Pitch angle blocking device

Patent metadata

Field	Value
Publication number	US-12060149-B2
Application number	US-202117445130-A
Country	US
Kind code	B2
Filing date	Aug 16, 2021
Priority date	Dec 18, 2020
Publication date	Aug 13, 2024
Grant date	Aug 13, 2024

Abstract

A pitch angle blocking device for blocking the pitch angle of a multi-blade rotor that has neighboring first and second rotor blades in circumferential direction that extend from a rotor hub of a rotary-wing aircraft In non-operational mode of the rotary-wing aircraft. The present embodiments further relate to a multi-blade rotor of a rotary-wing aircraft that is adapted to receiving such a pitch angle blocking device, and to a rotary-wing aircraft with such a multi-blade rotor. The pitch angle blocking device comprises first and second attachment means that are configured to be non-rotatably and releasably attached to the first and second rotor blades spaced apart from the rotor hub, and a connecting device that non-rotatably connects the first attachment means with the second attachment means.

First claim

What is claimed is:

1. A pitch angle blocking device for blocking a pitch angle of a multi-blade rotor of a rotary-wing aircraft in non-operational mode of the rotary-wing aircraft, the multi-blade rotor having neighboring first and second rotor blades in circumferential direction that extend from a rotor hub that is rotatable around a rotor axis in a rotor plane, comprising:
first attachment means configured to be non-rotatably and releasably attached to the first rotor blade spaced apart from the rotor hub;
second attachment means configured to be non-rotatably and releasably attached to the second rotor blade spaced apart from the rotor hub; and
a connecting device that extends along the rotor plane in the circumferential direction directly between the first attachment means and the second attachment means and non-rotatably connects the first attachment means with the second attachment means.

2. The pitch angle blocking device of claim 1 wherein the first attachment means further comprises:
a bracket that at least partially encompasses the first rotor blade, and at least two fasteners that are configured to non-rotatably and releasably attach the bracket to the first rotor blade.

3. The pitch angle blocking device of claim 2 wherein the second attachment means further comprises:
an additional bracket that at least partially encompasses the second rotor blade, and at least two additional fasteners that are configured to non-rotatably and releasably attach the additional bracket to the second rotor blade.

4. The pitch angle blocking device of claim 3 wherein the fastener and the additional fastener comprise at least one of a threaded rod, a nut, a bolt, a pin, a quick release pin, a bearing, a spherical washer, or an elastic element.

5. The pitch angle blocking device of claim 3 wherein the at least one of the bracket, the additional bracket, and the connecting device are integrally formed.

6. The pitch angle blocking device of claim 1 wherein the connecting device further comprises:
a first extension that extends from the first attachment means; and
a second extension that extends from the second attachment means.

7. The pitch angle blocking device of claim 6 wherein the connecting device further comprises:
at least one interface connection that connects the first extension with at least one of the second attachment means or the second extension.

8. The pitch angle blocking device of claim 7 wherein the at least one interface connection further comprises:
a length adjustment device that couples the first extension with the at least one of the second attachment means or the second extension and that is configured to adjust a distance between the first extension and the at least one of the second attachment means or the second extension.

9. The pitch angle blocking device of claim 7 wherein the at least one interface connection further comprises:
at least one interface fastener that couples the first extension with the at least one of the second attachment means or the second extension.

10. The pitch angle blocking device of claim 9 wherein the at least one interface fastener comprises at least one of a screw, a nut and a bolt, a threaded rod, or a rivet.

11. The pitch angle blocking device of claim 9 wherein the at least one interface connection further comprises:
a slot in the first extension through which the at least one interface fastener is adapted to slide for enabling a displacement of the first extension relative to the at least one of the second attachment means or the second extension.

12. A multi-blade rotor of a rotary-wing aircraft that is adapted to receiving a pitch angle blocking device of claim 1 for blocking the pitch angle of the multi-blade rotor in non-operational mode of the rotary-wing aircraft, comprising:
the rotor hub; and
the neighboring first and second rotor blades in the circumferential direction that extend from the rotor hub, wherein the first rotor blade comprises first receiving means at a first location that is spaced apart from the rotor hub and configured to receiving at least a portion of the first attachment means of the pitch angle blocking device; and the second rotor blade comprises second receiving means at a second location that is spaced apart from the rotor hub and configured to receiving at least a portion of the second attachment means of the pitch angle blocking device.

13. The multi-blade rotor of claim 12 wherein the first receiving means comprise at least one of a threaded rod, a bearing, an elastic element, a threaded hole, or a non-threaded hole.

14. The multi-blade rotor of claim 12 wherein the second receiving means comprise a non-circular cross section of the second rotor blade at the second location.

15. A rotary-wing aircraft comprising a multi-blade rotor of claim 12 .

16. The pitch angle blocking device of claim 1 wherein the connecting device extends between the neighboring first and second rotor blades along a connecting direction that extends along the rotor plane including circumferential directions of the neighboring first and second rotor blades and sequent to each of the circumferential directions of the neighboring first and second rotor blades.

17. A pitch angle blocking device for blocking a pitch angle of a multi-blade rotor of a rotary-wing aircraft in non-operational mode of the rotary-wing aircraft, the multi-blade rotor having neighboring first and second rotor blades in circumferential direction that extend from a rotor hub that is rotatable around a rotor axis in a rotor plane, comprising:
a first fastener configured to be non-rotatably and releasably attached to the first rotor blade spaced apart from the rotor hub;
a second fastener configured to be non-rotatably and releasably attached to the second rotor blade spaced apart from the rotor hub; and
a connecting device that extends along the rotor plane in the circumferential direction directly between the first fastener and the second fastener and non-rotatably connects the first fastener with the second fastener.

Assignees

• Airbus Helicopters Deutschland GmbH

Inventors

• Buesing Moritz
• Kahl Bernward
• Bauer Markus

Classifications

• B64C27/06

  with single rotor · CPC title

• B64C27/50

  Blades foldable to facilitate stowage of aircraft · CPC title

• B64C11/32

  mechanical · CPC title

• B64C27/322 Primary

  Blade travel limiting devices, e.g. droop stops · CPC title