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公开(公告)号：US11935661B2
公开(公告)日：2024-03-19
申请号：US17399859
申请日：2021-08-11
CPC分类号： G21C21/02 , G21C3/64 , B22F3/15 , B22F2301/20 , B64G1/408 , C22C1/05 , F02K7/02 , G21C5/02 , G21C5/12
摘要： CERMET fuel element includes a fuel meat of consolidated ceramic fuel particles (preferably refractory-metal coated HALEU fuel kernels) and an array of axially-oriented coolant flow channels. Formation and lateral positions of coolant flow channels in the fuel meat are controlled during manufacturing by spacer structures that include ceramic fuel particles. In one embodiment, a coating on a sacrificial rod (the rod being subsequently removed) forms the coolant channel and the spacer structures are affixed to the coating; in a second embodiment, a metal tube forms the coolant channel and the spacer structures are affixed to the metal tube. The spacer structures laterally position the coolant channels in spaced-apart relation and are consolidated with the ceramic fuel particles to form CERMET fuel meat of a fuel element, which are subsequently incorporated into fuel assemblies that are distributively arranged in a moderator block within a nuclear fission reactor, in particular for propulsion.
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公开(公告)号：US20230282373A1
公开(公告)日：2023-09-07
申请号：US18118193
申请日：2023-03-07
摘要： Fuel bundle has plurality of twisted ribbon fuel rodlets arranged in hexagonal packing or circle packing arrangement in a reactor core encased in a multilayer casing. Arrangement of twisted ribbon fuel rodlets is facilitated by rodlet seating fixture with seating surface having a plurality of protrusions that form a receiving space for ends of the twisted ribbon fuel rodlets. Manufacture of the fuel bundle incorporates fiber manufacturing technologies and, optionally, infiltration of spaces in the reactor core by infiltrant. Twisted ribbon fuel rodlet manufacturing system has sub-systems that impart twist periodicity to extruded ribbons, inspect twisted extruded ribbons, and cut twisted extruded ribbons to length. Inspection sorts twisted ribbon fuel rodlets as well as provides feedback to adjust operation of sub-systems. The fuel bundle (and optional fuel bundle support) can be incorporated into a fuel assembly of nuclear propulsion fission reactor structure of, for example, a nuclear thermal propulsion engine.
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公开(公告)号：US20180223815A1
公开(公告)日：2018-08-09
申请号：US15426952
申请日：2017-02-07
申请人： The Boeing Company
发明人： Jeffery S. Anderson , Erin R. Gish
IPC分类号： F03H1/00
CPC分类号： F03H1/0081 , B64G1/408 , F03H1/0012 , F15D1/08 , H05H1/06 , H05H1/54
摘要： An injection system includes a reservoir for containing liquid, and a gating plate having a circular array of gating plate apertures. The injection system additionally includes a faceplate positioned adjacent to the gating plate and having a circular array of faceplate orifices. The injection system also has a motor to rotate the gating plate, and a controller to control the motor for rotating the gating plate into an aligned clocking orientation in which the gating plate apertures and the faceplate orifices are aligned to initiate the formation of a cylindrical array of liquid jets, and rotate the gating plate into a non-aligned clocking orientation terminate formation of the liquid jets after a predetermined discrete quantity of the liquid is injected.
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公开(公告)号：US20180105292A1
公开(公告)日：2018-04-19
申请号：US15490056
申请日：2017-04-18
申请人： Jerome Drexler
发明人： Jerome Drexler
CPC分类号： B64G1/12 , B64G1/401 , B64G1/403 , B64G1/405 , B64G1/408 , B64G1/409 , B64G1/46 , B64G2700/00
摘要： A spacecraft propulsion method uses cosmic ray triggered nuclear micro-fusion events to provide repeated or continuous thrust for artificial gravity during a space flight. In one embodiment, successive packages of deuterium-containing micro-fusion particle fuel material is projected in a specified direction outward from a spacecraft. In another embodiment, the micro-fusion fuel material is a coating upon a set of angled rings arranged circumferentially around the spacecraft. In a third embodiment, the micro-fusion fuel is dispersed in proximity to “wind” turbines to generate electricity for ion thrusters. In each case, the material interacts with the ambient flux of cosmic rays to generate micro-fusion products having kinetic energy that either produce thrust upon the spacecraft or drive the turbines whose electrical output in turn powers the ion thrusters.
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公开(公告)号：US09822769B2
公开(公告)日：2017-11-21
申请号：US14400204
申请日：2013-05-10
CPC分类号： F03H1/0093 , B64G1/408 , F02K9/08 , G21B1/052 , Y02E30/122
摘要： A system and method for producing and controlling high thrust and desirable specific impulse from a continuous fusion reaction is disclosed. The resultant relatively small rocket engine will have lower cost to develop, test, and operate that the prior art, allowing spacecraft missions throughout the planetary system and beyond. The rocket engine method and system includes a reactor chamber and a heating system for heating a stable plasma to produce fusion reactions in the stable plasma. Magnets produce a magnetic field that confines the stable plasma. A fuel injection system and a propellant injection system are included. The propellant injection system injects cold propellant into a gas box at one end of the reactor chamber, where the propellant is ionized into a plasma. The propellant and fusion products are directed out of the reactor chamber through a magnetic nozzle and are detached from the magnetic field lines producing thrust.
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公开(公告)号：US09346565B1
公开(公告)日：2016-05-24
申请号：US14851665
申请日：2015-09-11
申请人： Richard Hardy , Jonathan Hardy
发明人： Richard Hardy , Jonathan Hardy
摘要： 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.
摘要翻译： 核热力推进火箭发动机。 提供反应器以接收可裂变燃料和推进剂流体。 燃料可以使用载体流体输送和注入。 用于燃料的载体流体可以是氢或其同位素。 燃料可以是钚或选择的锕系元素。 提供中子发生器，并且利用离子发生器和目标容器，其延伸到反应器中以将目标材料保持在其中。 通过来自离子发生器的离子与目标材料的冲击，中子几乎可以全方位地发射。 目标容器的冷却可以由接收和循环冷却流体的冷却套筒提供，并且在冷却流体被加热之后排出冷却流体。 燃料喷射器通过燃料喷射阀提供燃料，其通过定时频率和燃料供给的持续时间以及调节喷射的燃料量来调节在离散时间段内释放的能量，从而循环开启和关闭火箭发动机的脉冲输出功率。 反应器接收反应物和可膨胀的推进剂流体如氢气，并限制加热和加压的气体通过喉管排出，并进入用于推进排放的火箭发动机膨胀喷嘴。
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7.发明申请APPARATUS, SYSTEMS AND METHODS FOR FUSION BASED POWER GENERATION AND ENGINE THRUST GENERATION 有权基于FUSION的发电和发动机发电的装置，系统和方法公开(公告)号：US20150364220A1
公开(公告)日：2015-12-17
申请号：US14750771
申请日：2015-06-25
申请人： MSNW LLC
发明人： John Thomas Slough
IPC分类号： G21B1/05
CPC分类号： G21B1/052 , B64G1/408 , B64G1/422 , Y02E30/122
摘要： Systems and methods establish a magnetically insulated fusion process. An exemplary embodiment establishes a Field Reversed Configuration (FRC) plasma, wherein the FRC plasma is a closed field, magnetically confined plasma; collapses a metal shell about the FRC plasma; and establishes a fusion reaction in response to collapsing the metal shell about the FRC plasma.
摘要翻译： 系统和方法建立了磁绝缘融合过程。 示例性实施例建立场反转配置（FRC）等离子体，其中FRC等离子体是闭磁场，磁限制等离子体; 围绕FRC等离子体折叠金属壳; 并且响应于围绕FRC等离子体使金属壳折叠而建立聚变反应。
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公开(公告)号：US09180985B1
公开(公告)日：2015-11-10
申请号：US14692349
申请日：2015-04-21
申请人： Richard Hardy , Jonathan Hardy
发明人： Richard Hardy , Jonathan Hardy
摘要： 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.
摘要翻译： 基于裂变的核热推进火箭发动机。 一个实施例提供了诸如氘等载气中的可裂变材料的来源，例如钚。 提供中子源，例如来自中子束发生器。 通过发动机设计几何形状，各种实施例可以提供中子与通过载气注入的可裂变材料的交点，而在以反应室形式提供的反应器中。 中子对可裂变材料的影响导致反应堆中亚临界质量反应条件下的核裂变，导致热能释放到反应器内的材料。 反应器的尺寸和形状被设计成接收反应物和可膨胀流体例如氢，并且将加热和加压的气体限制通过喉部排放到用于推进排放的火箭发动机膨胀喷嘴中。
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公开(公告)号：US20100176248A1
公开(公告)日：2010-07-15
申请号：US12452971
申请日：2008-09-28
申请人： Mehmet Terziakin
发明人： Mehmet Terziakin
摘要： A propulsion method employing gyroscopes (1,2) with electric motors (4) which are being moved along a closed path in the spacecraft. Rotation axis of the gyroscopes are rotated periodically relative to movement direction so that gyroscopic effect is only obtained during movement in one direction. Thereby a gyroscopic resistance difference is obtained and used as a propulsion force. Another application is to use gyroscopes connected to generators in order to decelerate a spacecraft, transforming the moment created in gyroscope during deceleration into the electrical energy, distribute it to the space as heat transfer by means of radiation through the heat resistant panels.
摘要翻译： 使用具有电动机（4）的陀螺仪（1,2）的推进方法，其沿着空间飞行器中的封闭路径移动。 陀螺仪的旋转轴相对于移动方向周期性地旋转，因此仅在一个方向的运动期间获得陀螺效应。 由此获得陀螺仪电阻差并用作推进力。 另一个应用是使用连接到发电机的陀螺仪，以减速航天器，将减速期间在陀螺仪中产生的力矩转化为电能，并通过耐热板通过辐射传热将其分配到空间。
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公开(公告)号：US07588213B2
公开(公告)日：2009-09-15
申请号：US11703287
申请日：2007-02-07
CPC分类号： B64G1/1078 , B64G1/007 , B64G1/222 , B64G1/242 , B64G1/283 , B64G1/288 , B64G1/363 , B64G1/405 , B64G1/406 , B64G1/408 , B64G1/422 , B64G1/44 , B64G1/503 , B64G1/646 , B64G1/66
摘要： A preferred In Orbit Transportation & Recovery System (IOSTAR™) (10) includes a space tug powered by a nuclear reactor (19). The IOSTAR™ includes a collapsible boom (11) connected at one end to a propellant tank (13) which stores fuel for an electric propulsion system (12). This end of the boom (11) is equipped with docking hardware (14) that is able to grasp and hold a satellite (15) and as a means to refill the tank (13). Radiator panels (16) mounted on the boom (11) dissipate heat from the reactor (19). A radiation shield (20) is situated next to the reactor (19) to protect the satellite payload (15) at the far end of the boom (11). The IOSTAR™ (10) will be capable of accomplishing rendezvous and docking maneuvers which will enable it to move spacecraft between a low Earth parking orbit and positions in higher orbits or to other locations in our Solar System.
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