Paper Title:
Non-Cylindrical Fuselage Structural Optimization of BWB Civil Aircraft
  Abstract

Blended-Wing-Body (BWB) civil aircraft possesses so light structure, high lift-drag ratio and low fuel burn that it has been an important topic of future civil aircraft. But internal pressure causes large bending stress instead of skin-membrane stress in BWB non-cylindrical fuselage. For 150 seats BWB fuselage, a composite 3-bay fuselage model is analyzed and two improved configurations of braced fuselage derivatives are designed in this paper. By optimization analysis, the optimized non-cylindrical fuselage structures are obtained in low bending stress and deformation condition, and optimized layer thicknesses ratio of composite material are presented. The optimization conclusions are very valuable and applicable for the fuselage structural design of BWB civil aircraft.

  Info
Periodical
Key Engineering Materials (Volumes 474-476)
Edited by
Garry Zhu
Pages
1736-1739
DOI
10.4028/www.scientific.net/KEM.474-476.1736
Citation
Y. J. Zhang, B. T. Wang, "Non-Cylindrical Fuselage Structural Optimization of BWB Civil Aircraft", Key Engineering Materials, Vols. 474-476, pp. 1736-1739, 2011
Online since
April 2011
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Price
$32.00
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