Bi-modal micro cathode arc thruster

Patent metadata

Field	Value
Publication number	US-10107271-B2
Application number	US-201414825356-A
Country	US
Kind code	B2
Filing date	Feb 17, 2014
Priority date	Feb 17, 2013
Publication date	Oct 23, 2018
Grant date	Oct 23, 2018

Abstract

A thruster for a micro-satellite is disclosed. The thruster includes a voltage source, an inductor and a resistor. A switching device is coupled to the inductor and the resistor. The thruster includes an exterior electrode composed of a first propellant, an insulator located coaxially within the exterior electrode and an interior electrode composed of a second propellant located coaxially to the insulator and the exterior electrode. An exterior housing has a proximate end and an opposite distal end with a thrust channel. The exterior housing holds the exterior electrode, the insulator and the interior electrode. The switching device is coupled to either the exterior electrode or the interior electrode. The switching device is switched to pulse voltage from the inductor to create an arc between the exterior electrode and the interior electrode. Either the exterior electrode or the interior electrode may serve as a cathode to generate a plasma jet.

First claim

What is claimed is:

1. A thruster for a micro-satellite, the thruster comprising:
a voltage source;
an inductor having a first input coupled to the voltage source and a second input;
a resistor;
a switching device coupled to the second input of the inductor and the resistor;
a substantially tubular exterior electrode composed of a first propellant material;
a substantially tubular insulator located coaxially within the exterior electrode;
a substantially tubular interior electrode composed of a second propellant material located coaxially to the insulator and the exterior electrode;
an exterior housing having a proximate end and an opposite distal end having a thrust channel, the exterior housing holding the exterior electrode, the insulator and the interior electrode; and
wherein the switching device is operable to be switched between being coupled in a first circuit to the exterior electrode and being coupled to a second circuit to the interior electrode, wherein the switching device is switched to pulse voltage from the inductor to create an arc between the exterior electrode and the interior electrode, and wherein the exterior electrode serves as a cathode to generate a plasma jet through the thrust channel when coupled to the switching device in the first circuit and the interior electrode serves as a cathode to generate a plasma jet through the thrust channel when coupled to the switching device in the second circuit.

2. The thruster system of claim 1 , wherein the exterior electrode and the interior electrode are different materials.

3. The thruster system of claim 1 , wherein the first and second propellant material are one of a group of carbon, aluminum, titanium, chromium, iron, yttrium, molybdenum, tantalum, tungsten, lead, nickel or bismuth.

4. The thruster system of claim 1 , further comprising an annular magnet attached around the thrust channel producing a magnetic field to channel the plasma jet.

5. The thruster system of claim 1 , further comprising a controller coupled to the switching device.

6. The thruster system of claim 5 , wherein the controller controls thrust by changing the pulse output to the switching device.

7. The thruster system of claim 5 , wherein the controller controls thrust by selecting the exterior electrode or interior electrode as the cathode.

8. The thruster system of claim 1 , further comprising:
an exterior biasing member to force the exterior electrode to the distal end of the exterior housing; and
an interior biasing member to force the interior electrode to the distal end of the exterior housing.

9. The thruster system of claim 1 , wherein the tubular insulator has interior and exterior surfaces coated with a conductive film layer, the conductive film layer in proximity to the respective exterior and interior electrodes.

10. A thruster for a micro-satellite, the thruster comprising:
a voltage source;
an inductor having a first input coupled to the voltage source and a second input;
a resistor;
a switching device coupled to the second input of the inductor and the resistor;
a substantially tubular exterior electrode composed of a first propellant material;
a substantially tubular insulator located coaxially within the exterior electrode;
a substantially tubular interior electrode composed of a second propellant material located coaxially to the insulator and the exterior electrode;
an exterior housing having a proximate end and an opposite distal end having a thrust channel, the exterior housing holding the exterior electrode, the insulator and the interior electrode;
a controller coupled to the switching device; and
wherein the switching device is coupled to either the exterior electrode or the interior electrode and the switching device is switched to pulse voltage from the inductor to create an arc between the exterior electrode and the interior electrode, wherein the exterior electrode serves as a cathode to generate a plasma jet through the thrust channel when coupled to the switching device and the interior electrode serves as a cathode to generate a plasma jet through the thrust channel when coupled to the switching device, and wherein the controller controls thrust by selecting the exterior electrode or interior electrode as the cathode.

Assignees

• Univ George Washington

Inventors

• Keidar Michael
• Chiu Dereck
• Zhuang Taisen
• Teel George
• Shashurin Alexy

Classifications

• F03H1/0081 Primary

  Electromagnetic plasma thrusters · CPC title

• B64G1/10

  Artificial satellites; Systems of such satellites; Interplanetary vehicles (space shuttles B64G1/14) · CPC title

• F03H1/0087

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

• B64G1/405

  Operations & Transport · mapped topic

• B64G1/406

  Operations & Transport · mapped topic