Contact Versus Non-Contact Measurement of a Helicopter Main Rotor Composite Blade

• Published in: 9th International Conference Vol. 1253; no. 1; pp. 352 - 360
• Main Authors: Luczak, Marcin, Dziedziech, Kajetan, Vivolo, Marianna, Desmet, Wim, Peeters, Bart, Van Der Auweraer, Herman
• Format: Journal Article
• Language: English
• Published: United States 01.01.2010
• Subjects: ACCELEROMETERS; Accuracy; Aging aircraft; AIRCRAFT; Blades; Cables; COMPOSITE MATERIALS; Consistency; Contact; Damage detection; Distortion; Dynamic mechanical properties; Dynamics; Error analysis; Error detection; ERRORS; EXCITATION SYSTEMS; Harmonic excitation; HELICOPTERS; Instrumentation; Inversions; Lightweight; MATERIALS; MATERIALS SCIENCE; Mathematical models; MEASURING INSTRUMENTS; Model updating; Mounting; Parameter identification; PRESSURE MEASUREMENT; Quality assessment; RANDOMNESS; ROTORS; SENSORS; SIGNALS; Substructuring; Vibration meters; Vibrometers; Weight reduction
• ISBN: 9780735408029; 0735408025
• ISSN: 0094-243X; 1551-7616
• DOI: 10.1063/1.3455477

The dynamic characterization of lightweight structures is particularly complex as the impact of the weight of sensors and instrumentation (cables, mounting of exciters...) can distort the results. Varying mass loading or constraint effects between partial measurements may determine several errors on the final conclusions. Frequency shifts can lead to erroneous interpretations of the dynamics parameters. Typically these errors remain limited to a few percent. Inconsistent data sets however can result in major processing errors, with all related consequences towards applications based on the consistency assumption, such as global modal parameter identification, model-based damage detection and FRF-based matrix inversion in substructuring, load identification and transfer path analysis [1]. This paper addresses the subject of accuracy in the context of the measurement of the dynamic properties of a particular lightweight structure. It presents a comprehensive comparative study between the use of accelerometer, laser vibrometer (scanning LDV) and PU-probe (acoustic particle velocity and pressure) measurements to measure the structural responses, with as final aim the comparison of modal model quality assessment. The object of the investigation is a composite material blade from the main rotor of a helicopter. The presented results are part of an extensive test campaign performed with application of SIMO, MIMO, random and harmonic excitation, and the use of the mentioned contact and non-contact measurement techniques. The advantages and disadvantages of the applied instrumentation are discussed. Presented are real-life measurement problems related to the different set up conditions. Finally an analysis of estimated models is made in view of assessing the applicability of the various measurement approaches for successful fault detection based on modal parameters observation as well as in uncertain non-deterministic numerical model updating.