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<p>A deployable aeroshell using a membrane is proposed as a concept to avoid severe aerodynamic heating by decelerating at higher altitudes and in a thinner atmosphere during atmospheric entry. This study focuses on an advanced passive deployable aeroshell that uses a shape memory alloy (SMA). In this concept, thin plates made of SMA are used as umbrella ribs, and aerodynamic heating leads to automatic deployment. This design can yield an ultra-lightweight and simple aerodynamic entry system. The feasibility of such an SMA-type deployable aeroshell is investigated for the Martian atmospheric entry mission. In the assumed mission, the atmospheric entry vehicle has membrane flares on both the front and rear, and SMA ribs are placed on the rear flare; consequently, it looks like a rhombus when viewed from the side. The trajectory simulation considered the following experimental results: structural strength against aerodynamic load, which is evaluated by a low-speed wind tunnel test, and deployment behavior, which is observed by a hypersonic wind tunnel test. These results indicate that the SMA-type aeroshell with a diameter of 810&#xa0;mm can withstand an aerodynamic load of approximately 100 N, and its scale model can be passively deployed in a hypersonic airflow for around 15&#xa0;s. In addition, the trajectory simulation results reveal that this SMA-type aeroshell can be utilized in Mars exploration missions as an atmospheric entry system for nanoscale landers.</p>

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Study on the application of shape memory alloy-type aeroshell to the Mars exploration mission based on wind tunnel tests

  • 期刊论文

  • 发表日期：

    2026年2月16日

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  • Shion Okada,
  • Kazuhiko Yamada,
  • Yasunori Nagata,
  • Hiroyuki Nishida

摘要

A deployable aeroshell using a membrane is proposed as a concept to avoid severe aerodynamic heating by decelerating at higher altitudes and in a thinner atmosphere during atmospheric entry. This study focuses on an advanced passive deployable aeroshell that uses a shape memory alloy (SMA). In this concept, thin plates made of SMA are used as umbrella ribs, and aerodynamic heating leads to automatic deployment. This design can yield an ultra-lightweight and simple aerodynamic entry system. The feasibility of such an SMA-type deployable aeroshell is investigated for the Martian atmospheric entry mission. In the assumed mission, the atmospheric entry vehicle has membrane flares on both the front and rear, and SMA ribs are placed on the rear flare; consequently, it looks like a rhombus when viewed from the side. The trajectory simulation considered the following experimental results: structural strength against aerodynamic load, which is evaluated by a low-speed wind tunnel test, and deployment behavior, which is observed by a hypersonic wind tunnel test. These results indicate that the SMA-type aeroshell with a diameter of 810 mm can withstand an aerodynamic load of approximately 100 N, and its scale model can be passively deployed in a hypersonic airflow for around 15 s. In addition, the trajectory simulation results reveal that this SMA-type aeroshell can be utilized in Mars exploration missions as an atmospheric entry system for nanoscale landers.