An aircraft includes an electromechanical actuator and a decoupling device. A form-fit between a drive element and a linkage point outside of the actuator element can be reversibly decoupled and recoupled. The decoupling device allows the actuator element to run freely in the event of a malfunction, which effectively prevents a jam.
Electromechanically controlled decoupling device for actuators
29.11.2016
Patent
Elektronische Ressource
Englisch
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