A motor integrated type fluid machine suctions a fluid from a suction port and discharges the suctioned fluid from a discharge outlet. The machine includes: a shaft portion provided at a center of a rotation axis; a rotating portion rotating around the shaft portion; an outer peripheral portion provided on an outer periphery of the shaft portion; and an outer peripheral drive motor rotating the rotating portion. The rotating portion includes a hub rotatably supported by the shaft portion, blades provided on an outer peripheral side of the hub and provided side by side in a circumferential direction of the rotation axis, and a rotating outer peripheral portion having an annular shape along the circumferential direction. A ratio of a rigidity of the rotating outer peripheral portion against a centrifugal force to a rigidity of the rotating portion against the centrifugal force is 50% to 95%.

A system for estimating flight range of an electric aircraft. The system generally includes at least a sensor and a flight controller. The at least a sensor is communicatively connected to at least a flight component. The at least a sensor is configured to detect a performance datum of the at least a flight component. The flight controller is communicatively connected to the at least a sensor. The flight controller is configured to receive the performance datum from the at least a sensor, determine an energy performance datum from the performance datum, determine a flight performance datum from the performance datum, generate a projected flight range datum as a function of the energy performance datum and the flight performance datum, and display the projected flight range datum. A method for estimating flight range of an electric aircraft is also provided.

Disclosed is a control apparatus for an electric power generation system. The electric power generation system is configured to generate electric power and thereby charge a secondary battery that is an electric power source of a motor included in an electric drive system. The electric drive system further includes an inverter circuit for driving the motor and a power transmission unit for transmitting electric power from the secondary battery to the inverter circuit. The control apparatus includes a temperature acquisition unit and a power generation control unit. The temperature acquisition unit is configured to acquire a temperature of the power transmission unit. The power generation control unit is configured to control the electric power generation system to generate electric power and thereby charge the secondary battery when the temperature of the power transmission unit acquired by the temperature acquisition unit is higher than or equal to a predetermined threshold temperature.

A VTOL aircraft (1), including: a fuselage (2) for transporting passengers and/or load; a front wing (3) attached to the fuselage (2); an aft wing (4) attached to the fuselage (2), behind the front wing (3) in a direction of forward flight (FF); a right connecting beam (5a) and a left connecting beam (5b), which connecting beams (5a, 5b) structurally connect the front wing (3) and the aft wing (4), which connecting beams (5a, 5b) are spaced apart from the fuselage (2); and at least two propulsion units (6) on each one of the connecting beams (5a, 5b). The propulsion units (6) include at least one propeller (6b, 6b′) and at least one motor (6a) driving the propeller (6b, 6b′), preferably an electric motor, and are arranged with their respective propeller axis in an essentially vertical orientation (z).

An unmanned aerial vehicle includes a body, a first wing, a second wing, a first rotor assembly, a third rotor assembly, and a fourth rotor assembly. The body has a first accommodating cavity and a second accommodating cavity. The first wing and the second wing are disposed on two sides of the body. The first rotor assembly is mounted to the first wing, and the second rotor assembly is mounted to the second wing. The third rotor assembly includes a third motor and a third propeller connected to the third motor. The third motor is mounted in the first accommodating cavity and partially exposed to the body. The fourth rotor assembly includes a fourth motor and a fourth propeller connected to the fourth motor. The fourth motor is mounted in the second accommodating cavity and partially exposed to the body.

A system for producing a control signal of an electric vertical take-off and landing (eVTOL) aircraft includes a flight controller configured to obtain a requested aircraft force, generate an optimal command mix, wherein the optimal command mix includes a plurality of commands to a plurality of actuators as a function of the requested aircraft force, wherein generating further comprises receiving an ideal actuator model includes at least a performance parameter, producing a model datum as a function of the ideal actuator model, and generating the optimal command mix as a function of the request aircraft force and the model datum, and produce a control signal as a function of the optimal command mix.

The lifting, stabilizing and propelling arrangement for vertical take-off and landing aircraft, uses rotating wings, turbines or lift fans, propellers and stabilizers on the trailing edges of the wings and empennages, centrifugal or tangential turbines applied on the sides of the fuselage, on the inlet and outlet edges of the wings, or centrifugal or tangential turbines on the sides of the fuselage and inside the wings, those that carry the fuselage are fixed and produce only lift and those that go in the wings they rotate with them and produce lift during vertical flight and propulsion during horizontal flight, add some horizontal stabilizing fans at the tips of the wings and others for direction in the vertical empennage.

A system for estimating flight range of an electric aircraft. The system generally includes at least a sensor and a computing device. The at least a sensor is communicatively connected to at least a flight component. The at least a sensor is configured to detect a performance datum of the at least a flight component. The computing device is communicatively connected to the at least a sensor. The computing device is configured to receive the performance datum from the at least a sensor, determine an energy performance datum from the performance datum, determine a flight performance datum from the performance datum, generate a projected flight range datum as a function of the energy performance datum and the flight performance datum, and display the projected flight range datum. A method for estimating flight range of an electric aircraft is also provided.

Provided in this disclosure is a high voltage distribution system of an electric aircraft. The system includes a power source mechanically connected to an electric aircraft, where the power source is configured to supply power to the electric aircraft. The system also includes a flight component mechanically connected to the electric aircraft. The system also includes a distribution component configured to control the providing of power to and from the power source and the flight component as needed during recharging and/or operation of the electric aircraft.

A system for swarm communication for an electric aircraft fleet, wherein the system includes a plurality of electric aircrafts connected by a mesh network. The system further includes a computing device communicatively connected to the mesh network, wherein the computing device includes an authentication module configured to authenticate each electric aircraft and facilitate communication of a plurality of aircraft data between the plurality of electric aircrafts. The computing device includes a plurality of communication components, each assigned to an electric aircraft of the electric aircraft fleet, wherein each communication component is configured to transmit the aircraft data to the communication component of its assigned electric aircraft. The system further includes a cloud database configured to record the plurality of aircraft data.