Abstract
At Japan Aerospace Exploration Agency, a non‐stop Mars sample return project has been planned. In the project, sampling of Martian dust particles is planned between 35 and 45 km, and the impact of Martian dust particles on a shock structure and aerodynamics for a spacecraft must be clarified. In this work, a mechanism for hypersonic dusty flow simulations in DSMC has been developed, and hypersonic dusty flows were simulated for clear weather and dust storm conditions using two dust‐surface interaction models at the descent altitude. It was found that although the impact of dust particles on the shock structure and drag is negligible, the total heat flux is increased with the consideration of dust particles.
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