TY - JOUR
T1 - Proposal of specific impulse prediction method for bipropellant thrusters
AU - Terauchi, Yuto
AU - Inoue, Chihiro
AU - Daimon, Yu
AU - Fujii, Go
N1 - Funding Information:
A part of this study was funded by KAKENHI (JP17H00844 and JP19K21934). The authors would like to thank them for their kind support.
Publisher Copyright:
© 2020 The Japan Society for Aeronautical and Space Sciences
PY - 2020
Y1 - 2020
N2 - For attitude control and orbital transfer of satellites, bipropellant thrusters are crucial components in space propulsion systems. The overall performance of the thruster is evaluated by the specific impulse (ISP), which directly determines the lifetime and propellant mass of satellites. Therefore, in the present study, a new theoretical framework is firstly proposed to predict ISP directly from injection conditions and nozzle configurations by considering the distribution of mixture and mass flow rates in the thrust chamber. As the performance index of the combustion chamber, the characteristic velocity is formulated. The frozen flow assumption is applied to the nozzle internal flow to calculate the thrust coefficient. The analytical results of ISP are compared to the corresponding combustion test of a 10 N bipropellant thruster using a propellant combination of mixed nitrogen oxides with 3% nitric oxide and monomethyl hydrazine, which validates the prediction model proposed.
AB - For attitude control and orbital transfer of satellites, bipropellant thrusters are crucial components in space propulsion systems. The overall performance of the thruster is evaluated by the specific impulse (ISP), which directly determines the lifetime and propellant mass of satellites. Therefore, in the present study, a new theoretical framework is firstly proposed to predict ISP directly from injection conditions and nozzle configurations by considering the distribution of mixture and mass flow rates in the thrust chamber. As the performance index of the combustion chamber, the characteristic velocity is formulated. The frozen flow assumption is applied to the nozzle internal flow to calculate the thrust coefficient. The analytical results of ISP are compared to the corresponding combustion test of a 10 N bipropellant thruster using a propellant combination of mixed nitrogen oxides with 3% nitric oxide and monomethyl hydrazine, which validates the prediction model proposed.
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U2 - 10.2322/tjsass.63.189
DO - 10.2322/tjsass.63.189
M3 - Article
AN - SCOPUS:85095705849
VL - 63
SP - 189
EP - 194
JO - Transactions of the Japan Society for Aeronautical and Space Sciences
JF - Transactions of the Japan Society for Aeronautical and Space Sciences
SN - 0549-3811
IS - 5
ER -