Double hinged tilting mount for coaxial contra rotating electric propulsion

1 . An assembly for controlling an orientation of a counterrotating rotor, the assembly comprising:

a main connecting member having a first end and a second end opposite the first end;

a first connecting member having a first coupling end and a first outer end, wherein the first coupling end is rotatably coupled to the first end of the main connecting member via a first hinge, the first hinge defining a first rotational axis;

a second connecting member having a second coupling end and a second outer end, wherein the second coupling end is rotatably coupled to the second end of the main connecting member via a second hinge, the second hinge defining a second rotational axis being parallel to the first rotational axis;

a first rotor having first rotor blades, the first rotor coupled to the first outer end;

a first motor mounted on the first outer end, configured to rotate the first rotor;

a second rotor having second rotor blades, the second rotor coupled to the second outer end;

a second motor mounted on the second outer end, configured to rotate the second rotor; and

an actuator assembly configured to rotate about a third rotational axis to apply torque to the first and second connecting members, causing rotation of the first connecting member about the first rotational axis and the second connecting member about the second rotational axis.

2 . The assembly of claim 1 , wherein the first rotor blades have a first pitch and the second rotor blades have a second pitch that is lower than the first pitch.

3 . The assembly of claim 1 , wherein the actuator assembly is configured to tilt the first rotor by a first tilt angle and simultaneously tilt the second rotor by a second tilt angle that is equal and opposite to the first tilt angle.

4 . The assembly of claim 3 , wherein the first and the second tilt angles can range from a vertical zero orientation to a horizontal ninety degree orientation.

5 . The assembly of claim 3 , wherein the first and the second tilt angles can further have at least some negative values.

6 . The assembly of claim 5 , wherein the negative values for the first and the second tilt angles can range between −20 degrees and 0 degrees.

7 . The assembly of claim 3 , wherein, the second rotor blades are configured to fold when the second tilt angle is ninety degree in amplitude.

8 . The assembly of claim 1 , wherein the actuator assembly comprises:

an actuator member having a first actuator end and a second actuator end;

a first actuator element having a first element end and a second element end, the first actuator element being configured to:

rotatably connect its first element end to the first actuator end;

rotatably connect its second element end to the first connecting member at a first connecting point located between the first outer end and the first coupling end of the first connecting member;

a second actuator element having a third element end and a fourth element end, the second actuator element being configured to:

rotatably connect its third element end to the second actuator end:

rotatably connect its fourth element end to the second connecting member at a second connecting point located between the second outer end and the second coupling end of the second connecting member; and

a servo motor configured to move the actuator member, thereby moving the first and second actuator elements, and causing a rotation of the first and second connecting members.

9 . The assembly of claim 8 , wherein the actuator member comprises a dampening link.

10 . The assembly of claim 8 , wherein at least one of the first actuator element, the second actuator element, or a combination thereof includes a dampening link.

11 . An aircraft vehicle comprising:

an elongated spine element having a first end and a second end;

an elongated lift boom disposed at the first end of the spine element, the elongated lift boom extending perpendicular to the elongated spine element;

a plurality of assemblies of counterrotating rotors, each assembly from the plurality of assemblies coupled to the elongated lift boom, each assembly from the plurality of assemblies comprising:

a main connecting member having a first end and a second end opposite the first end;

a first connecting member having a first coupling end and a first outer end, wherein the first coupling end is rotatably coupled to the first end of the main connecting member via a first hinge, the first hinge defining a first rotational axis;

a second connecting member having a second coupling end and a second outer end, wherein the second coupling end is rotatably coupled to the second end of the main connecting member via a second hinge, the second hinge defining a second rotational axis being parallel to the first rotational axis;

a first rotor having first rotor blades, the first rotor coupled to the first outer end;

a first motor mounted on the first outer end, configured to rotate the first rotor;

a second rotor having second rotor blades, the second rotor coupled to the second outer end; and

a second motor mounted on the second outer end, configured to rotate the second rotor; and

an actuator assembly configured to rotate about a third rotational axis to apply torque to the first and second connecting members, causing rotation of the first connecting member about the first rotational axis and the second connecting member about the second rotational axis.

12 . The aircraft vehicle of claim 11 , wherein the plurality of assemblies comprises at least a left assembly coupled to a left end of the elongated lift boom and a right assembly coupled to a right end of the elongated lift boom.

13 . The aircraft vehicle of claim 12 , wherein the main connecting member corresponding to each the left assembly and the right assembly is solidly coupled to the respective left and right ends of the elongated lift boom.

14 . The aircraft vehicle of claim 13 , wherein the main connecting member corresponding to each the left assembly and the right assembly is solidly coupled to the respective left and right ends of the elongated lift boom at a midpoint of the main connecting member.

15 . The aircraft vehicle of claim 13 , wherein the first rotor blades of each of the left and right assemblies include front rotor blades having a first pitch, and the second rotor blades of each of the left and right assemblies include aft rotor blades having a second pitch, wherein the second pitch is lower than the first pitch.

16 . The aircraft vehicle of claim 15 , wherein the actuator assembly is configured to tilt the first rotor by a first tilt angle and simultaneously tilt the second rotor by a second tilt angle that is equal and opposite to the first tilt angle.

17 . The aircraft vehicle of claim 11 , wherein the second rotor blades are configured to fold when the axis of rotation of the second rotor aligns with a main axis extending along the main connecting member from the second rotor to the first rotor, and a movement of the aircraft exceeds a threshold value in a direction along the main axis.

18 . A method for actuating a rotor assembly, the method comprising:

activating a first rotation of a first set of rotor blades of a first rotor via a first motor, the first rotor and the first motor being coupled to a first outer end of a first connecting member;

activating a second rotation of a second set of rotor blades of a second rotor via a second motor, the second rotor and the second motor being coupled to a second outer end of a second connecting member; and

activating an actuator assembly to rotate about a third rotational axis to apply torque to the first connecting member and the second connecting member, thereby causing:

a rotation of the first connecting member about a first rotational axis defined by a first hinge, the first hinge being coupled to a main connecting member at a first end of the main connecting member, with the first connecting member connected to the first hinge at its first coupling end; and

a rotation of the second connecting member about a second rotational axis defined by a second hinge, the second hinge being coupled to the main connecting member at a second end of the main connecting member, with the second connecting member connected to the second hinge at its second coupling end.

19 . The method of claim 18 , wherein the first connecting member rotates by a first tilt angle, and the second connecting member rotates by a second tilt angle that is equal in magnitude but opposite in direction to the first tilt angle.

20 . The method of claim 19 , wherein the first tilt angle is configured to range between about 0 to about 90 degrees.