US 12,344,404 B2
Device for regulating the rate of flow of propellant fluid for an electric thruster
Mathieu Diome, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 16/614,135
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed May 16, 2018, PCT No. PCT/EP2018/062724
§ 371(c)(1), (2) Date Nov. 15, 2019,
PCT Pub. No. WO2018/210929, PCT Pub. Date Nov. 22, 2018.
Claims priority of application No. 1754314 (FR), filed on May 16, 2017.
Prior Publication US 2020/0148397 A1, May 14, 2020
Int. Cl. B64G 1/10 (2006.01); B64G 1/40 (2006.01); C22C 19/05 (2006.01); F03H 1/00 (2006.01)
CPC B64G 1/10 (2013.01) [B64G 1/402 (2013.01); B64G 1/413 (2023.08); C22C 19/055 (2013.01); F03H 1/0012 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A thermo-capillary device for regulating a flow rate of a propellant fluid for an electric thruster, the thermo-capillary device consisting of at least one capillary duct that is electrically conductive and regulates the flow rate of the propellant fluid under the action of a change in temperature of the at least one capillary duct,
wherein said at least one capillary duct comprises a nickel-based alloy configured to avoid oxidation of the at least one capillary duct and maintain the flow rate for a service life of the thermocapillary device,
wherein the thermo-capillary device comprises Xenon or Krypton as said propellant fluid,
wherein the at least capillary duct of the thermo-capillary device is configured to be connected to a source of electric current such that an electric current passing through the at least one capillary duct provides heating of said at least one capillary duct by Joule effect, and
wherein said at least one capillary duct is connected to an electric current source.