In the last few decades, the employment of composite materials in the industrial field is widely increasing, thanks to their high mechanical properties compared to metallic alloys of the same weight. In particular, the higher benefits can be found in the aeronautical field, where the research is mainly focused in the development of lightweight structures. On the other hand, the damage behavior of composites is difficult to predict and control, leading to the development of structures heavier than needed, which reduce the intrinsic advantages, in terms of weight, of composite materials. This work is focused on the development of an optimization procedure able to find the lighter configuration of a stiffened aeronautical panel resistant to impact damages located in the bay and on the stringer foot.
An Optimization Procedure for the Design of Damage Resistant Stiffened Panels
Sellitto A.;Riccio A.
2017
Abstract
In the last few decades, the employment of composite materials in the industrial field is widely increasing, thanks to their high mechanical properties compared to metallic alloys of the same weight. In particular, the higher benefits can be found in the aeronautical field, where the research is mainly focused in the development of lightweight structures. On the other hand, the damage behavior of composites is difficult to predict and control, leading to the development of structures heavier than needed, which reduce the intrinsic advantages, in terms of weight, of composite materials. This work is focused on the development of an optimization procedure able to find the lighter configuration of a stiffened aeronautical panel resistant to impact damages located in the bay and on the stringer foot.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
