Integrated flap control unit

A vertical take-off and landing aircraft comprising:

• a wing;
• a fuselage;
• an engine motor;
• a servo motor;
• and
• an integrated controller unit configured to:
• determine respective control commands for driving the engine motor and the servo motor;
• and
• drive the engine motor and the servo motor based on the respective control commands;
• wherein:
• the engine motor is tiltably mounted relative to at least one of the aircraft fuselage or the wing, and the servo motor is configured to tilt the engine motor.

A vertical take-off and landing aircraft comprising:

• a wing;
• a fuselage;
• an engine motor;
• a servo motor;
• and
• an integrated controller unit configured to:
• determine respective control commands for driving the engine motor and the servo motor;
• and
• drive the engine motor and the servo motor based on the respective control commands;
• a power supply supplying direct-current power at about 500-900 V to the integrated controller unit;
• and
• wherein the integrated controller unit comprises a DC-DC converter configured to receive the direct-current power from the power supply and convert the received direct-current power into direct current power with an output voltage of about 20-48 V.

A vertical take-off and landing aircraft comprising:

• a wing;
• a fuselage;
• an engine motor which is part of a ducted fan;
• a servo motor;
• and
• an integrated controller unit configured to:
• determine respective control commands for driving the engine motor and the servo motor;
• and
• drive the engine motor and the servo motor based on the respective control commands;
• and
• wherein the integrated controller unit is at least partially installed in a back cone area of the ducted fan.

A vertical take-off and landing aircraft comprising:

• a wing;
• a fuselage;
• an engine motor;
• a servo motor;
• and
• a controller unit configured to:
• determine respective control commands for driving the engine motor and the servo motor;
• and
• drive the engine motor and the servo motor based on the respective control commands;
• wherein:
• the controller unit comprises a first circuit board configured to drive the engine motor and the servo motor based on the respective control commands, and a second circuit board configured to determine the respective control commands;
• the first circuit board is positioned in a first installation area of the aircraft, the second circuit board is positioned in a second installation area of the aircraft which is spatially distributed from the first installation area;
• and
• the first and second circuit boards are interconnected by a data and power link.