Publication detail

Fractography reconstruction of time line of fatigue failure of aircraft wing bearer

AUGUSTIN, P.

Czech title

Fraktografická rekonstrukce časového průběhu únavového porušování nosníku křídla letounu

English title

Fractography reconstruction of time line of fatigue failure of aircraft wing bearer

Type

conference paper

Language

cs

Original abstract

One of the most important parts of the damage-tolerance evaluation of aircraft structure is full-scale fatigue test. This test must demonstrate that widespread fatigue damage will not occur within the design service goal. Experimental study was focused on the crack growth in a model specimen the geometry of witch corresponds to Ayres Loadmaster LM200 wig spar. Fatigue crack initiated on sharp notches in a rivet hole. In the first period, the flange plane covers the web and thus no direct monitoring of the crack growth in web was possible. Macroscopic data was completed with fractographic results. Measurement of striation spacing allowed the reconstruction of growth of four fatigue cracks (two in the web and two in the flange plate). Precision of the fractographics reconstruction results strongly depends on the volume and the quality of input information.

Czech abstract

One of the most important parts of the damage-tolerance evaluation of aircraft structure is full-scale fatigue test. This test must demonstrate that widespread fatigue damage will not occur within the design service goal. Experimental study was focused on the crack growth in a model specimen the geometry of witch corresponds to Ayres Loadmaster LM200 wig spar. Fatigue crack initiated on sharp notches in a rivet hole. In the first period, the flange plane covers the web and thus no direct monitoring of the crack growth in web was possible. Macroscopic data was completed with fractographic results. Measurement of striation spacing allowed the reconstruction of growth of four fatigue cracks (two in the web and two in the flange plate). Precision of the fractographics reconstruction results strongly depends on the volume and the quality of input information.

English abstract

One of the most important parts of the damage-tolerance evaluation of aircraft structure is full-scale fatigue test. This test must demonstrate that widespread fatigue damage will not occur within the design service goal. Experimental study was focused on the crack growth in a model specimen the geometry of witch corresponds to Ayres Loadmaster LM200 wig spar. Fatigue crack initiated on sharp notches in a rivet hole. In the first period, the flange plane covers the web and thus no direct monitoring of the crack growth in web was possible. Macroscopic data was completed with fractographic results. Measurement of striation spacing allowed the reconstruction of growth of four fatigue cracks (two in the web and two in the flange plate). Precision of the fractographics reconstruction results strongly depends on the volume and the quality of input information.

Keywords in English

fatigue life, residual static strangth, fractographic analysis

Released

12.11.2003

Publisher

Institute of Materials Research of Slovak Academy of Sciences

Location

Košice

ISBN

80-968543-2-1

Book

Fractography 2003

Pages count

8

BIBTEX


@inproceedings{BUT9187,
  author="Petr {Augustin},
  title="Fraktografická rekonstrukce časového průběhu únavového porušování nosníku křídla letounu",
  booktitle="Fractography 2003",
  year="2003",
  month="November",
  publisher="Institute of Materials Research of Slovak Academy of Sciences",
  address="Košice",
  isbn="80-968543-2-1"
}