An aerial vehicle adapted for vertical take-off and horizontal flight, said aerial vehicle comprising:
- a main vehicle body;
- a right side wing, said right side wing comprising:
- a right wing rotor assembly, said right wing rotor assembly comprising an electric motor and a propeller, said right wing rotor assembly attached to said right side wing along the midspan of the right side wing by a deployment mechanism adapted to deploy said right wing rotor assembly from a forward facing horizontal flight configuration to a vertical take-off configuration, wherein said deployment mechanism resides within a nacelle when in said forward facing horizontal flight configuration;
- and
- a right wingtip rotor assembly, said right wingtip rotor assembly comprising an electric motor and a propeller, said right wingtip rotor assembly attached to said right side wingtip by a deployment mechanism adapted to deploy said right wingtip rotor assembly from a forward facing horizontal flight configuration to a vertical take-off configuration;
- and
- a left side wing, said left side wing comprising:
- a left wing rotor assembly, said left wing rotor assembly comprising an electric motor and a propeller, said left wing rotor assembly attached to said left side wing along the midspan of the left side wing by a deployment mechanism adapted to deploy said left wing rotor assembly from a forward facing horizontal flight configuration to a vertical take-off configuration, wherein said deployment mechanism resides within a nacelle when in said forward facing horizontal flight configuration;
- and
- a left wingtip rotor assembly, said left wingtip rotor assembly comprising an electric motor and a propeller, said left wingtip rotor assembly attached to said left side wingtip by a deployment mechanism adapted to deploy said left wingtip rotor assembly from a forward facing horizontal flight configuration to a vertical take-off configuration;
- a right rear rotor assembly, said right rear rotor assembly coupled to the rear of said vehicle body by a deployment mechanism adapted to deploy said right rear rotor assembly from a forward facing horizontal flight configuration to a vertical take-off configuration, said right rear rotor assembly comprising an electric motor and a propeller;
- and
- a left rear rotor assembly, said left rear rotor assembly coupled to the rear of said vehicle body by a deployment mechanism adapted to deploy said left rear rotor assembly from a forward facing horizontal flight configuration to a vertical take-off configuration, said left rear rotor assembly comprising an electric motor and a propeller;
- and
- one or more electric power sources, said one or more electric power sources electrically coupled to said electric motors.