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An injector for use with the rocket thruster has a plurality of fuel ports separated from a plurality of oxidizer ports. The oxidizer and fuel ports are paired together directing their respective fluids along a path with radial and tangential components so that the two fluids impinge at a predetermi

An injector for use with the rocket thruster has a plurality of fuel ports separated from a plurality of oxidizer ports. The oxidizer and fuel ports are paired together directing their respective fluids along a path with radial and tangential components so that the two fluids impinge at a predetermined spaced apart distance from the chamber wall of the combustion chamber at an impingement track. By providing the fuel at a steeper angle relative to the chamber walls than the oxidizer, the fuel can be utilized to provide a fuel rich zone near the chamber walls to assist in cooling the chamber walls during operation.

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1. A propellant injector comprising:a housing having a head end, a nozzle end, and a combustion chamber defined by a chamber wall in the housing; a fuel inlet port connected to a fuel manifold in the housing, the fuel manifold communicating fluid fuel from the fuel inlet port to a plurality of fuel

1. A propellant injector comprising:a housing having a head end, a nozzle end, and a combustion chamber defined by a chamber wall in the housing; a fuel inlet port connected to a fuel manifold in the housing, the fuel manifold communicating fluid fuel from the fuel inlet port to a plurality of fuel outlet ports disposed about the combustion chamber; an oxidizer inlet port connected to an oxidizer manifold in the housing, the oxidizer manifold communicating fluid oxidizer from the oxidizer inlet port to a plurality of oxidizer outlet ports disposed about the combustion chamber; the oxidizer outlet ports and fuel outlet ports are located along a port plane, terminate at the chamber wall; and direct their respective fluid to contact at a point on an impingement track, said impingement track spaced from the chamber wall by a predetermined distance, and said outlet ports spaced from the head end of the housing. 2. The propellant injector of claim 1, the fuel and oxidizer outlet ports direct their respective fluid along an impingement plane.3. The propellant injector of claim 1 wherein contact of fluids from the oxidizer and fuel outlet ports creates a vortex in the combustion chamber.4. A propellant injector comprising:a housing having a head end, a nozzle end and a combustion chamber defined by a chamber wall in the housing; a fuel inlet port connected to a fuel manifold in the housing, the fuel manifold communicating fluid fuel from the fuel inlet port to a plurality of fuel outlet ports disposed about the combustion chamber; an oxidizer inlet port connected to an oxidizer manifold in the housing, the oxidizer manifold communicating fluid oxidizer from the oxide inlet port to a plurality of oxidizer outlet ports disposed about the combustion chamber; the fuel outlet ports and fuel outlet ports direct their respective fluid to contact at a point on an impingement track, said impingement track spaced from the chamber wall by a predetermined distance, and said outlet ports spaced from the head end of the housing and the fuel outlet ports terminate at the chamber wall. 5. A propellant injector comprising:a housing having a head end, a nozzle end, and a combustion chamber defined by a chamber wall in the housing; a fuel inlet port connected to a fuel manifold in the housing, the fuel manifold communicating fluid fuel form the fuel inlet port to a plurality of fuel outlet ports disposed about the combustion chamber; an oxidizer inlet port connected to an oxidizer manifold in the housing the oxidizer manifold communicating fluid oxidizer from the oxidizer inlet port to a plurality of oxidizer outlet port disposed about the combustion chamber; the fuel outlet ports and fuel outlet ports direct their respective fluid to contact at a point on an impingement track, said impingement track spaced from the chamber wall by a predetermined distance, and said outlet torts spaced from the head end of the housing, and the oxidizer outlet ports terminate at the chamber wall. 6. A propellant injector comprising:a housing having a head end, a nozzle end, and a combustion chamber defined by a chamber wall in the housing; a fuel inlet port connected to a fuel manifold in the housing, the fuel manifold communicating fluid fuel from the fuel inlet port to a plurality of fuel outlet ports disposed about the combustion chamber; an oxidizer inlet port connected to an oxidizer manifold in the housing, the oxidizer manifold communicating fluid oxidizer from the oxidizer inlet port to a plurality of oxidizer outlet ports disposed about the combustion chamber; the fuel outlet ports and fuel outlet tons direct their respective fluid to contact at a point on an impingement track, said impingement track spaced from et the chamber wall by a predetermined distance, and said outlet ports spaced from the head end of the housing and the fuel outlet ports are angled at a first angle relative to a first radian extending from a center axis of the combustion chamber to the fuel outlet port at the chamber wall, said center axis extending from the head end to the bottom end of the housing. 7. The propellant injector of claim 6 wherein the oxidizer outlet ports are angled at a second angle relative to a second radian extending from the center axis of the combustion chamber to the oxidizer outlet port at the chamber wall.8. The propellant injector of claim 7 wherein the first angle is greater than the second angle.9. A liquid propellant injector comprising:a housing having a head end, a nozzle end, and a combustion chamber defined by a chamber wall extending intermediate the head end and nozzle end of the housing; a fuel inlet port connected to a fuel manifold in the housing, the fuel manifold communicating fluid fuel from the fuel inlet port to a plurality of fuel outlet ports disposed about the combustion chamber; an oxidizer inlet port connected to an oxidizer manifold in the housing, the oxidizer manifold communicating fluid oxidizer from the oxidizer inlet port to a plurality of oxidizer outlet ports disposed about the combustion chamber; wherein each of the oxidizer outlet ports and the fuel outlet ports are paired to direct their respective fluid to contact at a point on an impingement track, said impinge ent track spaced from the chamber wall by a predetermined distance, said outlet ports spaced firm the head end of the housing and the oxidizer and fuel outlet ports are located along a port plane and terminate at the chamber wall. 10. The liquid propellant injector of claim 9 wherein the oxidizer and fuel outlet ports arm located along an impingement plane with the impingement track.11. The liquid propellant injector of claim 9, wherein the fuel outlet port extends along a first axis, said first axis angled at a first angle relative to a first radian extending from the center axis to the fuel outlet port.12. The liquid propellant injector of claim 11, wherein the oxidizer outlet port extends along a second axis, said second axis angled at a second angle relative to a second radian extending from the center axis to the oxidizer outlet port.13. The liquid propellant injector of claim 12 wherein the first angle is greater than the second angle.14. The liquid propellant injector of claim 9 wherein contact of fluids from the oxidizer and fuel outlet ports creates a vortex in the combustion chamber.15. A fluid propellant injector comprising:a housing having a combustion chamber defined by a cylindrical chamber wall; a fuel manifold communicating fluid fuel to a plurality of fuel outlet ports disposed about the chamber wall directing fuel into the combustion chamber; an oxidizer manifold communicating fluid oxidizer to a plurality of oxidizer outlet ports disposed about the chamber wall directing fuel into the combustion chamber; and wherein the plurality of oxidizer and fuel outlet ports are paired and direct their respective fluids to contact along an impingement track spaced from the cylindrical chamber wall, and at least one of the fuel outlet ports and the oxidizer outlet ports terminate at the chamber wall. 16. The liquid propellant injector of claim 15 wherein the oxidizer and fuel outlet ports are located along an impingement plane with the impingement track.17. The liquid propellant injector of claim 15 wherein the fuel outlet port extends along a first axis, said first axis angled at a first angle relative to a first radian extending from the center axis to the fuel outlet port.18. The liquid propellant injector of claim 15 wherein the oxidizer outlet port extends along a second axis, said second axis angled at a second angle relative to a second radian extending from the center axis to the oxidizer outlet port.19. The liquid propellant injector of claim 18 herein the first angle is greater than the second angle.20. The fluid propellant injector of claim 15 wherein contact of fluids from the oxidizer and fuel outlet ports creates a vortex in the combustion chamber.