# US 11,307,077 B2 · Method for thermally gauging the tank of a spacecraft and a spacecraft equipped with means for implementing such a method > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,307,077 B2 - Document ID: US11307077B2 - Status: Granted - Kind: B2 - Application number: 16/468,200 - Filed: 2017-12-08 - Published: 2019-12-26 - Granted: 2022-04-19 - Earliest claimed: 2016-12-09 - Assignees: Airbus Defence and Space GmbH - Applicants: Airbus Defence and Space SAS - Inventors: Sophie Jallade; Mathieu Monge-Cadet; Sylvain Arnaud; Barbara Busset - Web page: https://patentgrep.com/patent/US11307077B2 ## CPC - G01F 23/247: {for discrete levels} - B64G 1/402: {Propellant tanks; Feeding propellants} - F17C 13/008: {for use under microgravity conditions} - F17C 13/026: {having the temperature as the parameter} - G01F: MEASURING VOLUME, VOLUME FLOW, MASS FLOW OR LIQUID LEVEL; METERING BY VOLUME - B64G: COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR - F17C: VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES (storing fluids in natural or artificial cavities or chambers in the earth B65G5/00; construction or assembling of bulk storage containers employing civil-engineering techniques E04H7/00; variable-capacity gas-holders F17B; liquefaction or refrigeration machines, plants, or systems F25) ## Abstract 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. ## Claims ### Claim 1 A method for gauging the liquid propellant tank of a spacecraft, said propellant tank comprising a thermally-conductive wall, having a known geometry and containing a volume of liquid propellant, and said spacecraft being equipped with means of propulsion capable of exerting, according to a given thrust axis, a high thrust allowing said spacecraft to achieve an acceleration of greater than or equal to 0.05 m/s2, said method comprising steps of: during a phase of high-thrust along said thrust axis exerted by said means of propulsion supplied with liquid propellant from said propellant tank, remotely controlling said spacecraft in which are attached, on an outer surface of said wall of the tank, a heating member and at least two temperature sensors, each of which is in a known position in proximity to said heating member and arranged on the outer surface of the wall of the propellant tank in a position for measuring the temperature of said wall, in a plane perpendicular to said thrust axis, referred to as plane of interest, in which the liquid-gas interface in said tank is likely to be located at some time during a phase of high-thrust exerted by said means of propulsion along said thrust axis, said temperature sensors being aligned along a so-called measurement axis, the heating member having a height, measured along said measurement axis, that is greater than the height occupied by said temperature sensors along said measurement axis, and a height of the heating member protruding beyond an end temperature sensor being greater than a distance between adjacent temperature sensors arranged along said measurement axis, further comprising the steps of: heating the wall of the tank using the heating member; and acquiring measurements of a temperature of the wall of the tank using a first of said temperature sensors, at an acquisition rate of one measurement every 30 seconds or less; determining a moment I at which the temperature measured by said temperature sensor changes, which corresponds to a moment at which a break of slope occurs on a digital curve representing the temperature recorded by said temperature sensor as a function of time, such a change indicating a presence, in the plane of interest associated with said first temperature sensor, of the liquid-gas interface in the tank; and determining, from a geometrical data of the tank and the known position of the first temperature sensor on the wall of the tank, the volume of liquid propellant present in said tank at the moment I. ### Claim 2 (depends on 1) The method according to claim 1, wherein determining the moment I at which the temperature measured by said temperature sensor changes is carried out by detecting the moment at which a break of slope occurs on a digital curve representing the temperature recorded by said temperature sensor as a function of time. ### Claim 3 (depends on 1) The method according to claim 1, wherein, in said spacecraft, a plurality of temperature sensors are attached on the outer surface of the wall of the tank, each of said plurality of temperature sensors being arranged on the outer surface of the wall of the propellant tank in a position for measuring the temperature of said wall, in proximity to the heating member and in a plane perpendicular to said thrust axis, referred to as the plane of interest associated with each respective temperature sensor of said plurality of temperature sensors, in which the liquid-gas interface in said tank is likely to be located at some time during a phase of high-thrust exerted by said means of propulsion along said thrust axis, said method comprising, for at least one of said plurality of temperature sensors, steps of: determining the moment I at which the temperature measured by said at least one of said plurality of temperature sensors changes, which corresponds to the moment at which a break of slope occurs on a digital curve representing the temperature recorded by said at least one of said plurality of temperature sensors as a function of time, said change indicating the presence of the liquid-gas interface in the plane of interest associated with said at least one of said plurality of temperature sensors; and determining, from the geometrical data of the tank and the known position of the at least one of said plurality of temperature sensors on the wall of the tank, the volume of liquid propellant present in said tank at the moment I. ### Claim 4 (depends on 3) The method according to claim 3, wherein, in said spacecraft, said plurality of temperature sensors are aligned along a so-called measurement axis, parallel to said thrust axis. ### Claim 5 (depends on 1) The method according to claim 1, wherein, in said spacecraft, said temperature sensors are situated at an equal distance from said heating member. ### Claim 6 (depends on 5) The method according to claim 5, wherein, in said spacecraft, said temperature sensors are aligned along a so-called measurement axis, and the heating member has a height, measured along said measurement axis, that is greater than the height occupied by said temperature sensors along said measurement axis. ### Claim 7 (depends on 6) The method according to claim 6, wherein, in said spacecraft, a distance between adjacent temperature sensors arranged along said measurement axis is equal to a distance between two additional adjacent temperature sensors, and a height of the heating member protruding beyond an end temperature sensor is greater than said distance. ### Claim 8 (depends on 5) The method according to claim 5, wherein, in said spacecraft, the distance between two adjacent temperature sensors along said measurement axis, measured according to an axis parallel to the thrust axis, is between 10 and 50 mm. ### Claim 9 (depends on 5) The method according to claim 5, wherein determining the moment I at which the temperature measured by a first of said temperature sensors changes is carried out by: for said first temperature sensor and for a temperature sensor arranged upstream of said first temperature sensor in the direction of the thrust exerted by the means of propulsion along the thrust axis, remotely controlling said spacecraft in order to carry out simultaneous acquisitions of measurements of the temperature of the wall of the tank, at an acquisition rate of one measurement every 30 seconds or less, for each pair of simultaneous acquisitions, determining the difference between the temperature measured by said upstream temperature sensor and the temperature measured by said first temperature sensor, and determining the moment at which said difference is the highest. ### Claim 10 (depends on 1) The method according to claim 1, further comprising a second heating member, wherein, in said spacecraft, the two heating members are attached on the outer surface of the wall of the tank, on opposing side of said temperature sensor and at an equal distance from said temperature sensor. ### Claim 11 (depends on 1) The method according to claim 1, wherein said spacecraft is remotely controlled by a control device, whereby control signals are successively determined and sent to said spacecraft by the control device in order to carry out the steps of heating the wall of the tank using the heating member and of acquiring measurements of the temperature of the wall of the tank using said temperature sensor. ### Claim 12 (depends on 1) A computer program product, comprising a set of program code instructions which, when executed by a processor, implement the steps of a method for gauging the liquid propellant tank of a spacecraft according to claim 1. ### Claim 13 (depends on 1) The method of claim 1, wherein a proximity location of the at least one temperature sensor is at a location close enough to the heating member wherein the at least one temperature sensor can measure a rise in the temperature of the wall of the tank caused by the heating of the wall by the heating member. ### Claim 14 A spacecraft comprising: a propellant tank comprising a thermally-conductive wall and having a known geometry, containing a volume of liquid propellant, means of propulsion capable of exerting, according to a given thrust axis, a high thrust allowing said spacecraft to achieve an acceleration of greater than or equal to 0.05 m/s2, and supplied with liquid propellant from said propellant tank, and a heating member attached on an outer surface of said wall of the tank, wherein the spacecraft comprises at least two temperature sensors attached on said outer surface in proximity to said heating member, said temperature sensors being aligned along a so-called measurement axis parallel to said thrust axis, and each being arranged on the outer surface of the wall of the propellant tank in a position for measuring the temperature of said wall, in a plane perpendicular to said thrust axis, referred to as the plane of interest associated with said temperature sensor, in which the liquid-gas interface in said tank is likely to be located at some time during a phase of high-thrust exerted by said means of propulsion along said thrust axis, and wherein the heating member has a height, measured along said measurement axis, that is greater than the height occupied by said temperature sensors along said measurement axis, and a height of the heating member protruding beyond an end temperature sensor is greater than a distance between adjacent temperature sensors arranged along said measurement axis. ### Claim 15 (depends on 14) The spacecraft according to claim 14, wherein said temperature sensors are situated at an equal distance from said heating member. ### Claim 16 (depends on 14) The spacecraft according to claim 14, wherein the heating member has a height, measured along an axis parallel to said thrust axis, that is greater than the height occupied by said temperature sensors along said measurement axis. ### Claim 17 (depends on 14) The spacecraft according to claim 14, further comprising a second heating member, wherein the two heating members are attached to the outer surface of the wall of the tank, on opposing side of said temperature sensors and at an equal distance from said temperature sensors. ### Claim 18 (depends on 14) The spacecraft according to claim 14, comprising telemetry means suitable for transmitting the temperature values recorded by said temperature sensors to a remote receiver. ### Claim 19 (depends on 14) A system comprising: the spacecraft according to claim 14, and computing means for determining, from the temperature values recorded by at least one of said temperature sensors, a moment I at which the liquid-gas interface in the tank is located in the plane of interest associated with said temperature sensor, and the volume of liquid propellant present in the tank. ### Claim 20 (depends on 19) The system according to claim 19, wherein: the spacecraft comprises telemetry means suitable for transmitting the temperature values recorded by said temperature sensors to a remote receiver, and the system comprises the remote receiver capable of receiving the temperature values transmitted by said telemetry means of the spacecraft, and of transferring them to said computing means. ### Claim 21 (depends on 14) The spacecraft of claim 14, wherein a proximity location of the at least two temperature sensors is at a location close enough to the heating member wherein the at least two temperature sensors can measure a rise in the temperature of the wall of the tank caused by the heating of the wall by the heating member.