Electro/hydraulic system for a 2 door thrust reverser
US5819527A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Dec 5, 1995 |
| Grant date | Oct 13, 1998 |
| Priority date | — |
| Expiry date | Dec 5, 2015 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K1/76
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A thrust reverser for a turbo-fan engine having an improved system for security against inflight inadvertent deployment. The reverser has two pivoting doors for use on engines mounted on an aircraft rear fuselage or under the aircraft wing. The pivoting doors are positioned forward of an aft ring structure that is essentially the nacelle exit nozzle in forward thrust mode. The pivoting doors are actuated by a hydraulic actuator and are locked and unlocked by hook locks operated by an electric solenoid on one side of the door and a small hydraulic actuator on the opposite side. The two locking systems are completely independent, thereby assuring that an inadvertent in-flight deployment will not occur as a result from failure, faulty command or maintenance malpractice.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.