基于变刚度复合材料的热颤振等效模型设计方法

王守申,肖诗雄,张兵

振动与冲击 ›› 2024, Vol. 43 ›› Issue (15) : 44-50.

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振动与冲击 ›› 2024, Vol. 43 ›› Issue (15) : 44-50.
论文

基于变刚度复合材料的热颤振等效模型设计方法

  • 王守申,肖诗雄,张兵
作者信息 +

Design method of thermal flutter equivalent model based on variable stiffness composite material

  • WANG Shoushen, XIAO Shixiong, ZHANG Bing
Author information +
文章历史 +

摘要

针对热颤振风洞实验面临的有效风洞时间短、结构难以达到热平衡的问题,提出一种基于变刚度复合材料的实验模型热模态等效动力学模型的设计方法,为解决制作复杂热颤振风洞实验模型提供一种技术途径。该方法充分利用变刚度复合材料的局部刚度可设计性强的特性,并结合NSGA-II遗传优化算法来进行模型设计,以等效复合材料翼板模型与目标模型的固有特性的误差最小为优化目标,对等效复合材料翼板模型进行了纤维角度的优化设计。研究结果表明,两种模型的固有频率、固有振型以及颤振分析结果吻合较好,从而验证了等效模型设计方法的可行性。

Abstract

To address the problems of short wind tunnel time and difficulty in achieving thermal equilibrium of the structure faced by thermal flutter wind tunnel experiments, a design method is proposed to establish a dynamical model equivalent to the thermal modal of the experimental model by using variable stiffness composite materials through structural optimization design, which provides a technical way to solve the thermal flutter wind tunnel experiments of complex models. The method takes full advantage of the designability of the local stiffness of the variable stiffness composites and combines the NSGA-II genetic optimization algorithm to perform the model design. Based on this method, an arithmetic study is conducted to optimize the fiber angle design of the equivalent composite airfoil model with the optimization objective of minimizing the error between the inherent properties of the equivalent composite airfoil model and the target model. The results of the study show that the inherent frequencies, inherent vibration patterns and chattering analysis of the two models are in good agreement, thus verifying the feasibility of the equivalent model design.

关键词

热气弹 / 颤振 / 变刚度复合材料 / 等效模型 / NSGA-II

Key words

aerothermoelastic / flutter / tow-steered composite / equivalent model / NSGA-II

引用本文

导出引用
王守申,肖诗雄,张兵. 基于变刚度复合材料的热颤振等效模型设计方法[J]. 振动与冲击, 2024, 43(15): 44-50
WANG Shoushen, XIAO Shixiong, ZHANG Bing. Design method of thermal flutter equivalent model based on variable stiffness composite material[J]. Journal of Vibration and Shock, 2024, 43(15): 44-50

参考文献

[1] 吴志刚,惠俊鹏,杨超.高超声速下翼面的热颤振工程分析[J].北京航空航天大学学报,2005(03):270-273. Wu Zhigang, Hui Junpeng, Yang Chao. Engineering analysis of thermal flutter of airfoil at hypersonic speeds [J]. Journal of Beihang University, 2005(03):270-273. [2] McNamara J, Friedmann P, Powell K, et al. Three-dimensional Aeroelastic and Aerothermoelastic Behavior in Hypersonic Flow[J].Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, 2008, 46(10): 2591-2610. [3] Heeg J, Zeiler T A, Pototzky A S, et al. Aerothermoelastic analysis of a NASP demonstrator model[J]. AIAA/ASME/ASCE/AHS/ASC 34th Structures, Structural Dynamics, and Materials Conference, 1993. [4] 刘磊,桂业伟,耿湘人,等. 热气动弹性变形对飞行器结构温度场的影响研究[J].空气动力学学报,2015,33(01):31-35+47. Liu Lei, Gui Yewei, Geng Xiangren,et al. Anling. Research on the influence of thermoaeroelastic deformation on the temperature field of aircraft structure [J]. Journal of Aerodynamics, 2015, 33(01): 31-35+47. [5] 王梓伊,张伟伟,刘磊等.适用于复杂流动的热气动弹性降阶建模方法[J].航空学报,2023,44(04):190-202. Wang Ziyi, Zhang Weiwei, Liu Lei, et al. Thermoaeroelastic reduced-order modeling method suitable for complex flows [J]. Acta Aeronautica Sinica, 2023, 44(04): 190-202. [6] 徐飞. 高超声速翼面的流固热多场耦合分析[D].南京航空航天大学,2015. Xu Fei. Fluid-solid-thermal multi-field coupling analysis of hypersonic airfoil[D]. Nanjing University of Aeronautics and Astronautics, 2015. [7] 张兵. 高超声速多场耦合及其GPU计算加速技术研究[D].南京航空航天大学,2012. Zhang Bing. Research on hypersonic multi-field coupling and its GPU computing acceleration technology[D]. Nanjing University of Aeronautics and Astronautics, 2012. [8] 宣传伟. 高超声速气动热弹性数值与风洞实验研究[D]. 南京:南京航空航天大学,2020. Xuan Chuanwei. Numerical and wind tunnel experimental research on hypersonic aerodynamic thermoelasticity [D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2020. [9] D. Sziroczak and H. Smith. A review of design issues specific to hypersonic flight vehicles[J]. Progress in Aerospace Sciences,2016, 84:1-28. [10] Gürdal Z, Olmedo R. In-plane response of laminates with spatially varying fiber orientations: variable stiffness concept[J]. AIAA Journal, 1993,31(4): 751-758. [11] 欧阳小穗,刘毅.高速流场中变刚度复合材料层合板颤振分析[J].航空学报,2018,39(03):116-126. OUYANG X S, LIU Y. Panel flutter of variable stiffness composite laminates in supersonic flow[J]. Acta Aeronautica et Astronautica Sinica, 2018, 39(3):116-126. [12] Stodieck O, Cooper J E, WEAVER P M, et al. Aeroelastic Tailoring of a Representative Wing Box Using Tow-Steered Composites[J]. AIAA Journal, 2016, 55(4): 1-15. [13] Zhang B, Chen K, Zu L. Aeroelastic tailoring method of tow-steered composite wing using matrix perturbation theory[J]. Composite Structures,2020,234(C).

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