The increasing use of composite materials for commercial aircrafts has encouraged research activities in structural modelling, post-buckling response, determination and failure mode characterization, of the aircraft structures made of these materials. In order to predict the full potential of aircraft composite structures, is essential to develop a reliable methodology that overcomes the current failure design approach, that is based on the first ply failure criteria, aiming at predicting the effective collapse load of a composite structure taking into account the propagation and/or accumulation of initial local failures. In the last years, Progressive Failure Analysis (PFA) methodologies, based on the Finite Element Method (FEM), have been developed and employed to evaluate the ultimate load carrying capability of complex composite structures. The scope of this work is to evaluate the collapse load of stiffened CFRP wing panels in post-buckling regime, by applying PFA methodology. The panel shown in this work is stiffened with T shaped stringers, and it is representative of the upper surface of a typical regional aircraft wing box. By non-linear methodology, with progressive failure option, is possible to estimate the influence that the decrease of the panel stiffness, due to local buckling onset, has on the panel ultimate failure load. A comparison between the undamaged wing panel and the damaged one has been performed in order to evaluate, under compressive load and in post-buckling regime, the combined effect of the reduction of the panel stiffness and of the damage propagation. In detail, a stiffened CFRP panel without any hole and with holes (notched panel), has been analysed in post-buckling regime by applying PFA capability of MSC NASTRAN® code. Different hole locations have also been considered, in order to predict which panel zones, when damaged, can more affect the panel collapse load.
Numerical Investigation on the Failure Phenomena of Stiffened Composite Panels in Post-Buckling Regime with Discrete Damages / Romano, Fulvio; Di Caprio, F.; Mercurio, U.. - (2014). (Intervento presentato al convegno ICEFA VI – Sixth International Conference on Engineering Failure Analysis tenutosi a Lisbona, Portogallo nel 6-9 Luglio 2014).
Numerical Investigation on the Failure Phenomena of Stiffened Composite Panels in Post-Buckling Regime with Discrete Damages
ROMANO, FULVIO;
2014
Abstract
The increasing use of composite materials for commercial aircrafts has encouraged research activities in structural modelling, post-buckling response, determination and failure mode characterization, of the aircraft structures made of these materials. In order to predict the full potential of aircraft composite structures, is essential to develop a reliable methodology that overcomes the current failure design approach, that is based on the first ply failure criteria, aiming at predicting the effective collapse load of a composite structure taking into account the propagation and/or accumulation of initial local failures. In the last years, Progressive Failure Analysis (PFA) methodologies, based on the Finite Element Method (FEM), have been developed and employed to evaluate the ultimate load carrying capability of complex composite structures. The scope of this work is to evaluate the collapse load of stiffened CFRP wing panels in post-buckling regime, by applying PFA methodology. The panel shown in this work is stiffened with T shaped stringers, and it is representative of the upper surface of a typical regional aircraft wing box. By non-linear methodology, with progressive failure option, is possible to estimate the influence that the decrease of the panel stiffness, due to local buckling onset, has on the panel ultimate failure load. A comparison between the undamaged wing panel and the damaged one has been performed in order to evaluate, under compressive load and in post-buckling regime, the combined effect of the reduction of the panel stiffness and of the damage propagation. In detail, a stiffened CFRP panel without any hole and with holes (notched panel), has been analysed in post-buckling regime by applying PFA capability of MSC NASTRAN® code. Different hole locations have also been considered, in order to predict which panel zones, when damaged, can more affect the panel collapse load.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
