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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

Inactive Publication Date: 2008-07-16
TONGJI UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] Most of the existing aircraft fuselages are made of alloy materials. Due to their high density and heavy weight, they cannot be used to manufacture large aircraft

Method used

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  • Composite stressed-skin construction for fuselage and technique of preparing the same

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Embodiment Construction

[0020] The present invention is further described below in conjunction with accompanying drawing.

[0021] As shown in Figure 1, the composite skin structure for the aircraft fuselage includes, in turn, 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.

[0022] The inner wall layer 1 is an aramid fiber layer or a glass fiber reinforced resin-rich layer. It can meet the functional requirements of interior decoration, fire prevention, seepage prevention and impact prevention

[0023] The foam core layer 3 is a high-performance structural foam layer selected from polymethacrylimide foam layer or polyetherimide foam layer.

[0024] A certain number of stringers are arranged in the foam core layer. The number of stringers can be determined according to specific requirements. The inner carbon fiber reinforced plastic layer 2, the foam core layer 3 and the ...

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Abstract

The invention discloses a composite skin structure used in the airframe of the airplane, which is characterized in that: the skin structure comprises an internal wall layer, an internal carbon fiber reinforced plastic layer, a foam-core layer, and an external fiber reinforced plastic layer and an external protective layer in sequence. The invention also discloses a technique for preparing the composite skin structure used in the airframe of the airplane. The invention has the advantages of light weight, good impact resistance property and is applicable to being used in producing the airframes of the large airplanes.

Description

technical field [0001] The invention relates to a composite skin structure for aircraft and a preparation process thereof. Background technique [0002] Most of the existing aircraft fuselages are made of alloy materials. Due to their high density and heavy weight, they cannot be used to manufacture large aircraft. [0003] Composite materials have been applied in many fields due to their excellent mechanical properties such as low density, high specific strength, and high specific modulus. The application of advanced composite materials in aircraft will significantly improve the performance and market competitiveness of aircraft. The fuselage structure is the component with the largest amount of material used in the entire aircraft structure. If composite materials can be applied to the fuselage, the performance of the aircraft will be greatly improved. Contents of the invention [0004] According to the deficiencies in the prior art, the invention provides a composite ...

Claims

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Application Information

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IPC IPC(8): B32B5/18B32B27/04B64C1/12B29C70/02B29K105/06
CPCY02T50/433Y02T50/43Y02T50/40
Inventor 薛元德周仕刚
Owner TONGJI UNIV
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