An electronic component unit integrates a plurality of electronic components. The electronic component unit includes, a plurality of electronic components, a case that accommodates the plurality of electronic components, a mold material with which an inside of the case is filled and that seals the plurality of electronic components, and at least one bus bar connected to each of the electronic components. The case includes a case body that supports the plurality of electronic components, and at least one wall body formed separately from the case body and attached to the case body, and the bus bar penetrates through a gap between the case body and the wall body.

An electronic component unit integrates a plurality of electronic components. The electronic component unit includes, a plurality of electronic components, a case that accommodates the plurality of electronic components, a mold material with which an inside of the case is filled and that seals the plurality of electronic components, and at least one bus bar connected to each of the electronic components. The case includes a case body that supports the plurality of electronic components, and at least one wall body formed separately from the case body and attached to the case body, and the bus bar penetrates through a gap between the case body and the wall body.

An electric drive device includes one shaft extending in a prescribed axial direction, a first rotary electric machine and a second rotary electric machine each arranged coaxially with the shaft and connected to the shaft, a first controller electrically connected to the first rotary electric machine and configured to control driving of the first rotary electric machine, and a second controller electrically connected to the second rotary electric machine and configured to control driving of the second rotary electric machine. The first rotary electric machine and the second rotary electric machine are spaced apart from each other in the axial direction of the shaft, and the first controller and the second controller are arranged between the first rotary electric machine and the second rotary electric machine.

An electric drive device includes one shaft extending in a prescribed axial direction, a first rotary electric machine and a second rotary electric machine each arranged coaxially with the shaft and connected to the shaft, a first controller electrically connected to the first rotary electric machine and configured to control driving of the first rotary electric machine, and a second controller electrically connected to the second rotary electric machine and configured to control driving of the second rotary electric machine. The first rotary electric machine and the second rotary electric machine are spaced apart from each other in the axial direction of the shaft, and the first controller and the second controller are arranged between the first rotary electric machine and the second rotary electric machine.

Thrust values for motors in an aircraft are generated where each flight controller in a plurality of flight controllers generates a thrust value for each motor in a plurality of motors using an optimization problem with a single solution. Each flight controller in the plurality of flight controllers passes one of the generated thrust values to a corresponding motor in the plurality of motors, where other generated thrust values for that flight controller terminate at that flight controller. The plurality of motors perform the passed thrust values.

Systems and methods for flight control on an electric aircraft. The system includes a propulsor configured to generate lift to propel an electric aircraft, a pilot input mechanically coupled to the electric aircraft, a sensor communicatively connected to the pilot input, and a flight controller communicatively connected to the sensor. Sensor is configured to detect an input datum from the pilot input and convert the input datum into a command datum for the propulsor as a function of input mapping. Input mapping is determined as a function of the phase of flight.

A controller (a control unit) of a power supply system of a vertical take-off and landing aircraft is configured to: after lift is generated by wings (a front wing and a rear wing), perform stop control of controlling electric power supplied to a motor so that rotation of a VTOL rotor continues to stop; temporarily cancel the stop control in response to the temperature of any one switching element detected by a temperature detection unit (a temperature sensor) becoming equal to or higher than a temperature threshold during the stop control; and resume the stop control after the stop control has been temporarily canceled.

To provide an electric aircraft and an aerodynamic performance control method therefor that are capable of optimizing aerodynamic performance of a wing in each flight phase or an emergency such as gust action without depending on the shape of a wing.

To provide an electric aircraft and an aerodynamic performance control method therefor that are capable of optimizing aerodynamic performance of a wing in each flight phase or an emergency such as gust action without depending on the shape of a wing.

[Solving Means] An electric aircraft 1 includes: one or two or more electric propulsion systems 20 each including a propeller or fan 21 for propulsion disposed to contribute to a lift of a main wing 11, 12, and an electric motor 22 that drives the propeller or fan 21; and a controller that adjusts the electric propulsion system 20 on the basis of a relationship between a variable relating to an operating state of the electric propulsion system 20 and an aerodynamic force generated on the main wing 11, 12 such that a total thrust by the electric propulsion systems 20 or the aerodynamic force on the main wing 11, 12 has a predetermined value or falls within a predetermined range.

To provide an electric aircraft and an aerodynamic performance control method therefor that are capable of optimizing aerodynamic performance of a wing in each flight phase or an emergency such as gust action without depending on the shape of a wing.

To provide an electric aircraft and an aerodynamic performance control method therefor that are capable of optimizing aerodynamic performance of a wing in each flight phase or an emergency such as gust action without depending on the shape of a wing.

[Solving Means] An electric aircraft 1 includes: one or two or more electric propulsion systems 20 each including a propeller or fan 21 for propulsion disposed to contribute to a lift of a main wing 11, 12, and an electric motor 22 that drives the propeller or fan 21; and a controller that adjusts the electric propulsion system 20 on the basis of a relationship between a variable relating to an operating state of the electric propulsion system 20 and an aerodynamic force generated on the main wing 11, 12 such that a total thrust by the electric propulsion systems 20 or the aerodynamic force on the main wing 11, 12 has a predetermined value or falls within a predetermined range.

A method of controlling an electric aircraft that has a plurality of actuators that includes a plurality of electric propulsion units includes: receiving force and moment commands for the electric aircraft; determining control commands for the plurality of actuators based on the desired force and moment commands by solving an optimization problem that comprises a noise minimization term for minimizing noise generated by the electric propulsion units; and controlling the plurality of actuators according to the determined control commands to meet the force and moment commands for the electric aircraft.