Acoustic Emission Monitor for Drive System Coupling Crack Detection

The objective of this Phase II program is to develop a prototype system to detect and evaluate cracking signals in real time under operational conditions from diaphragm couplings in aircraft, in particular those found in the V-22 helicopter. The Phase II project includes extensive data acquisition runs concentrated on the large 9” diaphragms couplings specifically from hanger bearing #1 on the V-22’s rotating wing. These activities will be performed at Bell Helicopter test cell 202 spin rig, and in close cooperation with Bell’s personnel. Data will be acquired using both damaged and undamaged diaphragm couplings. These data will be used to develop a signal classifier capable of discriminating between signals from undamaged and damaged couplings. In parallel with the data acquisition activities, PAC will carry out the development of the prototype system software, in which the classifier will be incorporated, and PAC’s Engineering department will modify existing PAC hardware to satisfy the requirements for the prototype system. The complete AE cracking detection prototype system, hardware and classifying software, will be validated on Bell’s spin rig or, if available, during a V-22 helicopter ground run. The complete Phase II program will be completed within a 24 months time frame.