Abstract: An electric vertical takeoff and landing aircraft with a plurality of electric drive systems each including a drive motor for turning a rotor and a drive unit for driving the drive motor includes: a drive information detection unit that detects, for each of the plurality of electric drive systems, drive information including at least one of motor information serving as an indicator of the deterioration state of the drive motor and drive unit information serving as an indicator of the deterioration state of the drive unit; and a maintenance necessity detection unit that detects the necessity or lack of necessity of maintenance on each of the plurality of electric drive systems based on the detected drive information.

Abstract: A lock device can be shifted between a locked state and an unlocked state. The lock device includes a lock pin, a solenoid, and a pressing unit. The lock pin is movable between a locked position where a propeller is locked and an unlocked position where the propeller is not locked. The pressing unit presses the lock pin to the locked position by a mechanical pressing force. The solenoid includes a solenoid coil and a plunger. When the solenoid coil is energized, the plunger moves the lock pin to the unlocked position against the mechanical pressing force.

Abstract: An EPU includes a first DS and a second DS. The first DS includes a first motor and a first inverter control unit. The second DS includes a second motor and a second inverter control unit. The first motor and the second motor are connected to a propeller via an EPU shaft. The EPU shaft drives and rotates a propeller according to outputs of the motor. The first inverter control unit controls the first motor so that the output of the first motor and the output of the second motor become a same. The second inverter control unit controls the second motor so that the output of the first motor and the output of the second motor become same as each other.

Abstract: A control device controls an electric drive system mounted on an electric vertical takeoff and landing aircraft with a rotor, and including a drive motor that turns the rotor. The control device controls the electric drive system to operate selectively in any one operation mode of at least two operation modes: a normal mode and a functional test mode. In the normal mode, the control device controls the drive motor in accordance with a command from a body control device that controls the flight of the electric vertical takeoff and landing aircraft. In the functional test mode, the control device controls the drive motor in accordance with a command sent from outside according to a functional test program, or in accordance with the functional test program preset in the control device.

Abstract: Motor fins are provided to a motor outer peripheral surface of a motor housing. Inverter fins are provided to an inverter outer peripheral surface of an inverter housing. A fin cover covers the motor fins and the inverter fins from a radially outward direction. A cover flow passage is formed between the fin cover and the motor outer peripheral surface and between the fin cover and an inverter outer peripheral surface. The cover flow passage includes a first flow passage and a second flow passage, the motor fins being provided in the first flow passage, the inverter fins being provided in the second flow passage. In the second flow passage, a second air flow having flowed into a second inflow port reaches the inverter fins without passing through the first flow passage.

Abstract: A control apparatus, which controls a drive motor that drives a rotor installed in an electrical aircraft, instructs the drive motor to selectively operate in at least two motor-control modes. The at least two motor-control modes include a flying motor-control mode for causing the electrical aircraft to fly, and a cleaning motor-control mode for cleaning the rotor. The control apparatus controls, in the cleaning motor-control mode, the drive motor such that a rotational frequency of the drive motor is lower than a predetermined human-audible frequency range.

Abstract: In an aircraft monitoring system for monitoring a fuselage of an aircraft, an imaging device mounted to the fuselage is configured to capture and acquire at least images of driven parts involved in generation of lift or thrust for flight of the aircraft. An image processor is configured to use the captured images to generate an overhead image of the aircraft as viewed from above the fuselage.

Abstract: An electric vertical takeoff and landing aircraft with a plurality of electric drive systems each including a drive motor for turning a rotor and a drive unit for driving the drive motor includes: a drive information detection unit that detects, for each of the plurality of electric drive systems, drive information including at least one of motor information serving as an indicator of the deterioration state of the drive motor and drive unit information serving as an indicator of the deterioration state of the drive unit; and a maintenance necessity detection unit that detects the necessity or lack of necessity of maintenance on each of the plurality of electric drive systems based on the detected drive information.

Abstract: A control device controls an electric drive system mounted on an electric vertical takeoff and landing aircraft with a rotor, and including a drive motor that turns the rotor. The control device controls the electric drive system to operate selectively in any one operation mode of at least two operation modes: a normal mode and a functional test mode. In the normal mode, the control device controls the drive motor in accordance with a command from a body control device that controls the flight of the electric vertical takeoff and landing aircraft. In the functional test mode, the control device controls the drive motor in accordance with a command sent from outside according to a functional test program, or in accordance with the functional test program preset in the control device.

Abstract: A cathode active material for a non-aqueous electrolyte secondary battery satisfies conditions (1) to (5): (1) the cathode active material contains Li, Mn, and Ni and has a spinel structure; (2) a molar ratio of Ni to Mn is in a range from 0.10 to 0.43; (3) a molar ratio of Li to Mn is in a range from 0.70 to 1.80; (4) the cathode active material has a peak in a range of 2?=19.7 to 22.5° in an X-ray diffraction pattern; and (5) the cathode active material has at least one peak in a voltage range of voltage V1 and at least two peaks in a voltage range of voltage V2 in an initial dQ/dV curve of a discharge measured when a half cell is prepared using the cathode active material, V1=2.72 to 2.90 [V] V2=4.50 to 4.80 [V].

Abstract: A cathode active material for a non-aqueous electrolyte secondary battery satisfies conditions (1) to (5): (1) the cathode active material contains Li, Mn, and Ni and has a spinel structure; (2) a molar ratio of Ni to Mn is in a range from 0.10 to 0.43; (3) a molar ratio of Li to Mn is in a range from 0.70 to 1.80; (4) the cathode active material has a peak in a range of 2?=19.7 to 22.5° in an X-ray diffraction pattern; and (5) the cathode active material has at least one peak in a voltage range of voltage V1 and at least two peaks in a voltage range of voltage V2 in an initial dQ/dV curve of a discharge measured when a half cell is prepared using the cathode active material, V1=2.72 to 2.90 [V] V2=4.50 to 4.80 [V].