Minimisation of Failure Transients in a Fail-Safe Electro-Mechanical Actuator Employed for the Flap Movables of a High-Speed Helicopter-Plane

The work deals with the model-based characterization of the failure transients of a fail-safe rotary EMA developed by Umbragroup (Italy) for the flap movables of the RACER helicopter-plane by Airbus Helicopters (France). Since the reference application requires quasi-static position-tracking with hi...

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Bibliographic Details
Published in:Aerospace 2022-09, Vol.9 (9), p.527
Main Authors: Di Rito, Gianpietro, Kovel, Romain, Nardeschi, Marco, Borgarelli, Nicola, Luciano, Benedetto
Format: Article
Language:English
Subjects:
Actuators
Aircraft
Algorithms
Analysis
Aviation
Circuits
Control theory
Design
electro-mechanical actuators
Failure
Fault detection
Feedback control
Feedback loops
First principles
flight control
Flying-machines
health monitoring
Helicopters
modelling
Nested loops
Parameter identification
Power electronics
Simulation
Simulation methods
Stiffness
Temperature effects
testing
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Summary:The work deals with the model-based characterization of the failure transients of a fail-safe rotary EMA developed by Umbragroup (Italy) for the flap movables of the RACER helicopter-plane by Airbus Helicopters (France). Since the reference application requires quasi-static position-tracking with high disturbance-rejection capability, the attention is focused on control hardover faults which determine an actuator runaway from the commanded setpoint. To perform the study, a high-fidelity nonlinear model of the EMA is developed from physical first principles and the main features of health-monitoring and closed-loop control functions (integrating the conventional nested loops architecture with a deformation feedback loop enhancing the actuator stiffness) are presented. The EMA model is then validated with experiments by identifying its parameters by ad-hoc tests. Simulation results are finally proposed to characterize the failure transients in worst case scenarios by highlighting the importance of using a specifically designed back-electromotive damper circuitry into the EMA power electronics to limit the position deviation after the fault detection.
ISSN:2226-4310
2226-4310
DOI:10.3390/aerospace9090527