柔性飞艇主气囊干湿模态分析与影响因素

摘要/Abstract

摘要：

为了掌握柔性飞艇无约束状态下的模态特性，以25 m平流层验证飞艇为基本分析对象，对其自振特性进行研究.根据充气膜结构的力学特点，基于柔性飞艇主气囊初始形状，通过充气压力静力非线性分析得到充气平衡形态位形和应力，利用兰索斯法进行模态数值分析.分析表明,影响柔性飞艇模态特性的主要因素为：壳单元与膜单元模型、拼接缝、不均匀质量分布、内外压差、尺寸、飞艇周围空气附加质量，且最后三者为重要影响因素；壳单元和膜单元模型频率相近且振型一致.对柔性平流层飞艇结构设计具有参考价值.

关键词: 平流层飞艇, 主气囊, 干模态, 湿模态, 空气附加质量

Abstract:

In order to grasp the unconstrained modal characteristics of the flexible airship envelop, the natural vibration performance was investigated thoroughly for a 25 m long stratospheric demonstration airship. The flexible airship envelop features is a freefloating inflatable membrane structure. Based on the mechanical nature of pneumaticstressed membrane structures, the deformed equilibrium shape and stress were computed from the initial geometry configuration, subjected the inflated air pressure through nonlinear structural analysis. The block Lanczos method was employed for modal analysis. The main influencing factors were evaluated thoroughly for modal behavior, including shell element and membrane element, pressure, geometry size, weld seam, nonuniform distributed mass and the added atmosphere mass. The numerical models of membrane and shell element have close natural frequency and identical modal shape. The airadded mass, pressure and geometry size are the key factors to govern the modal performance. This paper can provide reference for structural engineering design of stratospheric airship.

Key words: stratospheric airship, airship envelop, dry mode, wet mode, air added mass

中图分类号:

V 274

陈宇峰，陈务军，何艳丽，张大旭. 柔性飞艇主气囊干湿模态分析与影响因素[J]. 上海交通大学学报（自然版）, 2014, 48(02): 234-238.

CHEN Yufeng,CHEN Wujun,HE Yanli,ZHANG Daxu. Dry and Wet Modal Analysis and Evaluation of Influencing Factors for Flexible Airship Envelop[J]. Journal of Shanghai Jiaotong University, 2014, 48(02): 234-238.

参考文献

［1］Roney J A.Statistical wind analysis for nearspace applications［J］.Journal of Atmospheric and SolarTerrestrial Physics,2007, 69(13):14851501.

［2］Newman D J. Some aeroelastic effects in airships［R］. Leics: Department of Transport Technology, Loughborough University of Technology, 1977.

［3］Bessert N, Frederich O. Nonlinear airship aeroelasticity［J］.Journal of Fluids and Structures, 2005, 21(8): 731742.

［4］GAO H J, CHEN W J, FU G Y. Structural design conception and analysis for the structural system of large flexible airship［J］. Journal of Shanghai Jiaotong University(Science), 2010, 15(6):16.

［5］CHEN W J, GAO H J. Overall design and analysis for large flexible airship of HALE stratospheric platform conception［C］//International Symposium on Advance in Mechanics, Materials and Structures. Hangzhou, Zhejiang University, 2008：288295.

［6］CHEN W J, GAO H J. Aerodynamic performance evaluation procedure for large flexible airship of HALE stratospheric platform conception［C］//International Symposium on Advance in Mechanics, Materials and Structures. Hangzhou: Zhejiang University, 2008: 136143.

［7］CHEN W J, Xiao W W, FU G Y, at al. Structural performance evaluation procedure for large flexible airship of HALE stratospheric platform conception［J］. Journal of Shanghai Jiaotong University(Science), 2007,12(2)：293300.

［8］高海健.大型平流层空间平台柔性飞艇结构分析理论

与特性研究［D］.上海：上海交通大学船建学院，2010.

［9］高海健,陈务军,付功义.预应力薄膜充气梁模态的分析方法及特性［J］.华南理工大学学报:自然科学版, 2010, 38(7):135139.

GAO Haijian, CHEN Wujun, FU Gongyi. Modal analysis method and modal behavior of prestressed inflatable fabric beam［J］. Journal of South China University of Technology: Natural Science Edition,2010, 38(7):135139.

［10］黄伟良，宋笔锋.基于有限元的软式飞艇主气囊动态特性分析［J］.科学技术与工程, 2008, 8(14): 38633867.

HUANG Weiliang, SONG Bifeng. Dynamic characteristics airship by analysis of the envelope of nonrigid finite element method［J］. Science Technology and Engineering,2008,8(14)：38633867.

［11］谭惠丰,李云良,毛丽娜,等.空间充气展开支撑管的自振特性研究［J］.哈尔滨工业大学学报,2008,40（5）:709713.

TAN Huifeng, LI Yunliang, MAO Lina, et al. Free vibration characteristics of inflatable supporting tube［J］. Journal of Harbin Institute of Technology, 2008,40（5）:709713.

［12］Minami H. Added mass of a membrane vibrating at finite amplitude［J］. Journal of Fluids and Structures, 1998, 18(12): 919923.

［13］高海健,陈务军,付功义.平流层验证飞艇结构体系比较研究［J］.宇航学报,2011, 32(4): 713718.

GAO Haijian, CHEN Wujun, FU Gongyi. Comparison investigation for architecture of stratospheric demonstration airship［J］. Journal of Astronautics,2011, 32(4): 713718.

［14］王磊,李元齐,沈祖炎.薄膜振动附加质量试验研究［J］.振动工程学报,2011,24(2):125132.

WANG Lei, LI Yuanqi, SHEN Zuyan. Experimental investigation on the added mass of membranes vibrating in air［J］. Journal o f Vibration Engineering,2011,24(2):125132.

［15］于肖宇,张继革,顾卫国,等.薄壁圆筒结构附加质量的实验研究［J］ .水动力学研究与进展,2010, 25(5):655658.

YU Xiaoyu, ZHANG Jige, GU Weiguo, at al. Experimental study of added mass of the thinwalled cylinder structure［J］.Journal of Hydrodynamic, 2010,25(5): 655658.

[1]	张波涛，朱晔晨，梅勇，龚圣捷. 平直条带流致振动特性实验及其数值模拟研究[J]. 上海交通大学学报, 2020, 54(1): 100-105.
[2]	陈宇峰，陈务军，邱振宇. 柔性飞艇主气囊不稳定构型阶段力学性能分析[J]. 上海交通大学学报（自然版）, 2015, 49(09): 1422-1428.
[3]	张礼学1，王中伟1，杨希祥1，宋庆雷2. 基于Gauss伪谱法的平流层飞艇上升段航迹规划[J]. 上海交通大学学报（自然版）, 2013, 47(08): 1205-1209.