Wheel Dynamometer System For Aircraft Landing Gear Testing

Abstract The aim of this study was to design, develop and apply practically a wheel dynamometer for aircraft landing gear testing. The dynamometer system was designed to measure two force components acting along the longitudinal and vertical axes of the wheel as well as and three moments acting around the longitudinal, transversal and vertical axes. It consists of a sensor unit that is embedded in the wheel hub, a modified rim with a tyre as well as a data acquisition and transfer system that enables the measured signals to transfer wirelessly to a portable computer or another device (smartphone, tablet). The sensor unit was developed based on strain gage measurement technology. The prototype system was calibrated in a stationary test stand, then installed on a PZL 104 Wilga 35A for airfield tests. Primary test measurements were performed with the aircraft taxiing at “walking man” speed and proved system’s performance. Certification for ground and flight tests of airplanes has been considered for the presented dynamometer system.