Nuclear thermal propulsion rocket engine

Abstract

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.