Development and Flight Demonstration of 5 kN Thrust Class CAMUI Type Hybrid Rocket

• NAGATA Harunori

  Division of Mechanical and Space Engineering, Hokkaido University

• WAKITA Masashi

  Division of Mechanical and Space Engineering, Hokkaido University

• TOTANI Tsuyoshi

  Division of Mechanical and Space Engineering, Hokkaido University

• UEMATSU Tsutomu

  Uematsu Electric Co., Ltd.

抄録

The authors have been developing CAMUI (Cascaded Multistage Impinging-jet) type hybrid rockets, explosive-flee small rocket motors. This is to downsize the scale of suborbital flight experiments on space related technology development. A key idea is a new fuel grain design to increase gasification rates of a solid fuel. By the new fuel grain design, the combustion gas repeatedly impinges on fuel surfaces to accelerate the heat transfer to the fuel. To demonstrate flight performance of a newly developed 5000 N thrust class motor and accumulate flight data around the sonic speed, a launch test was conducted from a coast to the sea. Basic technologies for the sea recovery are staged braking by parachutes, suspending the fuselage on the ocean, and locating the fuselage by an electric beacon and sea marker. Test results were successful and all of the fuselage was recovered. A typical drag coefficient profile around the sonic speed was obtained.

収録刊行物

• TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN

  TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 12 (ists29), Ta_1-Ta_4, 2014

  一般社団法人 日本航空宇宙学会

キーワード

• Hybrid Rocket
• Flight Test

詳細情報

• CRID: 1390282680297352704
• NII論文ID: 130003395437
• DOI: 10.2322/tastj.12.ta_1
• ISSN: 18840485
• Web Site: https://www.jstage.jst.go.jp/article/tastj/12/ists29/12_Ta_1/_pdf
• 本文言語コード: en
• データソース種別:
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