Double hinged tilting mount for coaxial contra rotating electric propulsion

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.

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.