A Finite Element Analysis of a Carbon Fiber Composite Micro Air Vehicle Wing
Abstract
Inaccuracies in the composite fiber orientation result in variations in the material properties. Experimental vibration data of manufactured three-ply [0/90/0] non-homogenous composite samples varied 33% from analytical results. Since the material was used in the manufacturing of a micro-air vehicle (MAV) based upon the Manduca Sexta, variance in the measured material properties and the effects on the manufacturing of the MAV wing needed to be understood. An analysis was performed on the material taken into account inaccuracies; ply orientation, cut angle, and material thickness. Using finite element analysis (FEA), misalignment in fiber orientation of less than 5? was determined to account for the difference between analytical and experimental results. Using optical techniques, observed variances in the ply orientation confirmed FEA results. A FEA model of the MAV wing was developed. To allow for quick changes to the model, the FEA model was generated using a developed MATLAB code that generated input files to be solved using ABAQUS, a finite element program. This MATLAB code generated beam cross-sections and corrected densities for the composite beam elements based upon the ply orientations and inaccuracies. An analysis was performed to determine the effects of the ply orientation misalignment on the FEA wing model.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 22, 2012
- Accession Number
- ADA558340
Entities
People
- Theodore A. Szelag
Organizations
- Air Force Institute of Technology