Aircraft with vertical take-off and landing—VTOL

A propulsion system for aerial vehicle, comprising:

• a fuselage assembly, including:
• a body defining a longitudinal axis;
• and
• a set of arms extending from the body;
• a front wing disposed on a front section of the fuselage assembly;
• a rear wing disposed on a rear section of the fuselage assembly;
• and
• diametrically opposed jet limiters having curved profiles, the jet limiters extending inwards towards the arms of the fuselage assembly,
• wherein the front wing and the rear wing each have an airfoil profile and a canted cross section, an upper surface, a lower surface, a leading edge, and a trailing edge, and wherein the front wing and the rear wing extend outwards symmetrically from the body in opposing directions, both being inclined at a fixed positive incidence angle ranging from between 15 degrees to 80 degrees relative to the longitudinal axis, the front wing defining a first axis transverse to the longitudinal axis and the rear wing defining a second axis transverse to the longitudinal axis;
• and
• a thruster assembly configured to generate an airflow, including:
• a plurality of rotors affixed to the arms of the fuselage assembly, the plurality of rotors disposed between the front wing and the rear wing and including:
• a pair of front rotors affixed to a front section of the fuselage assembly, the pair of front rotors disposed above the upper surface and alongside the trailing edge of the front wing;
• and
• a pair of rear rotors affixed to a rear section of the fuselage assembly, the pair of rear rotors disposed below the lower surface and alongside the leading edge of the rear wing, and
• wherein a relative position between the fuselage assembly, the front wing, the rear wing, and the thruster assembly remains unchanged during operation of the propulsion system.

A propulsion system for an aerial vehicle, comprising:

• a fuselage assembly, including:
• a body defining a longitudinal axis;
• and
• a set of arms extending from the body;
• a pair of wings disposed on opposite ends of the body of the fuselage assembly, the pair of wings extending outwards from the body in opposing directions at fixed, symmetrical angles ranging between 15 degrees to 80 degrees relative to the longitudinal axis;
• and
• a thruster assembly configured to generate an airflow, including:
• a plurality of rotors affixed to the arms of the fuselage assembly, the plurality of rotors disposed between the pair of wings;
• and
• at least one electric motor configured to power the plurality of rotors,
• wherein the thruster assembly is configured to:
• in a first phase, generate vertical flight, wherein the thruster assembly produces a greater lifting force than a thrusting force;
• in a second phase, generate a transition between vertical flight and horizontal flight, wherein the thruster assembly accelerates a rate of rotation of a subset of the plurality of rotors, altering a pitch angle of the aerial vehicle;
• and
• in a third phase, generate forward horizontal flight, wherein the wings are each respectively positioned at an optimal angle of attack,
• wherein a relative position between the fuselage assembly, the pair of wings, and the thruster assembly remains unchanged during operation of the propulsion system, and
• wherein the plurality of rotors includes:
• front rotors affixed to the front section of the fuselage assembly, the front rotors disposed above the upper surface and alongside the trailing edge of the front wing;
• and
• rear rotors affixed to the rear section of the fuselage assembly, the rear rotors disposed below the lower surface and alongside the leading edge of the rear wing.