Detail publikace

Damage Tolerance Evaluation of the Wing Spar with Cracked Web

AUGUSTIN, P.

Anglický název

Damage Tolerance Evaluation of the Wing Spar with Cracked Web

Typ

Článek recenzovaný mimo WoS a Scopus

Jazyk

en

Originální abstrakt

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.

Klíčová slova anglicky

damage tolerance, fatigue, residual strength

Vydáno

2001-01-01

Nakladatel

XXX

Místo

NEUVEDENO

ISSN

1425-2104

Časopis

RESEARCH BULLETIN

Ročník

2001

Číslo

11

Strany od–do

7–

Počet stran

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",
  pages="5",
  issn="1425-2104"
}