Characterization of aircraft electro hydrostatic actuator using virtual instrumentation

In Aerospace industry, implementation of Automated Test System (ATS) at the assembly and manufacturing floor improves characterization accuracy and plays a vital role to substantiate the airworthiness of the aircraft components. It is very useful in realizing high quality standards of aircraft components by virtue of meeting predefined acceptance test criteria. This paper outlines comprehensive design and development of the noise and vibration monitoring system at assembly and manufacturing floor for characterization of Electro Hydrostatic Actuator (EHA) of aircraft using progressions in virtual instrumentation. In aircraft, the flight control actuation system are powered by centralized hydraulic pumps that are driven by the aircraft engine, while the back-up system are driven by electric or ram turbines. Distributed control of electric actuators with integration of control function in Flight Control Computer (FCC) and power electronics is a cost effective approach. EHA does also play a significant role in electrical actuation system, which use distributed electric power drive in driving a hydraulic transmission system. Hence, before integrating with the primary flight control actuation systems in aircraft, EHA´s are required to be subjected to noise and vibration characterization, as part of assembly and manufacturing level testing. This method is intended at replacing the monotonous and time consuming traditional method of noise and vibration characterization of the electric actuators at assembly and manufacturing floor and to improve the reliability of the electric actuation components supplied to the aircraft manufacturers. The tests have been performed using a LabVIEW controlled virtual instrument measurement system that monitored the noise and vibration waveform with reference to the tacho signal.