Trajectory Optimization and Conceptual Study of Small Test Vehicles for Hypersonic Engine Using High-Altitude Balloon

• Tsuchiya Takeshi

  東京大学工学系研究科航空宇宙工学専攻

• Takenaka Youichi

  東京大学工学系研究科航空宇宙工学専攻

• Taguchi Hideyuki

  独立行政法人宇宙航空研究開発機構航空プログラムグループ

• Sawai Shujiro

  独立行政法人宇宙航空研究開発機構宇宙科学研究本部

Bibliographic Information

Other Title

• 高高度気球を用いた極超音速エンジン小型実験機に対する軌道最適化と概念検討
• コウコウド キキュウ オ モチイタ ゴク チョウオンソク エンジン コガタ ジッケンキ ニ タイスル キドウ サイテキカ ト ガイネン ケントウ

Abstract

Japan Aerospace Exploration Agency, JAXA announced a long-term vision recently. In the vision, JAXA aims to develop hypersonic aircrafts. A pre-cooled turbojet engine has great potential as one of newly developed hypersonic air-breathing engines. We also expect the engine to be installed in space transportation vehicles in future. For combustion test in real flight condition of the engines, JAXA has an experimental plan with a small test vehicle falling from a high-altitude balloon. This paper applies numerical analysis and optimization techniques to conceptual designs of the test vehicle in order to obtain the best configuration and trajectory that can achieve the flight test. The results show helpful knowledge when we design prototype vehicles.

Journal

• JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

  JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 54 (629), 266-271, 2006

  THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

Keywords

• Guidance and Control
• Flight Testing
• Optimal Trajectory

Details

• CRID: 1390282679446336256
• NII Article ID: 10018055265
• NII Book ID: AA11307372
• DOI: 10.2322/jjsass.54.266
• ISSN: 24323691
• ISSN: 13446460
• NDL BIB ID: 7996775
• Web Site: https://ndlsearch.ndl.go.jp/books/R000000004-I7996775
• Web Site: https://www.jstage.jst.go.jp/article/jjsass/54/629/54_629_266/_pdf
• Text Lang: ja
• Data Source:
  • JaLC
  • NDL
  • Crossref
  • CiNii Articles
  • KAKEN
• Abstract License Flag: Disallowed