SYSTEM AND METHOD FOR CONTROL OF QUADROTOR AIR VEHICLES WITH TILTABLE ROTORS

• US 20160023755A1
• Filed: 05/05/2014
• Published: 01/28/2016
• Est. Priority Date: 05/05/2014
• Status: Abandoned Application

• Current Assignee: King Fahd University of Petroleum & Minerals (Government of Saudi Arabia)
• Original Assignee: King Fahd University of Petroleum & Minerals (Government of Saudi Arabia)
• Inventors: Elshafei, Moustafa Elshafei Ahmed, Elfeky, Mahmoud Abdelmagid, Saif, Abdul-Wahid Abdul-Aziz, El ferik, Sami, Al-Malki, Mohammad Fahad
• Application Number:
  US14/269,322
• Publication Number:
  US 20160023755A1
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64C 29/0033 the propellers being tiltable relative to the fuselage
• CPC Class Codes: B64U 10/14 with four distinct rotor axes, e.g. quadcopters
• CPC Class Codes: B64U 2101/30 for imaging, photography or videography
• CPC Class Codes: B64U 2201/20 Remote controls
• CPC Class Codes: B64U 30/297 Tilting rotors
• CPC Class Codes: G08G 5/025 Navigation or guidance aids radar or analogous systems specially adapted for landing purposes G01S13/913

Abstract

A system and method of controlling quadrotor air vehicles (QRAV) that may include an additional two degrees of freedom for each of the four propellers of the QRAV. Each of the four rotors may be allowed to rotate (tilt) around two local axes selected from the x-axis (roll), y-axis (pitch), and z-axis (yaw). Control of the quadrotor including the additional two degrees of freedom allows thrust of each rotor to be direct in any direction of a semi-sphere. As a result, total control inputs of the QRAV may be increased to twelve, enabling smooth control to achieve superior and precise maneuverability. Additionally, the system and method is fault tolerant and capable of handling failures of any of the rotors. Commands to the propellers may be fully decoupled and achieved independently thereby giving pilots better control to execute difficult maneuvers.

Claims

1. An air vehicle comprising:

a flight computer;

a fuselage; and

four rotors mounted symmetrically to the fuselage, each of the four rotors including servo mechanism to tilt each of the four rotors about two axes of each respective rotor,

wherein the flight computer is configured to send control parameters to each of the four rotors, the control parameters including a rotational speed, a first tilt angle about a first axis of the two axes of each respective rotor, and a second tilt angle about a second axis of the two axes of each respective rotor.

2. The air vehicle according to claim 1, wherein each of the four rotors are independently tilted about the first axis and the second axis of each respective rotor.

3. The air vehicle according to claim 1, further comprising a control panel,

wherein the control panel receives flight commands,

wherein the flight commands are executed by the flight computer to control the control parameters of the four rotors.

4. The air vehicle according to claim 3, wherein the control panel comprises at least two 3-axis joysticks,

wherein the at least two 3-axis joysticks includes a first joystick and a second joystick,

wherein forward and reverse positions of the first joystick are proportionally linked to forward and reverse speeds of the air vehicle,

wherein left and right positions of the first joystick are proportionally linked to a lateral speed of the air vehicle,

wherein twist of the first joystick is proportionally linked to forward acceleration or forward thrust of the air vehicle.

5. The air vehicle according to claim 4,

wherein forward and reverse positions of the second joystick are proportionally linked to a pitch angle of the air vehicle,

wherein left and right positions of the second joystick are proportionally linked to a roll angle of the air vehicle,

wherein twist of the second joystick is proportionally linked to a yaw angular velocity of the air vehicle.

6. The air vehicle according to claim 5, wherein the control panel further comprises switches to alter and reconfigure the linked functions assigned to the first joystick and the second joystick.

7. The air vehicle according to claim 3, wherein the control panel comprises a first sliding stick and a second sliding stick,

wherein the first sliding stick is linked to an elevation control of the air vehicle, and

wherein the second sliding stick is linked to a speed of ascending and descending of the air vehicle.

8. The air vehicle according to claim 3, wherein the control panel comprises control inputs to set a lateral acceleration, a roll angular speed, a pitch angular speed, and yaw acceleration of the air vehicle.

9. The air vehicle according to claim 3, wherein the control panel receives the flight commands from a location remote from the air vehicle.

10. A method of operating an air vehicle having four rotors, comprising:

receiving flight commands via a control panel of the air vehicle;

translating the flight commands into one or more control parameters for the four rotors,

wherein the one or more control parameters includes a first tilt angle, about a first axis, for each of the four rotors and a second tilt angle, about a second axis, for each of the four rotors.

11. The method of operating the air vehicle according to claim 10, wherein the one or more control parameters includes a rotational speed for each of the four rotors.

12. The method of operating the air vehicle according to claim 10, wherein the flight commands include control of speed and acceleration of forward and lateral motions of the air vehicle without altering a pitch, a yaw, or a roll of the air vehicle.

13. The method of operating the air vehicle according to claim 10, wherein the flight commands include control of elevation and speed of assent or descent without altering a forward or lateral motion of the air vehicle, and without altering a pitch, a yaw, or a roll of the air vehicle.

14. The method of operating the air vehicle according to claim 10, further comprising producing translational motion commands and orientation commands, via a flight computer, based on a programmable flight mission.

15. The method of operating the air vehicle according to claim 10, further comprising:

operating, in a first mode, each of the four rotors when no failures or damage is detected in any of the four rotors;

operating, in a second mode, a front rotor and a rear rotor of the four rotors when a failure or damage is detected in at least a left rotor or a right rotor of the four rotors;

operating, in a third mode, the left rotor and the right rotor of the four rotors when a failure or damage is detected in at least the front rotor or the rear rotor of the four rotors;

operating, in a fourth mode, all four rotors to control angular speeds of each of the four rotors when servo systems for one or two of the four rotors fail, and operating to control tilt angles via servo systems of the four rotors that have not failed; and

operating, in a fifth mode, all four rotors to control angular speeds of the four rotors when the servo systems for all of the four rotors fail.