期刊文献+

单翼与有伞末敏子弹的扫描比较及分析 被引量:8

Comparison and Analyses of Single-fin TSA's and Parachute TSA's Scanning
下载PDF
导出
摘要 末敏子弹的铅直落速、扫描频率及扫描间距是其稳态扫描的重要参数,对利用四元数法的欧拉运动学方程得出的仿真结果系统的比较了两种子弹的这些参数。结果显示单翼末敏子弹以其强非对称性的气动力结构形成的稳态扫描较之有伞末敏子弹具备落速更快、扫描频率更高、扫描间距更为密集的优点。鉴于实际作战环境中横风的存在,分别设定风速比较,结果表明单翼末敏子弹受横风的干扰较小。较之有伞末敏子弹,单翼末敏子弹有着无可比拟的优势。 Considering the terminal sensing ammunition (TSA) 's falling velocity, scanning frequency and scanning distance are im- portant parameters in its stable scanning. These parameters were compared with the simulation based on Euler kinematics equation represented by quaternion method. The results show thai thc single fin TSA has more advantages than the parachute TSA, the sin- gle fin TSA has faster falling velocity, higher scanning frequency and more closely scanning distance in is stable scanning for its strongly non-symmetry aerodynamic structure. In addition, because of cross wind in the actual operational environment, comparing the scanning with the same speed of the cross wind, the results show that the single-fin TSA is less interfered by cross wind. So the single fin TSA has more distinct advantages than the parachute TSA.
出处 《弹箭与制导学报》 CSCD 北大核心 2011年第1期123-124,共2页 Journal of Projectiles,Rockets,Missiles and Guidance
基金 南京工程学院校级科研基金(OKJB2009006)资助
关键词 单翼末敏弹 有伞末敏弹 稳态扫描 减速伞 横风 single-fin TSA parachute TSA stable scanning parachute cross wind
  • 相关文献

参考文献4

二级参考文献4

共引文献33

同被引文献37

  • 1王冬梅,代文让,张永涛.信息化弹药的研究现状及发展趋势[J].兵工学报,2010,31(S2):144-148. 被引量:11
  • 2舒敬荣,张邦楚,韩子鹏,刘昌源,魏靖彪.单翼末敏弹扫描运动研究[J].兵工学报,2004,25(4):415-420. 被引量:15
  • 3杨青,梁强,杨永年.基于CFD的静气动弹性优化设计方法[J].空气动力学学报,2005,23(1):16-20. 被引量:3
  • 4付淑娟.翅果型减速装置[J].弹箭技术,1995,8(1):39-45. 被引量:1
  • 5Vicente N M,Piechocki J,Cuerva A, et al. Experimental research on a vertically falling rotating wing decelerator model [ C ] // 19th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar. Williamsburg, VA: AIAA,2007.
  • 6Vicente N M, Angel S A, Alvaro C. Experimental investigation of an autorotating-wing aerodynamic decelerator system [ C]// 18th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar. Munich, Alemania : AIAA,2005.
  • 7Crimi P. Finite element analysis of a samara-wing deeelerator[ J]. Journal of Aircraft, 1996,33 (4) :793 - 802.
  • 8Borgstrom D, Paulsson L, Karlsen L. Aerodynamics of a rotating body descending from the separation position of an artillery muni- tion shell[ C ] // 11 th Aerodynamic Decelerator Systems Technology Conference. San Diego, CA, US: AIAA, 1991.
  • 9Nicolaides J D. Two nonlinear problems in the flight dynamics of modern ballistic missiles[ M]. US: Bureau of Ordnance, Depart- ment of the Navy, 1959.
  • 10Vicente N M, Piechocki J, Cuerva A, et al.Experimental research on a vertically falling rotating wing decelerator model[C]//19th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar.Reston: AIAA, 2007.

引证文献8

二级引证文献17

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