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
27.12.2017
Patent
Elektronische Ressource
Englisch
Modeling and analysis of leading edge ribs of an aircraft wing
Europäisches Patentamt | 2019
|MODELING AND ANALYSIS OF LEADING EDGE RIBS OF AN AIRCRAFT WING
Europäisches Patentamt | 2017
|MODELING AND ANALYSIS OF LEADING EDGE RIBS OF AN AIRCRAFT WING
Europäisches Patentamt | 2017
|Modeling and analysis of leading edge ribs of an aircraft wing
Europäisches Patentamt | 2019
|New Topology Optimization Method for Wing Leading-Edge Ribs
Online Contents | 2011
|