Very large aircraft landing gear having eight wheel truck

• US 6,173,920 B1
• Filed: 03/20/1997
• Issued: 01/16/2001
• Est. Priority Date: 12/08/1994
• Status: Expired due to Fees

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Meneghetti, Michael J.
• Primary Examiner(s): Cuchlinski, Jr., William A.
• Assistant Examiner(s): Beaulieu, Yonel
• Application Number:
  US08/821,369
• Time in Patent Office: 1,398 Days
• Field of Search: 244/100 R, 244/102 R, 244/102 A, 244/102.55, 244/104 R, 244/104 FP, 244/104 CS
• US Class Current: 244/100.00R
• CPC Class Codes: B64C 2025/345 Multi-wheel bogies having one or more steering axes
• CPC Class Codes: B64C 25/34 wheeled type, e.g. multi-wheeled bogies

Abstract

Very large aircraft landing gear using single mounted eight wheel bogie on dual shock struts. A primary or main two-stage shock absorber and a semi-articulating secondary or auxiliary single-stage shock absorber, each of which are mounted using the second and third axles as pivot joints in a four axle, eight wheel truck beam.

Claims

1. A landing gear for an aircraft, comprising:

an eight wheel truck having four axles, all axles being substantially in line with each other and each carrying a pair of wheels with the forwardmost and rearwardmost wheels being steerable; and

a combination of a two-stage main shock absorber and a single-stage auxiliary shock absorber for mounting said wheel truck to a landing gear support structure on the aircraft, said main and auxiliary shock absorbers being pivotally and separately mounted to said support structure and likewise adjacent the second and third axles respectively of said wheel truck, said combination providing truck pitch control for all conditions of aircraft handling including suitable positioning prior to landing and for retraction into the wheel well.

2. The landing gear according to claim 1, wherein said main and auxiliary shock absorbers are pivotally and separately mounted on a rotating structural trunnion member such that with the inclusion of the truck, these elements comprise a 4-bar linkage such that their kinematic action permits the truck assembly to pitch up and down during aircraft ground, landing and take-off conditions.

3. The landing gear of claim 2, wherein said kinematic action permits the truck assembly to remain parallel or nearly so relative to the aircraft longitudinal axis such that aerodynamic frontal area is kept to a minimum during the extension and retraction phases of landing gear deployment.

4. The landing gear of claim 2, wherein said kinematic action permits the landing gear to be stowed in a reduced volume over that of two, separate, in-line with respect to each other, four-wheel trucks, each with single shock absorber, landing gears.

5. The landing gear of claim 1, wherein said main and auxiliary shock absorbers act to sustain pivoting loads on the truck during aircraft ground maneuvers or aircraft yaw loads at the initial contact of either forwardmost or rearwardmost wheels during landing;

pivoting loads being sustained through reactions at the upper and lower bearings of each shock absorber; and

in turn, through reactions at the attachment points of each shock absorber to a structural trunnion member or to an aircraft support structure.

6. A landing gear for an aircraft, comprising:

an eight wheel truck having four axles, all axles being substantially in line with each other and each carrying a pair of wheels with the forwardmost and rearwardmost wheels being steerable in some manner;

in combination;

a single stage main shock absorber having an internal sliding tube and a single-stage auxiliary shock absorber for mounting said wheel truck to a landing gear support structure on an aircraft, said main and auxiliary shock absorbers being pivotably and separately mounted to said support structure and likewise to or near the second and third axles respectively of said wheel truck, said combination providing truck pitch control for all conditions of aircraft handling including suitable positioning prior to landing and for retraction into the wheel well;

said main and auxiliary shock absorbers pivotally and separately mounted on a rotating structural trunnion member and including said eight wheel truck for providing a 4-bar linkage and kinematic action; and

,

said internal sliding tube being adjustable during various phases of the aircraft handling.