High propellant throughput hall-effect thrusters

Patent metadata

Field	Value
Publication number	US-11540381-B1
Application number	US-202016932023-A
Country	US
Kind code	B1
Filing date	Jul 17, 2020
Priority date	Jul 19, 2019
Publication date	Dec 27, 2022
Grant date	Dec 27, 2022

Abstract

High propellant throughput Hall-effect thrusters (HETs) and components thereof are disclosed. A compact and high propellant throughput HET has an improved magnetic circuit that mostly shields the discharge chamber walls from high-energy ionized propellant, low-profile sacrificial pole covers to delay magnetic pole erosion, a unique discharge chamber subassembly, a mechanically crimped cathode emitter retainer to increase efficiency, a center-mounted hollow cathode, or a combination thereof. Such feature(s) may balance propellant throughput and thruster performance, minimize the volume of the thruster envelope, and/or simplify the thruster assembly.

First claim

The invention claimed is:

1. A Hall-effect thruster (HET), comprising:
a discharge chamber comprising a wall;
an inner front pole;
an outer front pole located radially outward from the inner front pole;
an inner screen located at least partially below the inner front pole;
an outer screen located at least partially below the outer front pole; and
a back pole located below the inner front pole and the outer front pole;
an inner front pole cover comprising an orifice; and
a cathode keeper orifice plate comprising an orifice, wherein
the orifice of the inner front pole cover is at least a size equal to the orifice of the cathode keeper orifice plate, but smaller than an outside diameter of the cathode keeper orifice plate;
an inner magnet winding located radially inside the inner screen; and
an outer magnet winding located radially outside the outer screen, wherein
the inner front pole, the outer front pole, the inner screen, the outer screen, the back pole, the inner magnet winding, and the outer magnet winding collectively form a magnetic circuit configured to provide a magnetic field topology, and
the magnetic field topology is configured to provide a magnetic field that partially intersects with a downstream end of the wall of the discharge chamber of the HET such that some ions generated in the discharge chamber of the HET contact the downstream end of the wall of the discharge chamber.

2. The HET of claim 1 , wherein
the discharge channel comprises a chamfer at the downstream end of the wall of the discharge chamber, and
erosion of the discharge chamber from the ions occurs at the chamfer.

3. The HET of claim 2 , wherein the chamfer does not exist in the discharge chamber initially and forms during operation of the HET.

4. The HET of claim 1 , further comprising:
an anode, wherein
the ions contacting the downstream end of the wall of the discharge chamber are not at a potential of the anode of the HET.

5. The HET of claim 1 , wherein an interface between the inner front pole and the inner front pole cover, an interface between the outer front pole and the outer front pole cover, or both, are stepped in an upstream direction.

6. The HET of claim 1 , further comprising:
a discharge chamber subassembly comprising an annular discharge chamber back plate located between the discharge chamber and the back pole, wherein
the discharge chamber further comprises an anode/propellant manifold,
the anode/propellant manifold is affixed to and electrically isolated from the annular discharge chamber back plate, and
the discharge chamber is affixed to the back pole via the annular discharge chamber back plate.

7. The HET of claim 1 , further comprising:
a cathode subassembly, comprising:
a cathode tube, and
an emitter and an emitter retainer located within the cathode tube, wherein

the cathode tube is crimped or swaged around the emitter retainer at one or more locations along a length of the emitter retainer.

8. The HET of claim 7 , wherein the emitter retainer comprises a porous material configured to function as a propellant filter, a getter material for chemical contaminants in the propellant, or both.

9. A Hall-effect thruster (HET), comprising:
an inner front pole;
an outer front pole located radially outward from the inner front pole;
an inner front pole cover that covers and protects the inner front pole; and
an outer front pole cover that covers and protects the outer front pole, wherein
an end of the inner front pole cover, an end of the outer front pole cover, or both, are substantially coplanar with an exit plane of a discharge chamber of the HET in a downstream direction with respect to an emission of ions from the HET; and
the inner front pole cover comprises a thickened section that extends radially inward into a corresponding recess in the inner front pole, the outer front pole cover comprises a thickened section that extends radially inward into a corresponding recess in the outer front pole, or both.

10. The HET of claim 9 , wherein a downstream face of the inner front pole cover, the outer front pole cover, or both, is flat.

11. The HET of claim 9 , further comprising:
a cathode keeper orifice plate comprising an orifice, wherein
the inner front pole cover comprises an orifice, and
the orifice of the inner front pole cover is at least a size equal to the orifice of the cathode keeper orifice plate, but smaller than an outside diameter of the cathode keeper orifice plate.

12. A cathode subassembly, comprising:
a cathode tube; and
an emitter and an emitter retainer located within the cathode tube;
a spring located between the emitter and the emitter retainer within the cathode tube; and
a cathode tube orifice plate;
wherein:
the cathode tube is crimped or swaged around the emitter retainer at one or more locations along a length of the emitter retainer and the spring presses the emitter against the cathode tube orifice plate.

13. The cathode subassembly of claim 12 , wherein the emitter retainer comprises a porous material configured to function as a propellant filter, a getter material for chemical contaminants in the propellant, or both.

14. A Hall-effect thruster (HET), comprising:
a cathode subassembly, comprising:
a cathode tube, and
an emitter and an emitter retainer located within the cathode tube,
a spring located between the emitter and the emitter retainer within the cathode tube; and
a cathode tube orifice plate; wherein

the cathode tube is crimped or swaged around the emitter retainer at one or more locations along a length of the emitter retainer, and the spring presses the emitter against the cathode tube orifice plate
a discharge chamber comprising a wall;
an inner front pole;
an outer front pole located radially outward from the inner front pole;
an inner screen located at least partially below the inner front pole;
an outer screen located at least partially below the outer front pole; and
a back pole located below the inner front pole and the outer front pole;
an inner magnet winding located radially inside the inner screen; and
an outer magnet winding located radially outside the outer screen, wherein
the inner front pole, the outer front pole, the inner screen, the outer screen, the back pole, the inner magnet winding, and the outer magnet winding collectively form a magnetic circuit configured to provide a magnetic field topology, and
the magnetic field topology is configured to provide a magnetic field that partially intersects with a downstream end of the wall of the discharge chamber of the HET such that some ions generated in the discharge chamber of the HET contact the downstream end of the wall of the discharge chamber.

15. A Hall-effect thruster (HET), comprising:
an inner front pole;
an outer front pole located radially outward from the inner front pole;
an inner front pole cover that covers and protects the inner front pole; and
an outer front pole cover that covers and protects the outer front pole, wherein
an end of the inner front pole cover, an end of the outer front pole cover, or both, are substantially coplanar with an exit plane of a discharge chamber of the HET in a downstream direction with respect to an emission of ions from the HET; and
a cathode keeper orifice plate comprising an orifice, wherein
the inner front pole cover comprises an orifice, and
the orifice of the inner front pole cover is at least a size equal to the orifice of the cathode keeper orifice plate, but smaller than an outside diameter of the cathode keeper orifice plate.

16. The H

Assignees

• Nasa

Inventors

• Benavides Gabriel F
• Kamhawi Hani
• Verhey Timothy R

Classifications

• F03H1/0081

  Electromagnetic plasma thrusters · CPC title

• H01J27/022

  Details · CPC title

• H05H7/04 Primary

  Magnet systems {, e.g. undulators, wigglers (free-electron laser H01S3/0903)}; Energisation thereof · CPC title

• F03H1/0075

  with an annular channel; Hall-effect thrusters with closed electron drift · CPC title

• H05H1/54 Primary

  Plasma accelerators · CPC title