Health Monitoring of the Aircraft Structure during a Full Scale Fatigue Test with Use of Resistive Ladder Sensors


Article Preview

The paper presents an application of resistive ladder sensors (or resistive crack gages) for health monitoring of an aircraft structure. An experiment was conducted during a Full Scale Fatigue Test (FSFT) of PZL 130 ORLIK TC II turbo-prop military trainer. The sensor can be successively used to detect and quantify fatigue cracks. It is a parametric transducer, similar to foil strain gages. Differences in shape of the measuring grid can be noticed. Principle of operation, sensor’s characteristics as well as block diagram of measurement system is presented in the paper. Also examples, both laboratory and FSFT data are delivered to prove surface crack detection capabilities. Simultaneously with new data collection, some investigation is carried out, connected with customize hardware elaboration, signal processing and structure-sensor integration method, what is briefly described.



Solid State Phenomena (Volumes 220-221)

Edited by:

Algirdas V. Valiulis, Olegas Černašėjus and Vadim Mokšin




A. Kurnyta et al., "Health Monitoring of the Aircraft Structure during a Full Scale Fatigue Test with Use of Resistive Ladder Sensors", Solid State Phenomena, Vols. 220-221, pp. 349-354, 2015

Online since:

January 2015




* - Corresponding Author

[1] G. Deng, T. Nakanishi, Practical methods for crack length measurement and fatigue crack initiation detection using ion-sputtered film and crack growth characteristics in glass and ceramics, in C. Sikalidis (Ed. ). Advances in Ceramics – Characterization, Raw Materials, Processing, Properties, Degradation and Healing, Chapter 6, August, 2011. ISBN: 978-953-307-504-4.


[2] G. Deng, K. Nasu, T.R. Redda, T. Nakanishi, fatigue crack length measurement method with an ion sputtered film, Fracture of Nano an Engineering Materials and Structures (2006) 437–445.


[3] A. Kurnyta, Application of resistive ladder sensor for detection and quantification of fatigue cracks in aircraft structure, Monthly Scientific and Technical Journal PAR – Pomiary Automatyka Robotyka 2 (192) (February 2013) 558–563. ISSN 1427-9126.


[4] H. Speckmann, R. Henrich, Structural healh monitoring (SHM) – overview on technologies under development, in: Proc. of the World Conference on NDT, Montreal, Canada, (2004).

[5] M. Panitz, D.C. Hope, T. Sato, C.D. Harley, C. Christopoulos, P. Sewell, J.F. Dawson, A.C. Marvin, K.G. Watkins, G. Dearden, W.J. Crowther, The opportunities and challenges associated with wireless interconnects in aircraft, in: Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering (224) (2010).


[6] Vishay Micro-Measurement, Special Purpose Sensors – Crack Propagation Patterns, Document no. 11521, May 09 2003. Information on http: /www. vishay. com.

[7] Crossbow Technology, Inc., eKo Pro Series Data Sheet, San Jose, California, (2009).

[8] Information on http: /www. tenmex. pl.