太阳能无人机机翼几何非线性气动弹性分析
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摘要
以大展弦比机翼为研究对象,结合几何非线性结构有限元建模方法与非线性气动力计算技术,提出了一种利用插值技术求解几何非线性气动弹性问题的方法。并以某太阳能无人机机翼缩比模型为例进行计算分析以及试验研究。研究结果表明:提出的方法得到非线性颤振解与常规方法得到的计算结果基本一致,但应用此方法后,不仅计算效率成倍提高,而且能规避常规方法中由于计算工况设定不合理可能导致的严重计算偏差。
In this paper, taking the large aspect ratio wing as a research object, and combined with the geometric nonlinear structure finite element modeling method and the nonlinear aerodynamic calculation technology, a interpolation method is proposed to solve the geometically nonlinear aeroelastic problem. Taking a scaled model of solar UAV wing as an example, the calculation and analysis and experimental research are carried out. The resuts show that the nonlinear flutter solution obtained by the method in this paper is basically the same as that obtained by the conventional method. By so doing, not only the calculation efficiency is doubled, but also the serious calculation deviation may be avoided in the conventional method, which may result from the unreasonable setting of the calculation working condition.
In this paper, taking the large aspect ratio wing as a research object, and combined with the geometric nonlinear structure finite element modeling method and the nonlinear aerodynamic calculation technology, a interpolation method is proposed to solve the geometically nonlinear aeroelastic problem. Taking a scaled model of solar UAV wing as an example, the calculation and analysis and experimental research are carried out. The resuts show that the nonlinear flutter solution obtained by the method in this paper is basically the same as that obtained by the conventional method. By so doing, not only the calculation efficiency is doubled, but also the serious calculation deviation may be avoided in the conventional method, which may result from the unreasonable setting of the calculation working condition.
引文
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[10] 白鹏,崔尔杰,李锋,等.对称翼型低雷诺数小攻角升力系数非线性现象研究[J].力学学报,2006,38(1):1-8.BAI P,CUI E J,LI F,et al.Study of the Nonlinear Lift Coefficient of the Symmetrical Airfoil at Low Reynolds Number near the 0°Angle of Attack [J].Chinese Journal of Theoretical and Applied Mechanics,2006,38(1):1-8.(in Chinese)
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[2] HODGES D H,ORMISTON R A,PETERS D A.On the Nonlinear Deformation Geometry of Euler-Bernoulli Beams[Z].National Aeronautics and Space Administration,1980,NASA-1566.
[3] TANG D M,DOWELL E H.Comments on the ONERA Stall Aerodynamic Model and Its Impact on Aeroelastic Stability[J].Journal of Fluids and Structures,1996,10(4):353-366.
[4] PATIL M J,HODGES D H.On the Importance of Aerodynamic and Structural Geometrical Nonlinearities in Aeroelastic Behavior of High-Aspect-Ratio Wings[Z].AIAA 2000-1448,2000.
[5] TANG D M,DOWELL E H.Effects of Geometric Structural Nonlinearity on Flutter and Limit Cycle Oscillations of High-Aspect-Ratio Wings[J].Journal of Fluids and Structures,2004,19(3):291-306.
[6] DOWELL E H.Nonlinear Flutter of Curved Plates[J].AIAA Journal,1969,7(3):424-431.
[7] 谢长川,杨超.大展弦比飞机几何非线性气动弹性稳定性的线性化方法[J].中国科学(技术科学),2011,41(3) :385-393.XIE C C,YANG C.A Linearization Method to Analyze Geometrical Nonlinear Aeroelastic Stability of the High-Aspect-Ratio Aircraft[J].Scientia Sinica(Technologica),2011,41(3):385-393.(in Chinese)
[8] 杨智春,张惠,谷迎松,等.考虑几何非线性效应的大展弦比机翼气动弹性分析[J].振动与冲击,2014,33(16) 72-75.YANG Z C,ZHANG H,GU Y S.Aeroelastic Analysis of the High Aspect Ratio Wing Considering the Geometric Nonlinearity[J].Journal of Vibration and Shock,2014,33(16) 72-75.(in Chinese)
[9] 安效民,徐敏.一种几何大变形下的非线性气动弹性求解方法[J].力学学报,2011,43(1):97-104.AN X M,XU M.An Improved Geometrically Nonlinear Algorithm and Its Application for Nonlinear Aeroelasticity [J].Chinese Journal of Theoretical and Applied Mechanics,2011,43(1) :97-104.(in Chinese)
[10] 白鹏,崔尔杰,李锋,等.对称翼型低雷诺数小攻角升力系数非线性现象研究[J].力学学报,2006,38(1):1-8.BAI P,CUI E J,LI F,et al.Study of the Nonlinear Lift Coefficient of the Symmetrical Airfoil at Low Reynolds Number near the 0°Angle of Attack [J].Chinese Journal of Theoretical and Applied Mechanics,2006,38(1):1-8.(in Chinese)
[11] 谢长川,吴志刚,杨超.大展弦比柔性机翼的气动弹性分析[J].北京航空航天大学学报,2003,29(12):1087-1090.XIE C C,WU Z G,YANG C.Aeroelastic Analysis of Flexible Large Aspect Ratio Wing[J].Journal of Beijing University of Aeronautics and Astronautics,2003,29(12):1087-1090.(in Chinese)
[12] CHRISTOPHER C C,TIM F,BALAKUMAR B.GPGPU Implementation and Benchmarking of the Unsteady Vortex Lattice Method [Z].AIAA-2013- 0288,2013.
[13] RODDEN W P,JOHNSON E H.MSC/NASTRAN Aeroelastic Analysis Users Guide[Z].V68,1994.
[14] 管德.飞机气动弹性力学手册[M].北京:航空工业出版社,1994:215-222.GUAN D.Manual of Aircraft Aeroelasticity [M].Beijing:Aviation Industry Press,1994:215-222.(in Chinese)