Aircraft support structures, systems, and methods

Patent metadata

Field	Value
Publication number	US-10494111-B2
Application number	US-201615756365-A
Country	US
Kind code	B2
Filing date	Sep 12, 2016
Priority date	Sep 14, 2015
Publication date	Dec 3, 2019
Grant date	Dec 3, 2019

Abstract

Aircraft support structures, systems, and methods are disclosed. In one embodiment, an aircraft system includes a rotating component and a support (e.g. strut) that supports the rotating component. The support includes a locking assembly (P1) that is configured to lock, automatically, an inner member (214) of the support with respect to an outer member (208) of the support for stiffening the support in response to reaching or exceeding a predetermined threshold amount of displacement, load, stress, or rotation. The aircraft support structures, systems, and methods herein utilize self-locking and self-unlocking supports (e.g. struts) for increasing or decreasing a stiffness of the support.

First claim

What is claimed is:

1. An aircraft system ( 102 ) comprising:
a rotating component ( 106 ); and
a support ( 200 ) configured to support the rotating component, wherein the support includes a locking assembly (P 1 ) that is configured to lock, automatically, an inner member ( 214 ) of the support with respect to an outer member ( 208 ) of the support for stiffening the support in response to reaching or exceeding a predetermined threshold amount of displacement, load, stress, or rotation.

2. The aircraft system according to claim 1 , wherein the rotating component ( 106 ) comprises an aircraft engine, a turbofan, a fan, a turbine, or any other unbalance source.

3. The aircraft system according to claim 1 , wherein the rotating component ( 106 ) comprises an aircraft engine, and wherein the support ( 200 ) is disposed between the aircraft engine and at least one piece of aircraft equipment.

4. The aircraft system according to claim 3 , wherein the at least one piece of aircraft equipment includes a pump, an exhaust component, a fuselage component, a refrigeration unit, an auxiliary power unit (APU), or a controller.

5. The aircraft system according to claim 1 , wherein the locking assembly (P 1 ) is disposed internally within a housing ( 210 ) that is provided at one end ( 202 ) of the support, and wherein the locking assembly comprises at least one slot ( 220 ).

6. The aircraft system according to claim 5 , wherein, in response to reaching or exceeding a predetermined threshold amount of a linear or axial displacement, a locking member ( 218 ) moves with respect to the slot ( 220 ) for locking the inner member ( 214 ) of the support with respect to the outer member ( 208 ) of the support, thereby increasing stiffness of the support.

7. The aircraft system according to claim 6 , wherein the locking member ( 218 ) comprises centering fingers which extend to a diameter of a locking member recess in the outer member ( 208 ).

8. The aircraft system according to claim 1 , further comprising an elastomeric member ( 112 ) disposed around and contacting the support.

9. The aircraft system according to claim 1 , wherein the locking assembly (P 1 ) comprises a pin ( 316 ) that is lockable within a non-linear slot ( 314 ).

10. The aircraft system according to claim 1 , wherein the support ( 200 ) comprises a strut, and wherein the strut is at least partially hollow.

11. The aircraft according to claim 1 , wherein the support ( 200 ) comprises a strut, and wherein the strut is at least partially hollow.

12. An aircraft ( 100 ) comprising:
a plurality of supports ( 200 ) attached to an aircraft system ( 102 ) or aircraft equipment ( 104 ); and
a locking assembly (P 1 ) disposed within each of the plurality of supports;
wherein at least one locking assembly associated with a first support of the plurality of supports is selectively configured in an active, locked state for increasing a stiffness of the support; and
wherein at least one other of the plurality of supports is selectively configured in an inactive, unlocked state for isolating loads.

13. The aircraft according to claim 12 , wherein the aircraft system ( 102 ) comprises an aircraft engine, and wherein the plurality of supports is attached to the aircraft engine.

14. The aircraft according to claim 13 , wherein the plurality of supports ( 200 ) is disposed between the aircraft engine and at least one piece of aircraft equipment ( 104 ).

15. The aircraft according to claim 14 , wherein the at least one piece of aircraft equipment ( 104 ) includes a pump, an exhaust component, a fuselage component, a refrigeration unit, an auxiliary power unit (APU), or a controller.

16. The aircraft according to claim 12 , wherein the locking assembly (P 1 ) comprises at least one slot ( 220 ) and a locking ring ( 218 ) configured to be retained within a portion of the at least one slot.

17. The aircraft according to claim 12 , further comprising an elastomeric member ( 112 ) disposed around and contacting the support.

18. The aircraft according to claim 12 , wherein the locking assembly comprises a pin ( 316 ) that is lockable within a non-linear slot ( 314 ).

19. A method of increasing support of an aircraft system ( 102 ) or aircraft equipment ( 104 ), the method comprising:
providing a rotating component ( 106 , 108 );
supporting the rotating component via at least one support structure ( 200 ), wherein the support structure includes a locking assembly (P 1 );
displacing the support structure ( 200 ) by a predetermined threshold amount; and
in response to displacing the support structure by the predetermined threshold amount, locking, automatically, an inner member ( 214 ) of the support with respect to an outer member ( 208 ) of the support via the locking assembly (P 1 ) for stiffening the support.

20. The method according to claim 19 , wherein providing the rotating component ( 106 , 108 ) comprises providing an aircraft engine, a turbofan, a fan, a turbine, or any other unbalance source.

21. The method according to claim 19 , wherein providing the rotating component ( 106 ) comprises providing an aircraft engine, and wherein supporting the rotating component via at least one support structure comprises providing a plurality of support structures ( 200 ) between the aircraft engine and at least one piece of aircraft equipment ( 104 ).

22. The method according to claim 19 , further comprising providing the locking assembly (P 1 ) within a housing ( 210 ) at one end of the support structure, the locking assembly comprising a locking member ( 218 , 316 ) and at least one slot ( 220 , 314 ).

23. The method according to claim 22 , further comprising elastically deforming the locking member ( 218 ) in a radial direction until the locking member is received within the slot ( 220 ) to lock the inner member ( 214 ) of the support with respect to the outer member ( 208 ) of the support.

24. The method according to claim 22 , further comprising rotating the support structure ( 200 ) to move the locking member ( 316 ) with respect to a non-linear slot ( 314 ) to lock the inner member ( 214 ) of the support with respect to the outer member ( 208 ) of the support.

Assignees

• Lord Corp

Inventors

• Bozon Benjamin
• Kursner Alexandre
• Narbon Baptiste
• Zameroski Daniel

Classifications

• B64C27/001

  Vibration damping devices · CPC title

• F16F2230/16

  used in a strut, basically rigid · CPC title

• B64D2041/002

  Mounting arrangements for auxiliary power units (APU's) · CPC title

• B64D13/00

  Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space · CPC title

• B64D41/00

  Power installations for auxiliary purposes · CPC title