Parachutes have been widely used in the supersonic deceleration process of Mars probes due to its high deceleration efficiency. However, the canopy damage may occur and lead to the collapse of parachute under high dynamic load. To avoid parachute damage, the reefing method is commonly used to delay the inflation thus reduce the dynamic load. Numerical simulations were conducted on the inflation process of supersonic parachute using the ALE (Arbitrary Lagrange Euler) method. In order to investigate the influence of reefing time on the damage propagation process of parachute, the failure of canopy was simulated by adopting MAE (Material Add Erosion) model. The numerical model can effectively simulate the canopy shape and dynamic load during the inflation process. On this basis, the interactions between flow and canopy structure during the damage propagation process was studied, and the influence of the reefing time on the damage propagation process was analyzed. Results showed that the airflow through the canopy damaged zone led to the asymmetry of the flow, and this led to the stress concentration and the successive damage in multiple places on canopy surface. With the increasing reefing time, the dynamic pressure when canopy begins to re-inflate decreases, the stress near the damaged zone increases more slowly and so does the damage propagates; therefore, the canopy damage area decreases.

降落伞因其减速效率高，在火星探测器超音速减速过程中得到了广泛的应用。然而，在高动态载荷下，可能会发生座舱盖损坏并导致降落伞倒塌。为了避免降落伞损坏，通常采用收帆的方法来延迟充气，从而减少动载荷。采用ALE（任意拉格朗日欧拉）方法对超音速降落伞充气过程进行数值模拟。为了研究收帆时间对降落伞损伤传播过程的影响，采用MAE（Material Add Erosion）模型对座舱盖失效进行模拟。该数值模型可以有效模拟冠层形状和充气过程中的动态载荷。在此基础上，研究了损伤传播过程中流与冠层结构的相互作用，并分析了收帆时间对损伤传播过程的影响。结果表明，气流通过冠层受损区时，导致气流不对称，导致冠层表面多处应力集中，造成连续损伤。随着收帆时间的增加，冠层开始重新膨胀时的动压力减小，损伤区域附近的应力增加得更慢，损伤传播得更慢；因此，冠层损坏面积减少。