Air-breathing plasma thruster

Patent metadata

Field	Value
Publication number	US-12325537-B2
Application number	US-202318374941-A
Country	US
Kind code	B2
Filing date	Sep 29, 2023
Priority date	Sep 29, 2023
Publication date	Jun 10, 2025
Grant date	Jun 10, 2025

Abstract

One or more embodiments relates to an air-breathing plasma thruster including a thruster wall, an anode, a cathode, and at least one ring electrode. The thruster wall defines a cylindrical channel, the cylindrical channel having a first end and an opposing second end in fluid communication with the first end, where the cylindrical channel is adapted to receive incoming airflow. The anode is at the first end of the channel and the cathode is at the second end of the channel opposite the first end. The at least one ring electrode is positioned on the thruster wall.

First claim

What is claimed is:

1. An air-breathing plasma thruster comprising:
a thruster wall defining a cylindrical channel, the cylindrical channel having a first end and an opposing second end in fluid communication with the first end, the cylindrical channel adapted to receive incoming airflow;
an anode at the first end of the cylindrical channel;
a cathode at the second end of the cylindrical channel opposite the first end; and
at least one additional, intermediate electron-emitting electrode positioned on the thruster wall.

2. The air-breathing plasma thruster of claim 1 wherein the at least one, additional intermediate electrode is selected from the group consisting of a ring electrode, a semi-ring electrode, a non-ring electrode, and combinations thereof.

3. The air-breathing plasma thruster of claim 1 wherein the at least one, additional intermediate electrode is positioned proximate the first end.

4. The air-breathing plasma thruster of claim 1 wherein the at least one, additional intermediate electrode is biased positive.

5. The air-breathing plasma thruster of claim 1 wherein at least the anode is biased positive.

6. The air-breathing apparatus of claim 1 wherein the first end is an inlet having the anode and the at least one, additional intermediate electrode is at least one ring electrode proximate thereto and the second end is an outlet having the cathode proximate thereto.

7. The air-breathing apparatus of claim 1 wherein the second end is an outlet having the cathode and the at least one, additional intermediate electrode is at least one ring electrode proximate thereto and the first end is an inlet having the anode proximate thereto.

8. The air-breathing plasma thruster of claim 1 further comprising a plurality of ring electrodes positioned on the thruster wall and biased negative with respect to the anode.

9. The air-breathing plasma thruster of claim 8 wherein a bias voltage is applied to the plurality of ring electrodes wherein the bias voltage is selected from the group consisting of a DC bias, an RF bias, a pulsed bias, and a combination of a DC-RF and pulsed bias.

10. The air-breathing plasma thruster of claim 8 wherein at least one of the plurality of electrodes is the electron-emitting electrode.

11. The air-breathing plasma thruster of claim 10 wherein the electron-emitting electrode is selected from the group consisting of ion-induced secondary electron emission electrodes, thermionic emission electrodes, field emission electrodes and plasma cathodes.

12. The air-breathing plasma thruster of claim 8 further comprising an extra bias applied to the plurality of ring electrodes, wherein the extra bias is configured to control electron flow between the electrodes and plasma flow in the channel.

13. The air-breathing plasma thruster of claim 1 wherein the cylindrical chamber is longer than an ionization mean free path for electrons to ionize incoming air flow.

14. The air-breathing plasma thruster of claim 13 wherein the ionization mean free path has a length.

15. A satellite having an air-breathing plasma thruster, the air-breathing plasma thruster comprising:
a thruster wall having a plurality of magnetic fields formed therein and defining a cylindrical channel, the cylindrical channel having a first end and an opposing second end in fluid communication with the first end, the cylindrical channel adapted to receive an incoming airflow;
an anode proximate the first end;
a cathode proximate the second end;
at least one exit ring electrode biased positive and positioned on the thruster wall between the anode and the cathode; and
a plurality of ring electrodes biased negative with respect to the anode and positioned on the thruster wall between the at least one exit electrode and the anode.

16. The satellite of claim 15 wherein the first end is an inlet having the anode and at least one ring electrode of the plurality of ring electrodes proximate thereto and the second end is an outlet having the cathode proximate thereto.

17. The satellite of claim 15 wherein the second end is an outlet having the cathode and at least one ring electrode proximate to the second end and the first end is an inlet having the anode proximate thereto.

18. The satellite of claim 15 wherein the anode is biased positive and the plurality of ring electrodes are biased negative with respect to the anode.

19. The satellite of claim 15 , wherein the satellite is adapted to operate at very low orbits at an altitude below 250 km.

20. The satellite of claim 19 wherein the satellite is adapted to operate at very low orbits between 70 and 250 km.

21. A method of forming a plasma jet using an air-breathing plasma thruster, the method comprising:
receiving incoming air flow in a cylindrical channel defined by the inside wall of the air-breathing thruster, forming a volume of air;
ionizing the volume of air using electron beams generated by cathodes and confined by segmented electrodes and one or more magnetic field cusps, forming ionized air;
accelerating the ionized air using applied electric and diverging magnetic fields, forming a plasma jet; and
generating the plasma jet at an outlet of the air-breathing thruster.

Assignees

• Us Energy
• Us Dept Energy

Inventors

• Raitses Yevgeny

Classifications

• F03H1/0068

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

• B64G1/411

  Electric propulsion · CPC title

• F03H1/0093

  Electro-thermal plasma thrusters, i.e. thrusters heating the particles in a plasma (resistojets per se B64G1/415) · CPC title

• F03H1/0087

  Electro-dynamic thrusters, e.g. pulsed plasma thrusters · CPC title

• F03H1/0081

  Electromagnetic plasma thrusters · CPC title