A Repair Method for Local Damage of Composite Flap
A technology of composite materials and flaps, applied in the field of aircraft repair, can solve problems such as economic loss, increase of aircraft maintenance and use costs, and failure to restore the shape of flaps, etc., to achieve the effect of reducing maintenance and use costs and prolonging the service life
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Embodiment 1
[0042] Example 1, the two edges of the flap adjacent to the trailing edge and the wingtip are broken in a large range inwardly, the maximum distance from the broken edge to the back beam is about 30mm, the length of the broken part from the wingtip to the inside of the flap in the span direction is about 300mm, and the total length of the flap is 1200mm ;
[0043] 1. Determine whether the damaged area of the flap is suitable for repair by this method: do delamination and debonding non-destructive testing on the damage of the flap, and according to the test results: the front beam and the rear beam of the flap and the gap between the front beam and the rear beam The area is not damaged; the damaged area is 32mm away from the rear beam in the chord direction, and the damaged length of the damaged area in the wing direction does not exceed 1 / 3 of the length of the flap, and this method can be used to repair;
[0044] 2. Determine the cutting boundary: draw the parallel lines of t...
Embodiment 2
[0052] In Example 2, the two edges of the flap adjacent to the trailing edge and the wing root are broken in a large range inwardly. The distance from the maximum edge of the break to the rear beam is about 30mm. ;
[0053] 1. Determine whether the damaged area of the flap is suitable for repair by this method: do delamination and debonding non-destructive testing on the damage of the flap, and according to the test results: the front beam and the rear beam of the flap and the gap between the front beam and the rear beam The area is not damaged; the damaged area is 28mm away from the rear beam in the chord direction, and the damaged length of the damaged area in the wing direction does not exceed 1 / 3 of the length of the flap, and this method can be used to repair;
[0054] 2. Determine the cutting boundary: make parallel lines between the flap root and the trailing edge respectively. The two parallel lines are the cutting boundary and the inner edge of the cutting area, and...
Embodiment 3
[0062] In Example 3, the two edges of the flap adjacent to the leading edge and the wingtip are broken in a large range inwardly. The distance from the largest edge of the fracture to the front spar is about 30mm. 1200mm;
[0063] 1. Determine whether the damaged area of the flap is suitable for repair by this method: do delamination and debonding non-destructive testing on the damage of the flap, and according to the test results: the front beam and the rear beam of the flap and the gap between the front beam and the rear beam The area is not damaged; the damaged area is 31mm away from the front beam in the chord direction, and the damage length of the damaged area in the wing direction does not exceed 1 / 3 of the length of the flap, and this method can be used to repair;
[0064] 2. Determine the cutting boundary: make parallel lines between the flap tip and the leading edge respectively. The two parallel lines are the cutting boundary and the inner edge of the cutting area...
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