CONTROL SYSTEM FOR AN AIRCRAFT

• US 20160031554A1
• Filed: 07/30/2015
• Published: 02/04/2016
• Est. Priority Date: 07/30/2014
• Status: Abandoned Application

• Current Assignee: Siniger LLC
• Original Assignee: Siniger LLC
• Inventors: ESHKENAZY, Maxim, BARTSCH, Eric Richard
• Application Number:
  US14/814,009
• Publication Number:
  US 20160031554A1
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: A63H 27/02 Model aircraft
• CPC Class Codes: A63H 27/12 Helicopters A63H27/04 takes precedence; Flying tops
• CPC Class Codes: A63H 30/04 using wireless transmission
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 10/14 with four distinct rotor axes, e.g. quadcopters
• CPC Class Codes: B64U 10/20 Vertical take-off and landing [VTOL] aircraft flying platforms B64U10/13; helicopters B64U10/17
• CPC Class Codes: B64U 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• CPC Class Codes: B64U 2201/20 Remote controls
• CPC Class Codes: B64U 30/10 Wings
• CPC Class Codes: B64U 30/21 Rotary wings
• CPC Class Codes: B64U 30/40 Empennages, e.g. V-tails foldable or collapsible UAVs B64U20/50
• CPC Class Codes: B64U 50/19 using electrically powered motors
• CPC Class Codes: B64U 70/80 Vertical take-off or landing, e.g. using rockets rotorcrafts B64U10/10; VTOL aircraft B64U10/20

Abstract

An aircraft control system includes a vertical thrust system, a horizontal thrust system, and an aerodynamic system. The system further includes a controller in at least indirect communication with the vertical thrust system, the horizontal thrust system, and the aerodynamic system. The controller is configured to substantially simultaneously control, based on at least one of a single yaw input, a single pitch input, and a single roll input, the aerodynamic system and a differential thrust generated by the plurality of vertical thrust rotors of the vertical thrust system to adjust at least one of pitch, yaw, and roll of a vertical takeoff and landing aircraft in at least one of a plurality of flight stages. The controller is further configured to independently and substantially simultaneously control the vertical and horizontal thrust systems to generate vertical and horizontal thrust in at least one of the plurality of flight stages.

Claims

1. An aircraft control system, comprising:

a vertical thrust system having a plurality of vertical thrust rotors, each of the plurality of vertical thrust rotors having an axis of rotation that is substantially perpendicular to a horizontal direction of flight;

a horizontal thrust system having at least one horizontal thrust rotor, the at least one horizontal thrust rotor having an axis of rotation that is substantially parallel to the horizontal direction of flight;

an aerodynamic system having a plurality of movable aerodynamic surfaces; and

a controller in at least indirect communication with the vertical thrust system, the horizontal thrust system, and the aerodynamic system, wherein the controller is configured to;

substantially simultaneously control, based on at least one of a single yaw input, a single pitch input, and a single roll input, the aerodynamic system and a differential thrust generated by the plurality of vertical thrust rotors of the vertical thrust system to adjust at least one of pitch, yaw, and roll of a vertical takeoff and landing aircraft in at least one of a plurality of flight stages of the vertical takeoff and landing aircraft, and

independently and substantially simultaneously control the vertical thrust system and the horizontal thrust system to generate vertical and horizontal thrust in at least one of the plurality of flight stages.

2. The control system of claim 1, wherein one of the plurality of flight stages comprises a first transition flight stage from vertical flight to horizontal flight, and further wherein the controller is configured to independently and substantially simultaneously control the vertical thrust system and the horizontal thrust system to generate vertical and horizontal thrust in the first transition flight stage.

3. The control system of claim 1, wherein the plurality of vertical thrust rotors comprise at least three vertical thrust rotors and the axis of rotation of each of the at least three vertical thrust rotors is separated from remaining ones of the at least three vertical thrust rotors by a distance of at least one quarter of a wingspan of the vertical takeoff and landing aircraft.

4. The control system of claim 1, wherein the plurality of vertical thrust rotors comprise at least three vertical thrust rotors and the axis of rotation of each of the at least three vertical thrust rotors is separated from remaining ones of the at least three vertical thrust rotors by a distance of at least twice a diameter of one of the at least three vertical thrust rotors.

5. The control system of claim 1, wherein each of the plurality of vertical thrust rotors has associated with it a vertical thrust motor and a vertical thrust speed controller.

6. The control system of claim 1, further comprising a receiver located on the vertical takeoff and landing aircraft, the receiver in at least indirect communication with the controller and a pilot interface, wherein the receiver is configured to route input signals received from the pilot interface to the controller.

7. The control system of claim 6, wherein the receiver is configured to route at least some of the input signals received from the pilot interface to the horizontal thrust system.

8. The control system of claim 1, wherein each of the plurality of vertical thrust rotors has fixed pitch blades.

9. The control system of claim 1, wherein the plurality of aerodynamic surfaces comprises at least one rudder, and wherein the controller is further configured to, based on the single yaw input, substantially simultaneously control the vertical thrust system and a position of the at least one rudder to adjust the yaw of the vertical takeoff and landing aircraft.

10. The control system of claim 1, wherein the plurality of aerodynamic surfaces comprises at least one aileron, and wherein the controller is further configured to, based on the single roll input, substantially simultaneously control the vertical thrust system and a position of the at least one aileron to adjust the roll of the vertical takeoff and landing aircraft.

11. The control system of claim 1, wherein the plurality of aerodynamic surfaces comprises at least one elevator, and wherein the controller is further configured to, based on the single pitch input, substantially simultaneously control the vertical thrust system and a position of the at least one elevator to adjust the pitch of the vertical takeoff and landing aircraft.

12. A method for controlling flight of a vertical takeoff and landing aircraft, comprising:

receiving, at a controller located on the vertical takeoff and landing aircraft, input signals comprising a horizontal thrust input, a vertical thrust input, and at least one of a single yaw input, a single pitch input, and a single roll input from a pilot interface, wherein the input signals cause the controller to perform steps comprising;

substantially simultaneously controlling, based on the at least one of the single yaw input, the single pitch input, and the single roll input, an aerodynamic system and a differential thrust generated by a plurality of vertical thrust rotors of a vertical thrust system, wherein the controlling the differential thrust and the aerodynamic system adjusts at least one of pitch, yaw, and roll of the vertical takeoff and landing aircraft in at least one of a plurality of flight stages of the vertical takeoff and landing aircraft; and

independently and substantially simultaneously controlling, based on the horizontal thrust input and the vertical thrust input, the vertical thrust system and a horizontal thrust system to generate vertical and horizontal thrust in at least one of the plurality of flight stages, wherein;

the vertical thrust system comprises the plurality of vertical thrust rotors, wherein each of the plurality of vertical thrust rotors has an axis of rotation that is substantially perpendicular to a horizontal direction of flight,

the horizontal thrust system comprises at least one horizontal thrust rotor, wherein the at least one horizontal thrust rotor has an axis of rotation that is substantially parallel to the horizontal direction of flight, and

the aerodynamic system comprises a plurality of movable aerodynamic surfaces.

13. The method of claim 12, wherein the plurality of flight stages comprises a vertical flight stage and a horizontal flight stage, and wherein during transition from the horizontal flight stage to the vertical flight stage:

a horizontal airspeed of the vertical takeoff and landing aircraft decreases; and

the thrust generated by the plurality of vertical thrust rotors increases.

14. The method of claim 12, wherein the plurality of flight stages comprises a vertical flight stage and a horizontal flight stage, and wherein during transition from the vertical flight stage to the horizontal flight stage:

a horizontal airspeed of the vertical takeoff and landing aircraft increases; and

the thrust generated by the plurality of vertical thrust rotors decreases.

15. The method of claim 12, wherein as the vertical takeoff and landing aircraft transitions from a vertical one of the plurality of flight stages to a horizontal one of the plurality of flight stages, the thrust generated by the horizontal thrust system increases and the thrust generated by the vertical thrust system decreases.

16. The method of claim 12, wherein as the vertical takeoff and landing aircraft transitions from a horizontal one of the plurality of flight stages to a vertical one of the plurality of flight stages, the thrust generated by the horizontal thrust system decreases and the thrust generated by the vertical thrust system increases.

17. A control system to control flight of a vertical takeoff and landing aircraft, comprising:

a receiver located on the vertical takeoff and landing aircraft, the receiver configured to receive input signals input by a pilot into a pilot interface;

a vertical thrust system having a plurality of vertical thrust rotors, each of the plurality of vertical thrust rotors having an axis of rotation that is substantially perpendicular to a horizontal direction of flight;

a horizontal thrust system having at least one horizontal thrust rotor, the at least one horizontal thrust rotor having an axis of rotation that is substantially parallel to the horizontal direction of flight;

an aerodynamic system having a plurality of movable aerodynamic surfaces; and

a controller configured to receive the input signals from the pilot interface via the receiver, wherein the controller is in at least indirect communication with the vertical thrust system, the horizontal thrust system, and the aerodynamic system, wherein

the pilot interface is configured to receive the input signals comprising a horizontal thrust input, a vertical thrust input, a single yaw input, a single pitch input, and a single roll input,

the controller is configured to, based on the input signals, simultaneously control the vertical thrust system and the aerodynamic system to control an attitude of the vertical takeoff and landing aircraft, and

the controller is further configured to, based on the input signals and substantially simultaneously with the control of the attitude, substantially simultaneously adjust the vertical thrust system and the horizontal thrust system, wherein the horizontal thrust input and the vertical thrust input are configured to be input into the pilot interface independently.

18. The control system of claim 17, wherein the pilot interface is physically remote from the vertical takeoff and landing aircraft.

19. The control system of claim 17, wherein the aerodynamic system comprises a rudder, and the controller is further configured to:

transmit the single yaw input to a servo of the rudder, wherein the servo is configured to deflect the rudder to cause a desired direction of yaw of the vertical takeoff and landing aircraft based on the single yaw input; and

substantially simultaneously control the thrust generated by each of the plurality of vertical thrust rotors of the vertical thrust system to cause the vertical takeoff and landing aircraft to yaw in the desired direction.

20. The control system of claim 17, wherein the aerodynamic system comprises at least one aileron, and the controller is further configured to:

transmit the single roll input to a servo of the at least one aileron, wherein the servo is configured to deflect the aileron to cause a desired direction of roll of the vertical takeoff and landing aircraft based on the single roll input; and

substantially simultaneously control the thrust generated by each of the plurality of vertical thrust rotors of the vertical thrust system to cause the vertical takeoff and landing aircraft to roll in the desired direction.