Autonomous spacecraft propellant gauging

Patent metadata

Field	Value
Publication number	US-11518549-B1
Application number	US-201916560840-A
Country	US
Kind code	B1
Filing date	Sep 4, 2019
Priority date	Sep 4, 2019
Publication date	Dec 6, 2022
Grant date	Dec 6, 2022

Abstract

An autonomous spacecraft propellant-gauging system, the system including a propellant tank, one or more heating devices, at least one temperature sensor and a processor. The heating devices are used to heat up the propellant tank, and the temperature sensors sense the temperature of the propellant content of the propellant tank. The processor controls operations of the heating devices and the temperature sensor. The processor further executes an algorithm to automate gauging of the propellant content of the propellant tank based on a reduced order model (ROM) and a number of parameters, and reports out an estimate of the mass of the remaining propellant of the propellant tank.

First claim

What is claimed is:

1. An autonomous space propellant gauging system, the system comprising:
a propellant tank;
one or more heating devices configured to heat up the propellant tank;
at least one temperature sensor configured to sense a temperature of propellant content of the propellant tank;
a display; and
a processor configured to:
control operations of the one or more heating devices and the at least one temperature sensor;
execute an algorithm to automate gauging of the propellant content of the propellant tank based on a reduced order model (ROM) and a plurality of parameters, wherein the ROM is derived from a detailed physics-based model by a Gaussian process, and wherein the algorithm is a machine-learning based algorithm and is used for training the ROM; and
operate the display to report out an estimate of a mass of a remaining propellant of the propellant tank.

2. The system of claim 1 , wherein the processor is configured to statistically link an accuracy of the estimate to the ROM and temperature measurements received from the at least one temperature sensor.

3. The system of claim 1 , wherein the processor is configured to fit a multidimensional curve to simulated data points and to determine a goodness of the fit.

4. The system of claim 3 , wherein the processor is configured to cause further simulations to obtain a larger set of simulated data points to improve the determined goodness of the fit, when the goodness of the fit is below a threshold.

5. The system of claim 1 , wherein the processor is configured to report out the estimate of the mass of the remaining propellant of the propellant tank periodically.

6. The system of claim 1 , wherein the processor is configured to report out the estimate of the mass of the remaining propellant of the propellant tank with a respective uncertainty and a respective confidence level.

7. The system of claim 1 , wherein the plurality of parameters includes the measured temperature of the propellant content of the propellant tank and a heat load and material properties and other design-related parameters of the propellant tank and a space vehicle.

8. The system of claim 1 , wherein the processor comprises a processor onboard a host spacecraft including the propellant tank.

9. The system of claim 1 , wherein the heating device comprises electrical heaters wrapped around at least a portion of the propellant tank.

10. A method of automatic propellant gauging of a space vehicle, the method comprising:
heating up a propellant tank including propellant content;
measuring a temperature of the propellant content by using at least one temperature sensor; and
deriving a reduced order model (ROM) from a detailed physics-based model by a Gaussian process, and wherein the algorithm is a machine-learning-based algorithm and is used for training the ROM;
executing, by a processor, an algorithm to automate gauging of the propellant content based on the ROM and a plurality of parameters; and
operating a display to report out an estimate of a mass of a remaining propellant of the propellant tank.

11. The method of claim 10 , further comprising statistically linking an accuracy of the estimate to the ROM and temperature measurements received from the at least one temperature sensor.

12. The method of claim 10 , further comprising fitting a multidimensional curve to simulated data points and to determine a fit goodness, and causing further simulations to obtain a larger set of simulated data points to improve the determined fit goodness, when the fit goodness is below a threshold.

13. The method of claim 10 , further comprising reporting out the estimate of the mass of the remaining propellant of the propellant tank with a respective uncertainty and a respective confidence level.

14. The method of claim 10 , wherein the plurality of parameters include the measured temperature of the propellant content of the propellant tank and a heat load and material properties and other design-related parameters of the propellant tank and the space vehicle.

15. A space vehicle comprising:
a propellant tank including a plurality of vanes containing a propellant and a pressurant gas;
one or more heating elements configured to heat up the propellant tank;
at least one temperature sensor configured to measure a temperature of propellant content of the propellant tank;
a display; and
a processor configured to:
control operations of the one or more heating elements and the at least one temperature sensor;
execute an algorithm to automate gauging of the propellant content of the propellant tank based on a reduced order model (ROM) and a plurality of parameters, wherein the ROM is derived from a detailed physics-based model by a Gaussian process, and wherein the algorithm is a machine-learning-based algorithm and is used for training the ROM; and
operate the display to report out an estimate of a mass of a remaining propellant of the propellant tank with a respective uncertainty and a respective confidence level.

16. The space vehicle of claim 15 , wherein the processor is further configured to fit a multidimensional curve to simulated data points and to determine a fit goodness, and to cause further simulations to obtain a larger set of simulated data points to improve the determined fit goodness, when the fit goodness is below a threshold.

17. The space vehicle of claim 15 , wherein the plurality of parameters include the measured temperature of the propellant content of the propellant tank and a heat load and material properties and other design-related parameters of the propellant tank and the space vehicle.

Assignees

• Lockheed Corp
• Lockheed Martin Cdrporation

Inventors

• Ambrose Jay Harold

Classifications

• G01F22/02

  involving measurement of pressure · CPC title

• G01F22/00

  Methods or apparatus for measuring volume of fluids or fluent solid material, not otherwise provided for · CPC title

• G01F23/246

  thermal devices · CPC title

• B64G1/36 Primary

  using sensors, e.g. sun-sensors, horizon sensors · CPC title

• G06N20/00

  Machine learning · CPC title