Evaluation of Combustion Chamber Pressure of 1N-Class Green Monopropellant Thruster with Discharge Plasma System

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  • WADA Asato
    連絡先著者 （Corresponding author）：wada-asato@ed.tmu.ac.jp 首都大学東京大学院システムデザイン研究科航空宇宙システム工学域
  • MAEDA Hiroshi
    首都大学東京大学院システムデザイン研究科航空宇宙システム工学域
  • SHINDO Takahiro
    首都大学東京大学院システムデザイン研究科航空宇宙システム工学域
  • WATANABE Hiroki
    首都大学東京大学院システムデザイン研究科航空宇宙システム工学域
  • TAKEGAHARA Haruki
    首都大学東京大学院システムデザイン研究科航空宇宙システム工学域

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Other Title
  • 低毒性一液式推進剤を用いた1N級放電プラズマスラスタの燃焼室圧力評価
  • テイドクセイ イチエキシキ スイシンザイ オ モチイタ 1Nキュウ ホウデン プラズマスラスタ ノ ネンショウシツアツリョク ヒョウカ

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Description

Green monopropellant thrusters, such as HAN-based and ADN-based monopropellant thruster, have been continuously developed as replacement for conventional hydrazine thrusters. A green monopropellant reaction system by utilizing discharge plasma of swirling noble gas has been proposed in substitution for the solid catalyst. Objective of this study is to evaluate the thrust performance of HAN-based monopropellant thruster with discharge plasma system by the measurement of combustion chamber pressure under vacuum. As a result, stable operations were confirmed by the measurement of combustion chamber pressure and internal pressure of argon-tube. At argon mass flow rate of 0.13g/s, HAN-based monopropellant mass flow rate of 0.31g/s and nozzle expansion ratio of 1, power consumption, c-star efficiency and rising time of combustion chamber pressure were 484W, 54% and 597ms, respectively. In addition, predicted thrust and specific impulse by the measured combustion chamber pressure were 282mN and 93s, respectively.

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