Shrinking system for landing gear

Patent metadata

Field	Value
Publication number	US-9481453-B2
Application number	US-201414231004-A
Country	US
Kind code	B2
Filing date	Mar 31, 2014
Priority date	Mar 31, 2014
Publication date	Nov 1, 2016
Grant date	Nov 1, 2016

Abstract

Landing gear actuator systems and methods are disclosed. A landing gear actuator system may have an actuator body, an operating apparatus, a gas pressure adjustment apparatus, and a hydraulic fluid adjustment apparatus. The gas pressure adjustment apparatus may adjust at least one gas pressure in response to the operating apparatus. The hydraulic fluid adjustment apparatus may adjust at least one hydraulic fluid volume in response to the operating apparatus. The gas pressure and the hydraulic fluid volume may adjusted inversely. An isolation valve may be installed between the gas pressure adjustment apparatus and a strut gas chamber of a landing gear. In this manner, a landing gear strut may be shrunk without inducing high pressure in the strut, and stowed for flight, and a landing gear strut may be unshrunk and isolated by the valve to protect the actuator from high pressure and reaction forces during landing.

First claim

What is claimed is:

1. A landing gear actuator system comprising:
an actuator body;
an operating apparatus comprising a hydraulic fluid drive reservoir and a piston member, wherein the piston member is translatable in response to an introduction of hydraulic fluid in the hydraulic fluid drive reservoir;
a gas pressure adjustment apparatus comprising a gas storage reservoir;
a hydraulic fluid adjustment apparatus,
wherein the gas pressure adjustment apparatus adjusts a gas volume in response to the operating apparatus,
wherein the hydraulic fluid adjustment apparatus adjusts a hydraulic fluid volume in response to the operating apparatus, and
wherein the gas volume and the hydraulic fluid volume are adjusted inversely; and

a strut gas pressure isolation valve in fluid communication with the gas pressure adjustment apparatus, wherein the strut gas pressure isolation valve is configured to isolate the gas storage reservoir from a landing gear strut gas chamber, wherein the strut gas pressure isolation valve is configured to be closed by contact between the piston member and a trigger.

2. The landing gear actuator system
according to claim 1 ,
wherein the hydraulic fluid adjustment apparatus
wherein the piston member is disposed between the hydraulic fluid storage reservoir and the gas storage reservoir such that a translation of the piston member inversely changes a volume of the hydraulic fluid storage reservoir and a volume of the gas storage reservoir with respect to one another.

3. The landing gear actuator system according to claim 2 , wherein the operating apparatus comprises a piston locking apparatus disposed within the actuator body and oriented to lock the piston member in a fixed position.

4. The landing gear actuator system according to claim 3 , wherein the piston locking apparatus comprises a forward lock and an aft lock.

5. The landing gear actuator system according to claim 2 , wherein the hydraulic fluid drive reservoir is positioned annularly about a circumferential portion of the piston member.

6. The landing gear actuator system according to claim 2 , wherein the piston member is positioned annularly about a circumferential portion of the hydraulic fluid drive reservoir wherein the hydraulic fluid drive reservoir is disposed within a cavity of the piston member.

7. The landing gear actuator system according to claim 2 , wherein the hydraulic fluid drive reservoir is positioned so that filling the hydraulic fluid drive reservoir with hydraulic fluid translates the piston member such that the volume of the hydraulic fluid storage reservoir is increased and the volume of the gas storage reservoir is decreased in response to the filling.

8. The landing gear actuator system according to claim 2 , wherein the hydraulic fluid drive reservoir is positioned so that filling the hydraulic fluid drive reservoir with hydraulic fluid translates the piston member such that the volume of the hydraulic fluid storage reservoir is decreased and the volume of the gas storage reservoir is increased in response to the filling.

9. The landing gear actuator system according to claim 2 , further comprising:
a landing gear comprising:
a landing gear strut shrink chamber adapted to at least one of shrink and unshrink the landing gear; and
the landing gear strut gas chamber adapted to provide support for the landing gear.

10. The landing gear actuator system according to claim 1 , further comprising an aircraft sequencer valve wherein the aircraft sequencer valve controls a flow of hydraulic fluid to the operating apparatus.

11. A method comprising:
actuating a piston member of an actuator system in response to an introduction of hydraulic fluid into a hydraulic fluid drive reservoir of the actuator system;
moving hydraulic fluid between a landing gear strut shrink chamber and a hydraulic fluid storage reservoir of the actuator system in response to the actuating;
moving gas between a gas storage reservoir of the actuator system and a landing gear strut gas chamber in response to the actuating;
causing a landing gear strut to at least one of shrink and unshrink in response to the actuating: and
isolating, by a strut gas pressure isolation valve, the gas storage reservoir from the landing gear strut gas chamber during unshrink of the landing gear strut by mechanically triggering the strut gas pressure isolation valve with the piston member.

12. The method according to claim 11 , further comprising engaging a piston locking apparatus of the actuator system to lock the piston member in a fixed position.

13. The method according to claim 11 , further comprising disengaging a piston locking apparatus of the actuator system to unlock the piston member from a fixed position prior to the actuating.

14. The method according to claim 11 further comprising:
disengaging a piston locking apparatus of the actuator system to unlock the piston member from a first fixed position prior to the actuating; and
engaging the piston locking apparatus to lock the piston member in a second fixed position.

Assignees

• Goodrich Corp

Inventors

• Luce William E

Classifications

• B64C25/26

  Control or locking systems therefor · CPC title

• B64C25/22 Primary

  fluid · CPC title