Development of a Kinematics Model for the Assessment of Global Crash Scenarios of a Composite Transport Aircraft Fuselage

Abstract

The presented thesis develops in a first part a preliminary crash design tool for transport aircraft fuselage structures considering a standard section. A modelling approach is developed on the basis of the explicit finite element method which enables an efficient assessment of the structural behaviour. The developed modelling approach represents a combination of linear-elastic material behaviour and the description of structural failure by macro modelling. The thesis investigates typical failure mechanisms of a fuselage structure caused by crash related loads and derives appropriate macro models. In a second part, the thesis develops a design process using the new modelling approach. After an assessment of natural crash kinematics, a crash design is developed on the basis of a statically pre-sized fuselage structure. The development of the design process also comprises experimental approaches for the investigation of crash absorber concepts.