发动机推力的英文

• engine thrust
• motor power
• motor thrust

• "发动机"英文翻译    engine; motor
• "推力"英文翻译    visatergo; soot; propulsive ...
• "发动机推力表" 英文翻译 :    engine thrust indicator
• "发动机推力线" 英文翻译 :    engine thrust line
• "主发动机推力" 英文翻译 :    cruising thrust; sustainer thrust; sustaining power
• "发动机推力延迟" 英文翻译 :    engine thrust delay
• "火箭发动机推力" 英文翻译 :    thrust of rocket motor
• "火箭发动机推力室" 英文翻译 :    thrust chamber
• "火箭发动机推力线" 英文翻译 :    rocket thrust line
• "爬升发动机推力" 英文翻译 :    ascent egine thrust
• "喷气发动机推力" 英文翻译 :    jet thrust
• "升力发动机推力" 英文翻译 :    direct lift thrust; lift engine thrust
• "巡航发动机推力" 英文翻译 :    propulsion engine thrust
• "制动发动机推力" 英文翻译 :    descent engine thrust
• "发动机推力向量控制" 英文翻译 :    motor thrust-vector control (mtvc)
• "轨道飞行器发动机推力" 英文翻译 :    orbiter thrust
• "火箭发动机推力程序控制" 英文翻译 :    burning programing
• "控制发动机推力的电路" 英文翻译 :    throttle circuit
• "喷气发动机推力反向器" 英文翻译 :    jet thrust reverser
• "升力发动机推力增大" 英文翻译 :    jet life boosting
• "升力发动机推力指示器" 英文翻译 :    lift thrust indicator
• "巡航状态发动机推力" 英文翻译 :    cruising thrust
• "利用空气动力和发动机推力的机动飞行" 英文翻译 :    aerodynamic-propulsive maneuver
• "中断飞行系统发动机推力作用时间" 英文翻译 :    abort thrust duration
• "推进；推力；发动机" 英文翻译 :    propulsion

• Regression algorithm on thrust curve of rolling - control engine
  滚控发动机推力曲线还原算法
• Thrust vector control is one of objects being seeked by engineers in rocket propulsion area
  流场控制以及基于此的发动机推力方向控制长期以来都是国内外火箭推进领域广大工程技术人员追寻的目标之一。
• The influence of primary flow and secondary nozzle geometry on ejector effect and thrust was investigated , and the approach to increase thrust of rocket ejector was found gradually
  研究了一次流参数和二次喷管结构对引射效能和发动机推力的影响，找到了逐步提高推力的措施。
• As to the simulation , the inner flow field of thrust chamber was simulated . here the thrust chamber was treated as a two - dimension problem . the simulation model involved injection , mixing and combustion of gaseous propellant
  仿真方面，对三组元发动机推力室的稳态燃烧过程进行了数值模拟，分析了推进剂各组元和各燃烧产物组分在推力室内的分布。
• According to flight dynamics , a particle model and an attitude model in launching coordinate system and in quasi missile body coordinate system are established , the influence imposed by constant wind , thrust bias of the motor and connection bias are analyzed
  应用飞行动力学理论,建立了发射坐标系与准弹体系下助推段和分离过程质点运动和姿态动力学模型,分析常风干扰、发动机推力偏差和装配误差影响等。
• According to the definition and expression of the thrust , as well as the condition derived from them , a method of solid rocket ramjet thrust determination and its program are provided on the basis of engine ground simulation test
  本文以西北工业大学固体火箭冲压发动机直连式试车台为研究对象，探讨固体火箭冲压发动机地面试验技术。首先，从推力的定义出发，建立了试验中来流空气流量、燃料流量与固体火箭冲压发动机推力之关系。
• The results indicate that with decrease of exit area of secondary nozzle , the bypass ratio is decreasing , and the static pressure in integrated ejector combustor is increasing , and mixing condition becomes better . there exists an optimal exit area of secondary nozzle to get maximum thrust of rocket ejector
  结果表明：引射能力随着二次喷管出口面积的减小而减小；整体式引射燃烧室压强随着二次喷管出口面积的减小而上升，混合随之更为充分；存在一个最优的二次喷管出口面积，使发动机推力最大。
• It is shown that when the exit area of secondary nozzle and the fuel / oxidizer ratio is fixed , the increase of mass flow rate of secondary flow lead to the decrease of velocity of mixed flow , and increase of total mass flow rate . the synthetical result of these two phenomenon cause the increase of thrust of rocket ejector , but the increasing magnitude is relatively small , indicating that these is no necessary to claim large bypass ratio in rocket ejector design . in the comparison between two configurations , the typical one has better performance , indicating the importance of pressure ratio
  结果表明：在固定二次喷管出口面积和氧燃比的条件下，二次流(引射空气流)流量的增加引起混合气体出口速度的下降和总流量的增加，二者综合作用使发动机推力增加，但增幅不大，表明在设计发动机结构和工作参数时，不必过分追求大的引射系数；两种结构的性能对比分析表明了增压比对引射火箭性能的提高具有重要意义；对引射火箭的热力循环分析同样表明，增压比对于提高发动机性能非常关键。
• As to the experimental study , a test system was designed firstly , which include propellant feed system , cooling system , controlling system and measure system . secondly , a test engine was designed according to the experimental requirement . on this basis , experiments under different working conditions were done , and the results of them were analyzed , which showed the combustion efficiency and stability
  实验方面，首先设计了针对三组元发动机推力室工作过程进行试验的试验系统，包括推进剂供应系统与冷却水供应系统、控制系统以及压力、温度、流量的测量采集系统；其次，设计出符合试验要求的缩尺发动机；最后针对所设计的试验系统和发动机，进行了不同工况的试验，对所得数据进行了分析处理，得到了不同工况下燃烧效率和燃烧稳定性特性。