Aerodynamic design, analysis, and validation techniques for the Tianwen-1 entry module

Abstract The clear differences between the atmosphere of Mars and Earth coupled with lack a domestic research basis were significant challenges for aerodynamic prediction verification Tianwen-1. In addition, entry, descent, landing (EDL) mission led to specific requirements accuracy deceleration performance, stability, aerothermal heating, various complex coupling problems entry module. This study analyzes key difficult aerothermodynamic related EDL process. Then, process results design optimization module configuration are presented along calculations experiments used obtain characteristics in Martian atmosphere. simulation low-frequency free oscillation under large separation flow described, some special such as aeroelastic buffeting response trim tab discussed. Finally, atmospheric parameters obtained from flight data Tianwen-1 compared data. design, analysis, all meet engineering requirements. particular, parameters, angles attack, axial forces within envelopes deviation zones.