Conceptual Design of Single-Stage Launch Vehicle with Hybrid Rocket Engine for Scientific Observation Using Design Informatics

• CHIBA Kazuhisa

  Hokkaido Institute of Technology

• KANAZAKI Masahiro

  Tokyo Metropolitan University

• NAKAMIYA Masaki

  Kyoto University

• KITAGAWA Koki

  Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency

• SHIMADA Toru

  Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency

抄録

A single-stage launch vehicle with hybrid rocket engine has been conceptually designed by using design informatics, which has three points of view as problem definition, optimization, and data mining. The primary objective of the design in the present study is that the sufficient down range and duration time in the lower thermosphere are achieved for the aurora scientific observation whereas the initial gross weight is held down. The multidisciplinary design optimization and data mining were performed by using evolutionary hybrid computation under the conditions that polypropylene as solid fuel and liquid oxygen as liquid oxidizer were adopted and that single-time ignition is implemented in sequence. Consequently, the design information regarding tradeoffs and the behavior of the design variables was obtained.

収録刊行物

• Journal of Space Engineering

  Journal of Space Engineering 6 (1), 15-27, 2013

  一般社団法人 日本機械学会

キーワード

• Design Informatics
• Single-Stage Launch Vehicle for Scientific Observation
• Hybrid Rocket Engine Using Solid Fuel and Liquid Oxidizer

詳細情報

• CRID: 1390001205280462720
• NII論文ID: 130003368193
• DOI: 10.1299/spacee.6.15
• BIBCODE: 2013JSpEn...6...15C
• ISSN: 1881736X
• Web Site: https://www.jstage.jst.go.jp/article/spacee/6/1/6_15/_pdf
• 本文言語コード: en
• データソース種別:
  • JaLC
  • Crossref
  • CiNii Articles
  • KAKEN
• 抄録ライセンスフラグ: 使用不可