Design and aerostructural modeling in a mechanically deployable aeroshell for Mars entry

The mechanically deployable aeroshell, due to its repeatability, reusability, and other advantages, can adapt to the increasingly diverse needs of exploration missions. This paper proposes a novel aeroshell configuration based on a deployable mechanism and analyzes its mobility. Additionally, to study the coupling characteristics between structural deformation and aerodynamic loading of the mechanically deployable aeroshell, a six-degree-of-freedom (6-DOF) Mars ballistic atmospheric entry trajectory simulator is developed to evaluate the design of the configuration. Based on the modified Newton impact theory, the simulator not only considers the impact of the aeroshell’s structural shape on the trajectory and aerodynamic parameters but also incorporates the flexibility of the deployable structure within the aeroshell using the Euler–Bernoulli beam model. With this model, the influence of structural deformation on both the trajectory and aerodynamic parameters can be further analyzed. The results indicate that, within a certain range, reducing the stiffness of the aeroshell structure significantly reduces its mass. By reallocating this mass to increase the diameter of the aeroshell, it is possible to notably decrease the peak heat flux on the shell surface and extend the entry time.