A fission based nuclear thermal propulsion rocket engine. An embodiment provides a source of fissionable material such as plutonium in a carrier gas such as deuterium. A neutron source is provided, such as from a neutron beam generator. By way of engine design geometry, various embodiments may provi
A fission based nuclear thermal propulsion rocket engine. An embodiment provides a source of fissionable material such as plutonium in a carrier gas such as deuterium. A neutron source is provided, such as from a neutron beam generator. By way of engine design geometry, various embodiments may provide for intersection of neutrons with the fissionable material injected by way of the carrier gas, while in a reactor provided in the form of a reaction chamber. Impact of neutrons on fissionable material results in a nuclear fission in sub-critical mass reaction conditions in the reactor, resulting in release of heat energy to the materials within the reactor. The reactor is sized and shaped to receive the reactants and an expandable fluid such as hydrogen, and to confine heated and pressurized gases for discharge out through a throat, into a rocket engine expansion nozzle for propulsive discharge.
대표청구항▼
1. A rocket engine, comprising: a neutron beam generator;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 heati
1. A rocket engine, comprising: a neutron beam generator;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; and(d) an outlet;an expansion nozzle, said expansion nozzle connected to said outlet of said reactor;wherein said neutron beam generator is configured to direct neutrons to 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 one or more isotopes of 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 fissile material comprises an actinide. 5. The rocket engine as set forth in claim 1, wherein said fissile material comprises one or more Pu isotopes. 6. The rocket engine as set forth in claim 5, wherein said fissile material comprises plutonium 239 (239Pu). 7. The rocket engine as set forth in claim 4, wherein said actinide comprises uranium 235 (235U). 8. The rocket engine as set forth in any one of claim 4, 5, 6, or 7, wherein said fissile material, before injection into said reactor, is provided in particulate form. 9. 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. 10. 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. 11. The rocket engine as set forth in claim 8, wherein said first fluid comprises a gas at time of injection into said reactor. 12. The rocket engine as set forth in claim 1, wherein said expansion nozzle comprises nozzle coolant passageways. 13. The rocket engine as set forth in claim 12, wherein said second fluid is utilized as a coolant by passage through said nozzle coolant passageways, before injection of said second fluid into said reactor. 14. The rocket engine as set forth in claim 13, wherein said second fluid, at time of entry into said nozzle coolant passageway, comprises a liquid. 15. The rocket engine as set forth in claim 1, wherein said reactor comprises reactor coolant passageways. 16. The rocket engine as set forth in claim 15, wherein said second fluid is utilized as a coolant by passage through said reactor coolant passageways, before injection of said second fluid into said reactor. 17. The rocket engine as set forth in claim 16, wherein said second fluid, at time of entry into said reactor coolant passageways, comprises a liquid. 18. The rocket engine as set forth in claim 1, wherein said second fluid is injected into said reactor at a mixing zone, said mixing zone located downstream of said reaction zone. 19. The rocket engine as set forth in claim 1, wherein said reaction chamber comprises a tubular shaped portion. 20. The rocket engine as set forth in claim 1, wherein said rocket engine has a specific impulse in the range of from about 800 to about 2500 seconds. 21. The rocket engine as set forth in claim 1, wherein said rocket engine has a specific impulse in the range of from about 1000 to about 1215 seconds. 22. A rocket engine, comprising: a neutron beam generator;a first fluid storage compartment for storage of a first fluid, and wherein said first fluid comprises deuterium 1D2;a second fluid storage compartment for storage of a second fluid, wherein said second fluid, before heating, comprises hydrogen (H2);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) directing passage into said reactor of said first fluid received from said first fluid storage compartment, said first fluid containing at least some fissile material, wherein said fissile material comprises at least some 239Pu, and (ii) for injecting said first fluid containing at least some 239Pu into 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, said mixing zone located downstream of said reaction zone, and(e) an outlet;an expansion nozzle, said expansion nozzle connected to said outlet of said reactor;wherein said neutron beam generator is configured to direct neutrons to collide with at least some of said fissile material in said reaction zone, wherein said neutrons and said fissile material interact at a common point in said reactor, to thereby effect fission of at least some of said fissile material at sub-critical mass conditions, and release heat therefrom; 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 expelled through said expansion nozzle. 23. The rocket engine as set forth in claim 22, wherein said 239Pu, before injection into said reactor, is provided in particulate form. 24. The rocket engine as set forth in claim 22, wherein said 239Pu is provided at about sixty parts per million, by weight, in said deuterium (1D2). 25. The rocket engine as set forth in claim 22, wherein said first fluid comprises a gas at time of injection into said reactor. 26. The rocket engine as set forth in claim 22, wherein said expansion nozzle comprises nozzle coolant passageways. 27. The rocket engine as set forth in claim 26, wherein said second fluid is utilized as a coolant by passage through said nozzle coolant passageways, before injection into said reactor. 28. The rocket engine as set forth in claim 26, wherein said second fluid, at time of entry into said nozzle coolant passageway, comprises a liquid. 29. The rocket engine as set forth in claim 22, wherein said reactor comprises reactor coolant passageways. 30. The rocket engine as set forth in claim 29, wherein said second fluid is utilized as a coolant by passage through said reactor coolant passageways, before injection into said reactor. 31. The rocket engine as set forth in claim 30, wherein said second fluid, at time of entry into said reactor coolant passageways, comprises a liquid. 32. The rocket engine as set forth in claim 1, or in claim 22, further comprising a fuel turbopump, said fuel turbopump receiving said first fluid from said first fluid storage compartment, and providing said first fluid under pressure to said reaction chamber. 33. The rocket engine as set forth in claim 1, or in claim 22, wherein said first fluid further comprises tritium (1T3). 34. The rocket engine as set forth in claim 32, further comprising an oxygen storage compartment and a gas generating chamber, and wherein said fuel turbopump is driven by combustion products formed by combustion of hydrogen and oxygen in said gas generating chamber. 35. The rocket engine as set forth in claim 1, or in claim 22, further comprising a thrust fluid turbopump, said thrust fluid turbopump receiving said second fluid from said second fluid storage compartment, and providing said second fluid under pressure to said reaction chamber. 36. The rocket engine as set forth in claim 35, further comprising an oxygen storage compartment and a gas generating chamber, and wherein said thrust fluid turbopump is driven by combustion products formed by combustion of hydrogen and oxygen in said gas generating chamber. 37. The rocket engine as set forth in claim 35, wherein said thrust fluid turbopump further comprises an electrical generator, said electrical generator configured to generate electrical power, and to supply electrical power to said neutron beam generator. 38. The rocket engine as set forth in claim 35, wherein said thrust fluid turbopump further comprises a fuel turbopump, said fuel turbopump receiving said first fluid from said first fluid storage compartment, and providing said first fluid under pressure to said reaction chamber. 39. The rocket engine as set forth in claim 35, wherein said thrust fluid turbopump further comprises an electrical generator, said electrical generator configured to generate electrical power, and to supply electrical power to said neutron beam generator and wherein said thrust fluid turbopump further comprises a fuel turbopump, said fuel turbopump receiving said first fluid from said first fluid storage compartment, and providing said first fluid under pressure to said reaction chamber, and wherein said thrust fluid turbopump, said fuel turbopump, and said electrical generator are all driven by a gas turbine on a common shaft or via gearbox from a common shaft. 40. The rocket engine as set forth in claim 1, or in claim 22, wherein fission of said fissile material occurs under sub-critical mass conditions.
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이 특허에 인용된 특허 (8)
Fowler Michael C. (Farmington CT) Smith David C. (Glastonbury CT), CO2Coupling material.
Hardy Richard (Seattle WA) Hardy Jonathan (Seattle WA) Kornell Thomas J. (Federal Way WA) Tallquist Kenneth M. (Bellevue WA), Horizontal-takeoff transatmospheric launch system.
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