Assessment of Sensor Technologies for Aircraft SHM Systems

• Autorzy: Kurnyta A. , Dragan K. , Dziendzikowski M.

Identyfikatory

DOI

10.2478/fas-2013-0005

• Języki publikacji: EN

Abstrakty

EN

SHM is a monitoring system which uses sensors, actuators and data transmission, acquisition and analysis, permanently integrated with the inspected object. The objective of SHM is to detect, localize, identify and predict development of fatigue fractures, increasing safety and reliability. This paper presents an assessment of sensor technologies used in aircraft SHM system. Due to the fact that most of these measurement methods are relatively new and still under development the present appraisal focuses on a number of parameters with reference to each method, including a sensor’s installation issues, reliability, power consumption, sensor infrastructure, sensitivity and cost and availability. The work is predominantly focused on the assessment of permanently bonded sensors, such as foil strain gages, Comparative Vacuum Monitoring (CVM), Piezo sensors (PZT), Eddy-Current Transducers (ECT). Finally, all these methods are briefly discussed.

Słowa kluczowe

EN

SHM; sensor; fatigue crack; crack detection methods; usage monitoring

• Wydawca: Wydawnictwa Naukowe Sieci Badawczej Łukasiewicz - Instytutu Lotnictwa
• Czasopismo: Fatigue of Aircraft Structures
• Rocznik: 2013
• Tom: Iss. 5
• Strony: 53--59
• Opis fizyczny: Bibliogr. 7 poz., rys.,

Twórcy

autor

Kurnyta A.

• Air Force Institute of Technology, Warsaw, Poland

autor

Dragan K.

• Air Force Institute of Technology, Warsaw, Poland

autor

Dziendzikowski M.

• Air Force Institute of Technology, Warsaw, Poland

Bibliografia

• 1. S. Maley, J. Plets, N. D. Phan US Navy Roadmap to Structural Health and Usage Monitoring - The Present and Future, American Helicopter Society 63rd Annual Forum, Virginia Beach, VA;
• 2. G. Bartelds, Aircraft structural health monitoring, prospects for smart solutions from a european viewpoint, International Workshop on Structural Health Monitring, Stanford University, (USA), September 18 to 20, 1997;
• 3. H. Speckmann, R. Henrich, Structural healh monitoring (SHM) - overview on technologies under development, Proc. of the World Conference on NDT, Montreal - Canada, 2004, http://www.ndt.net/article/wcndt2004/pdf/aerospace/ 563_henrich.pdf;
• 4. D. Roach, Real time crack detection using mountable comparative vacuum monitoring sensors, Smart Structures and Systems, Vol. 5, No. 4, 317-328 (2009);
• 5. C. Boller, Aircraft structural health management" Smart materials and structures, vol. 10, pp. 432-440, 2001;
• 6. S. Klimaszewski, K. Dragan, Realizacja zadań związanych z Etapem II - Badania Doświadczalne Projektu Badawczego Własnego pt: Opracowanie koncepcji systemu monitorowania stanu technicznego łopat wirników nośnych śmigłowców z wykorzystaniem metod NDT i SHM. Wykonanie badań metodami SHM i NDT - ETAP II. Analiza uzyskanych wyników z badań. Opracowanie finalnego sprawozdania z badań, Sprawozdanie ITWL Nr 126/31/2010, Warszawa 2010;
• 7. B. P. C. Rao: Practical eddy current testing, Alpha Science International Ltd., Oxford, 2007, ISBN 978-1-84265-299-2.