Abstract: A reactor circulating pump system comprises a pump and a power supply apparatus for driving the pump. In the power supply apparatus, an AC/DC converter and a DC/AC converter provided with an AC voltage/frequency adjuster are connected in series between an in-plant AC bus and a reactor circulating pump, a DC voltage adjuster, a superconducting energy storage apparatus and an excitation power supply source are connected to the input side of the DC/AC converter. A controller is incorporated in the power supply apparatus so as to receive a signal indicating instantaneous power failure or power breakdown on the in-plant AC bus, or reactor trip, and change an AC voltage supplied to the reactor circulating pump with a ratio of AC voltage and frequency kept constant for controlling a pump delivery rate to have a predetermined value, while holding an output voltage from the superconducting energy storage apparatus at a predetermined value.

Abstract: A boiling water reactor comprises a reactor pressure vessel accommodated in a vertical fashion, a core disposed at a low portion in the reactor pressure vessel, a plurality of control rods to be inserted from an upper side of the core into the spaces between adjacent fuel assemblies and withdrawn therefrom upwardly, a shroud surrounding the fuel assemblies so as to define the core and having an upper end opening, a shroud head which closes the upper end opening of the shroud and through which the control rods are inserted or withdrawn, a separator standing upward from the shroud head to carry out gas-water separation of steam generated from the core, a fixing pedestal disposed above the separator, a control rod driving mechanism mounted on the fixing pedestal and adapted to drive the control rods, a drier unit including a plurality of drier elements annularly arranged along an upper inner wall surface of the reactor pressure vessel and adapted to dry the steam passing through the steam flow hole of the fixing

Abstract: For controlling the attitude of a rocket including a rocket fuselage and a thrust nozzle integrally attached to the rear end of the rocket fuselage and having a nozzle throat located longitudinally intermediate thereof, a rocket attitude control apparatus comprises a plurality of thrust vector control units disposed at the outer periphery of the thrust nozzle between the nozzle throat and the rear end of the thrust nozzle in circumferentially equiangularly spaced relationship to each other, and each including a fluid injecting nozzle projectable and retractable into and out of the thrust nozzle and having an injecting bore therein, wherein said fluid injecting nozzle is permitted to project into the thrust nozzle while being cooled by fluid injected from the injecting bore into the thrust nozzle. The projection of the fluid injecting nozzle causes a stream of combustion gas passing through the thrust nozzle to be partially disturbed for controlling the attitude of the rocket.