Semi-levered articulated landing gear system
US8752785B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Jun 25, 2012 |
| Grant date | Jun 17, 2014 |
| Priority date | — |
| Expiry date | Oct 24, 2032 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64C27/00
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
The landing gear system for an aircraft includes a shock strut assembly that is coupled to the airframe with a universal joint. A tire member is mounted to the shock strut assembly. The landing gear system also includes a drag brace assembly coupled to an airframe of the aircraft with a spindle, the spindle being rotatable about a spindle axis. A radius rod is rotatably coupled to the airframe of the aircraft. The radius rod and the shock strut assembly are retractable about a retraction rotation axis. Further, the spindle axis has a common intersection point with the centerline axis and the retraction rotation axis. The orientation of the spindle axis causes a translation of the tire member to have a longitudinal component during a compression of the shock strut assembly.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.