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A nuclear thermal propulsion rocket engine. A reactor is provided to receive a fissionable fuel and a propellant fluid. Fuel may be transported and injected using a carrier fluid. Carrier fluid for fuel may be hydrogen or an isotope thereof. Fuel may be plutonium or selected actinide. A neutron gene

A nuclear thermal propulsion rocket engine. A reactor is provided to receive a fissionable fuel and a propellant fluid. Fuel may be transported and injected using a carrier fluid. Carrier fluid for fuel may be hydrogen or an isotope thereof. Fuel may be plutonium or selected actinide. A neutron generator is provided, and utilizes an ion generator and a target container which extends into the reactor to hold a target material therein. Neutrons may be emitted almost omni-directionally by impact of ions from the ion generator on target material. Cooling of the target container may be provided by a cooling sleeve that receives and circulates a cooling fluid, and discharges the cooling fluid after it has been heated. Fuel injectors provide fuel through fuel injector valves regulated to cycle on and off to pulse output power of the rocket engine, by timing frequency and duration of fuel feed, and regulating injected fuel amounts, to regulate the energy released over discrete time periods. The reactor receives reactants and an expandable propellant fluid such as hydrogen, and confines heated and pressurized gases for discharge out through a throat, and into a rocket engine expansion nozzle for propulsive discharge.

대표청구항 ▼

1. A rocket engine, comprising: a first fluid storage compartment for storage of a first fluid;a second fluid storage compartment for storage of a second fluid;a reactor, said reactor comprising (a) a chamber for containing said first fluid and said second fluid during heating,(b) a first set of inj

1. A rocket engine, comprising: a first fluid storage compartment for storage of a first fluid;a second fluid storage compartment for storage of a second fluid;a reactor, said reactor comprising (a) a chamber for containing said first fluid and said second fluid during heating,(b) a first set of injectors for (i) confining passage into said reactor of said first fluid received from said first fluid storage compartment, said first fluid containing at least some fissile material, and (ii) for injecting said first fluid containing at least some fissile material to a reaction zone in said reactor,(c) a second set of injectors for directing passage into said reactor of said second fluid received from said second fluid storage compartment;(d) said reactor further comprising a mixing zone, and wherein said second fluid is injected into said reactor at said mixing zone, and(e) an outlet;an expansion nozzle, said expansion nozzle connected to said outlet of said reactor;a neutron beam generator, said neutron beam generator comprising an ion generator and a target container containing a target material, said target container extending into said reactor, said neutron beam generator configured to accelerate ions toward said target material to generate neutrons outwardly from said target material and collide with at least some of said fissile material in said reaction zone, wherein said neutrons and said fissile material interact to thereby effect fission of at least some of said fissile material and release heat; andwherein said first fluid and said second fluid are contained by and heated in said reaction chamber to produce a heated gas which is released through said outlet and then expelled through said expansion nozzle. 2. The rocket engine as set forth in claim 1, wherein said first fluid comprises hydrogen. 3. The rocket engine as set forth in claim 1, wherein said first fluid comprises deuterium. 4. The rocket engine as set forth in claim 1, wherein said first fluid comprises tritium. 5. The rocket engine as set forth in claim 1, wherein said first fluid comprises two or more isotopes of hydrogen. 6. The rocket engine as set forth in claim 1, wherein said second fluid comprises hydrogen. 7. The rocket engine as set forth in claim 1, wherein said fissile material comprises an actinide. 8. The rocket engine as set forth in claim 1, wherein said fissile material comprises one or more Pu isotopes. 9. The rocket engine as set forth in claim 8, wherein said fissile material comprises plutonium 239 (239Pu). 10. The rocket engine as set forth in claim 7, wherein said actinide comprises uranium 235 (235U). 11. The rocket engine as set forth in claim 1, wherein fission of said fissile material occurs under sub-critical mass conditions, and wherein said fissile material comprises 239Pu, and wherein said 239Pu is provided at about between thirty parts per million and one hundred and twenty parts per million, by weight, in said first fluid. 12. The rocket engine as set forth in claim 1, wherein fission of said fissile material occurs under sub-critical mass conditions, and wherein said fissile material comprises 239Pu, and wherein said 239Pu is provided at about between sixty parts per million, and ninety parts per million, by weight, in said first fluid. 13. The rocket engine as set forth in claim 1, wherein said fissile material comprises 239Pu, and wherein said 239Pu is provided at about between ninety parts per million, and one thousand parts per million, by weight, in said first fluid. 14. The rocket engine as set forth in claim 1, wherein said neutron generator comprises an ion beam pathway having a reactor portion that extends into said reactor, and wherein said target container includes a cooling sleeve that houses said ion beam pathway. 15. The rocket engine as set forth in claim 14, wherein said target container comprises a distal end, and wherein said cooling sleeve is coupled with said target container, to provide a housing for coolant for cooling said target container. 16. The rocket engine as set forth in claim 15, wherein said cooling sleeve comprises an outer wall having outlets therein, and wherein said outlets are configured to allow escape therethrough of a selected cooling fluid. 17. The rocket engine as set forth in claim 1, wherein one or more of said first set of injectors further comprises an injector control valve, said injector control valve sized and shaped for on-off control of passage of said first fluid therethrough. 18. The rocket engine as set forth in claim 1, wherein each of said first set of injectors further comprises an injector control valve, said injector control valve sized, shaped, and configured for modulated control of passage of said first fluid therethrough. 19. The rocket engine as set forth in claim 1, or in claim 17, wherein said rocket engine comprises a pulsed nuclear reaction engine. 20. The rocket engine as set forth in claim 19, wherein said injector control valve is operable to provide injection valve on and off cycle time selected to maintain heating and cooling of internal components of said reactor, so that materials of construction of said reactor are maintained within structurally operable parameters. 21. A rocket engine, comprising: a first fluid storage compartment for storage of a first fluid;a second fluid storage compartment for storage of a second fluid;a reactor, said reactor comprising (a) a chamber for containing said first fluid and said second fluid during heating,(b) a first set of injectors configured to confine passage into said reactor of said first fluid, wherein one or more injectors in said first set of injectors further comprises an injector control valve that controls timing of injection of selected amounts of said first fluid into said chamber, said first fluid further comprising at least some fissile material at time of injection into said chamber;(c) a second set of injectors for directing passage of said second fluid into said chamber for heating; and(d) an outlet;a nozzle, said nozzle connected to said outlet of said reactor;a neutron beam generator, said neutron beam generator comprising an ion generator and a target container containing target material, said target container extending into said chamber of said reactor, said neutron beam generator configured to accelerate ions toward said target material to generate neutrons outwardly from said target material, wherein neutrons collide with at least some of said fissile material in said chamber, wherein said neutrons and said fissile material interact to thereby effect fission of at least some of said fissile material and release heat; andwherein said first fluid and said second fluid are temporarily contained by and heated in said chamber to produce a heated gas which is released through said outlet and then expelled through said nozzle. 22. The rocket engine as set forth in claim 21, wherein said first fluid comprises hydrogen. 23. The rocket engine as set forth in claim 21, wherein said first fluid comprises deuterium. 24. The rocket engine as set forth in claim 21, wherein said first fluid comprises tritium. 25. The rocket engine as set forth in claim 21, wherein said first fluid comprises two or more isotopes of hydrogen. 26. The rocket engine as set forth in claim 21, wherein said second fluid comprises hydrogen. 27. The rocket engine as set forth in claim 21, wherein said fissile material comprises an actinide. 28. The rocket engine as set forth in claim 27, wherein said actinide comprises uranium 235 (235U). 29. The rocket engine as set forth in claim 21, wherein said fissile material comprises one or more Pu isotopes. 30. The rocket engine as set forth in claim 21, wherein said fissile material comprises plutonium 239 (239Pu). 31. The rocket engine as set forth in claim 21, wherein fission of said fissile material occurs under sub-critical mass conditions, and wherein said fissile material comprises 239Pu, and wherein said 239Pu is provided at about between thirty parts per million and one hundred and twenty parts per million, by weight, in said first fluid. 32. The rocket engine as set forth in claim 21, wherein fission of said fissile material occurs under sub-critical mass conditions, and wherein said fissile material comprises 239Pu, and wherein said 239Pu is provided at about between sixty parts per million, and ninety parts per million, by weight, in said first fluid. 33. The rocket engine as set forth in claim 21, wherein said fissile material comprises 239Pu, and wherein said 239Pu is provided at about between ninety parts per million, and one thousand parts per million, by weight, in said first fluid. 34. The rocket engine as set forth in claim 21, wherein said neutron generator comprises an ion beam pathway having a reactor portion that extends into said chamber of said reactor, and wherein said target container includes a cooling sleeve that houses said ion beam pathway. 35. The rocket engine as set forth in claim 34, wherein said target container comprises a distal end, and wherein said cooling sleeve is coupled with said target container, to provide a housing for coolant for cooling said target container. 36. The rocket engine as set forth in claim 34, wherein said cooling sleeve comprises an outer wall having outlets therein, and wherein said outlets are configured to allow escape therethrough of a selected cooling fluid. 37. The rocket engine as set forth in claim 21, wherein said injector control valve is sized shaped, and configured for on-off control of passage of said first fluid therethrough. 38. The rocket engine as set forth in claim 21, wherein said injector control valve is sized, shaped, and configured for modulated control of passage of said first fluid therethrough. 39. The rocket engine as set forth in claim 1, or in claim 37, or in claim 38, wherein said rocket engine comprises a pulsed nuclear reaction engine. 40. The rocket engine as set forth in claim 21, wherein said injector control valve is operable to provide (a) injector control valve on and off cycle times, or (b) injector control valve modulation cycles, or both, and wherein said injector control valve operation is configured to supply fissile material at a rate which avoids overheating of said reactor, so that materials of construction of said reactor are maintained within structurally operable parameters. 41. A method for operation of a rocket engine, comprising: providing a first fluid storage compartment for storage of a first fluid;providing a second fluid storage compartment for storage of a second fluid;providing a reactor, said reactor comprising a chamber for receiving and containing said first fluid and said second fluid during heating,a first set of injectors configured to confine passage of said first fluid into said chamber, and further comprising an injector valve that controls timing of injection of selected amounts of said first fluid into said chamber, said first fluid further comprising at least some fissile material at time of injection into said chamber;a second set of injectors for directing passage of said second fluid into said chamber for heating; and(d) an outlet;providing a nozzle, the nozzle connected to said outlet of said reactor;providing a neutron beam generator,injection the first fluid comprising at least some fissile material into the chamber;generating neutrons with said neutron beam generator at a location proximate to the at least some fissile material injected into the chamber, to cause fission of at least some of said fissile material and generating heat;heating said second fluid and said first fluid to provide a hot gas;ejecting said hot gas out said nozzle to provide propulsive force between 800 seconds and 2500 seconds.