While the benefits of electromechanical actuator systems (EMAS) have been well-publicized and several study and hardware development programs have been documented, little has been reported on the integration of the EMAS into the aircraft. This paper presentes the integration issues with particular emphasis in reliability, redundancy, electrical power supplies, velocity versus torque or force summing techniques, fault tolerance, fault isolation, performance after failures, and the overall implications of aerodynamic summing or control surface redundancy. In the case of transports, the incentive for control-surface redundancy is safety and the protection of passengers against failures and unexpected events that would cause severe structural and/or systems damage. In the case of military fighters, control-surface redundancy has been used to provide precise control and new control modes such as direct lift and direct side force.
A system look at electromechanical actuation for primary flight control
Zur Verwendung elektromechanischer Stellglieder bei Fugzeugen
1983
7 Seiten, 8 Bilder, 1 Tabelle, 8 Quellen
Conference paper
English
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