Method of making a monolithic part

Patent metadata

Field	Value
Publication number	US-10065370-B2
Application number	US-201615215978-A
Country	US
Kind code	B2
Filing date	Jul 21, 2016
Priority date	Apr 15, 2014
Publication date	Sep 4, 2018
Grant date	Sep 4, 2018

Abstract

A method of forming a monolithic aircraft part includes additively forming a first cavity, defined by a first wall of the part, additively forming a second cavity, defined by a second wall of the part, so that the first cavity and the second cavity are not in communication with each other and share a common wall portion so that the second cavity is partially contained within the first cavity. Additively forming the first cavity includes forming a first aperture, extending through the first wall, forming a second aperture, extending through the first wall, and forming a first inner surface of the first wall, defining a first shape, wherein a first object, permanently having the first shape, would not be able to be mechanically extracted from the first cavity via the first aperture or the second aperture.

First claim

What is claimed is:

1. A method of forming a monolithic aircraft part, the method comprising:
additively forming a first cavity, defined by a first wall of the monolithic aircraft part, wherein additively forming the first cavity comprises:
additively forming a first aperture, extending through the first wall;
additively forming a second aperture, extending through the first wall; and
additively forming a first inner surface of the first wall, defining a first shape, wherein a first object, permanently having the first shape, would not be able to be mechanically extracted from the first cavity via the first aperture or the second aperture:

additively forming a second cavity, defined by a second wall of the monolithic aircraft part, so that the first cavity and the second cavity are not in communication with each other and share a common wall portion so that the second cavity is partially contained within the first cavity, wherein additively forming the second cavity comprises:
additively forming a third aperture and a fourth aperture wherein the second wall extends beyond the first wall to define at least one of the third aperture and the fourth aperture; and
additively forming a second inner surface of the second wall, defining a second shape, wherein a second object permanently having the second shape would not be able to be mechanically extracted from the second cavity via the third aperture or the fourth aperture; and

filling the first cavity with one or more of an aircraft fire-insulation medium or an aircraft acoustic-insulation medium;
wherein the second cavity forms a portion of an aircraft electrical system, aircraft hydraulic system, or an aircraft cabin environmental system.

2. The method of claim 1 , further comprising additively forming an aperture plug, tethered to the first wall, defining the first cavity, adjacent the first aperture.

3. The method of claim 1 , further comprising forming, on the second wall, at least one connecting feature associated with at least one of the third aperture and the fourth aperture.

4. The method of claim 1 , further comprising forming at least one of the first wall of the first cavity or the second wall of the second cavity with a varying wall thickness.

5. The method of claim 1 , further comprising additively forming an integral wiring restraint on the monolithic aircraft part.

6. The method of claim 1 , further comprising additively forming a mounting bracket, integral with the first wall, for connecting the monolithic aircraft part to one or more other monolithic aircraft parts, to aircraft components, or to a mounting surface of an aircraft.

7. The method of claim 1 , further comprising additively forming a connector, additively integrally formed with the first wall for connecting the monolithic aircraft part to one or more other monolithic aircraft parts, to aircraft components, or to a mounting surface of an aircraft.

8. The method of claim 7 , wherein the connector is additively formed as one or more of a threaded member or a threaded aperture.

9. The method of claim 7 , wherein the connector is additively formed as a snap-fit member.

10. The method of claim 1 , further comprising additively forming an integral anti-crush feature within at least one of the first cavity or the second cavity.

11. The method of claim 1 , further comprising additively forming an integral reinforcement feature on the monolithic aircraft part.

12. The method of claim 1 , wherein:
the wall of the second cavity, defining the third aperture, is additively formed so as to extend beyond the wall of the first cavity on one side of the first cavity; and
the wall of the second cavity, defining the fourth aperture, is additively formed so as to extend beyond the wall of the first cavity on another side of the first cavity.

13. The method of claim 1 , wherein the first wall of the first cavity is additively formed to have at least one locally thickened portion that forms a rib, extending along one or more of an outer surface of the first wall of the first cavity, an inner surface of the first wall of the first cavity, or an inner surface of the second wall of the second cavity.

14. The method of claim 1 , further comprising forming the monolithic aircraft part by one of stereolithography, laser sintering, fused deposition modeling, three-dimensional modeling, or laser engineered net shaping.

15. The method of claim 1 , further comprising additively forming an aperture plug, tethered to the first wall, defining the first cavity, adjacent the second aperture.

16. The method of claim 1 , wherein the second cavity is additively formed so that a portion of the second wall of the second cavity defines at least one of the third aperture or the fourth aperture and extends beyond the first wall of the first cavity, defining a connecting feature, associated with a respective one of the third aperture or the fourth aperture, wherein the connecting feature joins the second cavity to another monolithic aircraft part or to aircraft components.

17. The method of claim 16 , wherein the connecting feature is additively formed as a flange.

18. The method of claim 16 , wherein the connecting feature is additively formed as a bell.

19. The method of claim 16 , wherein the connecting feature is additively formed as a bead.

20. The method of claim 1 , further comprising additively forming the monolithic aircraft part from a flame-retardant material.

Assignees

• Boeing Co

Inventors

• Lyons Brett I
• Bartel Aaron W
• Tucker Trevor E

Classifications

• B29C64/118 Primary

  using filamentary material being melted, e.g. fused deposition modelling [FDM] · CPC title

• B22F10/25

  Direct deposition of metal particles, e.g. direct metal deposition [DMD] or laser engineered net shaping [LENS] · CPC title

• B29C64/135

  the energy source being concentrated, e.g. scanning lasers or focused light sources · CPC title

• B32B2605/18

  Aircraft · CPC title

• B32B1/08

  Tubular products · CPC title