FATIGUE CRACK GROWTH ARREST CAPABILITY OF STIFFENEDSTRUCTURES

  MUNNANGI JAGADEESH REDDY,  K. N. BALAN,  RAJESH TALLURI

The aircraft fuselage shell is composed of stressed skin, longitudinal stringers, and circumferential frames. The skin is connected to the stringers and frames mostly by rivets. Due to presence of large number of rivet holes, the fuselage skin has a large number of high stress locations and these are locations of potential crack initiation. When the fuselage is pressurized and depressurized during each take-off and landing cycle of aircraft, the metal skin of fuselage expands and contracts resulting in fatigue crack initiation. In the present work, aircraft fuselage was selected as stiffened structure, Airbus A340 and Airbus A380 was selected for the process and modeling was done accordingly. The response of structure for the hoop stress and longitudinal stress developed in the fuselage due to cabin pressurization is studied by using finite element analysis technique. In addition, the tear strap can be used as bending material to increase the frame stiffness and static strength. The midway tear strap is installed by riveting. The possibility of starting a crack at a midway tear strap would be reduced if the strap were bonded to the skin without additional rivets. The tear strap will reduce the deformation and stress in the fuselage skin and the results are compared.

Keywords- Stiffened structure, cabin pressure, hoop and longitudinal stresses.

Unique Identification Number - IJEDR1401137
Page Number(s) - 752-755
Pubished in - Volume 2 | Issue 1 | March 2014
DOI (Digital Object Identifier) -   
Publisher - IJEDR (ISSN - 2321-9939)

  MUNNANGI JAGADEESH REDDY,  K. N. BALAN,  RAJESH TALLURI,   "FATIGUE CRACK GROWTH ARREST CAPABILITY OF STIFFENEDSTRUCTURES", International Journal of Engineering Development and Research (IJEDR), ISSN:2321-9939, Volume.2, Issue 1, pp.752-755, March 2014, Available at :http://www.ijedr.org/papers/IJEDR1401137.pdf