Methods for treating aircraft structures
The present invention relates to methods for repairing a structural weakness in an aircraft fuselage, or preventing the advancement of a structural weakness in an aircraft fuselage. Cold spray methods such as supersonic particle deposition have been shown to positively affect structural characteristics of sheet metal and lap joints as used in fuselage construction.
1. A method comprising:
(i) repairing a structural weakness, and/or (ii) preventing or inhibiting progression of a structural weakness in an aircraft structure, the structural weakness arising in a course of service of the aircraft, wherein repairing or preventing or inhibiting progression comprises:
bonding a plurality of metallic particles to the structural weakness of the aircraft structure arising in the course of service of the aircraft, the bonding being effected under conditions allowing the plurality of metallic particles to form a substantially continuous layer having a depth of at least about 0.2 mm, wherein the aircraft structure is returned to at least a proportion of its original strength.
2. A method according to claim 1 wherein the substantially continuous layer is positioned to prevent ingress of an environmental element into the structural weakness.
3. A method according to claim 1 wherein at least a proportion, or substantially all, of the particles are metallic particles.
4. A method according to claim 1 wherein the bonding does not involve melting or fusing of the particles.
5. A method according claim 1 wherein the bonding is achieved by a cold spray process.
6. A method according to claim 5 wherein the cold spray process is supersonic particle deposition.
7. A method according to claim 1 wherein the substantially continuous layer has substantially even depth across an application surface to which the plurality of metallic particles is bonded.
8. A method according to claim 1 wherein the aircraft structure is a fuselage component.
9. A method according to claim 1 wherein the aircraft structure is a sheet metal.
10. A method according to claim 1 wherein the aircraft structure is a lap joint.
11. A method according to claim 10 wherein the substantially continuous layer does not extend to cover a junction between a free end of a sheet metal component of the lap joint.
12. A method according to claim 1 wherein the structural weakness is a crack.