Single axle, semi-levered landing gear with shortening mechanism

Patent metadata

Field	Value
Publication number	US-10384767-B2
Application number	US-201715415346-A
Country	US
Kind code	B2
Filing date	Jan 25, 2017
Priority date	Jan 25, 2017
Publication date	Aug 20, 2019
Grant date	Aug 20, 2019

Abstract

A semi-levered landing gear including a shock strut configured for coupling to an airframe of an aircraft, a truck lever being rotatably coupled to the shock strut, a tension link assembly having a tension link assembly first end, a tension link assembly second end and at least one tension link assembly rotation axis, the tension link assembly first end being coupled to the shock strut, and the tension link assembly second end being coupled to the truck lever, and a positioning mechanism configured for coupling to one or more of the airframe and the shock strut and being coupled to the tension link assembly, wherein the tension link assembly is configured to rotate the truck lever about the truck pivot axis of rotation between a truck lever extended position and a truck lever stowed position.

First claim

The invention claimed is:

1. A semi-levered landing gear comprising:
a shock strut having an inner cylinder and an outer cylinder, the shock strut configured for coupling to an airframe of an aircraft;
a truck lever having a truck lever first end and a truck lever second end longitudinally spaced from the truck lever first end, the truck lever being rotatably coupled to the shock strut about a truck pivot axis of rotation that is disposed between the truck lever first end and the truck lever second end;
a tension link assembly having a tension link assembly first end, a tension link assembly second end, and at least one tension link assembly rotation axis disposed between the tension link assembly first end and the tension link assembly second end, the tension link assembly first end being coupled to the shock strut outer cylinder, and the tension link assembly second end being coupled to the truck lever second end, wherein the tension link assembly comprises:
an over-center link having an over-center link first end and an over-center link second end longitudinally spaced from the over-center link first end, the over-center link first end defining the tension link assembly first end and being rotatably coupled to the shock strut about an over-center pivot axis; and
a truck link having a truck link first end and a truck link second end longitudinally spaced from the truck link first end, the truck link first end being rotatably coupled to the over-center link second end about the tension link assembly rotation axis and the truck link second end defining the tension link assembly second end and being rotatably coupled to the truck lever second end; and

a positioning mechanism being configured for coupling to one or more of the airframe and the shock strut and being coupled to the tension link assembly proximate the tension link assembly first end;
wherein the tension link assembly is configured to rotate the truck lever about the truck pivot axis of rotation between a truck lever extended position and a truck lever stowed position.

2. The semi-levered landing gear of claim 1 , wherein the shock strut is substantially uncompressed with the truck lever at the truck lever extended position and with the truck lever at the truck lever stowed position.

3. The semi-levered landing gear of claim 1 , wherein the tension link assembly is configured so that the truck lever rotates about the truck pivot axis of rotation during compression of the shock strut.

4. The semi-levered landing gear of claim 1 , wherein the positioning mechanism comprises:
a connecting link having a connecting link first end and a connecting link second end, the connecting link first end being configured for coupling to one or more of the airframe and the shock strut;
a first pivot link having a first end and a second end longitudinally spaced from the first end, the first end of the first pivot link being rotatably coupled to the shock strut; and
a second pivot link having a first end and a second end longitudinally spaced from the first end, the first end of the second pivot link being rotatably coupled to the second end of the first pivot link;
wherein the connecting link second end is coupled to at least one of proximate the second end of the first pivot link and proximate the first end of the second pivot link.

5. The semi-levered landing gear of claim 4 , wherein the second end of the second pivot link is rotatably coupled to the over-center link proximate the over-center link second end so that movement of the connecting link causes rotation of the truck link first end about the over-center pivot axis.

6. The semi-levered landing gear of claim 1 , further comprising:
a retraction mechanism coupled to the airframe;
wherein the shock strut includes a trunnion, the trunnion being rotatably coupled to the airframe at a trunnion axis of rotation so that the shock strut rotates about the trunnion axis of rotation between a shock strut stowed position and a shock strut extended position relative to the airframe; and
wherein the positioning mechanism is coupled to the retraction mechanism so that rotation of the truck lever about the truck pivot axis of rotation, between the truck lever extended position and the truck lever stowed position, is mechanically slaved to rotation of the shock strut about the trunnion axis of rotation.

7. The semi-levered landing gear of claim 1 , wherein the truck lever includes but one wheel axis.

8. The semi-levered landing gear of claim 1 , wherein the truck lever comprises a monolithic member.

9. An aircraft comprising:
an airframe; and
a semi-levered landing gear including:
a shock strut coupled to the airframe;
a truck lever having a truck lever first end and a truck lever second end longitudinally spaced from the truck lever first end, the truck lever being rotatably coupled to the shock strut about a truck pivot axis of rotation that is disposed between the truck lever first end and the tuck lever second end;
a tension link assembly having a tension link assembly first end, a tension link assembly second end and at least one tension link assembly rotation axis disposed between the tension link assembly first end and the tension link assembly second end, the tension link assembly first end coupled to the shock strut, and the tension link assembly second end being coupled to the truck lever second end, wherein the tension link assembly comprises:
an over-center link having an over-center link first end and an over-center link second end longitudinally spaced from the over-center link first end, the over-center link first end defining the tension link assembly first end and being rotatably coupled to the shock strut about an over-center pivot axis; and
a truck link having a truck link first end and a truck link second end longitudinally spaced from the truck link first end, the truck link first end being rotatably coupled to the over-center link second end about the tension link assembly rotation axis and the truck link second end defining the tension link assembly second end and being rotatably coupled to the truck lever second end;

a positioning mechanism coupled to one or more of the airframe and the shock strut and being coupled to the tension link assembly proximate the tension link assembly first end;
wherein the tension link assembly is configured to rotate the truck lever about the truck pivot axis of rotation between a truck lever extended position and a truck lever stowed position.

10. The aircraft of claim 9 , wherein rotation of the truck lever to the truck lever extended position provides the aircraft with a greater angle of attack at takeoff compared to an aircraft having a same length and but one wheel axis on a shock strut.

11. The aircraft of claim 9 , wherein rotation of the truck lever about the truck pivot axis of rotation provides the aircraft with a same static ground height compared to an aircraft having a same length shock strut and but one wheel axis on the shock strut.

12. The aircraft of claim 9 , wherein the shock strut is substantially uncompressed with the truck lever at the truck lever extended position and with the truck lever at the truck lever stowed position.

13. The aircraft of claim 9 , wherein the tension link assembly is configured so that the truck lever rotates about the truck pivot axis of rotation during compression of the shock strut.

14. A semi-levered landing gear comprising:
a shock strut coupled to an airframe of an aircraft about a trunnion axis of rotation;
a retraction mechanism coupled to the airframe;
a truck lever having a truck lever first end and a truck lever sec

Assignees

• Boeing Co

Inventors

• Cottet Justin D
• Mellor Mitchell
• Drake Michael L
• Sonnenburg George

Classifications

• B64C25/12 Primary

  sideways · CPC title

• B64C2025/125

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

• B64C25/34

  wheeled type, e.g. multi-wheeled bogies · CPC title

• B64C25/10

  retractable, foldable, or the like · CPC title

• B64C25/60

  Oleo legs · CPC title