A spaceplane and hybrid reaction engine employ micro-fusion enhanced propulsion in the presence of ambient cosmic rays and muons in the upper atmosphere at altitudes greater than 20 km. The reaction engines for the spaceplane may be of different types operable in different speed and altitude regimes, but at least one engine type incorporates a supply of deuterium-containing micro-fusion fuel that can be injected into the fuel mix along with the primary chemical fuel or into the exhaust in the nozzle section. The energetic fusion products from particle-target and/or muon-catalyzed fusion provide supplemental thrust for the spaceplane.

A fusion reactor for a spacecraft adapted to be cooled by the resident temperatures in space. The fusion reactor includes a core containing fusion plasma and fuel, and a plurality of shaping coils adapted to contain and shape the fusion plasma and fuel. The fusion reactor including the core and the plurality of shaping coils are disposed within an outer structure of the spacecraft, and the shaping coils are adapted to be cooled by the resident temperatures in space.

A fission based nuclear thermal propulsion rocket engine. An embodiment provides a source of fissionable material such as plutonium in a carrier fluid having neutron moderating constituents, such as hydrogen and/or carbon, therein. In various embodiments, the carrier fluid may be methane, or ethane, or a combination thereof. 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 fluid, 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 fluids 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. The design provides a rocket engine with a specific impulse in the range of from about eight hundred (800) seconds to about twenty five hundred (2500) seconds.

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.

A nuclear thermal propulsion rocket engine. A source of fissionable material such as plutonium is provided utilizing a carrier fluid having neutron moderating constituents, such as hydrogen and/or carbon, therein. A carrier fluid may be methane, or ethane, or a combination thereof. A neutron source is provided, such as from a neutron beam generator. Reactor design geometry provides containment of fissionable material in the reactor during acceleration. Collisions occur between neutrons and fissionable material injected by way of the carrier fluid. 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 fluids provided to the reactor. The reactor is sized and shaped to receive the reactants and expandable fluids 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, The design provides a rocket engine with a specific impulse in the range of from about eight hundred (800) seconds to about twenty five hundred (2500) seconds.

A nuclear thermal propulsion rocket engine. A source of fissionable material is provided in a bed of fuel pebbles located in a reactor. A fluid having neutron moderating constituents, such as hydrogen and/or carbon, therein, is provided, which may be in the form of methane, or ethane, or a combination thereof, or may further include various isotopes of hydrogen. An external neutron source is provided using a neutron beam generator. Reactor design geometry provides containment of fissionable material, and for any byproducts of fission reactions, in the reactor during acceleration of the rocket. Impact of neutrons on fissionable material results in a nuclear fission reaction conditions in the reactor, resulting in release of heat energy to fluids provided to the reactor. The reactor is sized and shaped to contain fuel pebbles containing fissionable material, and to confine expandable fluids as they remove heat from fuel pebbles. the heated fluids are discharged out through a throat, into a rocket engine expansion nozzle for propulsive discharge, The design provides a rocket engine with a specific impulse in the range of from about eight hundred (800) seconds to about twenty five hundred (2500) seconds.

A method, operable in the presence of ambient cosmic rays, is provided for braking a craft upon approach to a planet, moon or other space body, e.g. in preparation for landing. Deuterium-containing particle fuel material is projected in a specified direction outward of the craft, which interacts with both the cosmic rays and their principal decay product muons to generate energetic micro-fusion products that produce a braking thrust on the craft for a specified trajectory. The micro-fusion products may push directly against the craft, e.g. upon a pressure plate, or upon a sail or parachute connected to the craft, to decelerate the craft. A prepositioned automated landing system at a landing site may project the fuel material toward the craft based on telemetry tracking of an incoming craft and likewise directly disperse the material cloud to form a braking cushion at the landing site. The micro-fusion landing system may be part of a site-to-site transport, where the craft was launched using either conventional chemical rockets or micro-fusion for accelerating thrust.

Nuclear propulsion fission reactor structure has an active core region including fuel element structures, a reflector with rotatable neutron absorber structures (such as drum absorbers), and a core former conformal mating the outer surface of the fuel element structures to the reflector. Fuel element structures are arranged abutting nearest neighbor fuel element structures in a tri-pitch design. Cladding bodies defining coolant channels are inserted into and joined to upper and lower core plates to from a continuous structure that is a first portion of the containment structure. The nuclear propulsion fission reactor structure can be incorporated into a nuclear thermal propulsion engine for propulsion applications, such as space propulsion.

Systems and methods for nuclear reactor direct drive of a cryocooler turbine. A nuclear thermal propulsion (NTP) system may have a nuclear reactor that heats a thermal working fluid for directly driving the turbine to power a cryogenic fluid management (CFM) system for keeping propellant at cryogenic temperatures. The features may be used on NTP rockets. The propellant may be liquid hydrogen.

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.