IET Electric Power Applications · 2011 · 105 citations · 16 references
EngineeringAerospace EngineeringElectrical EngineeringActuatorsAircraft DesignAvionicsActuator DesignActuator SystemsDrive SystemsElectric DrivesElectromechanical SystemsSafety RequirementsAerospace ActuatorsElectric Actuation DesignElectromechanical ActuationElectromechanical ActuatorsElectromechanical Drive SystemsFunctional Safety RequirementsOperational Safety RequirementsSafety Requirements Specification
Research increasingly focuses on incorporating electromechanical actuators into future More Electric Aircraft, where safety requirements and compatibility with conventional power and control systems are critical for feasibility. The study outlines generic safety‑centric design requirements for electromechanical actuators. It emphasizes the application of fault‑tolerant electric drives and presents two prototype actuators for topology comparison. The authors compare the two prototype actuators' topologies, highlighting design differences.
Research is increasingly focusing on the incorporation of electromechanical actuators into future More Electric Aircraft. For an actuator to be feasible in a commercial aircraft, the most critical design factor is attaining the strict safety requirements. The electrical drives used in More Electric technologies must also be suitable for the conventional power supply and control arrangements of aircraft, otherwise feasibility of a new technology may be reduced. This study discusses the generic design requirements for electromechanical actuators from a safety perspective, including the application of fault-tolerant electric drives. Later, two prototype electromechanical actuators, developed by the authors are discussed, comparing the different topologies.
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