Nondestructive Evaluation of Composite Material Damage Using Vibration Reciprocity Measurements

2012 ◽  
Vol 134 (4) ◽  
Author(s):  
Brandon R. Zwink

Maintenance personnel in the U.S. military are interested in developing methods of damage detection for composite materials that are field expedient and less dependent on the operator’s experience than the current methods. A vibration-based method was developed for detecting damage in composite materials based on a measurement of the nonlinear forced response that damaged materials are assumed to exhibit. A damage feature was extracted for a structural component by quantifying the degree to which the reciprocity between two input-output structural paths fail due to the nonlinearities associated with damage. A dynamic nonlinear theoretical model was used to develop a better understanding of why reciprocity fails for networks of nonlinear components. Experimental results were obtained from carbon fiber composite specimens subjected to various levels of damage. It was determined that reciprocity measurements were capable of identifying damage due to impact energies of 10.8 N·m; however, the method was not capable of discerning damage that was not directly beneath the sensor locations. The levels of damage that could be consistently detected using the new methodology could be discovered through a close visual inspection. In comparison to currently employed methods of damage detection, the proposed methodology is less subjective but also less sensitive to damage. More development work will be required to propose this technology as a replacement for current methods such as ultrasound and tap testing.

2014 ◽  
Vol 556-562 ◽  
pp. 3056-3059
Author(s):  
Chao Sun ◽  
En Sheng Dong ◽  
Yong Heng Li ◽  
Bing Zhu

The application of advanced composite materials in airplane is becoming more and more. Along with the increase of its service time, it may be abnormal. It needs to take an anomaly detection. The electrical impedance spectroscopy (EIS) is applied to the anomaly detection of composite material components in airplane. A uniplanar sensor with double-electrode and two carbon fiber composite samples are made, an experiment circuit is designed. In order to verify the effectiveness of the experimental circuit, the EIS of the Randles unit model circuit is measured, as well as the two composite material samples using the dual-electrode measurement method. The picture of EIS is drawn in Matlab and comparison and analysis are carried out. The preliminary experimental results indicate that the anomalies can be seen by measuring the EIS of the composite materials. It is feasible for the EIS to be applied in the anomaly detection of the composite materials in airplane.


2011 ◽  
Author(s):  
Jennifer A. VanderVennet ◽  
Terrisa Duenas ◽  
Yuris Dzenis ◽  
Chad T. Peterson ◽  
Charles E. Bakis ◽  
...  

2015 ◽  
Vol 39 (4) ◽  
pp. 829-843 ◽  
Author(s):  
Pu-Woei Chen ◽  
Kuan-Jung Chen

This study analyzes the crashworthiness of a light aircraft that is constructed from composite materials. The finite element method is employed to conduct dynamic impact simulations on carbon fiber composite fuselages. The results show that the safe impact speed for an aluminum alloy cockpit crashed at a 30° impact angle is 9.59 m/s, but a cockpit made of composite material can withstand a speed greater than 18.05 m/s. The safe impact angle for an aluminum alloy cockpit is 16.56°, but that for a composite cockpit is 84.9°. The safety crash zone for a composite material cockpit is 160% greater than that for an aluminum alloy cockpit.


Sensors ◽  
2020 ◽  
Vol 20 (13) ◽  
pp. 3732
Author(s):  
Jochen Moll ◽  
Matthias Schmidt ◽  
Johannes Käsgen ◽  
Jörg Mehldau ◽  
Marcel Bücker ◽  
...  

This paper presents a proof of concept for simultaneous load and structural health monitoring of a hybrid carbon fiber rudder stock sample consisting of carbon fiber composite and metallic parts in order to demonstrate smart sensors in the context of maritime systems. Therefore, a strain gauge is used to assess bending loads during quasi-static laboratory testing. In addition, six piezoelectric transducers are placed around the circumference of the tubular structure for damage detection based on the electro-mechanical impedance (EMI) method. A damage indicator has been defined that exploits the real and imaginary parts of the admittance for the detection of pin failure in the rudder stock. In particular, higher frequencies in the EMI spectrum contain valuable information about damage. Finally, the information about damage and load are merged in a cluster analysis enabling damage detection under load.


Author(s):  
J. S. Rao ◽  
Kiran Sheelavant ◽  
Balasaheb Bombale

A procedure is outlined to determine the composite lay-out of a given baseline metallic fan blades. The vane material Titanium is replaced by Carbon Fiber composite materials. For the operating speed the baseline maximum strain in the vane is maintained and weight reduction is taken as the objective function. Three phases of optimization are suggested. In the first phase free size optimization is performed on the composite blades to determine the required topology. A layout of composites is then proposed. In the second phase based on free optimization results gauge optimization setup is illustrated for determining the thicknesses. In the third phase Ply-stacking optimization can be performed. By using composite materials substantial savings in the weight can be achieved without affecting the performance of engine blade.


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