Structure Analysis and Aeroelastic Optimization Method for Composite Wing-box Structure with Curved Fiber

2019 ◽  
Author(s):  
Zexi Wang ◽  
Zhiqiang Wan ◽  
Siyan Zhu ◽  
Chao Yang
Keyword(s):  
Structure Analysis ◽  
Optimization Method ◽  
Box Structure ◽  
Composite Wing ◽  
Wing Box

Demonstration of detectability of SHM system with FBG/PZT hybrid system in composite wing box structure

2008 ◽  
Author(s):  
Hideki Soejima ◽  
Toshimichi Ogisu ◽  
Hiroshi Yoneda ◽  
Yoji Okabe ◽  
Nobuo Takeda ◽  
...  
Keyword(s):  
Hybrid System ◽  
Box Structure ◽  
Composite Wing ◽  
Wing Box

scholarly journals Effect of Interfacial Debonding on the Strength of Composite Structure-Similarity Scale Model for the Wing-Box

2015 ◽  
Vol 2015 ◽  
pp. 1-8
Author(s):  
Shiyong Sun ◽  
Rui Yang ◽  
Zibin Yan ◽  
Wei Qian
Keyword(s):  
Carrying Capacity ◽  
Bonding Strength ◽  
Ultimate Load ◽  
Scale Model ◽  
Load Carrying Capacity ◽  
Load Carrying ◽  
Box Structure ◽  
Ultimate Load Carrying Capacity ◽  
Composite Wing ◽  
Wing Box

Based on the wing-box structure, a model was established to analyze the strength of the scale model for the composite wing. Firstly, different failure criteria were set to determine damage onset of the components. The continuum damage variables were adopted in the stiffness degradation rule. Secondly, the interface elements were placed along the interface between the beam flange and the skin to investigate the effects of bonding strength on the ultimate load-carrying capacity of the wing-box. The failure modes of the wing-box structure were studied by using the nonlinear finite element method. The effect of flange’s width on the strength of wing-box was discussed based on the prediction method. The results indicated that the ultimate load-carrying capacity varied distinctly with the change of flange’s width. However, the bonding strength had limited effect on the model strength as the flange’s width increases to the critical value. The research methods and results of the study can serve as reference for the strength analysis on the scale model of composite wing as well as the determination of principles adopted in the design of the scale model for wing spar.

scholarly journals Weight trades in the design of a composite wing box: effect of various design choices

2018 ◽  
Vol 10 (2) ◽  
pp. 403-417 ◽  
Author(s):  
Gunther Moors ◽  
Christos Kassapoglou ◽  
Sergio Frascino Müller de Almeida ◽  
Clovis Augusto Eça Ferreira
Keyword(s):  
Composite Wing ◽  
Wing Box

Structural Optimization Design of an Aircraft Metal-Composite Wing

2013 ◽  
Vol 341-342 ◽  
pp. 519-523
Author(s):  
Ya Hui Zhang ◽  
Ji Hong Zhu ◽  
Jun Shuo Li ◽  
Wei Hong Zhang
Keyword(s):  
Structural Optimization ◽  
Optimization Design ◽  
Optimization Method ◽  
Design Solution ◽  
Metal Composite ◽  
Concept Design ◽  
Obvious Effect ◽  
Reinforced Composite ◽  
Three Phase ◽  
Composite Wing

The problem of metal-composite wing structural optimization is discussed and a strategy is presented. Topology optimization method is applied to provide load transferring path of structure for concept design. Size, shape and other optimization method are used to provide detailed design for individual components. A three-phase optimization method is discussed for fiber reinforced composite laminate skin. Optimal parameters include ply angle, percentage, thickness, layer shape and sequence. The design of laminate for ease of manufacture is based on a set of manufacturing constraints. This paper deals with a total optimal design solution for aileron structure of an aircraft. The result satisfies all the requirements of strength and stability, and has obvious effect of weight loss.

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