Method for repairing gouges on rear edge of composite blade and rear edge of blade tip

Abstract

The invention belongs to the field of rotor blade repairing, and discloses a composite blade rear edge and blade tip rear edge gouges repairing method which comprises the following steps: 1, judging that the damage type is blade rear edge gouges or blade tip rear edge gouges; 2, judging whether the damaged area adopts polishing repair or filling repair, if the damaged area adopts polishing repair, entering the step 3, and if the damaged area adopts filling repair, entering the step 4 to the step 7; 3, polishing and painting the damaged area of the blade; 4, isolating the repair area by using an adhesive tape, and carrying out paint removal, copper mesh removal and cleaning treatment on the repair area; 5, filling the damaged area with a filler, and maintaining the shape of the damaged area through a shape maintaining tool for first curing; 6, after the first curing is completed, grinding glue bumps until the appearance of the blade in the filling area is consistent with the theoretical appearance; and 7, laying glass cloth and a copper net on the surface of the filling area, and carrying out second-time vacuum curing after laying is completed; and carrying out polishing, cleaning and repairing paint after the second curing is completed.

Description

technical field [0001] The invention belongs to the field of repairing rotor blades, in particular to a method for repairing bruises on the trailing edge of a composite material blade and the trailing edge of a blade tip. Background technique [0002] Due to the high specific strength and specific stiffness of composite materials and good fatigue resistance, composite blades have been adopted by more and more helicopters. Composite blades are inevitably damaged during use, especially the trailing edge of the blade and the trailing edge of the tip. Due to the weak structure, the blade is often damaged during handling, installation and disassembly. This kind of damage is repairable damage. In order to save costs and ensure the flight safety of the aircraft, reasonable repair methods must be adopted to repair the blades. [0003] At present, the existing composite skin damage repair method mainly adopts gradient lap repair, but the implementation process of this repair method ...

AI Technical Summary

Problems solved by technology

[0003] At present, the existing composite skin damage repair method mainly adopts gradient lap repair, but the implementation process of this repair method is complicated. In the process of repairing the skin damage area into a gradient shape, due to the thin skin, the layers are not easy to peel off, and it is easy to Scratch the intact skin, and this method needs to remove the large area of ​​the skin

In addition, prepreg + adhesive film is used for gradient lap repair, which needs to be cured at a medium temperature (about 120°C). The external field does not have the conditions for implementation, and the curing temperature is close to the curing temperature of the blade molding, which will damage the non-damage area of ​​the blade. Intensity has a certain effect

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