Abstract: A storage system for a flying object is equipped with a landing portion having a landing surface on which the flying object can land, and a storage main body for storing the flying object that has landed on the landing surface. The storage main body includes opening and closing portions that cover the landing surface. The storage system is further equipped with retaining mechanisms adapted to retain the flying object in a state of having landed on the landing surface from a direction perpendicular to the landing surface.

Abstract: An aircraft propulsion system capable of improving power generation efficiency is provided. When a flight state of an aircraft is a first state after a plurality of engines operate and the aircraft takes off, the aircraft propulsion system causes at least one engine among the plurality of engines to be stopped, causes another engine, which has not been stopped, to be operated in an operating range in which the other engine is able to operate efficiently, and causes a generator corresponding to the other engine to output power.

Abstract: Technology for operating an engine smoothly is provided. In an aircraft propulsion system, a controller causes at least a first engine among the plurality of engines to be stopped and causes a second engine, which has not been stopped, to be operated when an aircraft is flying in a prescribed flight mode and causes the first engine to be operated and causes the second engine to be stopped when a detector detects that the temperature related to the first engine is less than or equal to a first prescribed temperature.

Abstract: An aircraft propulsion system capable of improving the restartability of an engine is provided. An aircraft propulsion system includes: a plurality of engines (60-1 and 60-2); an electric generator connected to engine shafts (63-1 and 63-2); a plurality of electric motors; a plurality of rotors; and a controller (100) which controls an operation state of the plurality of engines (60-1 and 60-2). The controller (100) causes a part of the plurality of engines (60-1 and 60-2) to operate while stopping the remaining engine when a flight state is in a first state. The plurality of engines (60-1 and 60-2) include circulators (65-1 and 65-2). A plurality of communication pipes (68 and 69) which communicate the circulator (65-1) in the first engine (60-1) among the plurality of engines (60-1 and 60-2) with the circulator (65-2) in the second engine (60-2) are provided.

Abstract: Provided is a gas turbine system in which electricity consumption of a battery when starting or stopping a gas turbine engine is reduced and sufficient battery power during flight can be secured. The present invention includes a plurality of gas turbine engines 21, 22, and 23, generators 41, 42, and 43, a battery 5, and a controller 7. The controller 7 decides at least one main starting gas turbine engine 21 from the plurality of gas turbine engines before the plurality of gas turbine engines are started, starts the main starting gas turbine engine 21 using electricity from the battery 5, and starts the secondary starting gas turbine engines 22 and 23 of the plurality of gas turbine engines other than the main starting gas turbine engine 21 using electricity from the generator 41 connected to the main starting gas turbine engine 21 after the main starting gas turbine engine 21 reaches a steady state.

Abstract: An aircraft propulsion system capable of reducing a rotational load of an engine shaft is provided. An aircraft propulsion system includes a plurality of engines (60-1 and 60-2) and a controller (100). When a flight state is a first state, the controller (100) causes some of the plurality of engines (60-1 and 60-2) to operate while stopping the remaining engine. At least one engine (60-1) of the plurality of engines (60-1 and 60-2) includes a bleed air hole (71-1), a bleed air pipe (72-1), and a bleed air valve (73-1). When causing the engine (60-2) which has stopped to start up again, the controller (100) opens a bleed air valve (73-1) in the engine (60-1) which is in operation and supplies compressed air of the compressor (62-1) to the compression chamber (64-2) of the engine (60-2) which has stopped.

Abstract: An analytical device is provided. The analytical device includes a battery condition analysis section configured to detect a state change of a constituent member of a battery based on a change in peak of a relaxation time in a predetermined frequency band.

Abstract: There is provided a vertical takeoff and landing aircraft (VTOL), having a main propulsion unit (GT engine) with high-pressure and low-pressure turbine shafts installed along a longitudinal axis of a frame to be rotated by pressurized gas jetted on combustion of an air-fuel mixture to produce propulsion force in a longitudinal direction of the frame, high-pressure side and low-pressure side motor generators coaxially attached to the high-pressure and low-pressure turbine shaft, four fans installed on the frame to be rotatable around axes parallel to a vertical axis of the frame, four propulsion units individually connected to the fans to rotate them and generate lift force in a vertical direction of the frame, and a controller. The controller control operation of the main propulsion unit, motor generators and sub propulsion units to obtain propulsion forces in the longitudinal direction and in the vertical direction of the frame.

Abstract: There is provided a multicopter having a frame, four rotors attached to the frame and each having an input shaft, four motor-generators installed one on each of the rotors and each having an input-output shaft, a single gas-turbine engine connected to the motor-generators and having an output shaft. The input shaft of each rotor, the input-output shaft of each motor-generator and the output shaft of the engine are respectively connected with each other by a speed reducer mechanism having a sun gear, ring gear and planetary carrier.

Abstract: A secondary battery includes: a cathode; an anode including a carbon material; and non-aqueous electrolytic solution. A photoelectron spectrum of oxygen 1s is obtained from an analysis of the anode by X-ray photoelectron spectroscopy. A first peak positioned in vicinity of 1360 reciprocal centimeters and a second peak positioned in vicinity of 1580 reciprocal centimeters are obtained from an analysis of the carbon material by Raman spectroscopy. A half band width ?W1 of the photoelectron spectrum is about 3 electron volts or more. A half band width ?W2 of the second peak is about 19 reciprocal centimeters or more. A ratio I1/I2 of intensity I1 of the first peak to intensity I2 of the second peak is from about 0.15 to about 0.3 both inclusive.

Abstract: A storage system for a flying object is equipped with a landing portion having a landing surface on which the flying object can land, and a storage main body for storing the flying object that has landed on the landing surface. The storage main body includes opening and closing portions that cover the landing surface. The storage system is further equipped with retaining mechanisms adapted to retain the flying object in a state of having landed on the landing surface from a direction perpendicular to the landing surface.

Abstract: There is provided a multicopter having a frame, four rotors attached to the frame and each having an input shaft, four motor-generators installed one on each of the rotors and each having an input-output shaft, a single gas-turbine engine connected to the motor-generators and having an output shaft. The input shaft of each rotor, the input-output shaft of each motor-generator and the output shaft of the engine are respectively connected with each other by a speed reducer mechanism having a sun gear, ring gear and planetary carrier.

Abstract: There is provided a vertical takeoff and landing aircraft (VTOL), having a main propulsion unit (GT engine) with high-pressure and low-pressure turbine shafts installed along a longitudinal axis of a frame to be rotated by pressurized gas jetted on combustion of an air-fuel mixture to produce propulsion force in a longitudinal direction of the frame, high-pressure side and low-pressure side motor generators coaxially attached to the high-pressure and low-pressure turbine shaft, four fans installed on the frame to be rotatable around axes parallel to a vertical axis of the frame, four propulsion units individually connected to the fans to rotate them and generate lift force in a vertical direction of the frame, and a controller. The controller control operation of the main propulsion unit, motor generators and sub propulsion units to obtain propulsion forces in the longitudinal direction and in the vertical direction of the frame.

Abstract: An analytical device is provided. The analytical device includes a battery condition analysis section configured to detect a state change of a constituent member of a battery based on a change in peak of a relaxation time in a predetermined frequency band.

Abstract: A battery capable of improving high-temperature characteristics is provided. The battery includes a cathode, an anode and an electrolytic solution. A separator provided between the cathode and the anode is impregnated with the electrolytic solution. A solvent of the electrolytic solution includes a main solvent such as a cyclic carbonate which includes halogen and a sub solvent such as carbonate dimer.

Abstract: A secondary battery capable of improving high-temperature characteristics is provided. The secondary battery includes a cathode, an anode and an electrolytic solution. A separator provided between the cathode and the anode is impregnated with the electrolytic solution. A solvent of the electrolytic solution includes a main solvent such as a cyclic carbonate which includes halogen and a sub solvent such as carbonate dimer.

Abstract: An electrolytic solution for a secondary battery is provided. The electrolyte solution includes an electrolyte salt; and a solvent including a first solvent and a second solvent; wherein the first solvent includes 4-fluoro-1,3-dioxolane-2-one; and wherein the second solvent includes at least one of Chemical Formula No. 23, Chemical Formula No. 24, or Chemical Formula No. 25.

Abstract: A secondary battery is provided. The secondary battery includes a cathode; an anode; and a non-aqueous electrolytic solution, wherein the cathode includes any one of a first lithium-containing compound and a second lithium-containing compound, the first lithium-containing compound having a bedded salt-type crystal structure, wherein the first lithium-containing compound includes one or more metal elements (M) other than lithium (Li), wherein the second lithium-containing compound having an olivine-type crystal structure, and wherein the nonaqueous electrolytic solution includes an unsaturated cyclic compound.

Abstract: A secondary battery includes: a cathode including an active material; an anode; and an electrolytic solution, and the active material includes a plurality of active material particles as primary particles and a carbon material. The active material particles contain a polyanion-based compound. The carbon material contains a first carbon material present on surfaces of the active material particles, and a second carbon material present between the active material particles provided with the first carbon material. A ratio B/A between a total carbon amount A and a surface carbon amount B of the active material satisfies 7<B/A<11.5. A ratio D/C between a specific surface area C of the active material, and an oil feed amount D of N-methyl-2-pyrrolidone satisfies 1.5<D/C?2.

Abstract: A current collector forming an electrode for battery is provided. The electrode current collector includes a conductive layer made of copper or a copper alloy. Furthermore, the conductive layer has a plurality of crystallites, the crystallites containing crystallites having a cross-section area of 20 ?m2 or more.