Approximate computational model for shear loaded stiffened composite panels

Abstract

The stability behavior is critical for thin‐walled composite structures. This type of structures is for example employed in aircraft, spacecraft and marine vessels, where weight is an important factor in the design. For stiffened panels of, e.g. a fuselage structure, shear is a relevant load case. A new approximate computational model for the local buckling behavior of omega‐stringer‐stiffened panels under shear loading is presented that is based on energy methods. To assess the quality of the derived solution, the results of suitable parameter studies are discussed. In comparison to numerical methods, the new model reduces the computational effort necessary for the preliminary design of omega‐stringer‐stiffened composite panels. Thus, it contributes to increase the performance of structures and consequently reduces the weight of the mentioned applications.