An actuator arrangement for an aircraft flexible control surface comprises a base and a rotary element having a joint axle articulated on the base. The actuator arrangement comprises at least two attachment struts, each having three joint axles. A first joint axle is rotatably articulated on the rotary element. A second joint axle, arranged at a first strut end, is configured to be articulated on a first control surface skin panel. A third joint axle, arranged at a second strut end, is configured to be articulated on a second control surface skin panel. The actuator arrangement also comprises at least one connecting element having one joint axle at both ends, a first joint axle being articulated on the base and a second joint axle being articulated on one of the two struts, and an actuator configured to rotate the rotary element relative to the base.
Actuator arrangement for a flexible control surface of an aircraft, control surface with actuator arrangement, and aircraft with flexible control surface
2021-12-07
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
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