HEAT AND MASS TRANSFER MEASUREMENT SYSTEM IN CRYOGENIC PROPELLANT TANK OF LAUNCH VEHICLE

摘要

The present invention is a system for measuring the transfer of heat and propellant in the propellant tank of the space launch vehicle, mounted on the inner side of the tank by a predetermined height, probe array having a plurality of component analysis sampling probes for detecting the component information of the propellant ; A temperature sensor array mounted on an inner side corresponding to the component analysis sampling probe array by a predetermined height and having a plurality of temperature sensors for measuring the temperature of the propellant; An induction rod installed between the tank upper surface and the tank base surface; A temperature sensor rake measuring a temperature gradient of the propellant surface while moving along the guide rod; A pipe installed at an outer upper portion of the tank to supply a pressurized gas for maintaining the pressure inside the tank; A pipe installed outside the tank to supply the propellant; A pipe installed at an outer lower portion of the tank to discharge the propellant; And a pipe installed at an outer upper portion of the tank to discharge the mixed gas of the propellant and the pressurized gas. The present invention relates to a system for measuring heat and propellant in a propellant tank of a space launch vehicle.;Temperature gradient, temperature sensor rake, cryogenic propellant