Non-destructive evaluation of rescue and patrol unmanned aerial vehicle

• Autorzy: Pawluczy-Majka J.

Identyfikatory

DOI

10.5604/12314005.1130497

• Języki publikacji: EN

Abstrakty

EN

With the growing intensity of civil usage of the UAV, one of the most important problems is safety. It consists of operational safe use of the UAV in the common air area and reliability of the aerial vehicle construction. Each flying object is subjected to external loads, which influence on it in flight and on the ground. The external loads are mainly caused by aerodynamic, weight and inertia influence, ground reaction force and the power unit [1]. That is why during service, UAV structures are prone to many mechanical and environmental conditions that can damage to composite structures in the form of delamination, fiber breakage, and matrix cracking. Monitoring the level and type of damage to a composite structure is vital to determining the component’s structural integrity and preventing the failure of the structure during flight [2]. Non-destructive testing which has been used so far to identify defects in the aircraft structure made from metallic materials has a quite limited application in the case of composite structures. With the growing use of composites in the aviation industry, a necessity appears to work out a method allowing identification of technological defects and damages appeared in the process of the UAV’s operation. The answer to the appearing demand could be, for instance, the active thermography technique used for the thin wall test of the skin elements of the UAV. The obtained research results bring closer the problem of selection of the quick, well-fitted non-destructive testing method depending on the kind of the diagnosed construction.

Słowa kluczowe

EN

UAV; NDT diagnostics; active thermography

• Wydawca: Łukasiewicz Research Network - Institute of Aviation ; European Science Society of Powertrain and Transport KONES Poland ; Wydawnictwo Instytutu Technicznego Wojsk Lotniczych
• Czasopismo: Journal of KONES
• Rocznik: 2014
• Tom: Vol. 21, No. 4
• Strony: 411--416
• Opis fizyczny: Bibliogr. 6 poz., rys.

Twórcy

autor

Pawluczy-Majka J.

• Rzeszow University of Technology Department of Aircrafts and Aircraft Engines Powstancow Warszawy Street 12, 35-959 Rzeszow, Poland tel.:[phone], fax: [phone]

Bibliografia

• [1] Gundlach, J., Designing Unmanned Aircraft Systems: A Comprehensive Approach, AIAA, Inc., Reston Virginia 2012.
• [2] Baker, A., Dutton, S., Kelly, D., Composite Materials For Aircraft Structures, AIAA, Inc., Reston 2004.
• [3] Majka, A., Flight Loads of Mini UAV, Solid State Phenomena, T. 198, pp. 194-199, 2013.
• [4] Bendada, A., Maillet, D., Degiovanni, A., Non destructive transient thermal evaluation of laminated composites: discrimination between delaminations thickness variations and multidelaminations.
• [5] Vavilov, V. P., Nondestructive testing Handbook Vol. 5 Thermal/ Infrared Testing, Spectra,Moscow 2009.
• [6] Niu, M., Airframe structural design. Practical Design Information and Data on Aircraft Structures, Lockheed Aeronautical Systems Company, Burbank 1988.