Ing. Petr Augustin, Ph.D.
E-mail:   augustin@fme.vutbr.cz  Dept.:   Institute of Aerospace Engineering Dept. of Aerospace Technology Position:   Assistant Professor

Supervised courses:

• Fatigue of Aircraft Structures (OUZ-A)
• Fatigue of Aircraft Structures (OUZ)

Publications:

• AUGUSTIN, P.:
  Simulation of Fatigue Crack Propagation in the Wing Main Spar Flange ,
  13th Research and Education in Aircraft Design Conference, pp.66-75, ISBN 978-80-214-5696-9, (2018)
  conference paper
  akce: 13th Research and Education in Aircraft Design Conference, Brno, 07.11.2018-09.11.2018
• AUGUSTIN, P.:
  Fatigue life analysis of aging aircraft based on previous service usage,
  New Trends in Civil Aviation, pp.113-118, ISBN 978-0-8153-7602-6, (2018), CRC Press/Balkema
  conference paper
  akce: New Trends in Civil Aviation 2017, Department of Air Transport, Czech Technical University in Prague, 07.12.2017-08.12.2017
• JETELA, V.; KLEMENT, J.; AUGUSTIN, P.:
  Possibility for improving damage tolerance of integral structure by high strength bonded straps,
  14th Seminar "Materials and technologies in Special Technics Production 2017", pp.29-33, ISBN 978-80-7231-420-1, (2017), University of Defence
  conference paper
  akce: Materiály a technologie ve výrobě speciální techniky, Brno, 01.06.2017-01.06.2017
• KATRŇÁK, T.; AUGUSTIN, P.; VLČEK, D.:
  Fatigue analyses and optimization of L 410 NG aircraft,
  Letecký zpravodaj, Vol.2016, (2016), No.2, pp.39-41, ISSN 1211-877X, ALV - Association of the Aerospace Manufacturers
  journal article - other
• J. KLEMENT, P. AUGUSTIN:
  Damage tolerance of high-speed machined integral panels made from 2024-T351 aluminium alloy,
  XIII. Odborný seminář Materiály a technologie ve výrobě speciální techniky, pp.52-59, ISBN 978-80-7231-999-2, (2015), Univerzita obrany, Brno
  conference paper
  akce: XIII. odborný seminář Materiály a technologie ve výrobě speciální techniky, Brno, 20.05.2015-20.05.2015
• KUNZ, J.; KOVÁŘÍK, O.; LAUSCHMANN, H.; SIEGL, J.; AUGUSTIN, P.:
  Fractographic reconstitution of fatigue crack growth in integrally stiffened panels,
  Procedia Engineering, Vol.2, (2010), No.1, pp.1711-1720, ISSN 1877-7058, Elsevier Ltd.
  journal article - other
  akce: 10th International Fatigue Conference, Praha, 06.06.2010-11.06.2010
• KLEMENT, J.; AUGUSTIN, P.; URÍK, T.:
  Damage tolerance behaviour of fibre metal laminate CARE,
  Letecký zpravodaj, Vol.2010, (2010), No.1, pp.56-59, ISSN 1211-877X, Asociace leteckých výrobců
  journal article - other
• AUGUSTIN, P.:
  Simulation of Fatigue Crack Growth in Integrally Stiffened Panels under the Constant Amplitude and Spectrum Loading,
  Fatigue of Aircraft Structures, pp.5-19, ISBN 978-83-929922-1-9, (2009), Institute of Aviation
  conference paper
  akce: 2nd Conference Fatigue of Aircraft Structures 2009, Varšava, 15.01.2009-16.01.2009
• AUGUSTIN, P.:
  Simulation of Fatigue Crack Growth in the High Speed Machined Panel under the Constant Amplitude and Spectrum Loading,
  Proceedings of the 25th Symposium of the International Committee on Aeronautical Fatigue, pp.1005-1018, ISBN 978-90-481-2745-0, (2009), Springer Science+Business Media
  conference paper
  akce: ICAF 2009, Bridging the Gap between Theory and Operational Practice, Rotterdam, 27.05.2009-29.05.2009
• JURAČKA, J.; AUGUSTIN, P.; KOULA, V.:
  Zkoušky únavového chování segmentu křídla,
  Transfer, Vol.2009, (2009), No.9, pp.33-45, ISSN 1801-9315, VZLÚ Praha
  journal article - other
• LAUSCHMANN, H.; AUGUSTIN, P.; KOVÁŘÍK, O.; ŠIŠKA, F.:
  The Reference Crack Growth Rate: An Unifying Concept for Fatigue under Variable Amplitude Loading,
  Proceedings of the Second International Conference on Material and Component Performance under Variable Amplitude Loading, pp.271-280, ISBN 978-3-00-027049-9, (2009), Deutscher Verband für Materialforschung und -prüfung
  conference paper
  akce: Second International Conference on Material and Component Performance under Variable Amplitude Loading, Darmstadt, 23.03.2009-26.06.2009
• AUGUSTIN, P.:
  Analysis of Fatigue Crack Growth under the Spectrum Loading,
  Letecký zpravodaj, Vol.2007, (2007), No.3, pp.18-21, ISSN 1211-877X
  journal article - other
• AUGUSTIN, P.:
  Prediction of Crack Growth in Integrally Stiffened Panels,
  Letecký zpravodaj, Vol.2007, (2007), No.2, pp.5-7, ISSN 1211-877X
  journal article - other
• AUGUSTIN, P., PLHAL, M., ŠPLÍCHAL, J.:
  Fatigue Testing and Analysis of VUT 100 Aircraft Landing Gear,
  Letecký zpravodaj, Vol.2006, (2006), No.3, pp.34-36, ISSN 1211-877X, VZLÚ, a.s.
  journal article - other
• AUGUSTIN, P.; PLHAL, M.; ŠPLÍCHAL, J.:
  FEM Based Fatigue Life Analysis of Landing Gear,
  Letecký zpravodaj, Vol.2005, (2005), No.3, pp.6-8, ISSN 1211-877X, VZLÚ, a.s.
  journal article - other
• KUNZ, J.; SIEGL, J.; NEDBAL, I.; AUGUSTIN, P.; PÍŠTĚK, A.:
  Application of Quantitative Microfractography in Damage-Tolerance and Fatigue Evaluation of Wing Spar,
  ICAS 2004, pp.564-573, ISBN 0-9533991-6-8, (2004)
  conference paper
  akce: ICAS 2004, Yokohama, 29.09.2004
• AUGUSTIN, P.:
  Fatigue and Crack Propagation Calculations of Wing Spar Structure,
  Letecký zpravodaj, Vol.2004, (2004), No.3, pp.12-15, ISSN 1211-877X
  journal article - other
• BUJNOCH, L.; AUGUSTIN, P.; LAPČÍK, L.:
  Railway Track Mats Based On Recycled Shredded Rubber,
  Materiálové inžinierstvo, Vol.VIII, (2001), No.3/2001, pp.47-52, ISSN 1335-0803, Strojnícka fakulta, Žilinská universita v Žilině
  journal article - other
• BUJNOCH, L., AUGUSTIN, P., LAPČÍK, L.:
  Railway track mats based on recycled shredded rubber,
  TRANSCOM 2001 - Proceedings Section 5, pp.155-158, ISBN 80-7100-850-8, (2001), University of Žilina
  conference paper
  akce: Transcom 2001, Žilina, 25.06.2001-27.06.2001
• Píštěk Antonín, Lapčík Lubomír, Augustin Petr, Bujnoch Luděk:
  Measurement of the dynamic stiffness of recycled rubber based railway track mats according to the DB-TL 918.071 standard

List of publications at Portal BUT

Abstracts of most important papers:

• AUGUSTIN, P.:
  Fatigue life analysis of aging aircraft based on previous service usage,
  New Trends in Civil Aviation, pp.113-118, ISBN 978-0-8153-7602-6, (2018), CRC Press/Balkema
  conference paper
  akce: New Trends in Civil Aviation 2017, Department of Air Transport, Czech Technical University in Prague, 07.12.2017-08.12.2017
  This paper describes the approach for the fatigue evaluation of Aero Ae 45 S aircraft (registration OK-KGB). An analysis was carried out to define the individual fatigue life of this airplane based on its service history. By applying a newly developed flight loading spectrum and airframe full-scale fatigue test results, the original safe-life limit was proposed to be extended from 3000 to 4600 flight hours, which was approved by CAA. The limit extension was supported by eddy current and penetrant inspection programs for the primary fatigue critical area of the lower wing main spar attachment lugs made of L-ROL steel. Inspection intervals were determined using damage tolerance analysis techniques, fracture mechanics, and fatigue crack growth code NASGRO.
• JETELA, V.; KLEMENT, J.; AUGUSTIN, P.:
  Possibility for improving damage tolerance of integral structure by high strength bonded straps,
  14th Seminar "Materials and technologies in Special Technics Production 2017", pp.29-33, ISBN 978-80-7231-420-1, (2017), University of Defence
  conference paper
  akce: Materiály a technologie ve výrobě speciální techniky, Brno, 01.06.2017-01.06.2017
  Integral stringer panels can attain weight reduction in a primary aircraft structures, but does not contain physical barriers for fatigue crack growth. One of the promising technique for prolonging fatigue life are bonded crack retarders made of materials with high stiffness. Experimental study was done on two specimens with different geometries. The straps consisted of high strength corrosion resistant steel AISI 301 was adhesively bonded to an aluminium alloy 2024-T351 Center-Cracked Tension (CCT) specimens fabricated by a high-speed machining process to promote fatigue crack growth retardation. Specimens were tested at constant amplitude load. The study concludes that the fatigue crack growth life can be significantly improved.
• KUNZ, J.; KOVÁŘÍK, O.; LAUSCHMANN, H.; SIEGL, J.; AUGUSTIN, P.:
  Fractographic reconstitution of fatigue crack growth in integrally stiffened panels,
  Procedia Engineering, Vol.2, (2010), No.1, pp.1711-1720, ISSN 1877-7058, Elsevier Ltd.
  journal article - other
  akce: 10th International Fatigue Conference, Praha, 06.06.2010-11.06.2010
  A research program was focused on design and experimental verification of fracture marking of integrally stiffened panels during the fatigue tests under flight-by-flight spectrum loading and testing the effectiveness of various fractographic methods. The panels represent complex testing models of aircraft wing parts. Three kinds of cyclic loading were used: constant amplitude loading, flight-by-flight type spectrum loading without marking and flight-by-flight spectrum with marking. Different methods were applied for fractographic reconstitution of fatigue crack growth: a) measurement of striation spacing, b) identification of beach marks, c) image textural analysis of SEM images of fatigue fracture surfaces (textural fractography) aimed at morphological features oriented in the direction of crack growth. The obtained crack growth curves enable the study of the influence of loading spectrum on crack growth kinetics and comparison of the different fractographic methods.
• AUGUSTIN, P.:
  Simulation of Fatigue Crack Growth in the High Speed Machined Panel under the Constant Amplitude and Spectrum Loading,
  Proceedings of the 25th Symposium of the International Committee on Aeronautical Fatigue, pp.1005-1018, ISBN 978-90-481-2745-0, (2009), Springer Science+Business Media
  conference paper
  akce: ICAF 2009, Bridging the Gap between Theory and Operational Practice, Rotterdam, 27.05.2009-29.05.2009
  The paper describes methodology of numerical simulation of fatigue crack growth under the constant amplitude and spectrum loading and its application on integrally stiffened panels made of 2024-T351 aluminium alloy using high speed cutting technique. Presented approach is based on the calculation of stress intensity factor function from finite element results, subsequent crack growth analyses were performed in NASGRO. For predictions of crack growth under the spectrum loading a sequence representing service loading of the transport airplane wing was prepared. Three crack growth models were applied: non-interaction, Willenborg and Strip Yield. Relatively large experimental program comprising both the constant amplitude and spectrum tests on integral panels and CCT specimens was undertaken in order to acquire crack growth rate data and enable verification of simulations.
• LAUSCHMANN, H.; AUGUSTIN, P.; KOVÁŘÍK, O.; ŠIŠKA, F.:
  The Reference Crack Growth Rate: An Unifying Concept for Fatigue under Variable Amplitude Loading,
  Proceedings of the Second International Conference on Material and Component Performance under Variable Amplitude Loading, pp.271-280, ISBN 978-3-00-027049-9, (2009), Deutscher Verband für Materialforschung und -prüfung
  conference paper
  akce: Second International Conference on Material and Component Performance under Variable Amplitude Loading, Darmstadt, 23.03.2009-26.06.2009
  A new concept of reference crack growth rate (RCGR) was proposed to cover all fatigue cracks regardless of the type of loading. The general idea has got a practical scope within textural fractography. The first suggestion of RCGR was based on cycle-by-cycle crack growth description. However, RCGR may be estimated directly from images of fracture surfaces. Both approaches are demonstrated in application - fractographical reconstitution of crack growth process in aluminium alloy. Two pairs of CCT specimen and panel were loaded by constant cycle and a flight spectrum, respectively. Common morphologic features of all fracture surfaces were found that are closely related to RCGR.