Investigation of an aeroelastic model for a generic wing structure

[摘要] ENGLISH ABSTRACT: Computational Aeroelasticity is a complex research field which combines structuraland aerodynamic analyses to describe a vehicle in flight. This thesis investigates thefeasibility of including such an analysis in the development of control systems for unmannedaerial vehicles within the Electronic Systems Laboratory at the Departmentof Electrical and Electronic Engineering at Stellenbosch University.This is done through the development of a structural analysis algorithm using theFinite Element Method, an aerodynamic algorithm for Prandtl's Lifting Line Theoryand experimental work. The experimental work was conducted at the Low-SpeedWind Tunnel at the Department of Mechanical and Mechatronic Engineering.The structural algorithm was applied to 20-noded hexahedral elements in a winglikestructure. The wing was modelled as a cantilever beam, with a fixed and a freeend. Natural frequencies and deflections were verified with the experimental modeland commercial software.The aerodynamic algorithm was applied to a Clark-Y airfoil with a chord of 0:1mand a half-span of 0:5m. This profile was also used on the experimental model.Experimental data was captured using single axis accelerometers. All postprocessingof data is also discussed in this thesis. Results show good correlationbetween the structural algorithm and experimental data.

[发布机构] Stellenbosch University