Dynamic loading of aircraft structures Optimizing the design of structural elements

摘要

The design and certification procedures of modern aircraft structures are usually based on static loading. Even dynamic loading conditions are usually treated as quasi-static conditions. Following the current design practice, the loads envelope, by which each aircraft structural element is sized, is considered as being statically applied. The primary objective of the DAEDALOS project is to investigate the dynamic effects on the actual loads acting on the airframe in order to improve the definition of the sizing loads for structural components of civil aircraft. The current work is focused on the different ways that dynamic loads can be applied to aircraft models and the effect on the resultant stress levels at different points on the structure. The results obtained using the dynamic loading procedures are compared to the results obtained using traditional static loading methods. The reduction in the stress levels at specific aircraft elements show the potential for new methods and procedures of loads calculations, which could lead to a more realistic sizing of critical elements of the aircraft structure.