The trend toward the 'more electric aircraft' , i.e. the replacement of hydraulic and pneumatic actuators with electrically driven ones, has been ongoing for many years. However, the introduction of a new technology like electromechanical actuators (EMA) into a safety-critical system as primary flight controls is challenging. In this paper, aspects of a hybrid actuation system, where EAM and electrohydraulic servoactuators operate on the same control surface, are presented. The challenges and potentials of this configuration are evaluated. For this purpose, the operational aspects are compared to the conventional systems. Besides fault tolerance aspects, the power consumption characteristics are of importance for the discussion. A major challenge of hybrid actuation lies in the control of the actuators, which are focused on. While in conventional electrohydraulic systems an active/passive and an active/active mode are available, an additional mode for hybrid actuation, the active/no-load mode is proposed. It combines the advantages of both conventional operating modes which is better power consumption characteristics as in active/passive mode and low failure transients as in active/active mode. This is achieved by active control of both the EHSA (electrohydraulic servoactuator) and the EMA (elektromechanical actuator) such that only the EHSA carries the external forces. Hybrid actuation as outlined in this paper offers a promising step toward the 'All Electric Aircraft'.
Redundant hybrid actuation concept for primary flight controls
Redundantes hybrides Aktorkonzept für die primäre Flugregelung
2005
13 Seiten, 7 Bilder, 2 Tabellen, 5 Quellen
Conference paper
English
Electro-Mechanical Actuation of Primary Flight Controls
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