Aerodynamic and static aeroelastic computations of a slender rocket with all-movable canard surface

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The present paper is undertaken to better understand the impact of the all-movable canard surface on the aerodynamic and static aeroelastic of slender rocket. Numerical simulations are performed to numerically calculate the guided rocket aerodynamic coefficients using commercial steady-state Computational Fluid Dynamics software ANSYS®-CFX. The variations of lift and drag coefficients with Mach number are demonstrated in the linear range of angles of attack. Comparison is made between the aerodynamic results and experimental data, which verified the accuracy of the fluid domain numeric method. Rocket static aeroelastic study is simulated through the inertia relief approach and fluid–structure interaction two-way loosely coupled methods based on multi-physics coupling platform ANSYS Workbench. Comparisons are also made between the results and AGARD 445.6-Wing standard model. Moreover, the composite material is carried out to improve the canards strength. Numerically, it indicates that deflected angle of all-movable canard surface has remarkable effect on the aerodynamics of the rockets. Aerodynamic loads are mainly contributed to the static deformation of the flexible rocket, while thrust effect is tiny and may ignore. The static deformations push the center of pressure forward and increase the trim angle. By product, rocket control effectiveness is decreased about 38%. Canards with the original material experiences stresses beyond the allowable due to static deformation at high supersonic speed. Hence, composite material is adopted for strengthening the canards.