Sacrificial blade tips for ducted aircraft

Patent metadata

Field	Value
Publication number	US-11273910-B2
Application number	US-202016907093-A
Country	US
Kind code	B2
Filing date	Jun 19, 2020
Priority date	Jun 19, 2020
Publication date	Mar 15, 2022
Grant date	Mar 15, 2022

Abstract

A proprotor blade for a ducted aircraft including a duct includes a main body having a distal end and a sacrificial blade tip coupled to the distal end of the main body. The sacrificial blade tip includes a deformable core material and a shell layer at least partially covering the deformable core material. The sacrificial blade tip deforms upon contact with the duct, thereby reducing damage to the ducted aircraft.

First claim

What is claimed is:

1. A proprotor blade for a ducted aircraft including a duct, the proprotor blade comprising:
a main body having a distal end; and
a sacrificial blade tip coupled to the distal end of the main body, the sacrificial blade tip comprising:
a deformable core material; and
a shell layer at least partially covering the deformable core material and having a closed distal end;
wherein, the sacrificial blade tip is configured to deform upon contact with the duct, thereby reducing damage to the ducted aircraft.

2. The proprotor blade as recited in claim 1 wherein the main body is coupled to the sacrificial blade tip at an interface boundary, the sacrificial blade tip configured to separate from the main body at the interface boundary upon contact with the duct.

3. The proprotor blade as recited in claim 1 wherein the main body is coupled to the sacrificial blade tip at an interface boundary; and
wherein, the main body further comprises a skin, the skin and the shell layer forming an integral layer covering the interface boundary.

4. The proprotor blade as recited in claim 1 wherein the main body further comprises a skin, the shell layer overlapping the skin.

5. The proprotor blade as recited in claim 1 wherein the sacrificial blade tip is coupled to the main body using adhesive.

6. The proprotor blade as recited in claim 1 wherein the sacrificial blade tip is coupled to the main body using adhesive tape.

7. The proprotor blade as recited in claim 1 wherein the sacrificial blade tip is configured to compress upon contact with the duct.

8. The proprotor blade as recited in claim 1 wherein fragments of the sacrificial blade tip break away upon contact with the duct.

9. The proprotor blade as recited in claim 1 wherein the sacrificial blade tip deforms upon contact with the duct to increase a tip gap between the proprotor blade and the duct.

10. The proprotor blade as recited in claim 1 wherein the deformable core material is formed from a softer material than the shell layer.

11. The proprotor blade as recited in claim 1 wherein the deformable core material further comprises foam.

12. The proprotor blade as recited in claim 1 wherein the deformable core material further comprises a frangible lattice structure.

13. The proprotor blade as recited in claim 12 wherein the lattice structure further comprises a honeycomb structure.

14. The proprotor blade as recited in claim 1 wherein the deformable core material further comprises a polymer lattice structure.

15. The proprotor blade as recited in claim 1 wherein the shell layer further comprises at least one of fiberglass or carbon fiber reinforced plastic.

16. A rotorcraft comprising:
a fuselage; and
a proprotor system coupled to the fuselage, the proprotor system including a duct and a plurality of proprotor blades surrounded by the duct, each proprotor blade including a main body having a distal end and a sacrificial blade tip coupled to the distal end of the main body, each sacrificial blade tip comprising:
a deformable core material; and
a shell layer at least partially covering the deformable core material and having a closed distal end;
wherein, each sacrificial blade tip is configured to deform upon contact with the duct, thereby reducing damage to the rotorcraft.

17. The rotorcraft as recited in claim 16 wherein, for each proprotor blade, the main body is undeformed upon contact between the sacrificial blade tip and the duct.

18. The rotorcraft as recited in claim 16 wherein each sacrificial blade tip is configured to deform upon contact with the duct to increase a tip gap between the proprotor blade and the duct.

19. The rotorcraft as recited in claim 16 wherein each sacrificial blade tip is configured to compress upon contact with the duct.

20. The rotorcraft as recited in claim 16 wherein fragments of each sacrificial blade tip break away upon contact with the duct.

Assignees

• Textron Innovations Inc

Inventors

• Thompson George Matthew
• Knoll Jonathan Andrew
• Carlson Nicholas Ralph
• Carr Timothy Brian

Classifications

• B64C27/20

  Rotorcraft characterised by having shrouded rotors, e.g. flying platforms · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• B64C11/003

  Variable-diameter propellers; Mechanisms therefor · CPC title

• B64C11/32

  mechanical · CPC title

• B64C11/001 Primary

  Shrouded propellers · CPC title