Current Status of Rocket Developments in Universities -Development of a Small Hybrid Rocket with a Swirling Oxidizer Flow Type Engine

• YUASA Saburo

  Tokyo Metropolitan Institute of Technology

• KITAGAWA Koki

  Tokyo Metropolitan Institute of Technology

抄録

To develop an experimental small hybrid rocket with a swirling gaseous oxygen flow type engine, we made a flight model engine. Burning tests of the engine showed that a maximum thrust of 692 N and a specific impulse of 263 s (at sea level) were achieved. We designed a small hybrid rocket with this engine. The rocket measured 1.8 m in length and 15.4 kg in mass. To confirm the flight stability of the rocket, wind tunnel tests using a 112-scale model of the rocket and simulations of the flight attitude and trajectory were carried out. A flight test was conducted at Taiki-cho, Hokkaido, Japan on March 2001. The rocket reached an altitude of about 600 m, thus recording the first successful flight of a hybrid rocket in Japan. For the next stage, future issues to develop larger hybrid rockets using a swirling liquid oxygen flow type engine are discussed, and preliminary burning tests of the engine have been carried out.

収録刊行物

• The Journal of Space Technology and Science

  The Journal of Space Technology and Science 21 (1), 1_1-1_11, 2005

  特定非営利活動法人　日本ロケット協会

キーワード

• Hybrid Rocket

詳細情報

• CRID: 1390001205080647424
• NII論文ID: 130004562802
• NII論文ID: 10018377189
• NII書誌ID: AA10925183
• DOI: 10.11230/jsts.21.1_1
• ISSN: 21864772
• ISSN: 0911551X
• HANDLE: 10748/5990
• HANDLE: 10228/00008464
• Web Site: https://tokyo-metro-u.repo.nii.ac.jp/records/3899
• Web Site: https://kyutech.repo.nii.ac.jp/records/7260
• 本文言語コード: en
• データソース種別:
  • JaLC
  • IRDB
  • CiNii Articles
• 抄録ライセンスフラグ: 使用不可