软隔板双脉冲发动机二级点火延迟试验分析

曹熙炜; 任军学; 王长辉; 刘宇

软隔板双脉冲发动机二级点火延迟试验分析

北京航空航天大学宇航学院, 北京 100191

详细信息

中图分类号: V 435.23
计量
- 文章访问数: 2739
- HTML全文浏览量: 183
- PDF下载量: 824
- 被引次数: 0
出版历程
- 收稿日期: 2010-11-03
- 网络出版日期: 2012-02-29

Testing of ignition delay of second pulse of soft-clapboard dual-pulse motor

School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 在进行软隔板双脉冲发动机的试验研究时发现,二级脉冲出现远远超过指标要求的点火延迟.为了改进这种状况,从点火药量和隔板厚度两方面进行试验研究.结果表明单纯增加点火药量使得隔板破裂太快,能量过早地释放;而单纯增加隔板厚度使得隔板不能按预定位置和方式破裂,影响工作性能.最终结合软隔板双脉冲发动机的工作特点,从两方面同时改进,达到了比较合理的点火延迟.
- 软隔板 /
- 双脉冲发动机 /
- 点火延迟 /
- 点火药量 /
- 隔板厚度
Abstract: When doing the experiment of soft-clapboard dual-pulse motor, the delay time of the second pulse ignition was found exceeding the requirement. In order to improve the status, the experiments in terms of the quantity of ignition powder and the thickness of the soft-clapboard were carried out. The results show that increasing the ignition powder will promote the rupture of the clapboard and the release of the energy, and increasing clapboard thickness will not rupture the clapboard hopefully, and decrease the performance of motor. At last, according to the characteristic of the soft-clapboard dual-pulse motor, improving from the above two terms, the motor ignition can attain a good condition.
- soft-clapboard /
- dual-pulse motor /
- ignition delay time /
- mass of ignition powder /
- clapboard thickness

HTML全文

参考文献(10)

[1]	阮崇智.战术导弹固体发动机的关键技术问题[J].固体火箭技术,2002,25(2):8-12 Ruan Chongzhi.Key technical problems for tactical missile solid rocket motors[J].Journal of Solid Rocket Technology,2002,25(2):8-12(in Chinese)
[2]	刘廷国,何洪庆.多脉冲能量控制在战术导弹中的作用[J].推进技术,1998(5):110-114 Liu Tingguo,He Hongqing.Investigation of application of multiple-pulse energy control technology to tactical missiles[J].Journal of Propulsion Technology,1998(5):110-114(in Chinese)
[3]	Naumann K W,Stadler L,Trouillot P,et al.Double-pulse solid rocket technology at Bayern-Chemie/Protac .AIAA 2006-4761,2006
[4]	Stadler L J,Trouillot P,Rien cker C,et al.The dual pulse motor for LFK NG .AIAA 2006-4726,2006
[5]	Trouillot P,Audri D,Ruiz S.Design of internal thermal insulation and structures for the LFK-NG double-pulse motor .AIAA 2006-4763,2006
[6]	Schilling S,Trouillot P.On the development and testing of a 120mm caliber double pulse motor(DPM) .AIAA 2004-3387,2004
[7]	朱光辰,胡克娴,王春利,等.一种双脉冲发动机的技术研究[J].航空动力学报,1996,11(4):364-368 Zhu Guangchen,Hu Kexian,Wang Chunli,et al.A study of a dual-pulse motor technique[J].Journal of Aerospace Power,1996,11(4):364-368(in Chinese)
[8]	殷金其.固体火箭发动机的能量管理技术研究[J].推进技术,1993(4):24-30 Yin Jinqi.Studies of energy management technology of solid rocket motors[J].Journal of Propulsion Technology,1993(4):24-30(in Chinese)
[9]	李宜敏,张中钦,赵元修.固体火箭发动机原理[M].北京:国防工业出版社,1985:111-128 Li Yimin,Zhang Zhongqin,Zhao Yuanxiu.Principle of solid rocket motor[M].Beijing:National Defence Industry Press,1985:111-128(in Chinese)
[10]	李江,肖育民,贺国强,等.双脉冲固体火箭发动机二次点火内视研究[J].推进技术,1998,19(3):61-64 Li Jiang,Xiao Yumin,He Guoqiang,et al.Inner view of dual-pulse solid rocket motor during secondary firing[J].Journal of Propulsion Technology,1998,19(3):61-64(in Chinese)