Plasma propellant ablation/sublimation based systems

Patent metadata

Field	Value
Publication number	US-10047731-B2
Application number	US-201514735774-A
Country	US
Kind code	B2
Filing date	Jun 10, 2015
Priority date	Apr 6, 2015
Publication date	Aug 14, 2018
Grant date	Aug 14, 2018

Abstract

Systems and methods for improving plasma propellant ablation/sublimation based systems are provided. One set of embodiments provides systems and methods for reducing carbon charring during plasma system (e.g., a plasma coating application system) propellant (e.g., a carbon-fluorine polymer) ablation and increasing heat transfer, ablation, and plasma thrust from plasma systems. In particular, one embodiment can include using a nano or micro-sized magnetic or electromagnetic field responsive material as particulates or microcapsules that are intermixed with polytetrafluoroethylene (e.g., Teflon®) nano-fibers, and using resulting fiber composites as the propellant material. Embodiments can include improved plasma system, e.g., pulsed plasma thrusters, plasma torches, plasma coating systems, etc, as well as nozzle improvements such as embodiments with magnetic structures disposed in relation to the nozzle. Alternative embodiments also include recovery and reuse systems.

First claim

The invention claimed is:

1. A pulsed plasma thruster system, said system including: a plasma reaction chamber comprising a cathode, a nozzle formed with an exit, and an anode, wherein said pulsed plasma thruster system is configured to generate an electrical potential difference that is applied between said anode and said cathode; a propellant disposed within said plasma reaction chamber, wherein said propellant is located between said anode and said cathode between an area where the electrical potential difference is generated, wherein said propellant includes a polymer that is carbon-fluorine based, wherein said propellant further includes particles with an electrical conductivity greater than an electrical conductivity of said polymer, wherein said electrical potential difference causes an electric current to flow across a surface of said propellant, wherein said electric current ablates said propellant and creates a carbon-fluorine plasma, wherein said carbon-fluorine plasma includes said particles; and
a section for transferring the particles back to a storage/reuse chamber comprising electromagnetic field drift tube sections as well as fan systems.

2. The pulsed plasma thruster system of claim 1 , wherein said particles increase the current density in said carbon-fluorine plasma.

3. The pulsed plasma thruster system of claim 1 , wherein said polymer includes polytetrafluoroethylene.

4. The pulsed plasma thruster system of claim 1 , wherein said particles include magnetic compounds.

5. The pulsed plasma thruster system of claim 1 , wherein said particles include metal powder.

6. The pulsed plasma thruster system of claim 1 , further comprising a plurality of magnets attached around an inner diameter of said nozzle.

7. The pulsed plasma thruster system of claim 1 , further comprising one or more electromagnetic field generating sections along a thrust path of the carbon-fluorine plasma from ablation to the exit that which is configured for selectively generating an applied electric field that applies a propulsive force to the carbon-fluorine plasma and the particles to increase or adjust speed of the carbon-fluorine plasma towards the exit and push carbon-fluorine plasma and the particles away from the anode/cathodes.

8. The pulsed plasma thruster system of claim 1 , further comprising a pulsed plasma thruster system control system section configured for adjusting operation of the pulsed plasma thruster system so that the pulsed plasma thruster system operates or ablates the propellant on an intermittent basis operable for adjusting plasma output applied to a work piece in a manner that configured for intermittent or selective application of the plasma output.

9. The pulsed plasma thruster system of claim 1 , further comprising a nano or micro particle injector configured to inject one or more additional or different said particles into said carbon-fluorine plasma so as to vary particle content of the carbon-fluorine plasma during and after ablation which adjusts particle type and concentration.

10. The pulsed plasma thruster system of claim 1 , further comprising a scoop and recovery system section which pulls or manipulates the particles out of the thrust path and then recycles the particles by routing the particles back to the plasma thrust chamber which then permits reuse of the particles.

11. A method of a providing and operating a pulsed plasma thruster system comprising: providing a plasma generation system comprising an anode, cathode, voltage source, nozzle, and plasma reaction chamber that said anode, cathode, voltage source, and said nozzle are coupled with and connected with or disposed at least partially within, wherein said nozzle is formed to provide an exit for plasma generated by said system, wherein said voltage source is configured for applying a current between said cathode and said anode, wherein said anode is positively charge with respect to said cathode, wherein a propellant is located between said anode and said cathode between an area where an electrical potential difference is generated by said cathode and anode, wherein said propellant comprises a carbon based propellant and a plurality of nano- or micro-particles that have a magnetic or electromagnetic field response incorporated onto said propellant creating a fiber composite; creating an arc of electricity in said area of electrical potential difference wherein said arc of electricity passes through said propellant causing an ablation and sublimation of said propellant to create a charged gas cloud; providing and operating an igniter device wherein said igniter device is attached through said cathode, wherein said igniter device ignites said charged gas cloud and generates said plasma that is generated within said plasma reaction chamber and expelled through said nozzle;
wherein said arc creates an electromagnetic field that creates a Lorentz force on said nano- or micro-particles in said plasma, accelerating said plasma out of said nozzle at a higher velocity than said carbon based propellant without said nano- or micro-particles;
and providing and operating a section for transferring the particles back to a storage/reuse chamber comprising electromagnetic field drift tube sections as well as fan systems.

12. method of claim 11 , wherein said nozzle exit further comprises a plurality of magnets around an inner diameter of said nozzle.

13. A method of claim 11 , further comprising orienting said nozzle towards a work piece so as to apply said plasma on said work piece.

14. A method of claim 13 , wherein said plasma and system are configured and operated to coat said workpiece with said nano- or micro-particles.

15. A method of claim 13 , wherein said plasma and pulsed plasma thruster system are configured and operated to cut said workpiece.

16. A method of claim 11 , further comprising providing and operating one or more electromagnetic field generating sections along a path of the plasma from ablation to the exit which is configured for selectively generating an applied electric field that applies a propulsive force to the plasma and the nano- or micro-particles to increase or adjust speed of the plasma towards the exit and push the plasma and the nano- or micro-particles away from the anode/cathodes.

17. A method of claim 11 , further comprising providing and operating a pulsed plasma thruster system control system section configured for adjusting operation of the pulsed plasma thruster system so that pulsed plasma thruster system operates or ablates the propellant on an intermittent basis operable for adjusting plasma output applied to a work piece in a manner that configured for intermittent or selective application of the plasma output.

18. A method of claim 11 , further comprising providing and operating a nano or micro particle injector configured to inject one or more additional or different said particles into said plasma so as to vary particle content of the plasma during and after ablation which adjusts particle type and concentration.

19. The method of claim 11 , further comprising a scoop and recovery system section which pulls or manipulates the particles out of the a thrust path of the plasma and then recycles them by routing them back to the plasma thrust chamber which then permits reuse of the particles.

20. A pulsed plasma thruster system, said system including: a plasma reaction chamber comprising a cathode, a nozzle formed with an exit, and an anode, wherein said system is configured to generate an electrical potential difference th

Assignees

• Us Navy
• Us Navy

Inventors

• Deshpande Nishkamraj U
• Barsun H Fred
• Clark Steven D

Classifications

• F03H1/0012

  Means for supplying the propellant · CPC title

• F03H1/0087 Primary

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