1) electropulse engine
电脉冲发动机
2) pulse engine
脉冲发动机
1.
Based on practice,the airborne rockets guidance techniques have been studied elementarily,a terminal correction means of rockets using impulse engine has been put forward,the control equations of the impulse correction have been built,and the key problems have been studied and analyzed.
立足实际,对火箭弹末制导技术进行了初步研究,提出了一种利用脉冲发动机实现火箭弹末段修正的方法,建立了脉冲修正的控制方程,并对其关键问题进行了探讨和分析。
2.
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.
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。
3) pulse motor
脉冲发动机
1.
The blended control switch-time and the formula for deciding the pulse motor .
对比分析了国外已研制成功的直接力与气动力复合控制拦截弹;定性分析了直接侧向过载控制和力矩直接力控制的优缺点;探讨了复合控制拦截弹在末制导阶段是否需要滚转及转速对制导精度的影响;确定了复合控制的切换时间;推导出拦截弹所需要的脉冲发动机数量的公式,并对其详细讨论。
2.
In solving problems of breakage in nozzle throat inserts for a pulse motor,analysis on the strength of nozzle throat insert have been carried out using the MSC Patran 2004r2 finite element soft-ware.
为了解决脉冲发动机喷管喉衬曾出现过从其喷管座中打出的故障问题,利用MSC Patran 2004r2有限元软件对脉冲发动机喷管喉衬进行了强度分析。
3.
Optimum design of the composite shell of pulse motor has been presented using ANSYS soft ware.
采用ANSYS软件对脉冲发动机复合壳体进行了优化设计研究。
4) pulse jet
脉冲发动机
1.
To study the attitude stabilization control effect on short-range antitank rockets using pulse jets.
为研究近程反坦克火箭弹采用脉冲发动机进行姿态稳定控制的效果,文中提出脉冲点火算法和脉冲发动机的等效合力模型,通过弹道仿真分别研究了初始扰动、推力偏心、常值风等主要干扰因素作用下姿态稳定系统的控制效果。
2.
If the angle of fire is large,using pulse jets to correct the rocket trajectory,the error in theory in the relation between thrust vector produced by pulse jets and the error vector corrected will arise,which is established by the general coordinate transform in order to decide which pulse jet will be fired.
利用脉冲发动机对火箭弹弹道进行修正时,采用一般的坐标转换方法计算脉冲发动机产生的推力矢量与误差矢量对应关系,并由此决定脉冲发动机是否点火。
3.
The pulsed proportional navigation(PPN) guidance and attitude pursuit guidance(APG) by the concept of zero effort miss(ZEM) were established,and the corresponding ignition control strategy of the pulse jet was presented.
建立基于零效脱靶量概念的两种末制导律——弹体追踪和脉冲比例导引,并给出对应的脉冲发动机点火控制方法。
5) impulse engine
脉冲发动机
1.
In the condition of definitive structural parameter and part of operative parameter of impulse engine,the effect of controlling force of impulse engine on correct trajectory is analysed.
在确定了脉冲发动机的结构参数和部分工作参数的情况下,分析了脉冲发动机控制力对修正弹道的影响能力,确定了在满足修正能力及飞行稳定性的条件下脉冲发动机的总层数、单冲和点火间隔。
2.
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.
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。
6) impulse thruster
脉冲发动机
1.
In order to determine the attack area of semi-active laser guided mortar projectiles with impulse thrusters for terminal correction, the model of acquisition area for the seeker was established.
结果表明,提供的模型及仿真方法适用于该类弹箭攻击区的求解,对于导引头、脉冲发动机的设计也有一定的参考价值。
补充资料：航空发动机推重比(见航空发动机推力)
航空发动机推重比(见航空发动机推力)
thrust to weight ratio of aeroengine
hQngkong角dong)1 tuizhongbi航空发动机推重比〔thros*:。wdgh:ra-tio of aeroengine)见航空发动机推力。
说明：补充资料仅用于学习参考，请勿用于其它任何用途。
参考词条