Aircraft support structures, systems, and methods
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 (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. 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.
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.