gear pulse signal and top dead center pulse signal were simultaneously collected.
提出一种近月面定点悬停的控制方案，选用常推力液体发动机和脉冲式发动机实现悬停任务。
A control scheme is proposed, in which liquid engine of constant thrust and impulse thruster are chosen to achieve hover task.
提出了一种带有中间喷管的新型双脉冲固体火箭发动机技术方案，设计了一台结构参数可调的试验发动机；
A new type of dual-pulse solid rocket motor concept with an intermediate nozzle is presented and a test motor with changeable structural parameters was designed.
气动控制在低动压时其效率会有相当下降，为了使导弹在低动压时仍然具有一定的快速响应性，在导弹上安装脉冲姿控发动机参与姿态控制是一条可行的途径。
The effectiveness of aero control decreases as dynamic pressure decreases. Therefore impulse attitude control motor(ACM) is to be used to maintain fast response of missile in low dynamic pressure.
气动控制在低动压时其效率会有相当下降，为了使导弹在低动压时仍然具有一定的快速响应性，在导弹上安装脉冲姿控发动机参与姿态控制是一条可行的途径。
The effectiveness of aero control decreases as dynamic pressure decreases. Therefore impulse attitude control motor(ACM) is to be used to maintain fast response of missile in low dynamic pressure.
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