Shahrood University of Technology Journal of Solid and Fluid Mechanics 2251-9475 6 2 2016 06 21 Aeroelastic nonlinear analysis of a high aspect ratio wing with store flow steady incompressible Aeroelastic nonlinear analysis of a high aspect ratio wing with store flow steady incompressible 259 269 758 10.22044/jsfm.2016.758 FA O. Motaharifard S. Shokrollahi H. Golparvar Journal Article 2013 05 04 Today, the development of unmanned aircrafts with specific performance characteristics, Including UAVs which capable to fly at high altitude and long endurance is very regarded. In this paper, we have analyzed a nonlinear aeroelastic wing with a high aspect ratio as well as a store (tank) which attached to the wing. Also, the aerodynamic model and structural model have been coupled in steady states. The equations of motion have obtained from Hamilton's principle and the Lagrange equations have acquired from three modes of “bending outside the plate", "bending inside the plate" and” torsion". First of all, we have examined the aeroelastic stability analysis “k” approach. Then, by considering the non-linear terms in equations by using fourth order Rung -Kutta approach, we have studied the results of the simulation and noticed to some phenomena like limit cycle oscillations and bifurcation. The Nonlinear terms are structure and store types and aerodynamics flow have been studied in the linear modes. For solving the equations we have used Galerkin method. Also, the equations have governed in the domain time. By Comparing the results, acceptable accuracy of our modeling and undertaken analysis has observed. Today, the development of unmanned aircrafts with specific performance characteristics, Including UAVs which capable to fly at high altitude and long endurance is very regarded. In this paper, we have analyzed a nonlinear aeroelastic wing with a high aspect ratio as well as a store (tank) which attached to the wing. Also, the aerodynamic model and structural model have been coupled in steady states. The equations of motion have obtained from Hamilton's principle and the Lagrange equations have acquired from three modes of “bending outside the plate", "bending inside the plate" and” torsion". First of all, we have examined the aeroelastic stability analysis “k” approach. Then, by considering the non-linear terms in equations by using fourth order Rung -Kutta approach, we have studied the results of the simulation and noticed to some phenomena like limit cycle oscillations and bifurcation. The Nonlinear terms are structure and store types and aerodynamics flow have been studied in the linear modes. For solving the equations we have used Galerkin method. Also, the equations have governed in the domain time. By Comparing the results, acceptable accuracy of our modeling and undertaken analysis has observed. https://jsfm.shahroodut.ac.ir/article_758_ee2f678db811013681322c83922688e6.pdf