期刊文献+

一种新型姿控推冲器的设计和研究

Design on A New High Energy Attitude Control Motor
下载PDF
导出
摘要 为了设计一种高输出能量的姿控推冲器,从主装药、点火管、壳体、喷管和堵片等方面进行了分析和试验,确定了相关设计参数。试验结果表明推冲器作用一致性好,实测比冲最高达236.8s,满足技术指标要求;安全电流、冲击、锤击及飞行搭载试验表明该推冲器使用安全。 A new type attitude control moto(r ACM)was designed, and the main charge, igniter, shell, nozzle and shear slicewere analyzed and verified, then the related design parameters were identified. The results showed that the measured specificimpulse reached up to 236.8s with good functional consistency, and met with the technical requirement. The safety current, shock,hammer blow and flight carry test showed that the ACM can be used safely.
作者 李志良 杨正才 刘海旭 王科伟 赵亮 乔改霞 吴玉均 LI Zhi-liang;YANG Zheng-cai;LIU Hai-xu;WANG Ke-wei;ZHAO Liang;QIAO Gai-xia;WU Yu-jun(North Special Energy Group Co.Ltd., Xi’an, 710025)
出处 《火工品》 CAS CSCD 北大核心 2016年第4期5-8,共4页 Initiators & Pyrotechnics
关键词 姿控推冲器 设计 比冲 锤击 Attitude control motor(ACM) Design Specific impulse Hammer blow
  • 相关文献

参考文献2

二级参考文献26

  • 1范存杰,牛嵩高.微型固体火箭发动机推力测量[J].固体火箭技术,1995,18(3):35-38. 被引量:8
  • 2曹小兵,王中原,史金光,靳方留.火箭脉冲矢量控制弹道特性分析[J].弹箭与制导学报,2005,25(3):67-69. 被引量:14
  • 3Tsutomu Yamanaka, Hideki Tanaka. Effects of impulse thruster on exterior ballistic accuracy improvement for a hyper velocity rocket[ C ]// 16^th International Symposium on Ballistics. Snnfrancisco, 1996.
  • 4Magness R W. Impulsive control for hypervelocity missile[R]. ADA 103844,1981.
  • 5Chan S C, Roger R P,Edwards G L,et al. Integrated jet interaction CFD prediction and comparison to force and moment measurements for a thruster attitude controlled supersonic missile[ R]. AIAA93-3522.
  • 6Evans R N. Development of composite motor technology for the advanced kinetic energy missile[C]//28^th Joint Propulsion Conference and Exhibit, 1992.
  • 7Herman R, Butler J. Subsystems for the extended range intercepter (ERINT-1) missile[ R]. AIAA-92-2750.
  • 8Thanat J, Mark Costello. Dispersion reduction of a direct-fire rocket using lateral pulse jets[ R]. ARL-CR-465,2001.
  • 9Trosky B. Artillery rocket: USP 006685134B2[ P] ,2004.
  • 10Linick J M. Impulse motor and apparatus to improve trajectory correctable munitions including cannon launched munitions, glide bombs,missiles,rockets and the like: USP 006722609B2[ P] ,2004.

共引文献4

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部