Failsafe injected adhesive joint
First Claim
1. A method of joining a structural member to an aircraft skin, comprising:
- (a) providing the structural member with a bonding surface having a first end and a second end and a groove that extends along the bonding surface of the structural member from the first end to the second end;
(b) providing an interface member with a base and a leg, the leg having a bonding surface with a first end and a second end and a groove that extends along the bonding surface of the leg from the first end to the second end of the leg;
(c) placing the bonding surfaces of the structural member and the leg in contact with each other so that the grooves mate to define a cavity extending from the first ends to the second ends of the bonding surfaces;
(d) injecting adhesive into the cavity; and
(e) bonding the base of the interface member to the skin.
1 Assignment
0 Petitions
Accused Products
Abstract
A composite member is joined to another composite or noncomposite member, using liquid or paste adhesive resin that cures in the joint. The joint is configured in such a way that the adhesive forms an interlocking key within recesses in the joined members that prevents joint disassembly once the adhesive has cured and hardened. Both of the members are provided with recesses extending along their lengths in the joint. The recesses register with each other to define a cavity and may undulate. The recessed are designed in such a way as to take the full load capability if the joint, even if there is no adhesion to the joined members. Adhesive is injected into the cavity through injection ports spaced periodically along the length of the joint.
39 Citations
14 Claims
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1. A method of joining a structural member to an aircraft skin, comprising:
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(a) providing the structural member with a bonding surface having a first end and a second end and a groove that extends along the bonding surface of the structural member from the first end to the second end; (b) providing an interface member with a base and a leg, the leg having a bonding surface with a first end and a second end and a groove that extends along the bonding surface of the leg from the first end to the second end of the leg; (c) placing the bonding surfaces of the structural member and the leg in contact with each other so that the grooves mate to define a cavity extending from the first ends to the second ends of the bonding surfaces; (d) injecting adhesive into the cavity; and (e) bonding the base of the interface member to the skin. - View Dependent Claims (2, 3, 4, 5, 6, 7)
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8. A method of joining a structural member to an aircraft skin, comprising:
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(a) providing the structural member with opposite sides that are parallel to each other and face in opposite directions from each other, and providing a pair of grooves, the grooves being on the opposite sides of the structural member and extending lengthwise along the structural member; (b) providing an interface member having a base and a pair of legs extending orthogonally therefrom, each of the legs having an inside surface, the inside surfaces being parallel to and facing each other, and providing a groove on each of the inside surfaces extending lengthwise along the interface member; (c) inserting the structural member between the legs such that the opposite sides of the structural member are in contact with the inside surfaces of the interface member, the grooves of the structural member aligning with the grooves of the legs to define elongated cavities; (d) injecting adhesive into each of the cavities; and (e) curing the adhesive and bonding the interface member to the skin. - View Dependent Claims (9, 10, 11, 12, 13, 14)
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Specification