摘要为了满足地面颤振模拟试验中气动力计算的实时性以及插值点数量要求，本文提出一种基于计算流体力学(computational fluid dynamics ，CFD)的非定常气动力重构方法，首先通过模态激励的方式建立广义坐标下的气动力降阶模型(reduced order model ，ROM)，提高气动力计算效率，然后利用提出的物理坐标与广义坐标物理量的转换关系将模型转换至物理坐标下，并基于优化算法对插值点进行缩聚处理，最终采用标准模型AGARD445.6对建立的非定常气动力进行了仿真，分析结果表明基于重构的气动力模型获得的颤振边界与计算流体力学/计算固体力学直接耦合及风洞试验结果吻合较好，证实了该方案的可行性。
Abstract：In order to meet the requirements of real-time aerodynamic calculation and the number of interpolation points in ground flutter simulation test, an unsteady aerodynamic reconstruction method based on computational fluid dynamics (CFD) is proposed in this paper. Firstly, the reduced order aerodynamic model (ROM) in generalized coordinates is established by means of modal excitation to improve the efficiency of aerodynamic calculation, and then the proposed coordinates transformation between physical and generalized coordinates are used to establish aerodynamic model in physical coordinates, also the interpolation node is condensed through optimization. Finally, the standard model AGARD445.6 is used to simulate the unsteady aerodynamics mode. The flutter boundary obtained from the reconstructed aerodynamic model is in good agreement with those of direct computational fluid dynamic and computational solid dynamic(CFD/CSD) coupling and wind tunnel test result, which proves the feasibility of the scheme.
宋巧治，王彬文，李晓东. 基于CFD的地面颤振模拟试验非定常气动力重构方法研究[J]. 振动与冲击, 2022, 41(10): 40-46.
SONG Qiaozhi，WANG Binwen，LI Xiaodong. Unsteady aerodynamic model reproduction method for ground flutter simulation test based on CFD. JOURNAL OF VIBRATION AND SHOCK, 2022, 41(10): 40-46.
[1] 管德.气动弹性试验[M].北京:北京航空学院出版社, 1986.11.
Guan De. Aeroelastic test[M]. Beijing: Beijing Institute of Aeronautics Press, 1986.11.
[2] Rajagopal P. Simulation of aerodynamic of large aircraft on the ground [D].ONERA NT 222, 1974.
[3] Kearns JP. Missile wing flutter simulation[J]. Johns Hopkins APL Technical Digest, 1962, 2(4), 12–16
[4] P Karkle, V I Smyslov. Electromechanical simulation method in dynamic aeroelasticity usage experience and future trends [C]. International Forum on Aeroelasticity and Structural Dynamics, Stockholm, June 2007.
[5] J Zeng, D W Kingsbury, E Ritz, P C Chen, et al. GVT-based ground flutter test without wind tunnel [C]. 52nd AIAA/ASME/ASCE/AHS/ ASC structure, Structural Dynamics and material Conference, Denver, Colorado, USA, April 4-7, 2011, AIAA 2011-1942.
[6] G Liseykin, M Bogatyrev, M Pronin et al, Structural nonlinearitities simulation on the flutter electromechanical modeling test bench. 29th Congress of the international council of the aeronautical sciences[C], St. Petersburg Russia September 7-12 2014.
[7] Dhital K, Han JH, Lee YK. Approximation of distributed aerodynamic force to a few concentrated forces for studying supersonic panel flutter[J]. Transactions of the Korean Society for Noise and Vibration Engineering, 2016, 26(5): 518-527.
[8] Dhital K, Han JH. Subsonic flutter emulation of composite laminate using a few concentrated forces[C].21st International Conference on Composite Materials Xi’an, 20-25th August 2017.
[9] 潘树祥, 齐丕骞. 地面模拟热颤振试验研究[J]. 强度与环境, 1984(2): 10-14.
Pan, S. X. and Qi, P. Q. Studies on ground thermo-flutter simulation test. Structure and Engineering Environment , 1984(2):10-14.
[10] Wu ZG, Chu L, Yuan R, Yang C, et al. Studies on Aeroservoelasticity Semi-Physical Simulation Test for Missiles [J], Science China Technological Sciences, 2012, 55(9): 2482-2488.
[11] Zhigang Wu, Chengji Ma, Chao Yang. New Approach to the Ground Flutter Simulation Test [J]. Journal of Aircraft, Vol. 53, No. 5, September-October 2016.
[12] 许云涛, 吴志刚, 杨超. 地面颤振模拟试验中的非定常气动力模拟[J]. 航空学报, 2012, 33(11): 1947-1957.
Xu Y T, Wu Z G, Yang C. Simulation of the unsteady aerodynamic forces for ground flutter simulation test. Acta Aeronautica Astronautica Sinica, 2012, 33(11): 1947-1957
[13] 胡巍, 杨智春,谷迎松. 带操纵面机翼气动弹性地面试验仿真系统中的气动力降阶方法[J]. 西北工业大学学报, 2013, 31(5): 810-815.
Hu Wei, Yang Zhichun, Gu Yingsong, A New and Effective Method for Reducing Order of Aerodynamics of a Wing with Control Surface for Ground Flutter Test[J]. Journal of Northwestern Polytechnical University, 2013, 31(5): 810-815.
[14] 邵崇晖, 超声速流中壁板颤振的抑制和地面试验研究[D]. 哈尔滨工业大学, 2017. 06.
Shao CH. Suppression of nonlinear panel flutter in the supersonic flow and ground flutter test [D]. Harbin Institute of Technology, 2017.06.
[15] Dowell EH. A modern course in aeroelasticity, 3rd Revised and Enlarged Edition [M]. New York: Klewer Academic Publishers, 1995.
[16] 陈刚, 李跃明. 非定常流场降阶模型及其应用研究进展与展望[J]. 力学进展, 2011, 41(6): 686-701.
CHEN Gang, LI Yueming. Advances and Prospects of the Reduced Order Model for Unsteady Flow and Its Application [J]. ADVANCES IN MECHANICS, 2011, 41(6): 686-701.
[17] Gupta KK and Bach C. Systems identification approach for a computational fluid dynamics-based aeroelastic analysis [J]. AIAA Journal, 2007, 45(12): 2820-2827.
[18] Cowan TJ, Gupta KK. Development of discrete-time aerodynamic model for CFD-based aeroelastic analysis[C]. Proceedings of the 37th Aerospace Sciences Meeting and Exhibit, 1999.
[19] 张伟伟, 叶正寅. 基于非定常气动力辨识技术的气动弹性数值模拟[J]. 航空学报, 2006, 27(4) : 579-583.
ZHANG Wei-wei, YE Zheng-yin. Numerical simulation of aeroelasiticity basing on identification technology of unsteady aerodynamic loads[J]. Acta Aeronautica Astronautica Sinica, 2006, 27(4): 579-583.
[20] 聂雪媛, 刘中玉, 杨国伟, 基于CFD气动力辨识模型的气动弹性数值计算[J]. 振动与冲击, Vol. 33 No. 20, 2014, 20-25.
NIE Xueyuan，LIU Zhongyu, YANG Guowei. Identification of unsteady aerodynamic CFD-based model for numerical aeroelastic analysis[J]. Journal of Vibration and Shock. Vol. 33 No. 20, 2014, 20-25.
[21] 贺顺, 杨智春, 谷迎松. 机翼跨音速颤振特性的频域分析[J]. 中国科学: 物理学 力学 天文学, 2014, 44(3): 285-292.
He S, Yang ZC, Gu YS. Frequency domain analysis for wing transonic flutter[J]. Science China Physics, Mechanics & Astronomy ，2014, 44(3):285-292.
