Study on Estimating the Mass of the Upper Stage of a Launch Vehicle Using Electric Pump Cycle and an ED Nozzle

초록

A mass estimation study was conducted to improve the inert mass fraction of an electric pump cycle by applying a next-generation battery and an ED nozzle to the 3 tonf class upper stage of a two-stage launch vehicle. In an electric pump cycle, the battery remains at dry mass in the final stages of the mission, which can result in disadvantage of inert mass fraction. Accordingly, the mass of the launch vehicle was estimated when applying the rapidly developing next-generation battery technology and an ED nozzle to reduce the mass of the launch vehicle. In the case of the nozzle, the mass was calculated considering an ED nozzle, which was shorter than the 80% Bell nozzle, and the inert mass fraction and performance of the launch vehicle were compared. An electric pump cycle has a lower inert mass fraction than the gas generator cycle depending on the total burning time at a combustion chamber pressure of 2.5 MPa or less through the application of a next-generation battery and ED nozzle. In addition, when launched into a 500 km SSO at the same combustion chamber pressure, the payload demonstrated a maximum increase of 26.34% compared to an electric pump cycle with the application of current technology battery, and a 2.72% increase compared to the gas generator cycle.

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