充气机翼的褶皱与失效行为研究
收稿日期: 2015-10-20
修回日期: 2016-01-06
网络出版日期: 2016-03-16
基金资助
国家自然科学基金（11172238）；中央高校基本科研业务费专项资金（3102014KYJD015）；高等学校创新引智计划（B07050）
Wrinkling and failure behavior research of inflated wing
Received date: 2015-10-20
Revised date: 2016-01-06
Online published: 2016-03-16
Supported by
National Natural Science Foundation of China (11172238); The Fundamental Research Funds for the Central Universities(3102014KYJD015); "111" project (B07050)
在经典工程梁理论的基础上，结合张力薄膜的应力状态分析，提出充气机翼褶皱失稳的判据。计入表面薄膜褶皱引起的刚度退化效应，将机翼等效处理为一个变截面刚度的梁，建立了充气悬臂机翼的等效梁模型，并采用微分求积法进行充气机翼弯曲变形分析。计算结果与充气机翼的静力弯曲试验结果相吻合，验证了充气机翼弯曲变形分析方法的有效性。应用片条理论引入气动力模型，并与所建立的等效梁模型相耦合，建立充气机翼的静气动弹性耦合模型，并用迭代算法进行求解。考虑起皱和失稳两种判据，并计算获取了试验机翼的起皱动压和皱褶失稳动压形式，计算结果与风洞试验结果一致。根据所建立的充气机翼静气动弹性分析方法，可以预测充气机翼表面褶皱区的扩展和弯曲变形，进而绘制充气机翼的静气弹许用包线，为充气机翼的设计提供必要的安全边界参考依据。
李斌 , 董楠楠 , 冯志壮 , 牛文超 . 充气机翼的褶皱与失效行为研究[J]. 航空学报, 2016 , 37(10) : 3044 -3053 . DOI: 10.7527/S1000-6893.2016.0056
Based on classical engineering beam theory, combined with the stress state analysis of tense membrane, the wrinkling and instability criterions of inflated wing are proposed. We consider stiffness degradation caused by wrinkle of inflated wing, and treat the inflated wing as a beam which possesses a variable section stiffness with the expansion of wrinkle; an equivalent beam model of inflated wing is established, and the differential quadrature method is applied to calculate the bending deformation of inflated wing. The calculated results are consistent with the experimental results from the static bending tests of inflated wing, and hence verify the effectiveness of the proposed deformation analysis method of inflated wing. We use the strip theory to introduce the aerodynamic model which is then coupled with the equivalent beam model of inflated wing, and thus a static aeroelastic model of inflated wing is developed, which applies an iterative method to solve. According to the wrinkling and instability criterions, we use the proposed model to calculate the critical wrinkle dynamic pressure and critical instability dynamic pressure of the experimental inflated wing, and the obtained results are consistent with the results from tunnel tests. Furthermore, the proposed model is used to predict the extending process of membrane wrinkled zone and bending failure load for the inflated wing, and then obtain the available static aeroelastic envelope curves of inflated wing under different criterion conditions, and provide necessary safety boundary analysis for the design of inflated wing.
Key words： inflated wing; wrinkle; variable stiffness; static aeroelasticity; instablility
[1] PAHLE J W, THOMTON S V, VOGUS S, et al. Ground and flight evaluation of a small-scale inflatable-winged aircraft[C]//40th AIAA Aerospace Sciences Meeting & Exhibit. Reston:AIAA, 2002.
[2] USUI M, SIMPSON A, SMITH S, et al. Development and flight testing of a UAV with inflatable-rigidizable wings[C]//42nd AIAA Aerospace Sciences Meeting and Exhibit. Resston:AIAA, 2004.
[3] USUI M, JACOB J D, SMITH S W, et al. Second generation inflatable/rigidizable wings for low-density flight applications[C]//46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston:AIAA, 2005:1-9.
[4] 吕强, 叶正寅, 李栋. 充气结构机翼的设计和试验研究[J]. 飞行力学, 2007, 25(4):77-80. LV Q, YE Z Y, LI D. Design and capability analysis of an aircraft with inflatable wing[J]. Flight Dynamic, 2007, 25(4):77-80(in Chinese).
[5] 王伟, 王华, 贾清萍. 充气机翼承载能力和气动特性分析[J]. 航空动力学报, 2010, 25(10):2296-2303. WANG W, WANG H, JIA Q P. Analysis on bearing capacity and aerodynamic performance of an inflatable wing[J]. Journal of Aerospace Power, 2010, 25(10):2296-2303(in Chinese).
[6] 王长国, 杜星文, 赫晓东. 空间充气薄膜结构的褶皱分析[J]. 力学学报, 2008, 40(3):331-338. WANG C G, DU X W, HE X D. Wrinkling analysis of space inflatable membrane structures[J]. Chinese Journal of Theoretical and Applied Mechanics, 2008, 40(3):331-338(in Chinese).
[7] 杜振勇, 王长国, 谭惠丰. 受弯充气锥台的褶皱特性分析[J]. 工程力学, 2011, 28(7):73-78. DU Z Y, WANG C G, TAN H F. Wrinkle characteristic analysis of a conical inflated cantilaver beam under bending[J]. Engineering Mechanics, 2011, 28(7):73-78(in Chinese).
[8] 朱亮亮, 叶正寅. 充气式机翼的通用设计方法[J]. 空军工程大学学报(自然科学版), 2009, 10(5):16-21. ZHU L L, YE Z Y. Research on a universal design method for inflatable wings[J]. Journal of Air Force Engineering University (Natural Science Editioin), 2009, 10(5):16-21(in Chinese).
[9] 陈帅, 李斌, 杨智春. 充气悬臂梁的弯曲失效行为[J]. 工程力学, 2010, 27(S1):299-304. CHEN S, LI B, YANG Z C. Benging-collapse behavior of an inflatated circular-cylindrical cantilever beam[J]. Engineering Mechanics, 2010, 27(S1):299-304(in Chinese).
[10] GALROM Y C, RAVEH D E. Simplified aerostructural static model for inflated wings[J]. AIAA Journal, 2011, 49(6), 1180-1190.
[11] 黄其青,王生楠. 结构力学基础[M]. 西安:西北工业大学出版社,2002:90-115. HUANG Q Q, WANG S N. Foundation of structural mechanics[M]. Xi'an:Northwestern Polytechnical University Press, 2002:90-115(in Chinese).
[12] 聂国隽, 徐敏, 仲政. 轴向变刚度矩形截面梁的弹性及弹塑性弯曲[J]. 中国科学:物理学力学天文学, 2011, 41(1):86-93. NIE G J, XU M, ZHONG Z. Elastic and elasto-plastic bending of rectangular beams with variable stiffness along axial direction[J]. Scientia Sinica (Physica, Mechanica & Astronomica), 2011, 41(1):86-93(in Chinese).
/
| 〈 |
|
〉 |
CJA