| 控制力作用柔性喷管动力响应研究 |
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| 引用本文： | 史宏斌,关正西,侯晓.控制力作用柔性喷管动力响应研究[J].航空动力学报,2003,18(4):563-569. |
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| 作者姓名： | 史宏斌 关正西 侯晓 |
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| 作者单位： | 1.中国航天科技集团公司四院四十一所,陕西西安710025 |
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| 摘 要： | 选择某锥筒式扩张段柔性喷管作为目标,用弹簧模型取代柔性接头结构,运用结构动力有限元方法,纽马克差分格式,对结构模型进行了动力载荷作用下的响应分析,获得了三角波、正弦波和反正弦波三种激励下的结构响应结果。
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| 关 键 词： | 航空、航天推进系统 柔性喷管 动力响应 有限元法 |
| 文章编号： | 1000-8055(2003)04-0563-07 |
| 收稿时间： | 6/3/2002 12:00:00 AM |
| 修稿时间： | 2002年6月3日 |
Dynamic Response Study of Flexible Nozzle in a Solid Rocket Motor |
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| Institution: | 1.The 41st Institute of the Fourth Academy of CASC,Xi'an710025,China2.The Second Artillery Engineering Technology College,Xi'an710025,China3.The Fourth Academy of CASC,Xi'an710025,China |
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| Abstract: | Based on the dynamic finite element method of structures,the response analysis of a flexible nozzle having a cone cylinder shaped divergent section is presented.The flexible joint is simply treated as a distributed spring and to which the Newmark difference method is applied.The numerical results are obtained when triangular wave excitation,sine wave excitation and arcsine wave excitation are exerted correspondingly. |
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| Keywords: | aerospace propulsion system flexible nozzle dynamic responses finite element method |
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