Abstract: An aircraft hybrid motive power source system includes: a gas turbine engine mounted on an aircraft and including a low-pressure shaft and a high-pressure shaft as rotary shafts; a first motor generator drivingly connected to the high-pressure shaft; a second motor generator drivingly connected to the low-pressure shaft; a fuel cell to which a fuel gas and an oxidant gas are supplied; a fuel gas generator configured to generate the fuel gas from a raw material by heating using an exhaust gas from the gas turbine engine; and a controller configured to supply an electric power of the fuel cell obtained by a supply of the fuel gas to one of the first motor generator and the second motor generator, based on at least one of information indicating an operating status of the gas turbine engine and an electric power demand of the aircraft.

Abstract: According to one embodiment, an estimation device includes a processor. The processor is configured to acquire first and second images including a same subject continuously captured by a capture device installed in a mobile object, acquire a first distance to the subject included in the acquired first image and uncertainty of the first distance, extract a useful second distance from the acquired first distance based on the acquired uncertainty of the first distance, and estimate a position and orientation of the mobile object when the second image is captured by the capture device based on the acquired first and second images, and the extracted second distance.

Abstract: A fuel supply system includes a gear pump, and a minimum pressurizing check valve including a cylinder and a piston that partitions the internal space of the cylinder into a first chamber that communicates with the metering section and a second chamber that communicates with a system inlet, the piston is spring-biased in a direction toward the first chamber, a side wall of the cylinder is provided with an outflow port having an opening degree adjusted as the piston moves back and forth, the minimum pressurizing check valve keeps a differential pressure between the system inlet and the outlet of the metering section constant when the rotation speed of the gear pump is equal to or more than a lower threshold and is equal to or less than an intermediate threshold.

Abstract: A rotor of an electrical rotating device includes a rotor core, plural permanent magnets mounted on an outer circumference of the rotor core, a retaining sleeve that holds the permanent magnets from their outer side, a cooling fluid flow channel formed on each surface of the permanent magnets on a side of the retaining sleeve [or on each surface on a side of the rotor core], and a seal ring. The retaining sleeve is configured of plural divided sleeves divided along a direction of a rotation axis of the rotor. A seam is formed between adjacent divided sleeves in the plural divided sleeves. The seal ring covers the seam from an outer circumferential side [or an inner circumferential side].

Abstract: An aircraft air conditioning device provided in an aircraft includes: a plurality of base units each of which is provided with two electric compressors connected in series to an air flow path; a temperature controller which is configured to adjust a temperature of air discharged from a compressor of the two electric compressors; and a control device which is configured to control the plurality of base units and the temperature controller and each of the plurality of base units is configured to supply compressed air discharged from the temperature controller to an air-conditioned space as conditioned air.

Abstract: Composite particles for a non-aqueous electrolyte secondary battery include a lithium zirconate phase, and a silicon phase dispersed in the lithium zirconate phase. In the composite particles, a content proportion MZr of zirconium in all elements other than oxygen is, for example, 14.6 mass % or more and 54.6 mass % or less, and a content proportion MLi of lithium in all elements other than oxygen is, for example, 0.9 mass % or more and 10.4. mass % or less.

Abstract: A negative electrode active material for a non-aqueous electrolyte secondary battery includes composite particles containing a lithium aluminate phase, and a silicon phase dispersed in the lithium aluminate phase.

Abstract: A fuel supply control device (10) is configured to generate an operation amount used for feedback-controlling rotation of a gear pump (3) based on a deviation of a detected fuel flow rate with respect to a target flow rate, wherein the fuel supply control device generates the operation amount such that a rotation speed of the gear pump is equal to or greater than a predetermined lower limit rotation speed Nmin so as to protect a bearing of the gear pump.

Abstract: An electric generator equipped in a multi-shaft gas turbine engine for aircraft, includes: a rotor attached to the rear end portion of a low-pressure shaft rotatably supported by a bearing in the gas turbine engine; a stator provided around the rotor; wherein the electric generator has no structure to support the low-pressure shaft and the rotor.

Abstract: A negative electrode active material for a non-aqueous electrolyte secondary battery includes composite particles containing a lithium silicate phase, a silicon phase dispersed in the lithium silicate phase, and a crystalline phase of silicon dioxide dispersed in the lithium silicate phase. The crystalline phase of silicon dioxide contains ?-cristobalite and quartz.

Abstract: A system capable of appropriately cooling a generator and a power cable connected to the generator, disposed in a hot section of a turbo-fan engine, regardless of a rating of the engine is provided. The system includes: a junction box; a bypass air duct that supplies, to the junction box, air extracted from a portion of a bypass flow path of the engine on a side further downstream than a fan outlet; a core air duct that supplies, to the junction box, air extracted from a portion of a core flow path of the engine on a side further upstream than a compressor outlet; and a cooling air duct that extends from the junction box to a space for accommodating the generator, and valves capable of being independently controlled to open and close are provided at downstream ends of the bypass air duct and the core air duct.

Abstract: A negative electrode material for a non-aqueous electrolyte secondary battery includes composite particles, and a conductive layer disposed on a surface of each of the composite particles. The composite particles each have a silicate phase, and silicon phases dispersed in the silicate phase. The conductive layer contains a calcium component.

Abstract: In an external gear pump, a first bushing of a rotational shaft of a first gear has a second surface facing to a first surface of a pump body. A recess for supplying high-pressure lubricating oil between an inner circumferential surface of the first bushing and an outer circumferential surface of the rotational shaft is opened on the inner circumferential surface within a low pressure range associating with an inlet chamber of fluid. A bushing-side supply passage for supplying the high-pressure lubricating oil to the recess is formed within the first bushing. A bushing-side inlet port of the bushing-side supply passage is opened on the second surface within a high pressure range associating with an outlet chamber of the fluid. A body-side supply passage for supplying the high-pressure lubricating oil to a body-side supply port opened on the first surface is formed within the pump body.

Abstract: A secondary battery including a positive electrode, a negative electrode, and an electrolyte. The negative electrode includes a carbon material, a first silicon-containing material, and a second silicon-containing material. The first silicon-containing material includes a silicate phase, and first silicon phases dispersed in the silicate phase. The second silicon-containing material includes a carbon phase, and second silicon phases dispersed in the carbon phase.

Abstract: A negative electrode active material for a secondary battery includes a silicon-containing material. The silicon-containing material includes a lithium-ion conductive phase, silicon particles dispersed in the lithium-ion conductive phase, and particles containing vanadium dispersed in the lithium-ion conductive phase.

Abstract: A negative electrode active material for a secondary battery comprising silicate composite particles including silicon particles and a lithium silicate phase. The silicon particles are dispersed in the lithium silicate phase, the silicate composite particles have a porosity of 2% or less. In a diffraction pattern by X-ray diffraction (XRD), a ratio I2/I1 is 0.3 or less, the ratio I2/I1 being a ratio of an integrated intensity I2 of a peak derived from the lithium silicate phase that appears in a range of 2? of 23° to 25° relative to an integrated intensity I1 of a peak derived from Si(111) plane of the silicon particles that appears in a range of 2? of 27° to 30°.

Abstract: A negative electrode active material for a secondary battery includes silicate composite particles including silicon particles and a silicate phase. The silicon particles are dispersed in the silicate phase, and the silicon particles contain a first element of at least one selected from the group consisting of germanium and aluminum.

Abstract: Provided is a stator including a coil of a winding of a flat wire conductor, a stator core including a slot for housing a part of the coil, and a flow passage part through which a coolant flows, provided between a wall part of the slot and an outer surface of the coil facing the wall part. The extension shape of the flow passage part from an inlet to an outlet for the coolant changes along the axial direction of the stator core. The flow passage part is, for example, a concave part formed on the wall part of the slot.

Abstract: An electric generator equipped in a multi-shaft gas turbine engine for aircraft, includes: a rotor attached to the rear end portion of a low-pressure shaft rotatably supported by a bearing in the gas turbine engine; a stator provided around the rotor; wherein the electric generator has no structure to support the low-pressure shaft and the rotor.

Abstract: A cooling system includes: a core casing configured to house a compressor, a combustion chamber, and a turbine; a tail cone configured to form at least part of an exhaust passage of the turbine together with the core casing; struts configured to connect the core casing with a support body of the tail cone; a housing installed in the tail cone, configured to house an electrical apparatus; and at least one primary duct configured to connect between an internal space of the housing and an outlet passage of the compressor or a discharge port of a blower installed in a gas turbine engine via at least one of the struts and a radial outside of the core casing.