Aerodynamically efficient lightweight vertical take-off and landing aircraft with multi-configuration wing tip mounted rotors

An aerial vehicle adapted for vertical takeoff and horizontal flight, said aerial vehicle comprising:

• an aerial vehicle body;
• a flight control system, said flight control system adapted to control the attitude of said aerial vehicle while taking off vertically by varying the thrust of the three or more thrust producing elements;
• a first left wing, said first left wing comprising a first left wing tip rotor;
• and
• a first right wing, said first right wing comprising a first right wing tip rotor,
• wherein said wing tip rotors are powered by electric motors mounted at the tips of said wings, said electric motors comprising a rotor and a stator, and wherein each of said wing tip rotors comprises a first blade and a second blade, and wherein said first left wing tip rotor and said first right wing tip rotor are adapted to deploy from a forward flight configuration wherein said wing tip rotors are configured as tandem wingtips to a vertical takeoff configuration wherein said wing tip rotors are configured as a two bladed propeller, and wherein said first blade and said second blade have leading edges during vertical flight, and wherein each of said leading edges of said first blade and said second blade face forward when in said forward flight configuration, and wherein said electric motors rotate around a first axis, and wherein said first blade deploys from a forward flight configuration to a vertical takeoff configuration by rotating around a second axis within the rotor.