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Research on aerodynamic performance of parafoil for autonomous recovery

With the increasing requirement of the accuracy of the spacecraft’s autonomous fixed-point recovery, accurate calculation of the aerodynamic parameters of the parafoil in the recovery system is becoming very important. In this paper, we studied the aerodynamic parameter of the parafoil using Computational Fluid Dynamics, the aerodynamic parameters of the parafoil and its variation are obtained in different angle of attack. Compared with the traditional wind tunnel test, the Computational Fluid Dynamics method shows the superiority on the research of aerodynamic parameter of parafoil, not only can guarantee the accuracy of aerodynamic parameters, but also avoid the constraint from the size of parafoil.