Deployment Tests of Membrane Aeroshell with Shape Memory Alloy Frame in a Hypersonic Flow

• Imamura Osamu

  東京大学大学院新領域創成科学研究科

• Ishida Tomoki

  東京大学大学院工学系研究科

• Watanuki Tadaharu

  東京大学大学院工学系研究科

• Suzuki Kojiro

  東京大学大学院新領域創成科学研究科

Bibliographic Information

Other Title

• 極超音速気流中における形状記憶合金製フレームを有する柔構造体エアロシェルの展開実験

Abstract

For re-entry missions, deployable-flexible aeroshell is expected to have an advantage because it can significantly reduce the aerodynamic heating due to deceleration at relatively high altitudes thanks to its small mass and large area (i.e. low ballistic coefficient), while it can be stowed compactly during the launch phase. In this study, we propose deployable aeroshell supported by the shape memory alloy frame, which can deploy itself automatically by receiving the aerodynamic heating. The present system neither requires additional sensors nor acuators. It seems suitable for small re-entry capsule because of its simple, fault-tolerant and low-cost nature. It is experimentally demonstrated by the wind tunnel tests that a model having a membrane aeroshell with a shape memory alloy frame is smoothly deployed and kept stable in hypersonic flow.

Journal

• JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

  JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 55 (646), 561-562, 2007

  THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

Keywords

• Membrane Aeroshell
• Aerodynamic Heating
• Shape-Memory Alloy
• Hypersonic
• Deployable Structure

Details

• CRID: 1390001204470632320
• NII Article ID: 10021152638
• NII Book ID: AA11307372
• DOI: 10.2322/jjsass.55.561
• ISSN: 24323691
• ISSN: 13446460
• Web Site: https://www.jstage.jst.go.jp/article/jjsass/55/646/55_646_561/_pdf
• Text Lang: ja
• Data Source:
  • JaLC
  • Crossref
  • CiNii Articles
  • KAKEN
• Abstract License Flag: Disallowed