Two stage strut allowing low initial compression load

Patent metadata

Field	Value
Publication number	US-10384769-B2
Application number	US-201715451098-A
Country	US
Kind code	B2
Filing date	Mar 6, 2017
Priority date	Jan 6, 2017
Publication date	Aug 20, 2019
Grant date	Aug 20, 2019

Abstract

A landing detection system for a landing gear assembly of an aircraft may comprise a moveable member mechanically coupled between an aircraft wheel and a strut piston, wherein the moveable member is in communication with a strut chamber pressure of the landing gear assembly, wherein the moveable member moves relative to the strut piston in response to a first force applied to the aircraft wheel and the strut piston strokes in response to a second force applied to the aircraft wheel.

First claim

What is claimed is:

1. A landing detection system of a landing gear assembly of an aircraft, the landing detection system comprising:
a moveable member mechanically coupled between an aircraft wheel and a strut piston,
wherein the moveable member is in communication with a strut chamber pressure of the landing gear assembly;
wherein the moveable member moves relative to the strut piston in response to a first force applied to the aircraft wheel and the strut piston strokes in response to a second force applied to the aircraft wheel.

2. The landing detection system of claim 1 , wherein the second force is greater than the first force.

3. The landing detection system of claim 2 , wherein the moveable member comprises a secondary piston.

4. The landing detection system of claim 3 , wherein the secondary piston is disposed at least partially within an open end of the strut piston.

5. The landing detection system of claim 4 , wherein the secondary piston translates within the strut piston and at least partially defines a secondary chamber.

6. The landing detection system of claim 3 , wherein the moveable member is coupled to the strut piston via a first link pivotally coupled to the moveable member and a second link pivotally coupled to the strut piston.

7. The landing detection system of claim 1 , wherein the moveable member is pivotally coupled to the strut piston.

8. The landing detection system of claim 7 , wherein the moveable member is pivotally coupled to a secondary piston via a connecting link, the connecting link pivotally coupled to the secondary piston and pivotally coupled to the moveable member,
wherein the secondary piston translates relative to the strut piston in response to the moveable member pivoting.

9. A landing gear assembly for an aircraft, comprising:
a strut cylinder;
a strut piston operatively coupled to the strut cylinder;
a landing detection system comprising:
a moveable member mechanically coupled between an aircraft wheel and the strut piston,
wherein the moveable member is in communication with a strut chamber pressure of the landing gear assembly;
wherein the moveable member moves relative to the strut piston in response to a first force applied to the aircraft wheel and the strut piston strokes in response to a second force applied to the aircraft wheel.

10. The landing gear assembly of claim 9 , wherein the second force is greater than the first force.

11. The landing gear assembly of claim 10 , wherein the moveable member comprises a secondary piston.

12. The landing gear assembly of claim 11 , wherein the secondary piston is disposed at least partially within an open end of the strut piston.

13. The landing gear assembly of claim 12 , wherein the secondary piston translates within the strut piston and at least partially defines a secondary chamber.

14. The landing gear assembly of claim 13 , wherein the landing gear assembly further comprises:
a metering pin coupled to the strut piston; and
a metering pin orifice extending through the metering pin,
whereby the secondary chamber is in fluid communication with a strut chamber disposed within the strut cylinder via the metering pin orifice.

15. The landing gear assembly of claim 14 , wherein the strut chamber pressure acts on the secondary piston.

16. The landing gear assembly of claim 14 , further comprising a secondary metering pin for compression damping of the secondary piston.

17. The landing gear assembly of claim 9 , wherein the moveable member is pivotally coupled to the strut piston.

18. The landing gear assembly of claim 14 , wherein the landing detection system further comprises:
a piston head disposed within the secondary chamber and at least partially defining a recoil chamber;
a first piston orifice disposed in the piston head whereby a fluid travels from the secondary chamber to the recoil chamber in response to the secondary piston moving to a compressed position; and
a second piston orifice disposed in the piston head whereby the fluid travels from the recoil chamber to the secondary chamber in response to the secondary piston moving to an extended position.

19. The landing gear assembly of claim 18 , wherein the landing detection system further comprises:
a retaining member configured to seal the first piston orifice to prevent the fluid from flowing from the recoil chamber to the secondary chamber in response to the secondary piston moving to the extended position,
wherein a first cross-section area of the first piston orifice is greater than a second cross section area of the second piston orifice.

20. A method for detecting touchdown of an aircraft, comprising:
receiving, by a landing detection system, a first force;
translating, by a moveable member, relative to a strut piston, wherein the moveable member is mechanically coupled between an aircraft wheel and the strut piston;
wherein the moveable member is in communication with a strut chamber pressure of a landing gear assembly;
wherein the first force is less than a second force required to overcome the strut chamber pressure to stroke the strut piston relative to a strut cylinder; and
detecting that the moveable member has moved relative to the strut piston to determine that the aircraft wheel has touched down.

Assignees

• Goodrich Corp

Inventors

• Luce William E

Classifications

• B64D45/0005

  Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear · CPC title

• F16F9/3235

  of cylinders (F16F9/483 takes precedence) · CPC title

• B64C25/60 Primary

  Oleo legs · CPC title

• F16F9/3292

  Sensor arrangements · CPC title

• F16F9/3214

  of pistons (F16F9/0227 and F16F9/36 take precedence; throttling passages in or on piston body F16F9/3405) · CPC title