Design and Dynamic Analysis of a Mechanically Deployable Aeroshell for Mars Entry

To address the growing complexity of exploration mission demands, this study presents a mechanically deployable aeroshell that offers advantages such as repeatable deployment and reusability. A novel deployable mechanism is introduced, and its kinematics is analyzed. To explore the dynamic interactions between aerodynamic forces and structural deformation over the full duration of Mars’ atmospheric entry, a six-degree-of-freedom (6-DOF) ballistic entry simulation tool considering structural deformation is developed. This simulator incorporates a time-resolved coupling strategy alongside a modified Newtonian impact model to capture how ongoing changes in aeroshell geometry influence both flight trajectory and aerodynamic properties. The results show that stiffness has a nonlinear effect on trajectory parameters, especially when the system stiffness is reduced by more than 80%, the deformation of the structure will have a great impact on the trajectory.