Measurement of the mass of fuel components of a promising upper stage at the launch complex

Аuthors

Balakin S. V.^*, Stenyaeva D. A.

Korolev Rocket and Space Corporation «Energia», Korolev, Moscow region, Russia

*e-mail: stanislav.balakin@rsce.ru

Abstract

This article aims to improve the accuracy of measuring the mass of dielectric propellant components in liquid upper stage tanks during prelaunch processing at the launch pad. Existing fuel level measurement systems based on capacitive level sensors have significant errors associated with reference to the theoretical upper apex of the tank, thermal deformations of the structure, and changes in the density and permittivity of the propellant at cryogenic temperatures. A method based on capacitive level sensors and flow meters with corresponding temperature sensors is proposed for objective fuel monitoring. The proposed method implements two independent measurement principles, ensuring the objective determination of the propellant quantity.
This article presents a developed algorithm for the operation of a system for determining propellant parameters using a capacitive level sensor. The algorithm includes calibration of the measurement channels before system operation, determination of the fuel level and mass, taking into account thermal deformations of the tank and changes in the density and permittivity of the propellant components. The proposed method allows for improved accuracy in determining the amount of fuel during refueling and an increase in the mass of the payload carried.

Keywords:

launch vehicle; upper stage; mass measurement system; level gauge; capacitive sensor; dielectric constant; launch complex

References

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