Disclosed is a method for gauging the liquid propellant tank of a spacecraft during a phase of high-thrust along an axis, the tank being thermally conductive and having a known geometry. The method includes steps of: attaching, on a wall of the tank, a heating member and at least one temperature sensor in proximity to the heating member and in a plane of interest perpendicular to the thrust axis; during the high-thrust phase, heating the wall of the tank and acquiring temperature measurements of the wall of the tank at rapid frequency; determining the instant I when the temperature measured by the sensor changes, such change indicating the presence of the liquid-gas interface in the tank in the plane of interest; and determining the volume of liquid propellant present in the tank at instant I.
PROCÉDÉ DE JAUGEAGE THERMIQUE DU RÉSERVOIR D'UN VÉHICULE SPATIAL ET VÉHICULE SPATIAL ÉQUIPÉ DE MOYENS POUR LA MISE EN OEUVRE D'UN TEL PROCÉDÉ
METHOD FOR THERMALLY GAUGING THE TANK OF A SPACECRAFT AND A SPACECRAFT EQUIPPED WITH MEANS FOR IMPLEMENTING SUCH A METHOD
VERFAHREN ZUR THERMISCHEN MESSUNG DES TANKS EINES RAUMFAHRZEUGES UND RAUMFAHRZEUG MIT MITTELN ZUR DURCHFÜHRUNG SOLCH EINES VERFAHRENS
2020-02-26
Patent
Electronic Resource
French
European Patent Office | 2018
|European Patent Office | 2018
|Procédé de localisation d'un véhicule, procédé de mise en œuvre d'un véhicule, et système
European Patent Office | 2019
|European Patent Office | 2018
|European Patent Office | 2020
|