Abstract: An aircraft door includes a seal that integrates a flexible silicone seal portion and a rigid blade seal portion into a single continuous seal around the mold line gap between the door and frame. The arrangement allows for the use of space saving piano hinges to mount the door. The seal includes a rigid blade seal around three edges of the door and a flexible hinge cover seal adjacent to the hinge edge of the door. The flexible hinge cover seal is bonded to terminal blocks which in turn can be mounted to the door edge and to the door frame such that the flexible hinge cover seal covers the mold line gap adjacent to the hinge.

Abstract: When carrying the large structure out through an aperture portion provided at a roof of a reactor building, a chamber for covering the aperture is provided at the roof so that work of providing the chamber for covering the aperture portion can be performed independent of other work performed in the reactor building. At least a part of the work of using a roof crane, and at least a part of the work of handling fuel assemblies in the reactor building can be performed in parallel with forming the roof aperture.

Abstract: A ceiling panel speaker 100 comprises ceiling panel vibrating plates 110 and exciter units 200 mounted on said vibrating plates 110, each exciter unit 200 connected via line 270 to an amplifier not shown. The ceiling panel vibrating plates 110 are aligned to form a longitudinal size L1 extending above one or more aisles within the cabin, so that the ceiling panel speaker 100 realizes a long surface sound source. The sound waves output from the ceiling panel speaker 100 are transmitted along inner wall panels 12 etc. and spread throughout the closed space of the passenger cabin 50.

Abstract: A method of ejecting or jettisoning stores from an aircraft is disclosed that pertains essentially to the over-pressurizing of an on-board gas storage system such that the pressure of the gas stored therein remains at or above the proper pneumatic actuation pressure during all foreseeable temperature ranges. When a control signal to release a store is provided, the pressure of the gas is reduced to be within the desired pneumatic actuation pressure and the gas is then used to release the store. The present invention eliminates many of the concerns associated with prior art ejection systems by providing a method of supplying proper pneumatic actuating pressures during store release without the need for on-board compressors or heating elements.

Abstract: An aircraft composite assembly 10 is provided, including a first composite member 12, at least one first flange joint 26 comprising a first plurality of plies 24 cured to the first composite member 12, a second composite member 30, and at least one second flange joint 38 comprising a second plurality of plies 36 cured to the second composite member 30. The at least one second flange joint 38 is bonded to the at least one first flange joint 26 such that the first composite member 12 is affixed to the second composite member 30.

Abstract: A method of carrying equipment out of a nuclear reactor building that, in carrying equipment rendered radioactive out of a nuclear reactor building, makes it possible to shorten the operating time and reduce the number of casks to be used, wherein the structures of a nuclear power plant that are outside the equipment installed in the nuclear power plant are removed and these removed structures are then stored in the space in the equipment and carried out of the building.

Abstract: An incore monitoring method of a nuclear reactor, includes, measuring neutron flux levels at pitch levels corresponding to local power range monitor sensors arranged along an axial direction inside a detector assembly installed in a nuclear reactor; performing power calculation, including calculation of thermal characteristics, of fuel assembly group consisting of fuel assemblies adjacent to the corresponding detector assembly, based on indicated values of the local power range monitor sensors of the corresponding detector assembly at a first time, calculating thermal characteristics at a second, subsequent time in which the power calculation is not calculated, based on values indicated by the local power range monitor sensors and calculated thermal characteristics at the first time and values indicated by the corresponding local power range monitor sensors at the second time, and monitoring the calculated thermal characteristics.

Abstract: An expandable/collapsible enclosure positioned about the existing door of a flight crew compartment of an airliner, which is expanded either manually or automatically by the motion of the aircraft to form an airlock type enclosure about the door to the flight crew compartment, the enclosure having its own outer secondary door controllable from the flight crew compartment, an individual seeking access to the flight crew compartment having to position themselves in front of the outer door and again within the enclosure for observation by the flight crew personnel before entering the flight crew compartment, the enclosure having chemical or gaseous means for immobilizing an individual not authorized to enter the enclosure or the flight crew compartment who may have overwhelmed a properly identified individual that was authorized to enter the enclosure.

Abstract: A device for fastening a first part to a second part, particularly for fastening a lining element in the interior of a vehicle, for example an aircraft, is provided with at least one fastening element connectable with the first part and releasably attachable to the second part. The fastening element is provided with a locking element that is supported on the fastening element so as to be movable between a disengaged position in which the fastening element is able to be set to the second part and to be detached therefrom, and a pre-locking position in which the fastening element is held at the second part. Further, the fastening element comprises an actuating element for moving the locking element between the disengaged position and the pre-locking position.

Abstract: One of methods for carrying out a reactor vessel according to the present invention comprises the steps of removing an overhead traveling crane in a reactor containment vessel of a pressurized water reactor, or the steps of, in an area where an overhead traveling crane is installed, operating the overhead traveling crane to move aside for creating a space, through which the reactor vessel is able to pass, and then carrying out the reactor vessel through an opening provided in a top portion of the reactor containment vessel. With the present method, the reactor vessel of the pressurized water reactor can be carried out in a short time with high efficiency.

Abstract: An absorber body arranged to absorb radiation in a nuclear energy arrangement. The absorber body comprises more than one area with a locally reduced thickness.

Abstract: An aerial cargo container is described that includes a cargo box with a plurality of hinged rotor blades having a stowed position against the sides of the box and a deployed position extending outwardly from the box, and a deceleration and orientation assembly to slow the descent of the container and align the longitudinal axis of the container with the relative wind direction, thereby minimizing damage to the blades upon opening. The assembly includes a drogue chute, a blade retainer to secure the blades in the stowed position, and a folded metering cord attached between the drogue chute and the box, and a segment securing the blade retainer, whereby the cord segments unfold sequentially upon exertion of a force to slow and orient the container, prior to release of the blade retainer to permit movement of the blades to their deployed positions.

Abstract: A mounting arrangement (46) for mounting a turbofan gas turbine engine (10) on an aircraft pylon (44). The gas turbine engine (10) comprises a core engine (24) having a core engine casing (26). The mounting (46) comprises a first mounting (48) for mounting the core engine casing (26) on the pylon (44) and a second mounting (50) for mounting the core engine casing (26) on the pylon (44). The first mounting (48) comprises a first hinge adjacent (52) the core engine casing (26) and a second hinge adjacent (54) adjacent the pylon (44). The first hinge (52) is arranged parallel to the axis (S) of the gas turbine engine (10) to form a roll hinge. The second hinge (54) is arranged in a plane perpendicular to the axis (S) of the gas turbine engine (10) to form a pitch hinge. The second mounting (50) comprises a third hinge (56) adjacent the core engine casing (26) and a fourth hinge (58) adjacent the pylon (44).

Abstract: A fuel channel box manufacturing method processes a fuel channel box of a zirconium-base alloy by a beta-quench treatment that heats the fuel channel box by a heating coil. The distance between the heating coil and the opposite walls of the fuel channel box is controlled so that temperature differences between the opposite walls of the fuel channel box are reduced. The fuel channel box of a zirconium-base alloy is heated at a temperature in a temperature range including &bgr;-phase temperatures so that temperature difference between the opposite walls is 50° C. or below. The fuel channel box manufacturing method is capable of manufacturing a fuel channel box that is not subject to significant irradiated bow even if a deflection is produced therein originally when the same is manufactured and of manufacturing the fuel channel box at a high production efficiency.

Abstract: Method of fabricating a fuel rod, comprising providing an effective amount of a metal oxide in the fuel rod to generate steam and mitigate the tendency for secondary hydriding. Fuel rods fabricated according to the method of the invention are also provided.

Abstract: An airborne platform comprising: (a) an aerodynamic body; (b) a protected element within the aerodynamic body; and (c) a cover, reversibly secured to the aerodynamic body, for protecting the protected element from an external atmosphere. The present invention is particularly suited for an electro-optical detection system equipped with an optical dome or window. Optical windows carried on airborne platforms are known to be particularly sensitive to the high temperatures generated by air friction at super-sonic speeds. By covering such a window when the airborne platform is in flight, and releasing the cover just before use, the electro-optical detection system equipped with the optical window can be made operative, even at airborne platform speeds of several Mach and higher.

Abstract: A method of ejecting or jettisoning stores from an aircraft is disclosed that pertains essentially a method of supplying the gas storage system with compressed gas that has a pressure-to-temperature ratio that ensures proper jettisoning of stores under all design temperature specifications, without the need for on-board compressors, heating elements, or venting systems. The invention can be practiced by simply making a temperature measurement, during or before the step of supplying the gas storage system with compressed gas, and determining therefrom the necessary pressure of compressed gas to initially supply to the gas storage system. By so doing, the performance of the ejection system at various temperatures is automatically controlled, regardless of the temperature of the compressed gas immediately after such gas is supplied to the gas storage system.

Abstract: A method and apparatus for optimizing the production of Pu-238 in a nuclear reactor during normal reactor operation is disclosed wherein the production of Pu-238 is confined to one or more selectively replaced fuel cells with target cells located in the inside of the active volume of the reactor core to maximize the neutron flux for target irradiation. The target cells are modified existing nuclear fuel assembly cells having some fuel rods replaced with target rods of Np-237 forming a cluster array and having rings of water filled rods surrounding the target cluster to produce the desired optimal Pu-238 production.

Abstract: A fuel assembly includes a bottom nozzle set on a lower core plate of a nuclear reactor, a top nozzle with a hold down spring to urge the bottom nozzle against the lower core plate, guide thimbles which guide control rods, having passed through the top nozzle, toward the lower core plate, a dashpot formed on each of the guide thimbles to reduce the fall velocity of a corresponding one of the control rods, a thimble screw which connects each of the guide thimbles to the bottom nozzle, and a drain hole formed to extend through each of the thimble screw. The dashpot has a large-diameter portion with substantially the same diameter as that of each of the guide thimbles. The diameter d of the drain hole falls within a range of 0.04D<d<0.08D where D is an inner diameter of the large-diameter portion.

Abstract: Apparatus particularly useful in aircraft for moving a container from a supporting surface on a lower level, e.g., cargo hold, to a higher level, e.g., passenger compartment, via a vertical lift shaft, includes: a lift member in the vertical lift shaft, a displaceable suspension member suspended from and below the lift member and displaceable in a horizontal direction from a normal position in precise alignment with the vertical lift shaft; and a spring urging the displaceable suspension member to its normal position.