Additive manufacture proprotor blade

Patent metadata

Field	Value
Publication number	US-11059566-B2
Application number	US-201916590618-A
Country	US
Kind code	B2
Filing date	Oct 2, 2019
Priority date	Oct 2, 2019
Publication date	Jul 13, 2021
Grant date	Jul 13, 2021

Abstract

An exemplary proprotor blade assembly includes a structural skin extending spanwise from a root to a tip and along a chord from leading edge to a trailing edge and a structural core positioned inside of the structural skin, the structural skin comprising hex-shaped structures oriented normal to the structural skin.

First claim

What is claimed is:

1. A proprotor blade assembly comprising:
a structural skin extending spanwise from a root to a tip and along a chord from leading edge to a trailing edge;
a structural core positioned inside of the structural skin, the structural core comprising hex-shaped structures oriented normal to the structural skin; and
wherein the hex-shaped structures have vertical walls surrounding a central opening and upper and lower cap flanges having faying areas, the faying areas bonded to the structural skin.

2. The proprotor blade assembly of claim 1 , wherein the structural skin does not dispose an internal tubular spar.

3. The proprotor blade assembly of claim 1 , wherein the structural skin includes centrifugal force material extending spanwise.

4. The proprotor blade assembly of claim 1 , wherein some of the hex-shaped structures have different geometries from other ones of the hex-shaped structures.

5. The proprotor blade assembly of claim 1 , wherein the upper and lower cap flanges are thicker than the vertical walls.

6. The proprotor blade assembly of claim 1 , wherein one or more of the hex-shaped structures comprises an opening extending laterally through one or more of the vertical walls.

7. The proprotor blade assembly of claim 1 , wherein two or more the hex-shaped structures comprise an opening extending laterally through one or more of the vertical walls, wherein the openings of the hex-shaped structures are different sizes.

8. The proprotor blade assembly of claim 1 , wherein some of the hex-shaped structures have different geometries from other ones of the hex-shaped structures.

9. The proprotor blade assembly of claim 1 , wherein the structural skin includes centrifugal force material extending spanwise.

10. The proprotor blade assembly of claim 1 , wherein the upper and lower cap flanges are thicker than the vertical walls; and
one or more of the hex-shaped structures comprises an opening extending laterally through one or more the vertical walls.

11. The proprotor blade assembly of claim 10 , wherein the structural skin includes centrifugal force material extending spanwise.

12. A rotorcraft comprising:
a fuselage;
a wing extending from the fuselage;
a proprotor assembly carried by the wing, the proprotor assembly comprising a plurality of proprotor blade assemblies each comprising:
a structural skin extending spanwise from a root to a tip and along a chord from leading edge to a trailing edge;
centrifugal force material forming a centrifugal force path;
a structural core positioned inside of the structural skin, the structural core comprising hex-shaped structures oriented normal to the structural skin; and
wherein the hex-shaped structures have vertical walls surrounding a central opening and upper and lower cap flanges having faying areas, the faying areas bonded to the structural skin, wherein the upper and lower cap flanges are thicker than the vertical walls.

13. The rotorcraft of claim 12 , wherein the structural skin does not dispose an internal tubular spar.

14. The rotorcraft of claim 12 , wherein some of the hex-shaped structures have different geometries from one or more of other ones of the hex-shaped structures.

15. The rotorcraft of claim 12 , wherein the hex-shaped structures of a proprotor blade assembly of the plurality of proprotor blade assemblies are configured to extend normal to the structural skin when the proprotor blade assembly twists during flight.

16. The rotorcraft of claim 12 , wherein one or more of the hex-shaped structures comprises an opening extending laterally through one or more of the vertical walls.

17. The rotorcraft of claim 12 , wherein two or more the hex-shaped structures comprise an opening extending laterally through one or more of the vertical walls, wherein the openings of the hex-shaped structures are different sizes.

18. The rotorcraft of claim 12 , wherein the upper and lower cap flanges are thicker than the vertical walls;
wherein one or more of the hex-shaped structures comprises an opening extending laterally through one or more the vertical walls; and
wherein the structural skin includes the centrifugal force material and the centrifugal force material extends spanwise.

19. The rotorcraft of claim 12 , wherein the centrifugal force material extends spanwise along the structural skin.

Assignees

• Bell Textron Inc

Inventors

• Foskey Christopher Edward
• Maresh Andrew

Classifications

• B64C29/0033

  the propellers being tiltable relative to the fuselage · CPC title

• B64C11/26 Primary

  Fabricated blades · CPC title

• B33Y80/00 Primary

  Products made by additive manufacturing · CPC title