Integrated flap control unit

1 . An integrated controller unit for controlling at least one engine motor and at least one servo motor, comprising:

a power link section for connecting the controller unit to an external power supply and supplying low-voltage and/or high-voltage electrical power to individual sections of the controller unit, wherein the external power supply comprises high-voltage direct current power at about 500-900 V, and the power link section further comprises a DC-DC converter that receives the high-voltage direct current power and converts it to the low-voltage electrical voltage with an output voltage of about 24-48 V;

a data link section for connecting the controller unit to an external data source, wherein the data link section is provided the low-voltage electrical power from the power link section;

a computing section operatively connected with the power link section and the data link section for receiving data from the external data source, performing computing tasks based on the received data and outputting control commands, wherein the computing section is provided the low-voltage electrical power from the power link section;

an engine interface section for driving the at least one engine motor, wherein the engine motor comprises an electric engine motor for an electrically driven ducted fan and the engine interface section is provided the high-voltage electrical power from the power link section, and wherein the engine interface section directly provides high-voltage electrical power to the electric engine motor; and

a servo interface section for driving the at least one servo motor, wherein the servo interface section is provided the high-voltage electrical power from the power link section, and wherein the servo interface section provides high-voltage electrical power to the at least one servo motor;

wherein the engine interface section and the servo interface section are both operatively connected to the computing section and adapted to drive the at least one engine motor and the at least one servo motor, respectively, based on control commands output by the computing section.

2 . The integrated controller unit according to claim 1 , further comprising:

at least one accessory interface section for driving an accessory component, in particular a de-icing system,

wherein the accessory interface section is operatively connected to the computing section and adapted to drive the accessory component based on control commands output by the computing section.

3 . The integrated controller unit according to claim 1 , wherein the computing section is further adapted to receive sensor data from at least one external sensor unit.

4 . The integrated controller unit according to claim 1 , wherein the computing section comprises a redundant and/or dissimilar architecture capable of dual independent processing of the received data.

5 . The integrated controller unit according to claim 1 , wherein the engine interface section and/or the servo interface section comprise at least one gate driver and at least one semiconductor switch, such as a power MOSFET, and at least one sensor unit for monitoring a voltage and/or a current.

6 . The integrated controller unit according to claim 1 , comprising at least one EMI filter as a part of the power link section, the engine interface section and/or the servo interface section and/or comprising at least one DC link block provided to the power link section, the engine interface section, the servo interface section and/or the accessory interface section.

7 . The integrated controller unit according to claim 1 , wherein the computing section is further adapted to communicate feedback and/or status information by means of the data link section.

8 . An assembly, comprising an integrated controller unit, at least one engine motor and at least one servo motor, wherein the integrated controller unit comprises:

a power link section for connecting the controller unit to an external power supply and supplying low-voltage and/or high-voltage electrical power to the individual sections of the controller unit, wherein the external power supply comprises high-voltage direct current power at about 500-900 V, and the power link section further comprises a DC-DC converter that receives the high-voltage direct current power and converts it to the low-voltage electrical voltage with an output voltage of about 24-48 V;

a data link section for connecting the controller unit to an external data source, wherein the data link section is provided the low-voltage electrical power from the power link section;

a computing section operatively connected with the power link section and the data link section for receiving data from the external data source, performing computing tasks based on the received data and outputting control commands, wherein the computing section is provided the low-voltage electrical power from the power link section;

an engine interface section for driving the at least one engine motor, wherein the at least one engine motor comprises an electric engine motor for an electrically driven ducted fan and the engine interface section engine interface section is provided the high-voltage electrical power from the power link section, and wherein the engine interface section directly provides high-voltage electrical power to the electric engine motor; and

a servo interface section for driving the at least one servo motor, wherein the servo interface section is provided the high-voltage electrical power from the power link section, and wherein the servo interface section provides high-voltage electrical power to the at least one servo motor;

wherein the engine interface section and the servo interface section are both operatively connected to the computing section and adapted to drive the at least one engine motor and the at least one servo motor, respectively, based on control commands output by the computing section; and

wherein the at least one engine motor and the at least one servo motor are adapted to be driven by the engine interface section and the servo interface section of the integrated controller unit, respectively.

9 . The assembly according to claim 8 , further comprising at least one accessory component, in particular a de-icing system, which is adapted to be driven by the accessory interface section of the integrated controller unit.

10 . The assembly according to claim 8 , wherein the at least one engine motor, the at least one servo motor and/or the at least one accessory component comprises a sensor unit which is adapted to monitor at least one operating parameter thereof and provide respective sensor data to the integrated controller unit.

11 . The assembly according to claim 8 , wherein the integrated controller unit is at least partially installed in a back cone area of the electrically driven ducted fan.

12 . The assembly according to claim 8 , wherein at least one of the power link section, the data link section, the computing section, the engine interface section and the servo interface section is positioned in a first installation area and/or on a first circuit board and at least one of said components is positioned in a second installation area and/or on the second circuit board, wherein the first and second installation areas and/or first and second circuit boards are spatially distributed and interconnected by dedicated data and power links.

13 . An aircraft comprising at least one pair of wings, a fuselage, at least one assembly according to claim 8 , a central computing unit and a central power supply, wherein the at least one engine motor is mounted to the aircraft in such a manner as to be tiltable relative to the fuselage and/or the at least one pair of wings, wherein the at least one servo motor is arranged to cause said tilting of the at least one engine motor.

14 . The aircraft according to claim 13 , wherein a plurality of flap elements are provided to the wings in a manner tiltable relative thereto by means of a servo motor, wherein each of the flap elements is further provided with at least one engine motor, wherein the servo motor and the at least one engine motors of the same flap are driven by the same integrated controller unit.

15 . The aircraft according to claim 14 , wherein to each flap element a single integrated controller unit is assigned and mounted thereon.