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As a part of research activities on ACT (Active Control Technology) at NAL, wind tunnel tests on the ACT wind tunnel model aircraft with elastic wings were performed to investigate the effect of rigid body movement mode to gust load alleviation effects. The mathematical model of the ACT wind tunnel model aircraft was to be constructed to design the control rule of gust load alleviation. Accordingly, the related data were to be obtained by vibration tests and by wind tunnel tests. The mathematical model was to be examined using an analytical method. In the beginning, the structural analysis model using Finite Element Method (FEM) was constructed based on the measurement results of rigidity distribution, mass distribution, and inertia moment distribution. The mathematical model on structural characteristics was derived with the adjustment of the structure parameters obtained from vibration tests. The static deformation analysis method is the mathematical model obtained by the combination of the the aerodynamic analysis software. The data obtained from the static aerodynamic elasticity analysis is compared with the wind tunnel test results. The inclusion of elastic effects was found to improve the correlation of analysis results with the wind tunnel test results. Details of the analysis results are reported.