Computational studies of some types of operational and technological damages impact on bearing capacity of stringer panels made of composite fiber reinforced plastic

Deformable body mechanics


Аuthors

Dudarkov Y. I.*, Levchenko E. A.**, Limonin M. V.***, Shevchenko A. V.*

Central Aerohydrodynamic Institute named after N.E. Zhukovsky, TsAGI, 1, Zhukovsky str., Zhukovsky, Moscow Region, 140180, Russia

*e-mail: dzuba@tsagi.ru
**e-mail: evgeniy.levchenko@tsagi.ru
***e-mail: mikhail.limonin@tsagi.ru

Abstract

At present, one of the main tendencies while aircraft design is carbon fiber reinforced plastics implementation in the load carrying structure of the airframe. Composites allow the structure weight reduction and the aircraft performance improvement. There are examples of composite materials successful implementation in the wing structure, stabilizer, fuselage and other aircraft structural elements in civil aviation.

A serious problem on the way of effective implementation of modern polymer composite materials in the aircraft airframe load-bearing structures is their high sensitivity to in-service damages and technological defects. The issues of strength characteristics degrading in the presence of damages and defects are generally being solved on the experimental basis. Nevertheless, computational methods allow performing similar estimations.

The article presents the results of numerical studies on operational and technological damages effect on strength and stability characteristics of a stringer panel. Impact damages of skin, stringer delamination, and the stringer peeling fr om the skin were regarded as damages. The effect of the above said damages' sizes on the strength and stability characteristics of the panel was being studied. The studies were performed by the finite elements method, including its nonlinear version.

The article demonstrates the presence of the critical damage size of the skin. Prior this size the requirements to residual strength can be met. This lim it exceeding leads to irreversible process of composite destruction and exhaustion of the panel bearing capacity. Numerical studies of the panel bearing capacity with damage in the stringer allowed determining the minimum value of the panel residual strength at the damage zone size increasing. The obtained results may be handy for the composite structure residual strength estimating and forming damage criteria with regard for possible in-service and technological damages.

Keywords:

composite materials, stringer panel, residual strength, buckling, load-bearing capacity

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