インフレータブル翼を用いた超小型火星飛行機の初期概念設計

• 間宮 一誠

  連絡先著者（Corresponding author）：[e-mail] 東北大学流体科学研究所 東北大学大学院工学研究科航空宇宙工学専攻

• 藤田 昂志

  東北大学流体科学研究所

• 永井 大樹

  東北大学流体科学研究所

書誌事項

タイトル別名

• Conceptual Design of Micro Mars Airplane Using Inflatable Wing

抄録

We propose a Mars aerial exploration mission using a micro Mars airplane released from CubeSat. In this paper, the airplane is designed, and its feasibility is evaluated in terms of maximum flight Mach number and wing structure mass. The airplane is small enough to be stored in 1U (a cube of 10cm) and has a total mass of 950g. A glider type is suitable considering the severe constraints of size and mass. The airplane also requires a relatively large wing to fly through the thin Martian atmosphere. Therefore, we adopt an inflatable wing to develop a compact and large wing. The cross-section of the wing is bumpy airfoil due to the multiple pressurized tubes that extend in the spanwise direction. Aerodynamic measurements are conducted in a wind tunnel to study the aerodynamic characteristics of the wing. Finally, the specifications of the airplane are proposed based on the wind tunnel tests results. The proposed airplane with its wingspan of 0.9m is capable of gliding over 40km in nine minutes.

収録刊行物

• 日本航空宇宙学会論文集

  日本航空宇宙学会論文集 69 (1), 16-23, 2021

  一般社団法人 日本航空宇宙学会

キーワード

• Mars Airplane
• Aerodynamics
• Conceptual Design

詳細情報

• CRID: 1390568617216766976
• NII論文ID: 130007981117
• DOI: 10.2322/jjsass.69.16
• ISSN: 24323691
• ISSN: 13446460
• Web Site: https://www.jstage.jst.go.jp/article/jjsass/69/1/69_69_16/_pdf
• 本文言語コード: ja
• データソース種別:
  • JaLC
  • Crossref
  • CiNii Articles
• 抄録ライセンスフラグ: 使用不可