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High performance propellants flow through specialized mechanical hardware that allows for effective and safe thermal decomposition and/or combustion of the propellants. By integrating a sintered metal component between a propellant feed source and the combustion chamber, an effective and reliable fu

High performance propellants flow through specialized mechanical hardware that allows for effective and safe thermal decomposition and/or combustion of the propellants. By integrating a sintered metal component between a propellant feed source and the combustion chamber, an effective and reliable fuel injector head may be implemented. Additionally the fuel injector head design integrates a spark ignition mechanism that withstands extremely hot running conditions without noticeable spark mechanism degradation.

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1. A combustion system comprising: a housing defining a cooling chamber and a combustion chamber separated by a flame barrier, wherein the cooling chamber is disposed around an electrode assembly, and the flame barrier comprises fluid paths with a diameter of less than about 10 microns that are conf

1. A combustion system comprising: a housing defining a cooling chamber and a combustion chamber separated by a flame barrier, wherein the cooling chamber is disposed around an electrode assembly, and the flame barrier comprises fluid paths with a diameter of less than about 10 microns that are configured to prevent combustion from propagating through the flame barrier, the electrode assembly comprises an interface sheath encompassing an insulating tube which encompasses an electrode; anda fuel inlet tube is disposed through the housing into the cooling chamber. 2. The combustion system of claim 1, wherein the electrode assembly is part of a spark ignition assembly that further comprises an electrical connector and a power supply. 3. The combustion system of claim 1, wherein the combustion chamber comprises an ablative liner adjacent the housing. 4. The combustion system of claim 1, wherein the combustion chamber defines proximal and distal ends, wherein the flame barrier is at the proximal and a throat constriction is at the distal end. 5. The combustion system of claim 1, wherein the fluid paths have a diameter of less than about 0.5 micron. 6. The combustion system of claim 1, wherein the electrode comprises a tip, single point, double point, triple point, quadruple point, star or split configuration. 7. The combustion system of claim 1, further comprising a seal between the flash barrier, the cooling chamber and the housing. 8. The combustion system of claim 1, wherein the cooling chamber receives fuel via the inlet tube. 9. The combustion system of claim 1, wherein the cooling chamber is adapted to cool the electrode assembly. 10. A combustion system comprising: a housing defining a chamber having distal and proximal ends; the housing defining a cooling chamber at the proximal end, a combustion chamber at the distal end and a flame barrier between the cooling chamber and the combustion chamber, wherein the flame barrier is fluid-permeable and comprises fluid paths configure to prevent combustion from propagating through the flame barrier;an electrode assembly disposed through the proximal end of the housing through the cooling chamber and through the flame barrier terminating at a surface of the flame barrier adjacent the combustion chamber, wherein the electrode assembly comprises an electrode disposed within an insulating tube, and wherein the insulating tube is disposed within an interface sheath; anda fuel inlet tube disposed through a side of the housing into the cooling chamber, wherein the fluid paths have a diameter of less than about 1 micron. 11. The combustion system of claim 10, wherein the fluid paths have a diameter of less than about 0.5 microns. 12. The combustion system of claim 10, wherein the fluid paths have a diameter of less than about 0.2 microns. 13. The combustion system of claim 10, wherein the fluid paths have a diameter of less than about 1 cm. 14. The combustion system of claim 10, wherein the interface sheath and the flame barrier comprise materials having similar coefficients of thermal expansion. 15. The combustion system of claim 10, wherein the interface sheath and the flame barrier each comprise one or more of stainless steel alloy, pure nickel, nickel alloys, niobium, rhenium, molybdenum, tungsten, tantalum, tantalum alloys, sintered ceramic or laminate structures. 16. The combustion system of claim 10, wherein the combustion chamber comprises an ablative or high temperature liner adjacent the housing. 17. The combustion system of claim 10, wherein the combustion chamber defines a throat constriction at the distal end of the housing. 18. The combustion system of claim 10, wherein the electrode comprises a tip, single point, double point, triple point, quadruple point, star or split configuration. 19. The combustion system of claim 10, further comprising a seal between the flash barrier, the cooling chamber and the housing. 20. The combustion system of claim 10, wherein the cooling chamber receives fuel via the inlet tube. 21. The combustion system of claim 10, wherein the cooling chamber is adapted to cool the electrode assembly. 22. A method of preventing flashback between a combustion chamber and a feed propellant and for providing regenerative cooling of an electrode assembly comprising: providing a propellant inlet into the cooling chamber, wherein a cooling Chamber circumscribes the electrode assembly;providing a micro-fluidic flame barrier configured to prevent combustion from propagating through the flame barrier to separate the cooling chamber and a combustion chamber, wherein the micro-fluidic flame barrier comprises paths having a diameter of about 5 microns or less, andrunning feed propellant through the fuel inlet, into the cooling chamber and through the flame barrier. 23. The method of claim 22, wherein the flame barrier comprises fluid paths having a diameter of about 2 microns or less. 24. The method of claim 22, wherein the fluid paths have a diameter of about 1 microns or less. 25. The method of claim 22, wherein the fluid paths have a diameter of about 0.5 microns or less. 26. The method of claim 22, wherein the fluid paths have a diameter of about 0.2 microns or less.