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Simulation of Fatigue Crack Growth in Integrally Stiffened Panels Under the Constant Amplitude and Spectrum Loadin Cover

Simulation of Fatigue Crack Growth in Integrally Stiffened Panels Under the Constant Amplitude and Spectrum Loadin

By: Petr Augustin  
Open Access
|Sep 2010

References

  1. Nesterenko, G. I. (2000). In: Proceedings of the 22nd International Council of the Aeronautical Sciences. Comparison of Damage Tolerance of Integrally Stiffened and Riveted Structures, 27 August - 1 September 2000, Harrogate, United Kingdom: ICAS.
  2. Krueger, R. (2002). The Virtual Crack Closure Technique: History, Approach and Applications. Hampton: NASA Langley Research Center. (NASA/CR-2002-211628)
  3. NASGRO Reference Manual, Version 4.2. San Antonio: NASA Johnson Space Center, Southwest Research Institute.
  4. Lanciotti, A., Lazzeri, L., & Polese, C. (2005). Description of the Test Programme, DaToN - WD - WP 3.1 - 1.0 / DIA. Pisa: University of Pisa.
  5. Jonge, J. B. de, Hol, P. A., & van Gelder, P. A. (1994). Reanalysis of European Flight Loads Data., DOT/FAA/CT-94/21, Atlantic City: FAA, Technical Center.
  6. Rustenberg, J., Skinn, D., & Tipps, D. O. (1998). Statistical Loads Data for Boeing 737-400 Aircraft in Commercial Operations. Washington: FAA, Office of Aviation Research. (DOT/FAA/AR-98/28)
  7. Skinn, D., Tipps, D. O., & Rustenberg, J. (1998). Statistical Loads Data for MD-82/83 Aircraft in Commercial Operations. Washington: FAA, Office of Aviation Research. (DOT/FAA/AR-98/65)
  8. Tipps, D. O., Rustenberg, J., & Skinn, D. (2000). Statistical Loads Data for Boeing 767-200ER Aircraft in Commercial Operations. Washington: FAA, Office of Aviation Research. (DOT/FAA/AR-00/18)
  9. Crabill, N. L. (1989). The NASA Digital VGH Program - Exploration of Methods and Final Results, Volume III - B727 Data 1978-1980: 1765 Hours. Hampton: NASA CR-181909.
  10. Crabill, N. L. (1989). The NASA Digital VGH Program - Exploration of Methods and Final Results, Volume IV - B747 Data 1978-1980: 1689 Hours. Hampton: NASA CR-181909.
  11. de Jonge, J. B., Schütz, D., Lowak, H., & Schijve, J. (1973). A Standardized Load Sequence for Flight Simulation Tests on Transport Aircraft Wing Structures, Amsterdam, Netherlands: National Aerospace Laboratory. (NLR TR 73029U)
  12. Lanciotti, A., & Lazzeri, L. (1992). Effects of Spectrum Variations on Fatigue Crack Growth. International Journal of Fatigue, 14(5), 319-324.10.1016/0142-1123(92)90483-S
  13. Akdenitz, A. (2001). The Impact of Mandated Aging Airplane Programs on Jet Transport Airplane Scheduled Structural Inspection Programs. Aircraft Engineering and Aerospace Technology, 73(1), 4-15.10.1108/00022660110366827
  14. Abelkis, P. R. (1980). Effect of transport aircraft wing loads spectrum variation on crack growth. In D.F. Bryan & J.M. Potter (Eds.). Effect of Load Spectrum Variables on Fatigue Crack Initiation and Propagation, ASTM STP 714, (pp.143-169). Philadelphia: American Society for Testing and Materials.
DOI: https://doi.org/10.2478/v10164-010-0001-2 | Journal eISSN: 2300-7591 | Journal ISSN: 2081-7738
Language: English
Page range: 5 - 19
Published on: Sep 23, 2010
In partnership with: Paradigm Publishing Services
Publication frequency: 1 issue per year

© 2010 Petr Augustin, published by ŁUKASIEWICZ RESEARCH NETWORK – INSTITUTE OF AVIATION
This work is licensed under the Creative Commons License.

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