Course Module for AA201: Wing Structural Design Project

摘要

This thesis defined a fundamental approach for aircraft wingbox designappropriate for an introductory course in aircraft structures based upon material strength and stiffness requirements. The process developed sought to encompass major conceptual engineering design considerations that ranged from load estimation at various points in the subsonic flight envelope, to initial structural sizing and layout. The goal was to present a process that could be readily conducted via hand calculations and applied by any student entering basic aircraft structures design. The sequence of analysis began with application of a comprehensive panel code method developed by NASA Ames Research Center known as PMARC. Loads obtained from the code were then used to formulate a strength of materials study of the structure subjected to combined bending, shear and torsion. The static load approach allowed initial estimation of component sizing based upon material or buckling allowable stress selection. Finally, the study demonstrated a strength to weight ratio comparison. Several calculation examples and computer-based spreadsheets were prepared for rapid analysis of multiple option design scenarios. Since the study employed analysis methods that could be performed without the aid of a finite element routine or extensive computer programming knowledge, it serves as a good introduction for the entry and intermediate level structural engineer. Course module for AA2021, Wing structural design project.