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Introduction of an Individual Aircraft Tracking Program for the Polish SU-22

REFERENCES [1] P. Reymer, A. Leski, W. Zieliński, K. Jankowski, Full Scale Fatigue Test concept of a Su-22 fighter bomber, Fatigue of Aircraft Structures , vol. 6, pp. 79-87, Warszawa 2015. [2] A. Leśniczak, P. Reymer, Warunki Techniczne WT-129/31/2014, Warunki techniczne nr WT-129/31/2014 do wykonania próby zmęczeniowej samolotu Su-22 UM3K nr 68507 , ITWL, Warszawa, 2014. [3] Ł. Kornas, Sprawozdanie SP-32/31/2016, Opracowanie i analiza wyników badań nieniszczących (etap I, II, III, IV) samolotu Su-22UM3K nr 68507 po zrealizowaniu

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Lightning Strike Protection of Aircraft Composite Structures: Analysis and Comparative Study

C., Cheron B.G., Lago F., Direct effects of lightning on aircraft structures: analysis of the thermal, electrical and mechanical constraints, Journal of Aerospace Lab , 5, AL05-09, 1-15, 2012. [8] Rupke E.J., Lightning direct effects handbook , Lightning Technologies Inc., Pittsfield, MA, 2002. [9] Gagné M., Therriault D., Lightning strike protection of composites, Progress in Aerospace Sciences , 64, 1-16, 2014. [10] Katunin A., Krukiewicz K., Herega A., Catalanotti G., Concept of a conducting composite material for lightning strike

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Enhancement of Damage Detectability in Aircraft Structures Using the Fusion of NDT Results

Conference on Computing for Sustainable Global Development (INDIACom) , New Delhi, 743–748, 2015. [5] Burt P., Adelson E., The Laplacian Pyramid as a compact image code, IEEE Transactions on Communications , 31(4), 532–540, 1983. [6] Zapłotny M., Damage identification in aircraft composite structures using information fusion methods , Master Thesis, Silesian University of Technology, Faculty of Mechanical Engineering, Gliwice, 2017. [7] Katunin A., Kostka P., Characterisation of impact damage of composite structures using wavelet-based fusion of

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A Brief Review on NDT&E Methods For Structural Aircraft Components

REFERENCES [1] Barrett J. F. and Keat N. (2004): Artifacts in CT: recognition and avoidance . RadioGraphics 24(6): pp. 1679-1691. [2] Berke M. (1996): Nondestructive Material Testing with Ultrasonics: Introduction to the Basic Principles . Krautkamer GmbH & Company. [3] Bowkett M. and Thanapalan K. (2017): Comparative analysis of failure detection methods of composites materials’ systems . Systems Science & Control Engineering 5(1): pp. 168-177. [4] Civil Aviation Authority (2010): Civil Aircraft Inspection Procedures: Part I - Basic

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Review of Aeronautical Fatigue Investigations in Poland (2013-2014)

REFERENCES [1] Brzęczek J, Gruszecki H, Pieróg L, Pietruszka J. Selected Aspects Related to Preparation of a Fatigue Test Plan of a Metallic Airframe. Fatigue of Aircraft Structures. Issue 2014. Institute of Aviation Scientific Publications, Warsaw, Poland. [2] Brzęczek J, Gruszecki H, Pieróg L, Pietruszka J. Selected Aspects Related to Preparation of Fatigue Tests of a Metallic Airframe. Fatigue of Aircraft Structures. Issue 2014. Institute of Aviation Scientific Publications, Warsaw, Poland. [3] Brzęczek J, Chodur J, Pietruszka J

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The Fatigue Life Assessment of PZL-130 Orlik Structures Based on Historical Usage Data

References United States Air Force. (1978, January). Individual Aircraft Tracking Methods for Fighter Aircraft Utilizing Counting Accelerometer Data. Ohio: Air Force Flight Dynamics Lab. Wright-Patterson Air Force Base. (AFFDL-TM-78-1-FBE) FAA. (1973). Fatigue Evaluation of Wing and Associated Structure on Small Airplanes. (AFS-120-73-2) Veldman Ray J. & Peckham C. (1982, October). Loads and Dynamics Branch Structures Division. In Handbook of Military Aircraft Design Normal

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Reconfiguration of Unmanned Aircraft Control System

REFERENCES [1] Goetzendorf-Grabowski, T., Frydrychewicz, A., Goraj, Z., et al., 2006, “MALE UAV design of an increased reliability level,” Aircraft Engineering and Aerospace Technology: An International Journal, vol. 78, No 3, pp. 226-235. [2] Lin, X., Fulton, N., and Horn, M., 2014, „Quantification of high level safety criteria for civil unmanned aircraft systems;” Proceedings of IEEE Aerospace Conference, Big Sky, March 1-8, pp. 1-13. [3] Loh, R., Bian, Y., and Roe, T., 2009, „UAVs in civil airspace: Safety requirements;” IEEE Aerospace and

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Diagnosis and Repair Technology of Damaged Elements of Casa Aircraft

References Dragan, K. & Klimaszewski, S. (2006). In-service Flaw Detection and Quantification on the MiG-29 Composite Vertical Tail Skin, ECNDT. Roach, D., Moore, D., Walkington, P. (1996). Nondestructive Inspection of Bonded Composite Doublers for Aircraft , Sandia National Labs, FAA Airworthiness Assurance NDI Validation Center. Technical Manual. (2005). Nondestructive Inspection Methods, Basic Theory , T.O. 33B-1-1, NAVAIR 01-1A-16, TM 1

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Test Flights in the Aircraft Operation Process

References [1] Ambroziak, T., About some aspects of modelling of transport systems , Scientific Papers of Warsaw University of Technology, Transport, p. 37, Publishing House of Warsaw University of Technology, Warsaw 2000. [2] Cur, K., Aircraft reliability and safety of test flights in the operation process , Doctoral dissertation, Air Force Institute of Technology, Warsaw 2015. [3] Kowaleczko, G., Krzonkalla, J., Nowakowski, M., Rymaszewski, S., Ułanowicz, L., Zgrzywa, F., In-flight tests of functional properties of the aircraft with special

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Investigations of Some Properties of Material Samples Taken from the Aircraft Withdrawn from Service

References Forman, R., G. & all (2005). Fatigue Crack Growth Database for Damage Tolerance Analysis. FAA, Waszyngton Nesterenko, G., I. Investigation of material properties degradation in operated airplanes structures. 9th Joint FAA/DoD/NASA Aging Aircraft Conference Norma PN-EN 10002-1:2004. Metale. Próba rozciągania. Część 1: Metoda badania w temperaturze otoczenia Procedura Laboratorium Badań Wytrzymałościowych Materiałów ITWL nr PB-5/31

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