Patent Number: 042467519
Section: claims

1. A nuclear engine and nozzle arrangement for a nuclear rocket, said arrangement comprising a cluster of elongated fissile fuel bearing and high temperature capacity modules suitably supported in a pressure vessel, said modules each having a plurality of coolant-propellant channels extending therethrough, a convergent-divergent nozzle structure of fixed cross-sectional dimension secured to the end portion of each of said modules said modules, a divergent-only unitary skirt member connected directly to the propellant exit end of said modular cluster in series with and diverging from the divergent ends of said convergent-divergent nozzle structures, said modules being formed to conduct a compressible propellant therethrough at sub-sonic velocities, said nozzle structures being formed to develop supersonic velocities of the propellant and said divergent-only skirt being formed to develop further the supersonic velocities of said propellant. 2. A nuclear engine and nozzle arrangement for a nuclear rocket, said arrangement comprising a cluster of elongated fissile fuel bearing and high temperature capacity modules suitably supported in a pressure vessel, said modules each having a plurality of coolant-propellant channels extending therethrough, a convergent-divergent nozzle structure of fixed cross-sectional dimensions secured to the discharge end portion of each of said modules for supersonic velocity development of the propellant as it flows at sub-sonic velocities from the module channels and then through the nozzle structures for discharge from each of the modules, and a divergent-only unitary skirt member secured directly to the propellant exit end of said modular cluster in series with and diverging from the divergent ends of said convergent-divergent nozzle structures to provide further velocity development for the propellant as it flows from the individual module nozzle structures to the exterior. 3. A nuclear engine and nozzle arrangement for a nuclear rocket as set forth in claim 2, wherein each of said modules is provided with a plurality of coolant-propellant channels in each of which a fuel bearing rod is supported, said channels extend longitudinally through each of said fuel rods, and the nozzle structure of each of said modules is integral therewith. 4. A nuclear engine and nozzle arrangement for a nuclear rocket as set forth in claim 2, wherein a body member of each of said modules has fissile fuel material incorporated interstitially therein and said coolant-propellant channels extend longitudinally through said body member, and the nozzle structure of each of said modules is a separate high temperature capacity element secured to the exit end of the respective body members by suitable means. 5. An engine and nozzle arrangement for a rocket, said arrangement comprising a suitably supported cluster of elongated and generally parallel propellant heating and high temperature capacity modules, a convergent-divergent nozzle structure of fixed cross-sectional dimensions secured to the end portion of each of said modules for supersonic velocity development of the propellant as it flows from the modules, and a main divergent-only nozzle member secured directly to the propellant exit end of said modular cluster to provide further velocity development for the propellant as it flows from the individual module nozzle structures to the exterior.