Systems for flight control on a multi-rotor aircraft

Patent metadata

Field	Value
Publication number	US-11975824-B2
Application number	US-202117236945-A
Country	US
Kind code	B2
Filing date	Apr 21, 2021
Priority date	Dec 11, 2020
Publication date	May 7, 2024
Grant date	May 7, 2024

Abstract

A system and method for controlling a multi-rotor aircraft that implements the unconventional use of an odd number of rotors. The odd or auxiliary rotor is designed to be smaller in diameter than the remaining main rotors and accordingly generates a smaller unbalanced torque and pitch on the aircraft. Additional configurations implement the use of smaller thrust rotors that can be used to generate thrust as well as control yaw and thus counteract any remaining unbalanced torque from the odd auxiliary rotor.

First claim

What is claimed is:

1. A multi-rotor vehicle comprising:
a body structure;
a plurality of main rotors connected to the body structure and evenly disposed about a symmetry plane of the vehicle;
an auxiliary rotor connected to the body structure and disposed forward of the plurality of main rotors along the symmetry plane, wherein the auxiliary rotor is configured to be smaller than each of the plurality of main rotors; and
at least two thrust rotors connected to the body structure and evenly disposed about the symmetry plane and configured to generate thrust and/or yaw control for the vehicle such that a rotational plane of the thrust rotors is perpendicular to a rotational plane of the main rotors, wherein a thrust axis of each of the at least two thrust rotors is parallel to the thrust axis of each other thrust rotor;
wherein the body structure is a plurality of elongated structural support elements and disposed such that at least one structural support element interconnects at least two of the plurality of main rotors and additional structural support elements interconnect the plurality of main rotors to the auxiliary rotor; and
wherein the at least two thrust rotors are disposed on a first and second end of a transecting structural support element, wherein the transecting structural support element transects at least two of the elongated structural support elements of the body structure.

2. The multi-rotor vehicle of claim 1 , wherein the at least two thrust rotors are positioned aft of the plurality of main rotors.

3. The multi-rotor vehicle of claim 1 , wherein the at least two thrust rotors are positioned forward of the plurality of main rotors but aft of the auxiliary rotor.

4. The multi-rotor vehicle of claim 1 , wherein the at least two thrust rotors are positioned between at least two sets of main rotors.

5. The multi-rotor vehicle of claim 1 , further comprising a shroud, wherein the shroud surrounds at least a portion of the plurality of main rotors and the auxiliary rotor of the vehicle.

6. The multi-rotor vehicle of claim 1 , wherein each of the plurality of main rotors, the auxiliary rotor, and the at least two thrust rotors are selected from a group consisting of fixed pitch and variable pitch rotors.

Assignees

• California Inst Of Techn
• Toofon Inc

Inventors

• Gharib Morteza
• Ol Michael V
• Dougherty Christopher J

Classifications

• B64U30/26

  Ducted or shrouded rotors · CPC title

• B64U30/294

  Rotors arranged in the UAV body · CPC title

• B64U10/13 Primary

  Flying platforms · CPC title

• B64C27/08 Primary

  with two or more rotors · CPC title

• B64C27/22

  Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft · CPC title