Prognostics and Health Management Guidelines for Electro-Mechanical Actuators
AIR8012
Reducing the power consumption—and hence, the fuel burn—is a major target for the next generation of aircraft, and electrical actuation is perceived as a technological area able to provide power saving. Electrical actuation can in fact contribute to the reduction of the non-propulsive power because electro-mechanical actuators, when compared to the conventional hydraulic actuators, rely on a form of power subjected to lower distribution losses and in general can lead to a weight savings at the aircraft level if the required power remains under a break-over point. Moreover, electro-mechanical actuators (EMAs) present higher reliability and maintainability with a lower life-cycle cost.
Two critical issues with electrically powered actuation are the temperature rise in the electric motor windings and in the power electronics, and the sensitivity to certain single point of failures that can lead to mechanical seizures, that has so far thwarted the use of EMAs for safety-critical applications. In order to address the issue of a possible actuator seizure, many research and development activities have been performed to identify ways of making an electro-mechanical actuator jam-free or jam-tolerant, since this would allow more flexibility in defining the overall architecture of the flight control system. Although interesting and ingenious design solutions have been proposed, they all have so far resulted in complex mechanical designs that on one hand allow the actuator to operate after a jam of an internal component, but on the other hand bring about increased weight, volume, and cost, and a reliability reduction due to the much larger number of parts.
With primary flight control actuators being some of the more safety-critical components of an aircraft, an undetected actuator failure can lead to serious consequences. Furthermore, failures that are not flight safety critical can still have negative consequences ranging from flight disruptions to unscheduled and costly maintenance.
The development of an effective and reliable PHM system for EMAs is thus seen as a possible way to contribute to the acceptance of EMAs as primary flight control actuators in commercial aircraft, for an effective PHM system will feature appropriate diagnostic functions to detect anomalous behavior, and prognostic capabilities indicating when an incipient fault develops and estimating how, under continuing usage, the fault will eventually become a failure. Providing EMAs with a PHM capability will entail positive results in different areas:
Progressively improve the EMA robustness; PHM algorithms can initially provide indication of the onset of a fault, while more sophisticated reasoning functions can then assess the remaining useful life and contribute to the safety of flight.
Minimize the unscheduled maintenance events, thereby increasing the EMA availability.
Facilitate maintenance operations and troubleshooting.
Simplify the supply chain.
It is important to note that a more extensive use of EMAs facilitated by PHM algorithms must be associated to all design provisions necessary to attain mandatory safety requirements.
Rationale:
Electro-mechanical actuators (EMAs) are used in different aerospace applications performing functions with different degrees of criticality, and a trend exists to progressively replace hydraulic actuators with EMAs for most flight-critical applications. This carries along a growing interest in providing EMAs with a prognostics and health management (PHM) system allowing effective diagnostics, prognostics, and recovery actions. Early fault detection is needed in flight-critical applications to allow enough time for contingency management in order to avoid the occurrence of safety-critical situations.
The development of an EMA PHM system is a challenging task since EMAs are complex systems made up by electronic, electrical, and mechanical subsystems, and are typically under-instrumented. This implies that a fault in an EMA component may have effects on other parts of the actuator, which makes it difficult to successfully identify and isolate the fault, especially when only a limited number of signals is available.
The purpose of this document is to provide the guidelines of the technological approach for developing a PHM system for EMAs with particular reference to their possible use as primary flight control actuators. It provides a basic description of the physics of the most common degradation processes, a reliability assessment, and a discussion on the signals, with the associated data processing, required to build up an effective health monitoring system.
Related Topics:
Failure modes and effects analysis
Fatigue
Materials properties
Bearings
Data acquisition and handling
Control systems
Electronic equipment
Safety critical systems
Embedded software
Electrical systems
Also known as: SAE AIR 8012
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