Optimization of Sandwich Composites Fuselages Under Flight Loads |
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Authors: | Chongxin Yuan Otto Bergsma Sotiris Koussios Lei Zu Adriaan Beukers |
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Affiliation: | (1) Section Composites, Faculty of Aerospace Engineering, Delft University of Technology, Delft, The Netherlands |
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Abstract: | The sandwich composites fuselages appear to be a promising choice for the future aircrafts because of their structural efficiency
and functional integration advantages. However, the design of sandwich composites is more complex than other structures because
of many involved variables. In this paper, the fuselage is designed as a sandwich composites cylinder, and its structural
optimization using the finite element method (FEM) is outlined to obtain the minimum weight. The constraints include structural
stability and the composites failure criteria. In order to get a verification baseline for the FEM analysis, the stability
of sandwich structures is studied and the optimal design is performed based on the analytical formulae. Then, the predicted
buckling loads and the optimization results obtained from a FEM model are compared with that from the analytical formulas,
and a good agreement is achieved. A detailed parametric optimal design for the sandwich composites cylinder is conducted.
The optimization method used here includes two steps: the minimization of the layer thickness followed by tailoring of the
fiber orientation. The factors comprise layer number, fiber orientation, core thickness, frame dimension and spacing. Results
show that the two-step optimization is an effective method for the sandwich composites and the foam sandwich cylinder with
core thickness of 5 mm and frame pitch of 0.5 m exhibits the minimum weight. |
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