Flow regulating system for supplying propellant fluid to an electric thruster of a space vehicle

Patent metadata

Field	Value
Publication number	US-9828975-B2
Application number	US-201415103240-A
Country	US
Kind code	B2
Filing date	Dec 9, 2014
Priority date	Dec 11, 2013
Publication date	Nov 28, 2017
Grant date	Nov 28, 2017

Abstract

A system for regulating the flow rate of a propellant fluid for an electrical thruster of a space vehicle, the vehicle including a tank of propellant fluid and a flow rate regulator connected to the outlet of said tank;
the flow rate regulator including a heater element controlled by a computer and adapted to heat the propellant fluid and to modify its physical properties so as to vary the flow rate of propellant fluid leaving the tank;
said system being characterized in that the computer also includes a plurality of empirical calibration curves that have been determined empirically for defining the flow rate of propellant fluid as a function of the magnitude of heating and as a function of environmental parameters, such that said computer also performs a function of determining the flow rate of the propellant fluid.

First claim

The invention claimed is:

1. A system for regulating a flow rate of a propellant fluid of a space vehicle, said system comprising:
an electrical thruster
a tank of propellant fluid and
a flow rate regulator connected to an outlet of said tank;
wherein said flow rate regulator further includes
a heater element controlled by a computer and configured to heat said propellant fluid and
modify said propellant fluid physical properties to vary said flow rate of said propellant fluid leaving said tank;

wherein said computer further includes a storage memory having loaded therein a plurality of empirical calibration curves that define said flow rate of said propellant fluid as a function of magnitude of heating and as a function of environmental parameters, so that said computer also determines said flow rate of said propellant fluid.

2. The system according to claim 1 , wherein said plurality of empirical calibration curves are determined during ground testing of said system under various environmental parameters.

3. The system according to claim 1 , wherein said computer has a plurality of semi-empirical calibration curves are calculated on the basis of said plurality of empirical calibration curves, said semi-calibration curves defining said flow rate of said propellant fluid as a function of magnitude of heating for environmental parameters that are different from those of said plurality of empirical calibration curves.

4. The system according to claim 1 , wherein said computer is configured to use said plurality of empirical calibration curves to calculate a semi-empirical calibration curve defining said flow rate of said propellant fluid as said function of magnitude of heating and as said function of environmental parameters.

5. The system according to claim 1 , wherein said heater element is a thermocapillary tube providing heating as a function of magnitude of heating current flowing through said thermocapillary tube.

6. The system according to claim 1 , wherein said propellant fluid is xenon.

7. A method of regulating a flow rate at which propellant fluid is fed to an electrical thruster of a space vehicle by means of a flow rate regulator, wherein said flow rate regulator further includes a heater element controlled by a computer, said method comprising:
heating, via said heater element, said propellant fluid at an outlet from a tank
modifying said propellant fluid physical properties to vary said flow rate of said propellant fluid leaving said tank;
regulating, via said flow rate regulator, said flow rate at which said propellant fluid is fed to said electrical thruster, wherein a plurality of empirical calibration curves define said propellant fluid rate as a function of magnitude of heating and as a function of environmental parameters, said plurality of empirical calibration curves being loaded into the computer so that said computer also performs a function of determining said flow rate of said propellant fluid.

8. The method according to claim 7 , wherein determining said plurality of empirical calibration curves during ground testing a system under various environmental parameters.

9. The method according to claim 7 , wherein determining a plurality of semi-empirical calibration curves by interpolation from said plurality of empirical calibration curves; and
loading a plurality of theoretical calibration curves into said computer.

10. The method according to claim 7 , wherein while using said flow rate regulator, said computer calculating a semi-empirical calibration curve defining said flow rate of said propellant fluid as said function of the magnitude of heating and as said function of environmental parameters based on said plurality of empirical calibration curves.

Assignees

• Snecma

Inventors

• Vial Vanessa
• Lorand Anthony
• Giboudeaux Kevin
• Leroi Vaitua

Classifications

• F03H1/0012 Primary

  Means for supplying the propellant · CPC title

• F03H1/0031

  Thermal management, heating or cooling parts of the thruster (temperature control for cosmonautic vehicles B64G1/50) · CPC title

• F03H1/0062

  grid-less with an applied magnetic field · CPC title

• B64G1/402 Primary

  Propellant tanks; Feeding propellants · CPC title

• B64G1/405

  Operations & Transport · mapped topic