An apparatus is provided for analysis of a leading edge rib of a fixed leading edge section of an aircraft wing. The apparatus may identify geometric or inertial properties of a plurality of stiffeners (402) of the rib in which respective stiffeners are represented by a collection of geometry within a solid model of the rib, and perform an analysis to predict a failure rate of the leading edge rib under an external load. From the failure rate, the apparatus may determine a structural integrity of the leading edge rib under the external load. Identifying the properties may include, extracting a section cut of the geometry that corresponds to and has one or more properties of the respective stiffener, and identifying the properties of the cross-section and thereby the respective stiffener based on a correlation of the cross-section to a generic profile of a plurality of different cross-sections.
MODELING AND ANALYSIS OF LEADING EDGE RIBS OF AN AIRCRAFT WING
MODELLIERUNG UND ANALYSE VON VORDERKANTENRIPPEN EINES FLUGZEUGFLÜGELS
MODÉLISATION ET ANALYSE DE NERVURES DE BORD D'ATTAQUE D'UNE AILE D'AVION
2017-12-27
Patent
Elektronische Ressource
Englisch
Modeling and analysis of leading edge ribs of an aircraft wing
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