초록 ▼

A nuclear rocket engine comprising a primary feed system (4) for pumping rocket propellant from a propellant source (10) to a nuclear reactor (6) and an auxiliary feed system (60) coupled to the primary feed system. The auxiliary feed system includes a space radiator (84) for discharging excess reac

A nuclear rocket engine comprising a primary feed system (4) for pumping rocket propellant from a propellant source (10) to a nuclear reactor (6) and an auxiliary feed system (60) coupled to the primary feed system. The auxiliary feed system includes a space radiator (84) for discharging excess reactor heat into space and a motorgenerator (74) for creating electricity from the excess reactor heat. A recuperator (20) operates to heat liquid propellant before it enters the reactor and to retain heat within the system. The auxiliary power system can be configured into a high thrust mode (see FIG. 1) for withdrawing heat from the engine when the reactor is operating at full power, a low thrust mode (see FIG. 2) for throttling propellant flow and radiating heat from the engine during reactor shutdown and a zero thrust mode (see FIG. 3) for cooling the nuclear reactor and generating electricity for the rocket\s auxiliary power requirements for the remainder of the mission.

대표청구항 ▼

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 a

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 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 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.