Low pressure dielectric barrier discharge plasma thruster
Some embodiments of the invention include a thruster system comprising a thruster and a pulsing power supply. The thruster may include a gas inlet port; a plasma jet outlet; and a first electrode. In some embodiments, the pulsing power supply may provide an electrical potential to the first electrode with a pulse repetition frequency greater than 10 kHz, a voltage greater than 5 kilovolts. In some embodiments, the pressure downstream from the thruster can be less than 10 Torr. In some embodiments, when a plasma is produced within the thruster by energizing a gas flowing into the thruster through the gas inlet port, the plasma is expelled from the thruster through the plasma jet outlet.
1. A thruster system comprising:
a thruster comprising:
a gas inlet port;
a plasma jet outlet; and
a first electrode; and
a pulsing power supply providing an electrical potential to the first electrode with a pulse repetition frequency greater than 10 kHz, a voltage greater than 5 kilovolts, and a downstream gas pressure of less than 10 Torr,
wherein a plasma is produced within the thruster by energizing a gas flowing into the thruster through the gas inlet port, the plasma is expelled from the thruster through the plasma jet outlet.
2. The thruster system according to claim 1 , wherein the pulsing power supply comprises a plurality of IGBTs and a transformer.
3. The thruster system according to claim 1 , wherein the pulsing power supply has a total inductance less than 100 nH.
4. The thruster system according to claim 1 , wherein the pulsing power supply has a capacitance less than 100 pF.
5. The thruster system according to claim 1 , wherein the pulsing power supply comprises a solid state pulsing power supply.
6. The thruster system according to claim 1 , wherein the pulse widths of the electrical potential are variable.
7. The thruster system according to claim 1 , wherein the pulsing power supply provides an electrical potential with rise times less than 100 nanoseconds.
8. The thruster system according to claim 1 , wherein the pulsing power supply provides an electrical potential with a pulse width less than 500 nanoseconds.
9. The thruster system according to claim 1 , wherein the thruster comprises a thruster selected from a group consisting of a dielectric free electrode thruster, a dielectric barrier discharge device, a dielectric barrier discharge-like device, and a single electrode thruster.
10. The thruster system according to claim 1 , wherein the pulsing power supply is configured to produce variable and/or controllable pulse widths between 20 to 500 nanoseconds.
11. The thruster system according to claim 1 , wherein the first electrode comprises a ring electrode.
12. The thruster system according to claim 11 , further comprising a second ring electrode electrically coupled with the pulsing power supply.
13. The thruster system according to claim 1 , wherein the thruster system comprises a dielectric tube.
14. The thruster system according to claim 1 , wherein the first electrode comprises a tube electrode.
15. The thruster system according to claim 1 , wherein the thruster system comprises:
a dielectric tube having a gas inlet and a jet outlet; and
two ring electrodes surrounding the dielectric tube, wherein the two ring electrodes are electrically coupled with the pulsing power supply.
16. The thruster system according to claim 1 , wherein the thruster system produces a plasma at input propellant flow rates of less than 50,000 SCCM.
17. The thruster system according to claim 1 , wherein the pulsing power supply is configured to produce a variable and/or controllable current output up to 200 A.