Simplification Method for Thrust Estimation of External Nozzle in Under-Expansion Condition

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  • MIKOSHIBA Ryo
    連絡先著者（Corresponding author）：mic-o-siver@keio.jp 慶應義塾大学大学院理工学研究科開放環境科学専攻
  • MATSUO Akiko
    慶應義塾大学大学院理工学研究科開放環境科学専攻
  • TOMIOKA Sadatake
    国立研究開発法人宇宙航空研究開発機構
  • FUJIKAWA Takahiro
    東京大学大学院工学系研究科航空宇宙工学専攻 現 九州工業大学大学院工学研究院機械知能工学研究系
  • TSUCHIYA Takeshi
    東京大学大学院工学系研究科航空宇宙工学専攻
  • ISONO Tatsushi
    東北大学大学院工学研究科航空宇宙工学専攻

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Other Title
  • 不足膨張条件下における外部ノズル推力予測の簡略化手法
  • フソク ボウチョウ ジョウケン カ ニ オケル ガイブ ノズルスイリョク ヨソク ノ カンリャクカ シュホウ

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An external nozzle is one of the altitude compensating nozzle for a wide range operating airframe like RLV (Reusable Launch Vehicle). This paper explores the possibility of simplifying thrust calculations of the external nozzle for a series of flight operations. We focused on a replacement of some 2D thrust calculations with a method at a low computation cost in thrust performance evaluation along a trajectory of RLV equipped with the external nozzle. The replacement is determined by threshold conditions of jet Mach number and slip line angle. Since strict calculation of the threshold conditions takes expensive computational cost, calculating models of the threshold conditions were constructed. These models were able to predict the threshold conditions with an error of 4% or less. Then, the models were applied to the calculation for 2604 nozzle shapes and 191 points along a trajectory of TSTO (Two Stage To Orbit) booster. Thrust calculations of 86% conditions were replaced by the method with low computational cost, so that the models proposed in this work demonstrated the achievement of simplification.

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