Volume 29 Issue 12
Dec.  2014
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Article Navigation >  Journal of Aerospace Power  > 2014  >  29(12): 2898-2904
ZUO Ying-tao, WANG Xiao-peng, CHEN Yun, CHEN Gang, GAO Zheng-hong. An efficient method for multidisciplinary design optimization of aircraft based on CFD/CSD coupling[J]. Journal of Aerospace Power, 2014, 29(12): 2898-2904. doi: 10.13224/j.cnki.jasp.2014.12.016
Citation: ZUO Ying-tao, WANG Xiao-peng, CHEN Yun, CHEN Gang, GAO Zheng-hong. An efficient method for multidisciplinary design optimization of aircraft based on CFD/CSD coupling[J]. Journal of Aerospace Power, 2014, 29(12): 2898-2904. doi: 10.13224/j.cnki.jasp.2014.12.016
shu

An efficient method for multidisciplinary design optimization of aircraft based on CFD/CSD coupling

doi: 10.13224/j.cnki.jasp.2014.12.016

  • 1. National Key Laboratory of Science and Technology on Aerodynamic Design and Research, Northwestern Polytechnical University, Xi'an 710072;

  • 2. Shanghai Electro-Mechanical Engineering Institute, Shanghai 201109, China;

  • 3. College of Computer and Information Sciences, Fujian Agriculture and Forestry University, Fuzhou 350002, China;

  • 4. State Key Laboratory for Strength and Vibration of Mechanical Structures, Xi'an Jiaotong University, Xi'an 710049, China

  • Received Date: 2014-02-23
  • Publish Date: 2014-12-28
    Abstract
  • A multidisciplinary design optimization method based on CFD/CSD (computational fluid dynamics/computational structure dynamics) coupling was built. The structural performance was predicted by the structural finite element equation, and the aerodynamic loads was predicted by solving N-S equations to get reliable optimization results. Surrogate model was adopted to alleviate the huge expense caused by high-fidelity models. RBF (radial basis function) was utilized to exchange data between fluid and structure, and energy conservation principle is guaranteed. Typical wing-body configuration was optimized by the proposed design optimization method to improve the aerodynamic and structural performance. After optimization, the drag and mass of the aircraft are reduced by 5.0% and 4.2%, respectively, and all the constraints are satisfied. All these indicate the effectiveness of the proposed method.

     

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