Aircraft landing gear having axle to brake plate integration

• US 6,354,537 B1
• Filed: 08/23/2000
• Issued: 03/12/2002
• Est. Priority Date: 04/10/1996
• Status: Expired due to Term

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Ralph, Harry C.
• Primary Examiner(s): Barefoot, Galen L.
• Application Number:
  US09/644,931
• Time in Patent Office: 566 Days
• Field of Search: 244/100.R, 244/102.R, 244/103.R, 244/50, 244/103.W, 244/111, 180/140-143, 180/134, 180/144, 180/264, 180/152, 180/158, 180/163, 180/81.1, 180/81.5, 180/81.6, 280/24.1, 280/24.01, 280/97, 280/23, 280/81.5, 280/24, 280/95.1, 280/99, 280/100, 188/71.5, 188/72.5, 188/72.4, 188/71.1, 188/194, 188/329
• US Class Current: 244/102.00R
• 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
• CPC Class Codes: B64C 25/42 Arrangement or adaptation of brakes

Abstract

An aircraft landing gear brake arrangement wherein a landing gear stub axle and brake pressure plate are integrated. Each of the integrated assemblies is attached to a support fitting which pivots on the truck axle thereby causing the torque links to be unaffected by steering operations.

Claims

1. A kingpin wheel steering system for an aircraft having retractable landing gears, retractable trucks, and:

said kingpin wheel steering system for an aircraft having retractable landing gears, retractable trucks further including axle to brake plate integration.

2. The combination according to claim 1 further including a single brake compensating link to transfer the torque of two brakes simultaneously, via a truck to shock absorber pivot and another point on the shock absorber.

3. The combination according to claim 1, wherein said axle to brake plate integration enables the wheel to be steered to angles in excess of the maximum angular capacity of self-aligning bearings.

4. The combination according to claim 3 wherein said angles are ±

15 degrees.

5. The combination according to claim 1, wherein said axle to brake plate integration provides the joining of two brake pressure plate assemblies reacting torque in the same direction and further provides rotation of said brake pressure assemblies in the same plane as the wheel assembly rotation, together with the indexing of said assemblies for the purposes of aircraft takeoff, landing, retraction into aircraft, and aircraft ground maneuvering.