基于高拟真度模型的高超声速飞行器静气动弹性优化

粟华; 谷良贤; 龚春林

基于高拟真度模型的高超声速飞行器静气动弹性优化

西北工业大学航天学院航天飞行动力学技术重点实验室, 西安 710072

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出版历程
- 收稿日期: 2012-09-24
- 刊出日期: 2013-08-28

Static aeroelastic optimization of hypersonic aircraft based on high-fidelity model

National Key Laboratory of Aerospace Flight Dynamics, School of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China

摘要

摘要: 为解决基于计算流体动力学(CFD)和计算结构动力学(CSD)高拟真度模型的静气动弹性优化过程中模型更新自动化困难、求解速度慢的难点,提出了基于几何主模型技术的CFD/CSD一体化参数化建模方法和基于网格单元修正的常体积四面体(CVT)数据交换技术,并引入响应面模型来降低气动弹性优化求解难度.通过AGARD 445.6机翼静气动弹性分析对上述方法的可行性和有效性进行了验证;并以某高超声速飞行器为例,采用基于二次响应面的多目标优化算法进行了CFD/CSD气动弹性分析与优化,优化后飞行器升阻比增加16%,结构质量减少9%,且响应面模型精度拟合误差不超过1.5%.计算结果表明:所发展的CFD/CSD一体化参数化建模与优化方法能够有效地解决高拟真度模型的静气动弹性优化问题.
- 气动弹性 /
- 计算流体动力学/计算结构动力学 /
- 参数化主模型 /
- 数据交换 /
- 响应面技术
Abstract: Static aeroelastic optimization was proposed for an entire aircraft vehicle based on computational fluid dynamics (CFD) and computational structural dynamics (CSD) coupling numerical computational methodology. To solve the problem of automatic modeling and computational demand on multidisciplinary optimization based on high-fidelity model, a geometric master model technology was presented to generate the CFD/CSD integrated models, an improved constant volume tetrahedral (CVT) method based on elements was used for the grid deformation and force transition between the CFD and CSD mesh, and the response surface model (RSM) was used in stead of the traditional optimization algorithms. The above methods were validated by AGARD 445.6 wing static aeroelastic analysis. A hypersonic aircraft multi-objective optimization based on RSM was accomplished through CFD/CSD static aeroelastic optimization. The optimized aircraft lift-to-drag ratio increased by 16%, structural weight reduced by 9%, and the fitting error of RSM was less than 1.5%. Results show the CFD/CSD integrated modeling and optimization method could solve effectively the static aeroelastic optimization problem with high-fidelity models.
- aeroelasticity /
- CFD/CSD /
- parameterized master model /
- interface mapping /
- response surface methodology

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参考文献(15)

[1]	Guruswamy G P,Obayashi S.Study on the use of high-fidelity methods in aeroelastic optimization[J].Journal of Aircraft,2004,41(3):616-619.
[2]	Jamshid A S,Pawel C,Lucas G H,et al.Integrated aerodynamic/structural/dynamic analyses of aircraft with large shape changes [C]//48th Structures,Structural Dynamics,and Materials Confrence.Honolulu,Hawaii:AIAA,2007:7740-7759.
[3]	Alonso J J,Martins R R A,Reuther J J.High-fidelity aero-structural design using a parametric CAD-based model.AIAA 2003-3429,2003.
[4]	Maute K,Nikbay M,Farhat C.Coupled analytical sensitivity analysis and optimization of three-dimensional nonlinear aeroelastic systems[J].AIAA Journal,2001,39(11):2051-2061.
[5]	Melike N,Levent A A.A multidisciplinary code coupling approach for analysis and optimization of aeroelastic systems.AIAA 2008-5876,2008.
[6]	杨青,梁强,杨永年.基于CFD的静气动弹性优化设计方法[J].空气动力学学报,2005,23(1):16-20. YANG Qing,LIANG Qiang,YANG Yongnian.Static aeroelastic optimization with CFD method[J].Acta Aerodynamica Sinica,2005,23(1):16-20.(in Chinese)
[7]	刘金辉,乔志德,杨旭东,等.基于响应面法的机翼气动/结构一体化优化设计研究[J].空气动力学学报,2006,24(3):300-306. LIU Jinhui,QIAO Zhide,YANG Xudong,et al.Research of aerodynamic structure integrative optimization design of wing based on response surface methodology[J].Acta Aerodynamica Sinica,2006,24(3):300-306.(in Chinese)
[8]	郑赟.基于非结构网格的气动弹性数值方法研究[J].航空动力学报,2009,24(9):2069-2077. ZHENG Yun.Computational aeroelasticity with an unstructured grid method[J].Journal of Aerospace Power,2009,24(9):2069-2077.(in Chinese)
[9]	马铁林,马东立,张朔.分析模型参数化建模在飞机多学科优化设计中的应用[J].航空学报,2008, 29(6):1576-1580. MA Tielin,MA Dongli,ZHANG Shuo.Application of parameterization of analysis model in airplane multidisciplinary design optimization[J].Acta Aeronautica et Astronautica Sinica,2008,29(6):1576-1580.(in Chinese)
[10]	徐敏,安效民,陈士橹.一种CFD/CSD耦合计算方法[J].航空学报,2006,27(1):33-37. XU Min,AN Xiaomin,CHEN Shilu.CFD/CSD coupling numerical computational methodology[J].Acta Aeronautica et Astronautica Sinica,2006,27(1):33-37.(in Chinese)
[11]	Sadeghi M,Liu F,Lai K L,et al.Application of three-dimensional interfaces for data transfer in aeroelastic computations [C]//22nd Applied Aerodynamics Conference and Exhibit.Rhode Island:AIAA,2004:1116-1145.
[12]	粟华.再入飞行器多学科优化技术研究 [D].西安:西北工业大学,2010. SU Hua.Investigation on multidisciplinary design optimization technologies for reentry vehicle [D].Xi'an:Northwestern Polytechnical University,2010.(in Chinese)
[13]	Yates E C.AGARD standard aeroelastic configurations for dynamic response Ⅰ:wing 445.6 [R].NASA TM-100492,1987.
[14]	Cai J,Liu F.Static aero-elastic computation with a coupled CFD and CSD method [R].AIAA 2000-0717,2000.
[15]	Ramadas K P.Summary report of the orbital X-34 wing static aeroelastic study [R].NASA CR-2001-210850,2001.