Patent Number: 056365128
Section: claims

1. A nuclear thermal rocket engine comprising: a rocket propellant source;  a nuclear reactor including an inlet for receiving propellant from said propellant source, fuel assemblies for heating said propellant, an outlet coupled to said fuel assemblies for discharging said heated propellant therefrom and a recycling port disposed between said fuel assemblies and said outlet;  a primary feed system including a line coupling said rocket propellant source to said nuclear reactor inlet and a pump coupled to said line for pumping said propellant through said line; and  an auxiliary feed system including a bypass line having an inlet receiving heated propellant from said recycling port, a first outlet for returning a first portion of said heated propellant to said rocket propellant source and a second outlet for returning a second portion of said heated propellant to a fluid line between said nuclear reactor inlet and said fuel assemblies, said auxiliary feed system further including means for withdrawing heat from propellant flowing through said bypass line.  a rocket propellant source;  a nuclear reactor including an inlet for receiving propellant from said propellant source, fuel assemblies for heating said propellant, an outlet coupled to said fuel assemblies for discharging said heated propellant and a recycling port disposed between said fuel assemblies and said outlet;  a primary feed system including a line coupling said rocket propellant source to said nuclear reactor inlet and a pump coupled to said line for pumping said propellant through said line; and  an auxiliary feed system including a bypass line having an inlet for receiving heated propellant from said recycling port and an outlet for directing a substantial portion of said heated propellant to said primary feed line downstream of said propellant source and upstream of said nuclear reactor inlet, said auxiliary feed system further including means for withdrawing heat from propellant flowing through said bypass line.  a rocket propellant source;  a nuclear reactor including an inlet for receiving propellant from said propellant source, fuel assemblies for heating said propellant, an outlet coupled to said fuel assemblies for discharging said heated propellant and a recycling port disposed between said fuel assemblies and said outlet;  a primary feed system including a line coupling said rocket propellant source to said nuclear reactor inlet and a pump coupled to said line for pumping said propellant through said line;  an auxiliary feed system including a bypass line having an inlet for receiving heated propellant from said recycling port and an outlet for directing a portion of said heated propellant to said primary feed line, said auxiliary feed system further including means for withdrawing heat from propellant flowing through said bypass line; and  a controllable valve coupled to said bypass line between said turbine and said recuperator, the valve being adapted to selectively control propellant flow such that a first: portion of said propellant flows through said recuperator to said radiator and a second portion of said propellant flow bypasses said recuperator and flows directly to said radiator. 2. The rocket engine of claim 1 further including a recuperator coupled to said bypass line and to said primary feed line between said pump and said nuclear reactor inlet, the recuperator being adapted to transfer heat from propellant flowing through said bypass line to propellant flowing through said primary feed line. 3. The rocket engine of claim 1 further including an electric pump coupled to said primary feed line between said pump and said propellant source for receiving said propellant from said propellant source and pumping said propellant to said nuclear reactor inlet, said auxiliary feed system providing power to said electric pump. 4. The rocket engine of claim 2 wherein said auxiliary feed system includes a turbine and a compressor coupled to said bypass line for pumping said second portion of said heated propellant from said recycling port to said nuclear reactor, said first portion of said heated propellant being allowed to flow back into said propellant source. 5. The rocket engine of claim 4 further including a valve coupled to said bypass line between a discharge side of said turbine and said recuperator, said valve being adapted to eject a portion of said propellant into space to decrease fluid pressure at said discharge side of said turbine. 6. A nuclear thermal rocket engine comprising: 7. The rocket engine of claim 6 further including a turbine and a compressor coupled to said bypass line for pumping propellant from said recycling port to said primary feed line. 8. The rocket engine of claim 6 further including a recuperator coupled to said primary feed line between said pump and said nuclear reactor inlet and to said bypass line between said turbine and said compressor, the recuperator being adapted to transfer heat from propellant flowing through said bypass line to propellant flowing through said primary feed line. 9. The rocket engine of claim 8 wherein the withdrawing means includes a radiator for withdrawing a substantial portion of the heat from said propellant and discharging said portion of said heat into space. 10. A nuclear thermal rocket engine comprising: