초록 ▼

A component of a rotary wing aircraft is provided including a surface configured to contact another component of the rotary wing aircraft such that the surface is susceptible to corrosion and/or pitting. The surface has an area from which a portion of material was removed. A structural deposit is fo

A component of a rotary wing aircraft is provided including a surface configured to contact another component of the rotary wing aircraft such that the surface is susceptible to corrosion and/or pitting. The surface has an area from which a portion of material was removed. A structural deposit is formed by cold spraying one or more layers of powdered material within the area. The structural deposit is configured to carry a load applied to the component.

대표청구항 ▼

1. A method of rebuilding a damaged portion of a surface of a gearbox housing, the surface configured to engage with and support a load of a portion of an aircraft, the method comprising: forming an area in the surface by removing all material exhibiting at least one of localized damage, corrosion a

1. A method of rebuilding a damaged portion of a surface of a gearbox housing, the surface configured to engage with and support a load of a portion of an aircraft, the method comprising: forming an area in the surface by removing all material exhibiting at least one of localized damage, corrosion and pitting;preparing the area;creating a structural deposit in the area, the structural deposit being integrally formed with the gearbox housing, and the structural deposit configured to share the load applied to the gearbox housing by the portion of the aircraft; andremoving excess material from the structural deposit. 2. The method according to claim 1, wherein the gearbox housing is configured for a rotary wing aircraft and the portion of the aircraft is a portion of the rotary wing aircraft. 3. The method according to claim 1, wherein the structural deposit includes one or more layers of powdered material applied to the area through a cold spray deposition process. 4. The method according to claim 3, wherein the powdered material includes aluminum. 5. The method according to claim 1, wherein the excess material is removed so that the structural deposit is substantially flush with the surface. 6. The method according to claim 1, wherein the excess material is removed so that a dimension of the component including the structural deposit is substantially equal to an original dimension of the component. 7. A method of preemptively forming a structural deposit on a non-corroded surface of a first component, the surface configured to engage with and support a load of a second component, the method, comprising the steps of: selecting an unused gearbox housing as the first component;identifying a portion of the non-corroded surface of the gearbox housing where at least one of corrosion and pitting is expected to occur;removing material from the portion of the non-corroded surface of the gearbox housing;preparing the portion of the surface;creating a structural deposit on the portion of the surface identified where at least one of corrosion and pitting is expected to occur, the structural deposit being integrally formed with the first component, and the structural deposit configured to share the load applied to the first component; andremoving excess material from the structural deposit. 8. The method according to claim 7, wherein selecting the gearbox housing includes selecting a gearbox housing of a rotary wing aircraft. 9. The method according to claim 7, wherein the structural deposit includes one or more layers of powdered material applied through a cold spray deposition process. 10. The method according to claim 9, wherein the powdered material includes aluminum. 11. The method according to claim 7, wherein the excess material is removed to achieve a desired dimension. 12. The method according to claim 11, wherein the desired dimension is substantially equal to an original dimension thereof. 13. The method according to claim 7, wherein the surface is one of a mating surface, a flight control surface, and a mounting foot portion, and the second component is one of a fastener, a flight control component, and an airframe. 14. A method of preemptively forming a structural deposit on a non-corroded surface of a first component, the surface configured to engage with and support a load of a second component, the method, comprising the steps of: selecting an unused gearbox housing as the first component;identifying a portion of the non-corroded surface of the gearbox housing where at least one of corrosion and pitting is expected to occur;creating a structural deposit on the portion of the surface identified where at least one of corrosion and pitting is expected to occur by adding the structural deposit to the surface without first removing material from the portion of the surface, the structural deposit configured to share the load applied to the first component; andremoving excess material from the structural deposit.