Electro-hydraulic braking system for the wheels of an aircraft
US5397173A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Mar 8, 1994 |
| Grant date | Mar 14, 1995 |
| Priority date | — |
| Expiry date | Mar 8, 2014 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64C25/42
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
The invention relates to an electro-hydraulic braking system for the wheels of aircraft landing gear. The system comprises two hydraulic pressure sources each feeding a hydraulic circuit that leads to the brakes of two groups of wheels via a single braking control stage. A circuit connects either a solenoid valve electrically controlled by the control unit or else a double metering valve mechanically controlled by the brake pedals via two shuttle valves, to one inlet of each control stage. A second circuit directly connects a solenoid valve to a second inlet of each of said control stages. Each control stage includes two symmetrical internal circuits having one servo-valve per corresponding brake, which servo-valves are cross-connected by means of a respective corresponding controlled valve. In the event of one of the circuits breaking down, the servo-valves associated with the other circuit then serve, after automatic reconfiguration, also to provide braking and anti-skid control in a paired tandem mode.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.