大展弦比柔性复合材料机翼的气动弹性剪裁

刘湘宁; 向锦武

大展弦比柔性复合材料机翼的气动弹性剪裁

北京航空航天大学航空科学与工程学院, 北京 100083

基金项目: 国家自然科学基金资助项目(10272012);教育部新世纪优秀人才支持计划资助项目(NCET-04-0169)

详细信息

作者简介:
刘湘宁(1977- ),男,湖南永兴人,博士生, morrist@163.com.

中图分类号: V 211.47
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出版历程
- 收稿日期: 2005-12-16
- 网络出版日期: 2006-12-31

Study of aeroelastic tailoring of high-aspect-ratio flexible composite wing

School of Aeronautic Science and Technology, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

摘要

摘要: 在考虑结构几何非线性、气动非线性影响的基础上,由气动弹性问题的最普遍方程,获得大展弦比柔性复合材料机翼颤振问题的非线性稳定性分析方程.使用解析方式推导得到机翼的临界颤振速度、颤振频率对于设计变量的灵敏度表达式.展示了复合材料机翼的铺设构型和铺层角对气动弹性特性的影响,指出产生负弯扭耦合效果的机翼截面构型有利于机翼的气动弹性性能.以机翼颤振速度作为目标函数,复合材料铺层角为设计变量进行了气动剪裁优化设计,在得到最优化的铺层构型和铺层角的同时,也比较了本文解析敏度和数值差分敏度得到的优化结果.
- 颤振 /
- 优化设计 /
- 几何非线性 /
- 复合材料 /
- 敏度分析
Abstract: The nonlinear government equations of the flutter problem of high-aspect-ratio flexible composite wing were derived from the most general aeroelasticequations with wing′s structure geometrical and aerodynamic nonlinearity being considered. Then the gradients of flutter speed and frequency of wing with respect to the design variables were deduced with analytical method. The influence of the composite wing′s configuration and ply angle on the flutter speed was revealed. It was concluded that the composite structure configuration that caused negative bending twist coupling was beneficial to wing′s flutter performances. An optimization design of a high-aspect-ratio flexible composite wing model was done with the flutter speed as object function and the composite plies as design variables. The best configuration and plies were obtained and the results obtained with analytical gradients of this paper and numerical difference gradients were compared at the same time.
- flutter /
- optimization design /
- geometrical nonlinear /
- composite material /
- sensitivity analysis

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参考文献(1)

[1] Shirk M H, Hertz T J, Weisshaar T A. Aeroelastic tailoring-theory, practice and promise[J]. J Aircraft, 1986, 23(1):6-18 [2] Hollowell S J, Dugundji J. Aeroelastic flutter and divergence of stiffness coupled, graphite/epoxy cantilevered plates[J]. J Aircraft, 1984, 21(1):69-76 [3] Tischer V A, Venkayya V B. Ply orientation as a variable in multidisciplinary optimization . AIAA Paper 92-4793, 1944 [4] Patil M J. Aeroelastic tailoring of composite box beams . AIAA-97-0015,1997 [5] 修英姝, 崔德刚. 复合材料蜂窝夹层结构的优化设计[J]. 北京航空航天大学学报, 2004, 30(9):855-858 Xiu Yingshu, Cui Degang. Optimal design of composite sandwich structure[J]. Journal of Beijing University of Aeronautics and Astronautics, 2004, 30(9):855-858(in Chinese) [6] Patil M J, Hodges D H. On the importance of aerodynamic and structural geometrical nonlinearities in aeroelastic behavior of high-aspect-ratio wings . AIAA-2000-1448,2000 [7] Tang D, Dowell E H. Experimental and theoretical study on aeroelastic response of high-aspect-ratio wings[J]. AIAA Journal, 2001, 39(8):1430-1441. [8] Patil M J, Hodges D H, Cesnik C E S. Characterizing the effects of geometrical nonlinearities on aeroelastic behavior of high-aspect-ratio wing Proceedings of the International Forum on Aeroelasticity and Structural Dynamics. Virginia:CEAS/AIAA/ICASE/NASE Langley, 1999 [9] Forsching H W. 沈史扬译.气动弹性力学原理[M]. 上海:上海科学技术文献出版社, 1982 Forsching H W. Translated by Shen Shiyang,Theory of aeroelasticity[M]. Shang Hai:Shanghai Scientific and Technical Literature Publishers, 1982(in Chinese) [10] Eastep F E, Tischler V A, Venkayya V B, et al. Aeroelastic tailoring of composite structures[J]. J Aircraft, 1999, 36(6):1041-1047 [11] Armanios E A, Badir A M. Free vibration analysis of anisotropic thin-walled closed section beams . AIAA-94-1327-CP,1994

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