ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Efficient transonic static aeroelastic analysis method based on high accuracy modal aerodynamics
Received date: 2017-01-22
Revised date: 2017-05-03
Online published: 2017-05-03
Transonic static aeroelastic analysis has always been a difficult problem in engineering design. In this paper, based on the linear static aeroelastic equation in the modal coordinate system, a new efficient transonic static aeroelastic analysis method based on high precision modal aerodynamics is developed. The method still solves the linear equation,but for the key aerodynamic increments caused by the modal deformation, which can be obtained by the one-way CFD(Computational Fluid Dynamics)/CSD(Computational Structural Dynamics) interaction. With the method, effective fusion of high efficiency linear method and high accuracy CFD/CSD interaction method is realized. To validate the effects of the method, static aeroelastic problems of a small aspect ratio wing with/without control surface and the aileron efficiency of a fighter aircraft are analyzed, and the results of the classical linear method, CFD/CSD interaction method and test flight identification are compared, which show that the method developed has a comprehensive advantage in terms of efficiency, accuracy and robustness, and has high engineering application value.
HE Fei , HONG Guanxin , LIU Hai , DAN Dan , WANG Ming . Efficient transonic static aeroelastic analysis method based on high accuracy modal aerodynamics[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017 , 38(11) : 121157 -121157 . DOI: 10.7527/S1000-6893.2017.121157
[1] PRANANTA B B, MEIJER J J. Transonic static aeroelastic simulations of fighter aircraft:NLR-TP-2003-187[R]. Amsterdam:NLR, 2003.
[2] 张书俊,王运涛,孟德虹. 大展弦比联接翼静气动弹性研究[J].空气动力学学报,2013,31(2):170-174. ZHANG S J,WANG Y T,MENG D H.Study on static aeroelasticity for high aspect ratio joinedwings[J]. Acta Aerodynamica Sinica, 2013,31(2):170-174(in Chinese).
[3] HEEG J, SPAIN C V, FLORANCE J R,et al. Experimental results from the active aeroelastic wing wind tunnel test program:AIAA-2005-2234[R].Reston, VA:AIAA, 2005.
[4] YANG C, ZHANG B C, WAN Z Q, et al. A method of static aeroelastic analysis based on the high-order panel method and modal method[J]. Science China Technological Sciences, 2011, 54(3):741-748.
[5] WAN Z Q, ZHANG B C, YANG C, et al. Static aeroelastic analysis of a high-aspect-ratio wing based on wind-tunnel experimental aerodynamic forces[J]. Science China Technological Sciences, 2011, 54(10):2716-2722.
[6] 万志强, 邓立东, 杨超, 等. 基于非线性试验气动力的飞机静气动弹性响应分析[J]. 航空学报, 2005, 26(4):439-445. WAN Z Q, DENG L D, YANG C, et al. Aircraft static aeroelastic response analysis based on nonlinear experimental aerodynamic data[J]. Acta Aeronautica et Astronautica Sinica, 2005, 26(4):439-445(in Chinese).
[7] 邵珂, 万志强, 杨超. 基于试验气动力的弹性飞机舵面效率分析[J]. 航空学报, 2009, 30(9):1612-1617. SHAO K, WANG Z Q, YANG C. Control surfaces efficiency analysis of flexible aircraft based on experimental aerodynamic forces[J]. Acta Aeronautica et Astronautica Sinica, 2009, 30(9):1612-1617(in Chinese).
[8] GIESING J P, KALMAN T P, RODDEN W P. Correction factory techniques for improving aerodynamic prediction methods:NASA-CR-144967[R]. Washington, D.C.:NASA, 1976.
[9] JADIC I, HARTLEY D, GIRI J. Improving the aerodynamic approximation in linear aeroelasticity:AIAA-2000-1450[R]. Reston, VA:AIAA, 2000.
[10] MORENO R, NARISETTI R, VON KNOBLAUCH F, et al. A modification to the enhanced correction factor technique to correlate with experimental data:AIAA-2015-1421[R]. Reston, VA:AIAA, 2015.
[11] ZONA Technology Inc. ZAERO theoretical manual V9.2[M]. Scottsdale, AZ:ZONA Technology Inc., 2008:15-25.
[12] XIE C C, YANG C. Surface splines generation and large deflection interpolation[J]. Journal of Aircraft, 2015, 44(3):1024-1026.
[13] FRANKE R. Scattered data interpolation:Tests of some methods[J]. Mathematics of Computation, 1982,38:181-200.
[14] ALLEN C B, RENDALL T C S. Unified approach to CFD-CSD interpolation and mesh motion using radial basis functions:AIAA-2007-3804[R]. Reston, VA:AIAA, 2007.
[15] 林言中, 陈兵, 徐旭. 基于径向基函数插值的气动弹性计算方法[J]. 北京航空航天大学学报, 2014, 40(7):953-958. LIN Y Z, CHEN B, XU X. Numerical method of aeroelasticity based on radial basis function interpolation[J]. Journal of Beijing University of Aeronautics and Astronautics, 2014, 40(7):953-958(in Chinese).
[16] SHENG C H, ALLEN C B. Efficient mesh deformation using radial basis functions on meshes[J]. AIAA Journal, 2013, 51(3):707-720.
[17] RENDALL T C S, ALLEN C B. An efficient fluid-structure interpolation and mesh motion scheme for large aeroelastic simulations:AIAA-2008-6235[R]. Reston, VA:AIAA, 2008.
[18] 王刚, 雷博琪, 叶正寅. 一种基于径向基函数的非结构混合网格变形技术[J]. 西北工业大学学报, 2011, 29(5):784-788. WANG G, LEI B Q, YE Z Y. An efficient deformation technique for hybrid unstructured grid using radial basis functions[J]. Journal of Northwestern Polytechnical University, 2011, 29(5):784-788(in Chinese).
[19] 谢亮, 徐敏, 张斌,等. 基于径向基函数的高效网格变形算法研究[J]. 振动与冲击, 2013, 32(10):141-145. XIE L, XU M, ZHANG B, et al. Space points reduction in grid deforming method based on radial basis functions[J]. Journal of Vibration and Shock, 2013, 32(10):141-145(in Chinese).
[20] 赵永辉. 气动弹性力学与控制[M]. 北京:科学出版社, 2007:45-60. ZHAO Y H. Aeroelasticity and control[M]. Beijing:Science Press, 2007:45-60(in Chinese).
[21] 何飞, 杨超, 但聃, 等. 跨声速副翼效率高精度静弹分析及试飞验证[J]. 北京航空航天大学学报, 2017, 43(3):457-463. HE F, YANG C, DAN D, et al. Transonic static aeroelastic analysis of fighter's aileron efficiecy and test flight verification[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(3):457-463(in Chinese).
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