Horizontal stabilizer mount for a rotorcraft

Patent metadata

Field	Value
Publication number	US-10407154-B2
Application number	US-201715490796-A
Country	US
Kind code	B2
Filing date	Apr 18, 2017
Priority date	Apr 18, 2017
Publication date	Sep 10, 2019
Grant date	Sep 10, 2019

Abstract

In one embodiment, a horizontal stabilizer spar is held on the empennage of a rotorcraft by saddle fittings clamping the stabilizer spar at positions spaced apart along a longitudinal direction of the stabilizer spar. Stabilizer mounts are connected at respective ends to the saddle fittings and to vertical spars on the empennage. At least one of the stabilizer mounts is constructed to allow movement of the saddle fittings with respect to the vertical spars with at least four directions of freedom. The movable stabilizer mount is floatingly attached to a vertical spar, while the saddle fittings are connected to the respective stabilizer mounts by way of spherical bearings.

First claim

What is claimed is:

1. A horizontal stabilizer mount for a rotorcraft, comprising:
a plurality of saddle fittings holding a stabilizer spar at positions that are spaced apart along a longitudinal direction of the stabilizer spar; and
stabilizer mounts having first and second ends, wherein the first ends are attached to respective ones of the saddle fittings at the spaced-apart positions and the second ends are attached to respective vertical spars disposed on the rotorcraft,
wherein at least one of the stabilizer mounts is constructed to allow movement of the saddle fittings with respect to the vertical spars with at least four directions of freedom.

2. The horizontal stabilizer mount of claim 1 , wherein the second end of a first of the stabilizer mounts is attached to the respective vertical spar by way of a fixed bearing which prevents the first stabilizer mount from being displaced in the longitudinal direction of the stabilizer spar.

3. The horizontal stabilizer mount of claim 2 , wherein the second end of at least one second stabilizer mount is floatingly attached to the respective vertical spar, allowing the at least one second stabilizer mount to be displaced in the longitudinal direction of the stabilizer spar.

4. The horizontal stabilizer mount of claim 1 , wherein respective first ends of the stabilizer mounts are each attached to a respective saddle fitting by way of a spherical bearing which allow the respective saddle fitting to rotate with respect to the respective first end about three orthogonal directions.

5. The horizontal stabilizer mount of claim 1 , wherein each of the plurality of saddle fittings comprises a projection with an opening, and wherein the spherical bearing is held captive in the opening.

6. The horizontal stabilizer mount of claim 5 , wherein the first ends of the stabilizer mounts are constructed as a fork with spaced-apart legs, and wherein the projection with the captive spherical bearing is accommodated between the legs.

7. The horizontal stabilizer mount of claim 5 , wherein the projection with the captive spherical bearing is secured between the legs by a bolt extending through the spherical bearing and the legs.

8. The horizontal stabilizer mount of claim 6 , wherein a width of the projection is smaller than a width of a gap between the legs.

9. The horizontal stabilizer mount of claim 1 , further comprising at least one adjustable pull rod operatively connected between the first end and the second end of a respective stabilizer mount and configured to adjust at least the attitude of the stabilizer spar with respect to the rotorcraft.

10. A horizontal stabilizer of a rotorcraft
a stabilizer spar;
a plurality of saddle fittings arranged at spaced-apart positions along a longitudinal direction of the stabilizer spar holding and clamping the stabilizer spar; and
stabilizer mounts having first and second ends, wherein the first ends are attached to respective ones of the saddle fittings at the spaced-apart positions and the second ends are attached to respective vertical spars disposed on the rotorcraft,
wherein at least one of the stabilizer mounts is constructed to allow movement of the saddle fittings with respect to the vertical spars with at least four directions of freedom.

11. The horizontal stabilizer of claim 10 , wherein the second end of a first of the stabilizer mounts is attached to the respective vertical spar by way of a fixed bearing which prevents the first stabilizer mount from being displaced in the longitudinal direction of the stabilizer spar.

12. The horizontal stabilizer of claim 11 , wherein the second end of at least one second stabilizer mount is floatingly attached to the respective vertical spar, allowing the at least one second stabilizer mount to be displaced in the longitudinal direction of the stabilizer spar.

13. The horizontal stabilizer of claim 10 , wherein respective first ends of the stabilizer mounts are each attached to a respective saddle fitting by way of a spherical bearing which allow the respective saddle fitting to rotate with respect to the respective first end about three orthogonal directions.

14. The horizontal stabilizer of claim 10 , wherein each of the plurality of saddle fittings comprises a projection with an opening, and wherein the spherical bearing is held captive in the opening.

15. The horizontal stabilizer of claim 14 , wherein the first ends of the stabilizer mounts are constructed as a fork with spaced-apart legs, and wherein the projection with the captive spherical bearing is accommodated between the legs.

16. The horizontal stabilizer of claim 15 , wherein a width of the projection is smaller than a width of a gap between the legs.

17. The horizontal stabilizer of claim 10 , further comprising at least one adjustable pull rod operatively connected between the first end and the second end of a respective stabilizer mount and configured to adjust an attitude of the stabilizer spar with respect to the rotorcraft.

18. A rotorcraft, comprising
a fuselage, and an empennage attached to the fuselage;
a horizontal stabilizer spar attached to the empennage;
a skin assembly covering parts of the horizontal stabilizer spar;
a plurality of saddle fittings arranged at spaced-apart positions along a longitudinal direction of the stabilizer spar holding and clamping the stabilizer spar; and
stabilizer mounts having first and second ends, wherein the first ends are attached to respective ones of the saddle fittings at the spaced-apart positions and the second ends are attached to respective vertical spars disposed on the rotorcraft,
wherein at least one of the stabilizer mounts is constructed to allow movement of the saddle fittings with respect to the vertical spars with at least four directions of freedom.

19. The rotorcraft of claim 18 , wherein at least one stabilizer mount is floatingly attached to the respective vertical spar, allowing the at least one second stabilizer mount to be displaced in the longitudinal direction of the stabilizer spar.

20. The rotorcraft of claim 18 , wherein the stabilizer mounts are each attached to a respective saddle fitting by way of a spherical bearing which allow the respective saddle fitting to rotate with respect to the respective stabilizer mount about three orthogonal axes.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Boucher Guillaume Noiseux
• Flynn-Robitaille Pascal
• Morris Kevin Donald

Classifications

• B64C2027/8281

  comprising horizontal tail planes · CPC title

• B64C27/06

  with single rotor · CPC title

• B64C27/82

  characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft · CPC title

• B64C9/02 Primary

  Mounting or supporting thereof · CPC title

• B64C5/02

  Tailplanes · CPC title