Development of 90 kgf Class CAMUI Hybrid Rocket for a CanSat Experiment

• NAGATA Harunori

  Hokkaido University

• UEMATSU Tsutomu

  Camuispaceworks Co. Ltd.

• ITO Mitsunori

  Hokkaido University

• KAKIKURA Akihito

  Hokkaido University

• KANEKO Yudai

  Hokkaido University

• MORI Kazuhiro

  Hokkaido University

• MURAI Norikazu

  Hokkaido Inst. Tech.

• SATO Tatsuhiro

  Hokkaido Inst. Tech.

• MITSUHASHI Ryuichi

  Hokkaido Inst. Tech.

• TOTANI Tsuyoshi

  Hokkaido University

Abstract

A newly designed CAMUI hybrid rocket motor of 900 N (90 kgf) thrust class, CAMUI-90, was developed. It uses a combination of polyethylene and liquid oxygen as propellants. CAMUI hybrid rocket is an explosive-flee small rocket motor to realize a small launch system with low cost and flexibility. The motor produces a thrust of 900 N for four seconds, keeping the optimal characteristic exhaust velocity of the fuel-oxidizer combination (exceeding 1800 m/s). A main application of the CAMUI-90 motor is for a CanSat experiment. A launch vehicle employing CAMUI-90 motor, 120 mm in diameter and 3.05 m in length, accelerates a payload of 500 g to 140 m/s in four seconds and reaches to an altitude of about 1 km. The first launch of this vehicle was on December 2006.

Journal

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

  TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN 7 (ists26), Tu_1-Tu_5, 2009

  THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

Keywords

• Hybrid Rocket
• Flight Test
• Small Launch System
• Solid Combustion

Details

• CRID: 1390282680189784192
• NII Article ID: 130000151925
• DOI: 10.2322/tstj.7.tu_1
• ISSN: 13473840
• Web Site: https://www.jstage.jst.go.jp/article/tstj/7/ists26/7_ists26_Tu_1/_pdf
• Text Lang: en
• Data Source:
  • JaLC
  • Crossref
  • CiNii Articles
• Abstract License Flag: Disallowed