| 温度载荷下装药内外径比和长径比对结构完整性影响的规律研究 |
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| 引用本文： | 于洋,王宁飞,张平.温度载荷下装药内外径比和长径比对结构完整性影响的规律研究[J].航空动力学报,2007,22(9):1565-1568. |
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| 作者姓名： | 于洋 王宁飞 张平 |
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| 作者单位： | 大连海事大学,机电与材料工程学院,大连,116026;北京理工大学,宇航科学技术学院,北京,100081;北京理工大学,宇航科学技术学院,北京,100081 |
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| 基金项目： | 国防科技应用基础研究基金 |
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| 摘 要： | 在固体火箭发动机装药设计中通常将药柱的外径与内径之比定义为m数(m=R/r)为研究装药设计参数m数和药柱长径比在温度载荷下对装药结构完整性的影响, 采用基于Total Lagrangian方法的热粘弹性大变形增量本构关系, 通过选取9种m数以及8种药柱长径比, 共72个计算模型, 对装药结构完整性进行了计算, 结果表明温度载荷下药柱最大Von Mises等效应力、应变值受药柱m数以及长径比共同影响.并得出当长径比大于3时, 药柱最大等效应力、应变值主要取决于m数的结论.
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| 关 键 词： | 航空、航天推进系统 固体火箭发动机 结构完整性 内外径比 长径比 热粘弹性 大变形 增量本构关系 |
| 文章编号： | 1000-8055(2007)09-1565-04 |
| 收稿时间： | 9/4/2006 12:00:00 AM |
| 修稿时间： | 2006年9月4日 |
Research on influence of diameter ratio and length-diameter ratio on structural integrity of solid propellant under temperature loading |
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| YU Yang,WANG Ning-fei and ZHANG Ping.Research on influence of diameter ratio and length-diameter ratio on structural integrity of solid propellant under temperature loading[J].Journal of Aerospace Power,2007,22(9):1565-1568. |
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| Authors: | YU Yang WANG Ning-fei and ZHANG Ping |
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| Institution: | 1.Electromechanics and Material College, Dalian Maritime University, Dalian 116026, China2.School of Aeronautics Science and Technology, Beijing Institute of Technology, Beijing 100081, China |
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| Abstract: | To investigate the influence of number m and length-diameter ratio on structural integrity of solid propellant under temperature loading,the thermoviscoelastic large deformation incremental constitutive equation was derived from Total Lagrangian method.Nine different numbers m and eight length-diameter ratios for calculation 72 models were selected to measure the effects on the structural integrity.The results show that,number m and length-diameter ratio have cooperative effects on the maximum value of equivalent Von Mises stress and strain.If the length-diameter ratio is larger than 3,it's concluded that the maximum value of equivalent Von Mises stress and strain are mainly determined by number m of solid propellant. |
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| Keywords: | aerospace propulsion system solid rocket motor structural integrity diameter ratio length-diameter ratio thermoviscoelasticity large deformation incremental constitutive equation |
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