Spall Fault Quantification Method for Flight Control Electromechanical Actuator

Flight control electro-mechanical actuators (EMAs) are among the primary onboard systems that significantly influence reliability and safety of unmanned aerial vehicles. Recent studies have shown ball-screw element a flight EMA is subject to oscillating operating conditions may initiate rapid degradation, such as fatigue spall defects. Accordingly, detecting quantifying faults crucial for developing efficient fault prognostic remaining useful life estimation capabilities. In this study, vibration-based quantification method developed quantify mechanism an EMA. The based on identifying ball passing instants through localized surface defect vibrational jerk rather than acceleration measurement. numerically determined from conventional accelerometers using Savitzky–Golay differentiator. This was successfully tested bearings it adjusted in paper faults. experimental validation investigated set fault-seeded samples NASA’s Ames Research Center Flyable Electro-Mechanical Actuator test stand.