Publication detail

Damage Tolerance Evaluation of the Wing Spar with Cracked Web

AUGUSTIN, P.

Czech title

Damage tolerance analýza nosníku křídla s trhlinou ve stojině

English title

Damage Tolerance Evaluation of the Wing Spar with Cracked Web

Type

journal article - other

Language

en

Original abstract

Damage tolerance evaluation is required for the aircraft life determination according to FAR Part 25 regulations. This concept is based on the crack propagation and residual strength determination. The damage tolerance evaluation of an aircraft structure results in the inspection program ensuring that fatigue initiated cracks would involve no failure prior to the detection. The inspection program must be developed for each principal structure element in the aircraft. Solutions to this problem usually found in the literature deal mainly with the components subjected to tension, such as stiffened panels or lugs. This paper presents the testing program and FEM analysis focused on the wing spar with cracks in the web. It is characteristic for fatigue cracks in the web that they usually change their growth direction due to a combined stress state. Measured crack shape was used for constructing of a FEM model of the spar, the residual strength was calculated and compared with the experimental results.

Czech abstract

Článek se zabývá programem zkoušek a MKP analýzou zbytkové pevnosti nosníku křídla s trhlinou ve stojině.

English abstract

Damage tolerance evaluation is required for the aircraft life determination according to FAR Part 25 regulations. This concept is based on the crack propagation and residual strength determination. The damage tolerance evaluation of an aircraft structure results in the inspection program ensuring that fatigue initiated cracks would involve no failure prior to the detection. The inspection program must be developed for each principal structure element in the aircraft. Solutions to this problem usually found in the literature deal mainly with the components subjected to tension, such as stiffened panels or lugs. This paper presents the testing program and FEM analysis focused on the wing spar with cracks in the web. It is characteristic for fatigue cracks in the web that they usually change their growth direction due to a combined stress state. Measured crack shape was used for constructing of a FEM model of the spar, the residual strength was calculated and compared with the experimental results.

Keywords in Czech

konstrukce s přípustným poškozením, únava, zbytková pevnost

Keywords in English

damage tolerance, fatigue, residual strength

RIV year

2001

Released

01.01.2001

Publisher

XXX

Location

NEUVEDENO

ISSN

1425-2104

Journal

RESEARCH BULLETIN

Volume

2001

Number

11

Pages count

5

BIBTEX


@article{BUT40511,
  author="Petr {Augustin},
  title="Damage Tolerance Evaluation of the Wing Spar with Cracked Web",
  journal="RESEARCH BULLETIN",
  year="2001",
  volume="2001",
  number="11",
  month="January",
  publisher="XXX",
  address="NEUVEDENO",
  issn="1425-2104"
}