Defect-caused alteration of a composite unit modal parameters

Research paper by Georgy M. Makaryants, Dmitry S. Molchanov, Artur I. Safin

Indexed on: 14 Oct '16Published on: 13 Oct '16Published in: Measurement


This paper presents research on diagnostic parameters for monitoring conditions of a light aircraft engine blade made of composite materials (CM) in flight. This study covers the modal parameters investigation of the blades in the frequency range of 30 to 60 Hz. Using the Doppler Effect the vibration response between the used blades and a new blade was compared. The used blades demonstrated a fourfold increase in amplitude of resonant vibration in the first bending mode. The amplitude growth of the first bending mode resonant vibration can be used as a diagnostic sign of emerging defects. The ease of amplitude and frequency analysis of a blade resonant vibration in flight conditions will allow researchers to develop an express-control device for technical condition analysis of CM blades while in air.

Figure 10.1016/j.measurement.2016.10.011.0.jpg
Figure 10.1016/j.measurement.2016.10.011.1.jpg
Figure 10.1016/j.measurement.2016.10.011.2.jpg
Figure 10.1016/j.measurement.2016.10.011.3.jpg
Figure 10.1016/j.measurement.2016.10.011.4.jpg
Figure 10.1016/j.measurement.2016.10.011.5.jpg
Figure 10.1016/j.measurement.2016.10.011.6.jpg
Figure 10.1016/j.measurement.2016.10.011.7.jpg
Figure 10.1016/j.measurement.2016.10.011.8.jpg