| 1. | The low frequency burning oscillation of the 85 % h202 - pe hybrid rocket motor is discussed
研究了85 hzoz ? pe固液火箭发动机的低频振荡燃烧现象。 |
| 2. | The combustion model of hybrid rocket propellant was established . the combustion flow in the hno3 + n2o4 - htpb hybrid rocket motor has been researched
研究了直径为706mm多孔分段装药全尺寸试验固液火箭发动机内部的燃烧与流动问题。 |
| 3. | Owing to the dissimilar combustion mode , their working process is different form that of solid rocket motors and the liquid rocket engines
由于氧化剂和燃料的燃烧方式不同,固液火箭发动机工作过程与液体及固体火箭发动机有很大的区别。 |
| 4. | Owing to the dissimilar combustion mode , their working process is different form that of solid rocket motors and the liquid rocket engines
由于氧化剂和燃料的燃烧方式不同，固液火箭发动机工作过程和液体火箭发动机及固体火箭发动机有很大的区别。 |
| 5. | Through the tests of the 85 % h2o2 - pe hybrid rocket motor , the operation process of the hybrid motor has been studied in the dissertation . the main aspects are as follows : 1
本文结合85 h _ 2o _ 2 ? pe固液火箭发动机试验，从以下几个方面比较系统地研究了固液火箭发动机的工作过程： 1 |
| 6. | 5 . the internal ballistics and the throttling performance of 85 % h2o2 - pe hybrid rocket motor loaded with tube grain are studied . the hot firing data of two test motors have been carefully analyzed
研究了管型药柱的85 h _ 2o _ 2 - pe固液火箭发动机的内弹道性能和节流特性，分析了两台发动机的试验结果。 |
| 7. | The pressurized 85 % h2o2 - pe hybrid rocket motor test system has been designed and built up for the research work . the hot firing tests and the shutdown - restart of the motor were successfully performed . 2
设计和建造了85 h _ 2o _ 2 ? pe固液火箭试验发动机和挤压式固液火箭发动机试验系统，并成功地进行了点火和再启动。 |
| 8. | Because of their low - cost , high safety and reliability , flexible energy management and shutdown - restart ability , hybrid rocket motors have received increasing attention from the space propulsion specialist all over the world
固液火箭发动机因具有低成本、高安全性和可靠性、灵活的能量管理和推力可控等特性,越来越受到国内外航天推进专家的重视。 |
| 9. | Because of their low - cost , high safety and reliability , flexible energy management and shutdown - restart ability , hybrid rocket motors have received increasing attention from the space propulsion specialist all over the world
固液火箭发动机因具有低成本、高安全性和可靠性、灵活的能量管理和多次启动等优良特性，越来越受到国内外航天推进专家的重视。 |
| 10. | Through malfunction of the tests of 810 research institute , the combustion performance of the hybrid motor and model about regression rate have been studied in the dissertation . the main aspects are as follows : the performance of the hno3 + n2o4 - htpb hybrid rocket motor were all discussed
本文结合航天科技集团公司810研究所正在研制的ak - 20l / htpb + al组合固液火箭发动机,开展了固液火箭发动机混合燃烧特性的数值模拟工作,在此基础上给出固体燃料退移速率预示模型及预示结果。 |
