System and Methods for Unmanned Aerial Vehicles (UAVs)

A method of operating an aerial vehicle to transition between a vertical take-off and landing (VTOL) flight mode and a horizontal forward flight mode, the method comprising:

• in a first phase, activating at least one electric motor of the aerial vehicle, wherein activating the at least one electric motor causes the aerial vehicle to take off from a horizontal surface and transition to vertical flight;
• in a second phase, transitioning the aerial vehicle from vertical flight to horizontal flight, wherein a fuselage of the aerial vehicle pivots towards a front of the aerial vehicle;
• and
• in a third phase, transitioning the aerial vehicle from horizontal flight to horizontal forward flight, wherein a front wing and a rear wing of the aerial vehicle are each positioned at an optimal angle of attack with a frontal air flow, the optimal angle of attack ranging from between 2 and 8 degrees.

A propulsion system for an unmanned aerial vehicle (UAV), including:

• a fuselage defining a central longitudinal axis;
• a nacelle defining a central axis and affixed to a middle portion of the fuselage;
• a front wing and a rear wing connected by the fuselage and extending perpendicularly from the central longitudinal axis to define a front axis and a rear axis, respectively, wherein the front wing and the rear wing are parallel and spaced apart from each other along the central longitudinal axis;
• and
• a thruster assembly configured to generate an airflow and including three pairs of thrusters supported by a plurality of arms extending symmetrically from the fuselage, the plurality of arms located in a middle portion of the UAV between the front wing and the rear wing, wherein the plurality of arms extend outwards at a length greater than arms located in a front portion and a rear portion of the UAV, and wherein each thruster includes at least one electric motor and at least one propeller driven by the electric motor,
• wherein a ring is affixed to a central area of a lower surface of the front wing, the ring having a central hole defined therein, and
• wherein the front wing and the rear wing each define a median profile chord, the central axis being substantially parallel to at least one median profile chord.