级发动机 meaning in Chinese
stage engine
stage motor
Examples
- Qualifying continuous duty class 1e motors for nuclear power generating stations
核电站用1e级发动机连续运行的考核 - The purpose of this paper is to make extensive study on the essence of impingement / effusion film cooling , and the research results will be applied in futural study on the higher performance aeroengine
本文旨在对冲击-发散复合冷却技术开展机理和基础性研究,研究成果可应用于更高推重比级发动机预研。 - In this thesis , based on pershing ii surface to surface missile , a new kind of ballistic missile was designed with an additional rocket engine , which can be ignited twice . firstly , aerodynamic computational models of missile body and warhead which reentry with supersonic are built according to the task requirements ; secondly , the propulsion system model of missile is built whose first two stages are solid rocket engines and the third stage is liquid - solid combined rocket engine . the nozzle and the shape of the engine are designed to meet the needs of the populsion project ; thirdly , the trajectory model of the mass point is built and a wavy trajectory is designed & optimized ; finally , the ability of a missile ' s breaking through defence is analyzed
以美国潘兴导弹为原型，增加可两次点火的末级发动机，改装成具有跳跃能力的地地弹道导弹；首先，根据任务需求，建立了导弹的气动模型，并建立了弹头再入时高超声速气动模型；其次，建立了导弹推进系统模型，前两级采用了固体火箭发动机，第三级采用了固?液组合火箭发动机，并在总体方案要求下，对发动机喷管和外形进行了设计；第三部分，建立了导弹质点弹道模型，设计了一条跳跃式弹道，并对跳跃式弹道进行了优化设计；最后，对导弹进行了突防能力分析，从分析的结果可以看出，跳跃式弹道的突防能力比常规的抛物线弹道要强。 - Abstract : solid propellant rocket motors are preferred for most ballistic missiles because they need simple maintenance and can be launched quickly . but the conventional thrust termination devices limit the depletion of every stage ' s grain and increase some extra - weight . an improved method for designing a multi - stage solid rocket based depleted shutdown was provided . in order to solve the problem of lack of thrust termination devices , a device to adjust the burnout angle will match the final burnout velocity and satisfy the desired range . the method can also limit the detection from anti - ballistic missile system
文摘:由于维护简单和发射快速,弹道导弹多用固体火箭发动机,但繁杂的推力终止装置使各级装药不能耗尽并让结构增重.提出了一种对基于耗尽关机多级固体火箭概念设计的改进方法,此方法满足导弹系统主要的战技要求.为解决无推力终止装置的末速不准问题,可在末级发动机采用姿态调整装置,对射角进行调整,配合末速以满足射程要求.本方法还可抑制敌方反导探测