Detail publikace

Damage tolerance of high-speed machined integral panels made from 2024-T351 aluminium alloy

Originální název

Damage tolerance of high-speed machined integral panels made from 2024-T351 aluminium alloy

Anglický název

Damage tolerance of high-speed machined integral panels made from 2024-T351 aluminium alloy

Jazyk

en

Originální abstrakt

The article describes results of experimental investigation and computer modelling of crack growth in integrally stiffened test panels high-speed milled from 2024 alloy plate. Data necessary for modelling were achieved by testing of coupons on constant and flight-simulation cyclic loading. Residual stresses after machining were meas-ured using strain gauge method. Integral panels were tested under constant amplitude loading with two values of amplitude and R and also under flight-simulation cyclic loading. Results of testing are compared with calculated cracks propagation curves. The comparison shows good correlation.

Anglický abstrakt

The article describes results of experimental investigation and computer modelling of crack growth in integrally stiffened test panels high-speed milled from 2024 alloy plate. Data necessary for modelling were achieved by testing of coupons on constant and flight-simulation cyclic loading. Residual stresses after machining were meas-ured using strain gauge method. Integral panels were tested under constant amplitude loading with two values of amplitude and R and also under flight-simulation cyclic loading. Results of testing are compared with calculated cracks propagation curves. The comparison shows good correlation.

Dokumenty

BibTex


@inproceedings{BUT115272,
  author="Josef {Klement} and Petr {Augustin}",
  title="Damage tolerance of high-speed machined integral panels made from 2024-T351 aluminium alloy",
  annote="The article describes results of experimental investigation and computer modelling of crack growth in integrally stiffened test panels high-speed milled from 2024 alloy plate. Data necessary for modelling were achieved by testing of coupons on constant and flight-simulation cyclic loading. Residual stresses after machining were meas-ured using strain gauge method. Integral panels were tested under constant amplitude loading with two values of amplitude and R and also under flight-simulation cyclic loading.  Results of testing are compared with calculated cracks propagation curves.  The comparison shows good correlation.",
  address="Univerzita obrany, Brno",
  booktitle="XIII. Odborný seminář Materiály a technologie ve výrobě speciální techniky",
  chapter="115272",
  howpublished="electronic, physical medium",
  institution="Univerzita obrany, Brno",
  year="2015",
  month="may",
  pages="52--59",
  publisher="Univerzita obrany, Brno",
  type="conference paper"
}