Two-stage low-power and high-thrust to power electric propulsion system

Patent metadata

Field	Value
Publication number	US-12044220-B2
Application number	US-202117802468-A
Country	US
Kind code	B2
Filing date	Feb 22, 2021
Priority date	Feb 26, 2020
Publication date	Jul 23, 2024
Grant date	Jul 23, 2024

Abstract

A satellite propulsion system and methods of operating the same include a first ionization stage and a second acceleration stage. The first ionization stage has a plasma source configured to produce an arc discharge and emit a preliminary plasma. The plasma source includes an external magnetic field configured to magnetize the arc discharge. The second acceleration stage has an accelerator positioned in series with the plasma source. The accelerator is configured to accelerate the preliminary plasma out through the accelerator, thereby creating an accelerated plasma flow. The application of an activation threshold voltage to the accelerator results in a surge in system performance parameters.

First claim

What is claimed is:

1. A satellite propulsion system, comprising:
a first ionization stage comprising a vacuum plasma source configured to produce a vacuum arc discharge and emit a preliminary ionized plasma, the plasma source including an external magnetic field configured to magnetize the arc discharge;
a second acceleration stage comprising a pulsed electromagnetic Lorentz accelerator positioned in series with the plasma source, the accelerator being configured to accelerate the preliminary plasma out through the accelerator using a pulsed electromagnetic Lorentz force, thereby creating an accelerated plasma flow; and
wherein application of an activation threshold voltage to the accelerator results in a surge in system performance parameters as a result of the pulsed electromagnetic Lorentz force.

2. The system of claim 1 , wherein the system performance parameters include one or more of thrust, thrust-to-power ratio, and system efficiency.

3. The system of claim 1 , wherein the plasma source has an output for emitting the preliminary plasma; and the accelerator is positioned near the output to receive the preliminary plasma emitted from the plasma source.

4. The system of claim 1 , wherein the accelerator is an electrode.

5. The system of claim 4 , wherein the electrode is a metal cone that has an inlet opening and an outlet opening, the inlet opening is configured to receive the preliminary plasma and the metal cone is configured to accelerate the plasma flow through the outlet opening.

6. The system of claim 1 , wherein the magnetic field is created by a magnet positioned at an interface of the plasma source and the accelerator.

7. The system of claim 6 , wherein the magnet is a magnetic ring.

8. The system of claim 1 , wherein the activation threshold voltage triggers said second acceleration stage.

9. The system of claim 1 , wherein acceleration of the preliminary plasma by the accelerator occurs due to an electromagnetic Lorentz force.

10. The system of claim 1 , wherein the plasma source comprising a cathode surrounded by an anode with an insulator therebetween.

11. The system of claim 1 , wherein the preliminary plasma is fully ionized.

12. The system of claim 1 , wherein the system is configured for low-power consumption.

13. A low-power plasma thruster, comprising:
a vacuum plasma source having an outlet for emitting plasma;
a pulsed electromagnetic Lorentz accelerator electrode positioned in series with the plasma source, the accelerator electrode having an inlet positioned near the outlet of the plasma source for receiving the plasma; and
means for increasing performance parameters of the thruster via application of a threshold voltage to the thruster as a result of the pulsed electromagnetic Lorentz accelerator electrode.

14. The thruster of claim 13 , wherein the threshold voltage is 30 Volts.

15. The thrust of claim 13 , wherein the accelerator electrode is a metal cone.

16. A method of operating a propulsion system, comprising the steps of:
energizing the propulsion system to produce a preliminary ionized plasma using low power, the preliminary plasma having a vacuum arc discharge;
applying a magnetic field to the arc discharge of the preliminary plasma;
accelerating the preliminary plasma using a pulsed electromagnetic Lorentz accelerator to create an accelerated plasma flow; and
applying a threshold voltage to create a surge in performance parameters.

17. The method of claim 16 , wherein the step of accelerating the preliminary plasma includes use of an accelerator electrode that receives the preliminary plasma.

18. The method of claim 17 , wherein the threshold voltage is applied to the accelerator electrode.

19. The method of claim 16 , wherein the threshold voltage is 30 Volts.

20. The method of claim 16 , wherein the performance parameters of the system include one or more of thrust, thrust-to-power ratio, and system efficiency.

Assignees

• Univ George Washington

Inventors

• Keidar Michael
• Zolotukhin Denis
• Bandaru Siva Ram Prasad

Classifications

• B64G1/415

  Arcjets or resistojets · CPC title

• B64G1/411

  Electric propulsion · CPC title

• B64G1/413

  Ion or plasma engines · CPC title

• F03H1/0068 Primary

  with a central channel, e.g. end-Hall type · CPC title

• F03H1/0081 Primary

  Electromagnetic plasma thrusters · CPC title