Lightweight Design of Outer Wing Based on Importance Evaluation Factor

Abstract:

The static and dynamic performance index is constraint condition to establish the mathematical model for optimization design of wing. Basically,the analysis of weighted sensitivity of objective function and state variable imports an importance evaluation factor of wing lightweight design to determine the optimization design variables, then using finite element software , with a optimization design module, to carry out a optimization design. As a result, the analysis of the outer wing shows that the premise of the maximum stress, maximum displacement and low modal frequency are better meet the operating requirements, which the wing weight cumulative reduce to 4.02%. Simultaneously, it proves the efficient and effective of such method.

• Periodical: Applied Mechanics and Materials (Volume 532)
• Pages: 461-465
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.532.461
• Online since: February 2014
• Authors: Da Qian Zhang, Ze Peng Zhu, Xiao Dong Tan
• Keywords: Importance Evaluation Factor, Optimization Design, Outer Wing, Weighted Sensitivity

References

[1] Li weiji, Song bi feng, Sun xiasheng, Aircraft Structural Optimization, M. Beijing: National Defense Industry Press, 2005: 132-198.

[2] Zhou hongxia, Liu bin. Structural optimization design and tailoring of high-aspect-ratio composite material wing, J. Ning bo: Ordnance Material Science and Engineering, 2012: 50-52.

[3] Wang wei, Zhao meiying, Chang nan, The structure geometrical optimization design of a certain interior wing, J. Beijing: Structure & Environment engineering, 2006, 33(3): 56-60.

[4] Chai hongpu, Yu zhefeng, Fu shan. Optimization Design and Analysis of Composite Wing Skins, J. Shanghai: Chinese Quarterly of Mechanics, 2011, 33(1): 109-116.

[5] Wang Wei, Yang Wei, Chan Nan. Integration shape and sizing optimization of composite  wing structure based on response surface method, J. Transactions of Nanjing University of Aeronautics & Astronautics, 2008, 25(2).

[6] Jin haibo. Study on The System of Composite Synthesis Optimization for Aircraft Structures, D. Nanjing University of Aeronautics and Astronautics, (2003).

[7] Lv gang. Study on Lightweight of a Certain Aircraft Parts Based on Composite Materials, D. Jilin University, (2013).

[8] Liu xiashi. Unitary Optimization Design for The Lager Aircraft Structure, J. Shanghai: ACTA Mechanica Solida Sinica, 2003(3): 216-228.

[9] Ji fengxian, Deng daming, Hua jun. The Research of Optimal Aerodynamic Layout for Aircraft Wing, J. Shanghai: Chinese Quarterly of Mechanics, 2003(3): 371-375.