Aerial vehicle with differential control mechanisms

An aerial vehicle comprising:

• a fuselage having a nose end and a tail end;
• a first wing member extending from the fuselage in a first direction, the first wing member comprising:
• a first drive motor coupled to a first rotor;
• a second drive motor coupled to a second rotor;
• and
• a third drive motor coupled to a third rotor;
• a second wing member extending from the fuselage in a third direction substantially opposite the first wing member, the second wing member comprising:
• a fourth drive motor coupled to a fourth rotor;
• a fifth drive motor coupled to a fifth rotor;
• and
• a sixth drive motor coupled to a sixth rotor;
• a first wing rotation motor coupled to rotate the first wing member and the first rotor about a first axis substantially perpendicular to a fuselage axis extending from the nose end to the tail end;
• and
• a second wing rotation motor coupled to rotate the second wing member and the fourth rotor about a second axis substantially perpendicular to the fuselage axis;
• and
• a controller circuit configured to:
• differentially actuate the first wing rotation motor and the second wing rotation motor:
• detect a rotation failure of the second wing member based on one or more sensors that generate a signal based on a position of the second wing member;
• and
• responsive to the detecting of the failure, determine a combination of rotor speeds for the first, second, and third rotors and rotation positions for the first wing member that brings about a desired thrust vector and/or moment of torque for the aerial vehicle, wherein in a second direction perpendicular to the first direction, the first wing member and the third drive motor are positioned between the first drive motor and the second drive motor, and wherein in a fourth direction perpendicular to the third direction, the second wing member and the sixth drive motor are positioned between the third drive motor and the fourth drive motor.

An aerial vehicle comprising:

• a fuselage having a nose end and a tail end;
• a first wing member extending from the fuselage in a first direction, the first wing member comprising:
• a first drive motor coupled to a first rotor;
• a second wing member extending from the fuselage in a third direction substantially opposite the first wing member, the second wing member comprising:
• a fourth drive motor coupled to a fourth rotor;
• a first wing rotation motor coupled to rotate the first wing member and the first rotor about a first axis substantially perpendicular to a fuselage axis extending from the nose end to the tail end;
• and
• a second wing rotation motor coupled to rotate the second wing member and the fourth rotor about a second axis substantially perpendicular to the fuselage axis;
• and
• a controller circuit configured to:
• differentially actuate the first wing rotation motor and the second wing rotation motor;
• operate the aerial vehicle in a first control mode when the aerial vehicle is above a threshold altitude, wherein said first control mode controls the aerial vehicle using variable rotor speeds;
• and
• operate the aerial vehicle in a second control mode when the aerial vehicle is below the threshold altitude, wherein said second control mode controls the aerial vehicle using rotor speeds that are substantially constant.