Topic: Aircraft Wing-box Structural Analysis
Question: Need to do the load and stress analysis for the aircraft wing-box structure. The details are attached with more explanation.
You need to do this "For this report you are required to provide detailed CAD drawings of your proposed design and its various components using an industry standard modeling tool (for example CATIA)". ?
Objective: Complete the structural design of the wing box based on the materials proposed in the first report. The selected materials for wing-box structure are the skin panel is set to be aluminum, ribs are set as steel, and the spar is set as S-Glass. The main objective is to design a box of an optimal weight while meeting all structural integrity requirements with special attention to buckling and yielding. Your design will focus on a 2-spar wing box capable of resisting limit loads at the PLAA flight condition with a safety factor of 1.5. To validate your design, you are to perform stress analyses at a minimum of 4 wing stations. You have to use schrenk method to evaluate your design for load-distribution and stress analysis.
Attachment:- Assignment Files.rar