Composite stressed-skin construction for fuselage and technique of preparing the same
A technology for aircraft fuselage and skin, which is applied in the field of composite skin structure and its preparation process, can solve the problems of inability to manufacture large aircraft, high density, heavy weight, etc., and achieves easy implementation of manufacturing process, convenient manufacturing, high weight light effect
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[0020] The invention will be further described below in conjunction with the accompanying drawings.
[0021] As shown in Fig. 1, the composite skin structure for aircraft fuselage includes an inner wall layer 1, an inner carbon fiber reinforced plastic layer 2, a foam core layer 3, an outer carbon fiber reinforced plastic layer 4, and an outer protective layer 5 in sequence.
[0022] The inner wall layer 1 is an aramid fiber layer or a glass fiber reinforced resin-rich layer. It can meet the relevant functional requirements of interior decoration, fire protection, anti-seepage, anti-washing, etc.
[0023] The foam core layer 3 is a high-performance structural foam layer, selected from a polymethacrylimide foam layer or a polyetherimide foam layer.
[0024] A certain number of long stringers are arranged in the foam core layer. The number of long stringers can be determined according to specific requirements. The inner carbon fiber reinforced plastic layer 2, the foam core layer 3 ...
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