Review of monolithic composite laminate and stiffened structures in aeronautic applications

This paper analyses laminated stiffened composite structures in aeronautic applications, covering many key subjects. Since the certification of these structures is based on the test pyramid methodology, several aspects will be addressed, mainly: static sizing and the obtention of allowable values, damage tolerance, post-buckling, large cuts and structural testing. Secondly, the main problems associated with the manufacturing of aeronautical composite structures will be discussed. Finally, a historical presentation of the main milestones in the introduction of fibrous materials will be given, based on the successive appearance of boron, glass and carbon fibres, with the help of a selection of examples. A detailed chronology of the pioneering introduction of carbon fibres into civil aeronautics by European industry will also be provided. Recent researches, trends and innovations will be discussed. Finally, conclusions and perspectives on this wide subject will be proposed.