A High-efficiency Method for Static Aeroelasticity Analysis in Preliminary Design
Flexible wings with large aspect ratio undergo elastic deformation under aerodynamic loads,resulting in changes of wing's aerodynamic characteristics.Therefore,in the preliminary design stage,it is expected to adopt a fast and efficient calculation method to study the redistribution of wing's aerodynamic load under static aeroelastic equilibrium.This work provides an efficient analysis method to solve the static aeroelastic deformation and the corresponding aerodynamic load,in which a loose coupling strategy is adopted,assuming that the angle of attack is unchanged.The undeformed load is first applied on the wing structure,the structural deformation is calculated,and then the aerodynamic load redistribution is calculated from the deformed aerodynamic shape.The final aeroelastic load distribution and aerodynamic characteristics of the wing are obtained by iterating repeatedly until the deformation/load converged.The feasibility of the method is demonstrated by a large aspect ratio elastic model aircraft.
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