Aerodynamic simulation and analysis of large ring-sail parachute

Abstract

Parachutes have been closely linked to many space missions. Many vehicles launched into space have had parachutes on board for recovery or landing deceleration, and relative research mainly adopts computer simulation methods due to high test costs. In order to investigate the aerodynamic force and the surrounding flow field structure of the parachutes in the process of vehicle return, a physical model is established for the main parachute used in spacecraft return, using trimmed mesh for spatial division, and numerical simulations of the steady-state flow field of the large ring-sail parachute at different angles of attack are conducted. The results show that, the drag coefficient increases and then decreases, and the lift coefficient decreases and then increases with increasing angle of attack; the high-low-high-low-incoming flow velocity of the axial flow field generated by the ring-sail canopy is demonstrated and analyzed. The simulation results provide theoretical guidance for the structural design of the return parachute.