Strength And Aeroelasticity Analysis For Wings Of An Unmanned Aerial Vehicle

In this thesis, a study of strength and aeroelasticity analysis for wings of an unmanned aerial vehicle is presented. After an introduction to the basic theory of structure analysis, engineering methods of strength and flutter analysis for an unmanned aerial vehicle are summarized.A static FEM model for wings is built, according to the principle of equivalent mass and equivalent stiffness. Then on the conditions of stable pitching and rolling, integral strength of the airfoil is analyzed, and safety check of the composite structure is performed against the maximum stress criterion. Based on the integral strength analysis, a local FEM model of wing-aileron is established and analyzed using nonlinear theory to check the maximum displacements and contact stresses. At the same time, eigenvalue buckling analysis for composite structures of the vehicle is executed to explore the stability under various loads.Based on the static model of the vehicle, a dynamic model of the wing and empennage is created. Then on the conditions of stable pitching and rolling, equivalent flutter velocities and flutter frequencies of the wing and empennage at different altitudes are obtained by means of variable depth flutter analysis with the p-k method. The computing results are compared with the flight parameters to check the rationality of the structure design. Finally, result of flutter analysis by the k-e method on the condition of stable pitching is executed and compared with the p-k method.