[특허]Propellant gauging tool for predicting propellant mass in a propellant storage volume

THE BOEING COMPANY

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Propellant gauging tool for predicting propellant mass in a propellant storage volume

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	G01F-022/00 F17C-005/06 B64G-001/10 B64G-001/24 B64G-001/40 G01N-009/00 G01N-025/00
출원번호	US-0962277 (2015-12-08)
등록번호	US-9880042 (2018-01-30)
발명자 / 주소	Core, Steven E. Novean, Michael Honda, Linton
출원인 / 주소	THE BOEING COMPANY
대리인 / 주소	Patterson + Sheridan, LLP
인용정보	피인용 횟수 : 0 인용 특허 : 6

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Apparatus, computer-readable medium, and method for calculating a mass of propellant in a propellant storage volume. A density of the propellant is calculated based on a detected pressure and temperature of the propellant and actual thermodynamic properties of the propellant. A volume of the propellant storage volume is calculated based on a measured nominal volume and changes to the nominal volume based on pressure. The mass of the propellant is calculated by multiplying the calculated volume of the propellant storage volume by the calculated density of...

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1. A satellite system, comprising: a satellite body;a propellant storage volume storing a gaseous propellant;at least one thruster operable to expel the gaseous propellant;at least one pressure transducer arranged on the propellant storage volume and operable to measure a pressure of the gaseous propellant in the propellant storage volume;at least one temperature sensor arranged on the propellant storage volume and operable to measure a temperature of the gaseous propellant in the propellant storage volume; anda controller that includes: a computer processor; andcomputer memory storing: thermodynamic property data of the gaseous propellant, wherein the thermodynamic property data provides densities of the gaseous propellant at different pressures and temperatures; andpropellant storage volume data that includes known volumes of the propellant storage volume at different pressures of the gaseous propellant;a propellant mass calculation application that, when executed on the computer processor, performs an operation for processing data, comprising: defining a volume of the propellant storage volume, based on at least one measured pressure from the pressure transducer and the propellant storage volume data;defining a density of the gaseous propellant in the propellant storage volume, based on the at least one measured pressure from the pressure transducer, at least one measured temperature from the temperature sensor, and the thermodynamic property data; andcalculating a mass of the gaseous propellant in the propellant storage volume, based on the defined volume and the defined density. 2. The satellite system of claim 1, wherein the controller sends thrust control commands to the at least one thruster, and wherein the controller is operable to send a deorbit thrust control command upon the calculated mass of the gaseous propellant in the propellant storage volume dropping below a threshold mass. 3. The satellite system of claim 1, wherein the tank volume data includes known volumes of the propellant storage volume at different temperatures of the gaseous propellant, and wherein the propellant mass calculation application defines the volume of the propellant storage volume based on a at least one measured temperature from the temperature sensor and the propellant storage volume data. 4. The satellite system of claim 1, wherein the at least one measured pressure includes an average of a plurality of measured pressures over the time interval, and wherein the at least one measured temperature includes an average of a plurality of measured temperatures over the time interval. 5. The satellite system of claim 1, wherein the propellant mass calculation application, when executed on the computer processor, performs additional operations for processing data, comprising: calculating a second mass of gaseous propellant in the propellant storage volume based on a bookkeeping method; andoutputting an alert upon the calculated second mass of gaseous propellant differing from the calculated mass of the gaseous propellant based on the defined volume and the defined density by more than a threshold amount. 6. The satellite system of claim 5, wherein the controller sends thrust control commands to the at least one thruster, and wherein the controller is operable to is configured to send a deorbit thrust maneuver control command upon: the calculated mass of the gaseous propellant in the propellant storage volume dropping below a threshold mass; andthe calculated second mass of gaseous propellant differs from the calculated mass of the gaseous propellant based on the defined volume and the defined density by less than a threshold amount. 7. The satellite system of claim 1, wherein the satellite system further comprises a second propellant storage volume storing the gaseous propellant, wherein the first and second propellant storage volumes are in fluid communication, and wherein the controller selectively operates a valve to control flow of the gaseous propellant from the second propellant storage volume to the first propellant storage volume. 8. The satellite system of claim 7, wherein the controller operates the valve to transfer gaseous propellant from the second propellant storage volume to the first propellant storage volume upon the calculated mass of gaseous propellant in the first propellant storage volume dropping below a threshold mass. 9. A method for calculating a mass of gaseous propellant in a propellant storage volume, comprising: receiving at least one measured temperature of the gaseous propellant from a temperature sensor;receiving at least one measured pressure of the gaseous propellant from a pressure transducer;defining a volume of the propellant storage volume by accessing a propellant volume data structure that provides known propellant storage volumes at different tank pressures and extracting from the tank volume data structure a volume corresponding to the received at least one measured pressure of the gaseous propellant;defining a density of the gaseous propellant in the propellant storage volume by accessing a thermodynamic property data structure that provides densities of the gaseous propellant at different pressures and temperatures and extracting from the thermodynamic property data structure a density of the gaseous propellant corresponding to the received at least one measured pressure and the at least one measured temperature; andcalculating, using a computer processor, a mass of the gaseous propellant in the propellant storage volume by calculating a product of the defined volume and the defined density. 10. The method of claim 9, further comprising sending deorbit thrust control commands to at least one thruster upon the calculated mass of the gaseous propellant in the propellant storage volume dropping below a threshold mass. 11. The method of claim 9, wherein the propellant storage volume data structure includes known volumes of the propellant storage volume at different temperatures of the gaseous propellant, and wherein the volume of the propellant storage volume is calculated by extracting from the propellant storage volume data structure a volume corresponding to the received at least one measured pressure and the at least one measured temperature. 12. The method of claim 9, wherein the at least one measured pressure includes an average of a plurality of measured pressures over a time interval, and wherein the at least one measured temperature includes an average of a plurality of measured temperatures over the time interval. 13. The method of claim 9, further comprising: calculating a second mass of gaseous propellant in the propellant storage volume based on a bookkeeping method; andoutputting an alert upon the calculated second mass of gaseous propellant differs from the calculated mass of the gaseous propellant based on the defined volume and the defined density by more than a threshold amount. 14. The method of claim 13, further comprising sending deorbit thrust control commands to at least one thruster upon: the calculated mass of the gaseous propellant in the propellant storage volume dropping below a threshold mass; andthe calculated second mass of gaseous propellant differs from the calculated mass of the gaseous propellant based on the defined volume and the defined density by less than a threshold amount. 15. A computer program product for calculating a mass of gaseous propellant in a propellant storage volume, the computer program product comprising: a computer-readable storage medium having computer-readable program code embodied therewith, the computer-readable program code executable by one or more computer processors to:receive at least one measured temperature of the gaseous propellant from a temperature sensor;receive at least one measured pressure of the gaseous propellant from a pressure transducer;define a volume of the propellant storage volume by accessing a propellant storage volume data structure that provides known propellant storage volumes at different propellant storage volume pressures and extracting from the propellant storage volume data structure a volume corresponding to the received at least one measured pressure of the gaseous propellant;define a density of the gaseous propellant in the propellant storage volume by accessing a thermodynamic property data structure that provides densities of the gaseous propellant at different pressures and temperatures and extracting from the thermodynamic property data structure a density of the gaseous propellant corresponding to the received at least one measured pressure and the at least one measured temperature; andcalculate a mass of the gaseous propellant in the propellant storage volume by calculating a product of the defined volume and the defined density. 16. The computer program product of claim 15, wherein the computer-readable program code is further executable to send deorbit thrust control commands to at least one thruster upon the calculated mass of the gaseous propellant in the propellant storage volume dropping below a threshold mass. 17. The computer program product of claim 15, wherein the propellant storage volume data structure includes known volumes of the propellant storage volume at different temperatures of the gaseous propellant, and wherein the volume of the propellant storage volume is calculated by extracting from the propellant storage volume data structure a volume corresponding to the received at least one measured pressure and the at least one measured temperature. 18. The computer program product of claim 15, wherein the at least one measured pressure includes an average of a plurality of measured pressures over a time interval, and wherein the at least one measured temperature includes an average of a plurality of measured temperatures over the time interval. 19. The computer program product of claim 15, herein the computer-readable program code is further executable to: calculate a second mass of gaseous propellant in the propellant storage volume based on a bookkeeping method; andoutput an alert upon the calculated second mass of gaseous propellant differs from the calculated mass of the gaseous propellant based on the defined volume and the defined density by more than a threshold amount. 20. The computer program product of claim 19, wherein the computer-readable program code is further executable to send deorbit thrust control commands to at least one thruster upon: the calculated mass of the gaseous propellant in the propellant storage volume dropping below a threshold mass; andthe calculated second mass of gaseous propellant differs from the calculated mass of the gaseous propellant based on the defined volume and the defined density by less than a threshold amount.

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Propellant gauging tool for predicting propellant mass in a propellant storage volume

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Propellant gauging tool for predicting propellant mass in a propellant storage volume

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