Shock absorber for aircraft landing gear
US5310139A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Jan 5, 1993 |
| Grant date | May 10, 1994 |
| Priority date | — |
| Expiry date | Jan 5, 2013 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64C2025/008
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
The invention relates to a shock absorber of the type comprising a cylinder and a sliding rod, together with a moving disk that defines a bottom hydraulic chamber that communicates via a diaphragm with a top hydraulic fluid chamber that is adjacent to a pressurized gas chamber formed in the top of the cylinder. According to the invention, a self-contained linear actuator is disposed coaxially inside the sliding rod, being interposed between the moving disk and a lower abutment secured to said sliding rod, independent control means being also provided to control the linear actuator, such that when said means are engaged they enable the landing gear to be extended when the aircraft is stationary on the ground.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.