Annular butt joint structure of fuselage with weatherproof composite skin

A composite material and anti-corrosion technology, applied in the direction of the fuselage frame, fuselage bulkhead, etc., can solve the problems of moisture intrusion, structural performance reduction, and low curing strength, so as to reduce product scrap rate, reduce maintenance costs, and reduce manufacturing costs. cost effect

Inactive Publication Date: 2015-06-24
AVIC SAC COMML AIRCRAFT
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  • Application Information

AI Technical Summary

Problems solved by technology

[0002] At the connection position of the aircraft fuselage ring, the windward end face of the composite skin is easily eroded by wind, rain or sand and stones, resulting in delamination of the end face of the skin, resulting in a decrease in structural performance, and in severe cases, structural damage
At present, the commonly used method is to wrap the end face of the composite skin and pneumatically seal the butt joints of the front and rear fuselage sections. The wrapping process is carried out at room temperature. The glue is peeled off or moisture intrudes from the place where the glue is opened

Method used

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  • Annular butt joint structure of fuselage with weatherproof composite skin
  • Annular butt joint structure of fuselage with weatherproof composite skin

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Embodiment Construction

[0017] An anti-corrosion fuselage circumferential butt structure with composite material skin, the upper end surfaces of two metal machined frames 1 respectively undertake the front fuselage skin 6 and the rear fuselage skin 7, and the two metal machined frames 1 For docking, there is a boss 4 structure at the butt joint, the fuselage skin is located on the side of the boss 4 and there is a step difference between the boss 4 and the gap between the boss 4 and the fuselage skin is provided with a sealant 5 . By providing the boss 4 on the upper end surface of the metal machined frame 1, the wind erosion of the end surface of the composite material can be avoided, which not only simplifies the protection means of the end surface of the skin of the composite material, but also reduces the assembly cost of the assembly line and sections.

[0018] Preferably, the above-mentioned butt joint mode is a tab joint butt joint mode and a metal machined frame butt joint mode.

[0019] Pref...

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Abstract

The invention relates to an annular butt joint structure of a fuselage with weatherproof composite skin. The annular butt joint structure is characterized in that a front fuselage skin body and a rear fuselage skin body are respectively borne on upper end faces of two metal machining frames, the metal machining frames are in butt joint, a boss structure is arranged at the position of the joint, the fuselage skin bodies are located on the rear side of a boss to form step difference with the boss, and a gap between the boss and the fuselage skin bodies is filled with sealant. The boss is arranged on the upper end faces of the metal machining frames, wind erosion to the end face of the composite skin can be avoided, protection means of the end face of the composite skin is simplified, and assembling cost of final assembly and partial assembly is lowered.

Description

technical field [0001] The invention relates to a fuselage circumferential butt joint structure, in particular to a fuselage circumferential joint structure with composite material skin anti-corrosion, which belongs to the field of aerospace processing. Background technique [0002] At the connection position of the aircraft fuselage ring, the windward end face of the composite skin is easily eroded by wind, rain, or sand and stones, resulting in delamination of the end face of the skin, resulting in a decrease in structural performance, and in severe cases, structural damage. At present, the commonly used method is to wrap the end face of the composite skin and pneumatically seal the butt joints of the front and rear fuselage sections. The wrapping process is carried out at room temperature. The glue is peeled off or moisture intrudes from the place where the glue is opened. Contents of the invention [0003] The technical problem to be solved by the present invention is...

Claims

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Application Information

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IPC IPC(8): B64C1/06B64C1/12
Inventor 张俊鼎刘杰徐丹魏士礼
Owner AVIC SAC COMML AIRCRAFT
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