Damage Tolerance Evaluation of the Wing Spar with Cracked Web

journal article - other

English

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.

damage tolerance, fatigue, residual strength

AUGUSTIN, P.

2001

1. 1. 2001

XXX

NEUVEDENO

1425-2104

RESEARCH BULLETIN

2001

11

Republic of Poland

7

11

5