A method for repairing aircraft pressurized cockpit skin

Abstract

The invention provides an airplane pressurized cabin skin repairing method. The method is characterized by including the following steps that firstly, a reinforcing cushion plate is manufactured and provided with lugs connected with a long purlin in a matched manner; secondly, rivets connecting the the damaged position of the long purlin with a skin are decomposed; thirdly, an interlayer sealing material is laid on the region of the damage position; fourthly, the reinforcing cushion plate is placed on the interlayer sealing material between the skin and the long purlin; fifthly, installation holes are drilled in the positions, corresponding to rivet holes in the long purlin, in the reinforcing cushion plate, the positions of the lugs are included, and the reinforcing cushion plate, the interlayer sealing material, the skin and the long purlin are riveted into a whole; and sixthly, the rivets are coated with sealing glue.

Description

technical field [0001] The invention relates to a method for repairing aircraft skin damage. Background technique [0002] Aircraft skins are exposed components that are susceptible to damage from foreign objects. At present, the general method for repairing aircraft pressurized cockpit skin damage is the external patch method. The method is to make a rectangular patch according to the size of the skin damage, chamfer the periphery of the patch, install the patch on the outer surface of the skin, and use a 90° countersunk Rivets are riveted to the skin. The shortcoming of existing method is: (1) patch is installed on the outside of fuselage skin shape, and aircraft aerodynamic shape is caused certain influence, especially in the front fuselage part (I grade aerodynamic zone), and the negative impact brought especially Obviously; (2) The damaged skin is sandwiched between the aircraft interior trim panel / insulation layer and the patch, which will make the regular inspection...

AI Technical Summary

Problems solved by technology

The shortcoming of existing method is: (1) patch is installed on the outside of fuselage skin shape, and aircraft aerodynamic shape is caused certain influence, especially in the front fuselage part (I grade aerodynamic zone), and the negative impact brought especially Obviously; (2) The damaged skin is sandwiched between the aircraft interior trim panel / insulation layer and the patch, which will make the regular inspection and maintenance work (A, C, D inspection, etc.) of the damaged part during the remaining life cycle of the aircraft less It is difficult to obtain, not only need to carry out a lot of disassembly work so that the maintenance personnel can get close to the inspection part, but also require the staff to have rich experience, and may also need to use special instruments and equipment; The model is a 90° countersunk rivet. Due to the large depth of the countersunk, when making the rivet hole, a cutting edge is formed in the opening area of ​​the backing plate, which reduces the fatigue strength of the rivet connection.

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