Cause clarification and countermeasures for excessive side-load of the nozzle

  • Tomita Takeo
    Rocket Engine Technology Center Institute of Aerospace Technology
  • Sakamoto Hiroshi
    Rocket Engine Technology Center Institute of Aerospace Technology
  • Takahashi Masahiro
    Combined Propulsion Research Group Institute of Aerospace Technology
  • Takahashi Mamoru
    Rocket Engine Technology Center Institute of Aerospace Technology
  • Sasaki Masaki
    Rocket Engine Technology Center Institute of Aerospace Technology
  • Ueda Shuichi
    Combined Propulsion Research Group Institute of Aerospace Technology
  • Tamura Hiroshi
    Rocket Engine Technology Center Institute of Aerospace Technology
  • Watanabe Yasuhide
    Launch Operations Division Kagoshima Space Center Office of Space Flight and Operations

Bibliographic Information

Other Title
  • ノズル過大横推力の原因究明と対策

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Description

Strong side-loads were observed for LE-7A engine during start-up and shut-down transient in the early development phase. To investigate causes of the side-load and to resolve the problem, co-laborative research work between NAL and NASDA has been conducted. As a result, the causes were revealed to be a separation jump and a restricted shock separation. Based on the results, the nozzle design of the LE-7A was renewed. No strong side-load as original nozzle design was observed for renewed nozzle design.

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Details 詳細情報について

  • CRID
    1574231877278811648
  • NII Article ID
    110007149127
  • NII Book ID
    AA1192675X
  • ISSN
    13491113
  • Text Lang
    ja
  • Data Source
    • CiNii Articles

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