Electromechanical actuator system with anti-jamming features
US4575027A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | May 16, 1983 |
| Grant date | Mar 11, 1986 |
| Priority date | — |
| Expiry date | May 16, 2003 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T74/20213
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
An actuator system for controlling the position of an aerodynamic control surface of an aircraft is disclosed. The actuator system (10) comprises a rotary actuator (12) rotatably mounted to the aircraft structure (20) with the actuator having an output member (22) adapted to be coupled to the control surface. A latch assembly (37) is provided which is mounted to the structure which releasably engages the actuator. Preferably, the latch assembly (37) comprises a grooved flange (38) mounted on the actuator (12) and a solenoid (47) mounted to the aircraft structure which is adapted to move a locking pin (44) from a first position in engagement with the grooved flange (38) to a second position out of engagement with the groove. In a second embodiment, a second rotary actuator (114) is mounted to the aircraft structure and is adapted to rotate the actuator (81) upon its failure and after the latch assembly is activated. In a third embodiment a second rotary actuator (164) is coupled to the input shaft (160) of the actuator (150) and after the latch assembly is activated rotation of the actuator (150) is accomplished by the second rotary actuator (164) via the input shaft. In addition, s…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.