火箭发动机燃烧室的英文

• chamber; rocket motor
• rocket chamber
• rocket-motor tube

• "燃烧室"英文翻译    combustion chamber; blast ch ...
• "火箭发动机燃烧室壁冷却" 英文翻译 :    rocket wall cooling
• "火箭发动机燃烧室运动" 英文翻译 :    chamber movement
• "绕丝火箭发动机燃烧室" 英文翻译 :    filament-wound rocket chamber
• "筒形火箭发动机燃烧室" 英文翻译 :    cylindrical rocket combustion chamber
• "液体火箭发动机燃烧" 英文翻译 :    liquid-rocket combustion
• "发动机燃烧室" 英文翻译 :    engine chamber; motor chamber
• "单燃烧室火箭发动机" 英文翻译 :    single-barrel rocket engine; single-chamber rocket engine; single-chamber rocket motor
• "多燃烧室火箭发动机" 英文翻译 :    multi-unit rocket engine
• "分隔燃烧室的火箭发动机" 英文翻译 :    partitioned rocket engine
• "双燃烧室火箭发动机" 英文翻译 :    dual-chamber rocket engine
• "四燃烧室火箭发动机" 英文翻译 :    four cylinder thrust unit; four-chamber rocket engine; four-engined rocket motor; quad chamber rocket engine; quad-chamber rocket engine
• "发动机燃烧室直径" 英文翻译 :    motor chamber diameter
• "主发动机燃烧室" 英文翻译 :    sustainer chamber
• "多燃烧室液体火箭发动机组" 英文翻译 :    multiple rocket-engine assembly
• "喷管收缩的发动机燃烧室" 英文翻译 :    mae west
• "涡轮喷气发动机燃烧室" 英文翻译 :    turbojet chamber
• "主发动机燃烧室壳体" 英文翻译 :    sustainer charge body tube
• "发动机燃烧" 英文翻译 :    cumbustion
• "火箭发动机" 英文翻译 :    engine; rocket; motor; rocket; rocket engine; rocket motor system; thrust chamber; thrust cylinder
• "侧面燃烧火箭发动机" 英文翻译 :    lateral-burning rocket engine; side-burning rocket engine
• "端面燃烧火箭发动机" 英文翻译 :    cigarette-burning rocket engine; end-burning rocket engine; end-burning rocket motor
• "火箭发动机中的燃烧" 英文翻译 :    rocket-motor combustion
• "径向燃烧固体火箭发动机" 英文翻译 :    radial-burning rocket motor
• "限制燃烧的火箭发动机" 英文翻译 :    restricted-burning rocket engine

• To appreciate the unsteady environment existing in liquid propellant rocket chambers it is necessary that the steady state be well understood .
  为了分析液体推进剂火箭发动机燃烧室中存在的非稳态环境，必须很好地了解稳态状态。
• Calculation of nozzle efficiency for solid rocket motor
  固体火箭发动机燃烧室喷管一体化网格生成
• Design optimization of chamber pressure and nozzle area expansion ratio of solid rocket motors
  固体火箭发动机燃烧室压强及喷管扩张比优化设计
• Coupling computation on radial vibration of chamber structure and internal ballistic property for solid rocket motor
  固体火箭发动机燃烧室结构径向振动与内弹道性能的耦合计算
• The causation of some defects and its effects on solid rocket motor were analyzed , the latest nondestructive testing methods of motor were also introduced
  摘要分析了固体火箭发动机燃烧室各种缺陷的形成原因及其对发动机的影响，介绍了目前用于发动机无损检测的几种方法。
• Disigning coolant channel on the firebox of liquid rocket engine to loxodrome ( equal - angle helix ) groove can improve firebox coolant capability greatly . because the width dimension of loxodrome groove is narrow and the depth is deep , some machining methods are incapable , such as end - milling or electrochemistry . according to the peculiarities , a cnc disk - cutter - milling method which is composed of five motion axes with four simultaneously interpolated ones is researched . because most firebox generatrix is composed of complex curves , it is very difficult to get cnc cutting program with manual means . in order to deal with the problem , the loxodrome mathematics model is studied , and an auto - programming software system is developed . the software system can generate cnc cutting program of loxodrome on many kinds of turned surface . the constriction - distension segment of firebox is the most representative workpiece . the sharp changing of its generatrix slope makes loxodrome milling difficult . with the theory analyzing and practice cutting experiment , some applied techniques , which include milling mode and direction , choosing cutter diameter and cutting start point setting , are developed . adopting the technology above , tens regular workpiece have been manufacturing . the two - year manufacture practice has confirmed the validity and feasibility of developed loxodrome coolant channel milling method . the developed technology is also worth to be referenced to other similar workpiece
  将液体火箭发动机燃烧室的冷却通道设计为斜航线(等倾角螺旋线)槽形,可以大幅度改善燃烧室的冷却性能.斜航线冷却槽的槽宽尺寸较小而槽深尺寸较大,所以无法使用棒铣刀铣削、电化学等加工方式.针对这些特点,提出了五轴控制、四轴联动的数控片铣刀铣削加工方法.由于燃烧室外表面的母线轮廓复杂,手工编制数控加工程序难度大.为了解决数控加工程序的编制问题,研究了斜航线的数学模型,开发了自动编程软件系统.使用该系统,可以生成多种母线轮廓回转体外表面上的斜航线数控加工程序.燃烧室收敛-扩张段的母线斜率变化大,加工难度大,是斜航线冷却通道加工的最典型工件.经过理论分析和实际切削实验,研究了针对该类型工件的片铣刀直径选择、铣削方式和方向、刀具调整和起刀点的设置等多项实际的加工方案.采用上述的一系列技术,已经成功地加工了数十个合格工件.经过两年多的实际生产过程应用,验证了所开发的斜航线冷却通道加工方法的正确性和可行性.这些加工技术的研制成功,对其他相似类型零件的加工亦具有参考意义
• Abstract : the review presents the recent status and achievements on numerical simulation studies of solid rocket motor chamber internal flow field from three aspects , including numerical analysis of internal flow during the ignition transient period , fin - slot flows in solid rocket motor , and calculation of particle trajectories and slag deposition . it also puts forward the focal points of research on numerical simulation of solid rocket motor chamber internal flow field in our country
  文摘:从三个方面介绍了固体火箭发动机燃烧室内流场数值模拟研究的现状及取得的成果，包括发动机点火传播及起动过程的数值研究，翼环槽内流场研究和粒子轨迹、熔渣计算，并对我国开展此项研究的重点提出了建议。
• In this paper , the backward simulation was summarizd at home andabroad , the characteristics of shell nosing were introduced , the theory and scheme of backward simul - ation of shell nosing was constructed , the determined methods of the boundary conditions were put forward in backward simulation for the processes of shell nosing
  通过对固体火箭发动机燃烧室绝热层作用、种类及其隔热机理的研究,分析了绝热层材料的性能特点,论述了绝热层配方选择与结构设计的过程,并给出了较优的材料选择和结构设计方法,对绝热层的具体工艺实施阶段具有一定的指导意义