Propellant gauging at microgravity within the pressure-temperature-density inflection zone of xenon
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02K-009/44
B64G-001/40
G01N-009/36
G01G-009/00
B64G-001/22
출원번호
US-0137945
(2016-04-25)
등록번호
US-10018546
(2018-07-10)
발명자
/ 주소
Honda, Linton Kaneki
Core, Steven Edward
McDonald, Gregory Cardon
출원인 / 주소
The Boeing Company
대리인 / 주소
Hanley, Flight & Zimmerman, LLC
인용정보
피인용 횟수 :
0인용 특허 :
9
초록▼
A method that is stored in tangible form and accessible by a data processing system for determination of xenon propellant remaining in a tank for a defined life condition. A heater controller establishes a first stable temperature of a propellant tank. A measurement is performed of a temperature and
A method that is stored in tangible form and accessible by a data processing system for determination of xenon propellant remaining in a tank for a defined life condition. A heater controller establishes a first stable temperature of a propellant tank. A measurement is performed of a temperature and a pressure at the first stable temperature of the propellant tank. A second higher stable temperature is provided in the propellant tank. A measurement is performed of a temperature and a pressure at a second stable temperature. A computer processor computes a mass based on density and volume in accordance with measurements of temperature and pressure at the first stable temperature and the second stable temperature.
대표청구항▼
1. A method comprising: heating, with a heater, a propellant stored in a tank to a first stable temperature at a first time and to a second stable temperature at a second time;measuring, with a pressure sensor and a temperature sensor, a first pressure and a first temperature, respectively, of the p
1. A method comprising: heating, with a heater, a propellant stored in a tank to a first stable temperature at a first time and to a second stable temperature at a second time;measuring, with a pressure sensor and a temperature sensor, a first pressure and a first temperature, respectively, of the propellant in a non-ideal gas zone while the propellant is at the first stable temperature at the first time;measuring, with the pressure sensor and the temperature sensor, a second pressure and a second temperature, respectively, of the propellant in the non-ideal gas zone while the propellant is at the second stable temperature at the second time; anddetermining, by executing an instruction with a processor, based on a differential pressure between the first pressure and the second pressure and a differential temperature between the first temperature and the second temperature, a mass of the propellant in the tank. 2. The method of claim 1, wherein the determining of the mass of the propellant includes comparing the differential pressure and the differential temperature to a table relating mass to temperature differentials as a function of pressure differentials. 3. The method of claim 1, wherein the propellant is xenon. 4. The method of claim 1, wherein the first time is a period of time, and the first pressure and the first temperature are an average pressure and an average temperature over the period of time. 5. The method of claim 4, wherein the period of time is approximately 48 hours. 6. The method of claim 1, wherein the tank is a propellant tank of a satellite thruster. 7. A spacecraft thruster comprising: a tank having a propellant;a pressure sensor and a temperature sensor disposed in the tank, the pressure sensor and the temperature sensor to measure (1) a first pressure and a first temperature of the propellant in a non-ideal gas zone while the propellant is at a first hold temperature at a first time, and (2) a second pressure and a second temperature of the propellant in the non-ideal gas zone while the propellant is at a second hold temperature at a second time; anda processor to determine a mass of the propellant in the tank based on the first pressure, the first temperature, the second pressure and the second temperature. 8. The spacecraft thruster of claim 7, wherein the processor is to determine the mass based a difference between the first pressure and the second pressure and a difference between the first temperature and the second temperature. 9. The spacecraft thruster of claim 7 further including a heater disposed in the tank. 10. The spacecraft thruster of claim 9, wherein the processor is to control the heater to maintain the propellant at the first hold temperature. 11. The spacecraft thruster of claim 10, wherein the processor is to control the heater to maintain the propellant at the second hold temperature. 12. The spacecraft thruster of claim 7, wherein the propellant is xenon. 13. A non-transitory machine readable storage medium comprising instructions that, when executed, cause a machine to at least: adjust, using a heater controller, a temperature of a propellant stored in a tank of a satellite thruster to a first stable temperature at a first time and to a second stable temperature at a second time;measure, using a pressure sensor and a temperature sensor, a first pressure and a first temperature, respectively, of the propellant in a non-ideal gas zone while the propellant is at the first stable temperature at the first time;measure, using the pressure sensor and the temperature sensor, a second pressure and a second temperature, respectively, of the propellant in the non-ideal gas zone while the propellant is at the second stable temperature at the second time; anddetermine, based on a differential pressure between the first temperature and the second temperature and a differential temperature between the first temperature and the second temperature, a mass of the propellant in the tank. 14. The non-transitory machine readable storage medium of claim 13, wherein the instructions, when executed, cause the machine to compare the differential pressure and the differential temperature to a table relating mass to temperature differentials as a function of pressure differentials to determine the mass of the propellant. 15. The non-transitory machine readable storage medium of claim 13, wherein the first time is a first period of time, and the first pressure and the first temperature are an average pressure and an average temperature over the first period of time. 16. The non-transitory machine readable storage medium of claim 13, wherein the second time is a second period of time, and the second pressure and the second temperature are an average pressure and an average temperature over the second period of time. 17. The non-transitory machine readable storage medium of claim 13, wherein the propellant is xenon.
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이 특허에 인용된 특허 (9)
Piacente Robert A. (Schenetady NY) Madulka Karol Anne Liu (Ballston Spa NY) Kenna John M. (Rensselaer NY), Ammunition propellant temperature measuring assembly.
Brauer Laura E. (Lawrence Township ; Mercer County NJ) Chun Siu H. (Langhorne PA) Davies Keith (Robbinsville NJ) Pulkowski Joseph A. (East Amwell Township ; Hunterdon County NJ), Method for measuring the mass of liquid in a storage tank.
Hasselmann Detlev E. M. (519 S. Nardo Ave. Solana Beach CA 92075), System and method for automatically monitoring liquid volume changes in storage tanks.
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