Aircraft landing gear, aircraft, and related methods

Patent metadata

Field	Value
Publication number	US-10669017-B2
Application number	US-201715445836-A
Country	US
Kind code	B2
Filing date	Feb 28, 2017
Priority date	Feb 28, 2017
Publication date	Jun 2, 2020
Grant date	Jun 2, 2020

Abstract

A strut assembly for an aircraft landing gear structure is transitioned between an extended configuration, corresponding to the aircraft being off the ground, and a retracted configuration, in which the strut assembly is shortened along its longitudinal axis with respect to the extended configuration, for stowage during flight. The strut assembly includes an upper bulkhead supported by an upper tubular housing, and a lower tubular housing configured to be longitudinally translated with respect to the upper tubular housing. To transition the strut assembly to the retracted configuration, translation of the upper bulkhead with respect to the upper tubular housing mechanically causes translation of the lower tubular housing to a retracted position, such that the overall length of the strut assembly is reduced. The strut assembly may be an oleo strut assembly.

First claim

The invention claimed is:

1. A strut assembly for an aircraft landing gear structure, wherein the strut assembly is configured to transition between a compressed configuration, in which the strut assembly has a compressed length when the strut assembly is weighted by an aircraft, an extended configuration in which the strut assembly has an extended length when the strut assembly is not weighted by the aircraft, and a retracted configuration for stowage of the aircraft landing gear structure within the aircraft and in which the strut assembly has a retracted length, wherein the compressed length and the retracted length are less than the extended length, wherein the compressed length, the retracted length, and the extended length are defined along a longitudinal axis of the strut assembly, and wherein the strut assembly comprises:
an upper tubular housing;
an upper bulkhead supported by the upper tubular housing and configured to be selectively and longitudinally translated with respect to the upper tubular housing, between a lower position and an upper position, wherein the upper bulkhead is in the lower position when the strut assembly is in the compressed configuration and when the strut assembly is in the extended configuration, and wherein the upper bulkhead is in the upper position when the strut assembly is in the retracted configuration;
a lower tubular housing operatively coupled to the upper tubular housing and configured to be longitudinally translated relative to the upper tubular housing;
a lower bulkhead fixed with respect to and supported by the lower tubular housing, wherein the lower tubular housing is configured to be longitudinally translated between a compressed position when the strut assembly is in the compressed configuration and an extended position when the strut assembly is in the extended configuration, wherein the lower tubular housing is further configured to be selectively and longitudinally translated to a retracted position when the strut assembly is in the retracted configuration, and wherein the strut assembly is configured such that translation of the upper bulkhead to the upper position mechanically causes translation of the lower tubular housing to the retracted position; and
a locking link assembly comprising an upper link and a lower link pivotally coupled to one another, wherein the lower link is pivotally coupled to the upper bulkhead, wherein the locking link assembly is configured to transition between a lengthened configuration and a shortened configuration, wherein the strut assembly is configured such that the locking link assembly is in the lengthened configuration when the strut assembly is in the compressed configuration and when the strut assembly is in the extended configuration, wherein the strut assembly is configured such that the locking link assembly is in the shortened configuration when the strut assembly is in the retracted configuration, and wherein the strut assembly is configured such that transitioning the locking link assembly from the lengthened configuration to the shortened configuration causes longitudinal translation of the upper bulkhead to the upper position.

2. The strut assembly according to claim 1 , further comprising a third tubular member extending longitudinally from a first end region to a second end region, wherein the first end region is coupled to the upper bulkhead such that the third tubular member is substantially fixed with respect to the upper bulkhead, wherein the second end region of the third tubular member is positioned within the lower tubular housing.

3. The strut assembly according to claim 2 , further comprising a third tubular member stop fixed within the second end region of the third tubular member.

4. The strut assembly according to claim 3 , wherein the lower tubular housing comprises an inner tube stop configured to limit longitudinal translation of the lower tubular housing with respect to the upper tubular housing, and wherein the third tubular member stop engages the inner tube stop when the strut assembly is in the extended configuration.

5. The strut assembly according to claim 4 , wherein the strut assembly is configured such that translation of the upper bulkhead to the upper position mechanically causes longitudinal translation of the third tubular member while the third tubular member stop contacts and causes longitudinal translation of the inner tube stop of the lower tubular housing, thereby causing translation of the lower tubular housing to the retracted position.

6. The strut assembly according to claim 1 , wherein, in the lengthened configuration, the upper link and the lower link are locked in an over-center position, wherein, in the shortened configuration, the upper link and the lower link are not held over-center, and wherein the locking link assembly is configured to withstand forces of the weight of the aircraft transferred to the locking link assembly via the lower tubular housing, the lower bulkhead, and the upper bulkhead, such that it remains in the lengthened configuration when the strut assembly is in the compressed configuration.

7. The strut assembly according to claim 1 , further comprising a shrink actuator coupled to the locking link assembly and configured to selectively transition the locking link assembly between the lengthened configuration and the shortened configuration, and wherein the shrink actuator is further configured to retract the aircraft landing gear structure into the aircraft.

8. The strut assembly according to claim 1 , wherein a pressure chamber is defined between the lower bulkhead and the upper bulkhead and within the upper tubular housing and the lower tubular housing.

9. The strut assembly according to claim 8 , wherein the upper bulkhead forms a dynamic gas seal within the upper tubular housing, thereby substantially preventing contents of the pressure chamber from exiting the pressure chamber at the upper bulkhead.

10. The strut assembly according to claim 9 , wherein the strut assembly is a gas-oil strut assembly having a strut gas and a strut fluid within the pressure chamber, wherein the strut assembly has an extended pressure within the pressure chamber when the strut assembly is in the extended configuration and in the retracted configuration, wherein the strut assembly has a compressed pressure within the pressure chamber when the strut assembly is in the compressed configuration, wherein the compressed pressure is greater than the extended pressure, wherein the pressure chamber has a first internal volume when the strut assembly is in the extended configuration and in the retracted configuration, wherein the pressure chamber has a second internal volume when the strut assembly is in the compressed configuration, and wherein the first internal volume is greater than the second internal volume due to compression of the strut gas.

11. An aircraft landing gear structure, comprising:
the strut assembly according to claim 1 ; and
at least one wheel assembly operably coupled to the lower tubular housing of the strut assembly.

12. An aircraft landing gear structure, comprising:
the strut assembly according to claim 7 ; and
at least one wheel assembly operably coupled to the lower tubular housing of the strut assembly.

13. An aircraft, comprising:
a fuselage;
a wing assembly operatively coupled to the fuselage, wherein one or more of the fuselage and the wing assembly define one or more wheel wells, landing gear storage bays, or wheel storage bays; and
one or more of the strut assembly according to claim 1 , operatively coupled to one or more of the fuselage and the wing assembly, wherein the one or more stru

Assignees

• Boeing Co

Inventors

• Simpson Mark Nicholas
• Mellor Mitchell Loren Ray
• Cusworth James E
• Cottet Justin

Classifications

• B64C2025/008

  Comprising means for modifying their length, e.g. for kneeling, for jumping, or for leveling the aircraft · CPC title

• B64C25/10 Primary

  retractable, foldable, or the like · CPC title

• B64C25/22

  fluid · CPC title

• B64C2025/125

  into the fuselage, e.g. main landing gear pivotally retracting into or extending out of the fuselage · CPC title

• B64C25/60

  Oleo legs · CPC title