An aerial vehicle includes a wing body. The aerial vehicle includes a plurality of rotors coupled to the wing body. Each one of the rotors includes a plurality of rotor blades. The aerial vehicle includes a drive assembly configured to rotate the rotors. The aerial vehicle includes a controller configured to selectively control thrust produced by each one of the rotors. Selective control of the thrust produced by each one of the rotors induces a pitch motion of the aerial vehicle to transition the aerial vehicle between a horizontal flight state and a vertical flight state. In the horizontal flight state, the wing body is approximately horizontal and a collective thrust from the rotors is directed forward. In the vertical flight state, the wing body is approximately vertical and the collective thrust from the plurality rotors is directed upward.

An aerial vehicle includes a wing body. The aerial vehicle includes a plurality of rotors coupled to the wing body. Each one of the rotors includes a plurality of rotor blades. The aerial vehicle includes a drive assembly configured to rotate the rotors. The aerial vehicle includes a controller configured to selectively control thrust produced by each one of the rotors. Selective control of the thrust produced by each one of the rotors induces a pitch motion of the aerial vehicle to transition the aerial vehicle between a horizontal flight state and a vertical flight state. In the horizontal flight state, the wing body is approximately horizontal and a collective thrust from the rotors is directed forward. In the vertical flight state, the wing body is approximately vertical and the collective thrust from the plurality rotors is directed upward.

A vertical take-off and landing aircraft using a hybrid electric propulsion system, according to an embodiment of the present invention, includes: a first control step (S1) of changing a destination when an engine (10), a power generator (20), an engine control unit (30), a power management device (40), a control unit (50), a battery management system (60), a main battery (62) and the like malfunction, thereby causing a normal flight to be difficult; a second control step (S2) of performing control so that an aerial vehicle (1) glides to a point (T), at which same has entered a first space (CEP-1) required for landing or a wider second space (CEP-2) considered safe, and maintains lift and has minimized flight air resistance after passing through the point (T); a third control step (S3) of performing control so that lift is increased and performing control so that a nose cone is switched into an upward direction; and a fourth control step (S4) of performing control so that lift is gradually reduced, and controlling a second variable-pitch control device (122) so that thrust does not act on the aerial vehicle at the moment the aerial vehicle lands, and thus the present invention can vertically land while minimizing impact to be applied to the aerial vehicle.

A vertical take-off and landing aircraft using a hybrid electric propulsion system, according to an embodiment of the present invention, includes: a first control step (S1) of changing a destination when an engine (10), a power generator (20), an engine control unit (30), a power management device (40), a control unit (50), a battery management system (60), a main battery (62) and the like malfunction, thereby causing a normal flight to be difficult; a second control step (S2) of performing control so that an aerial vehicle (1) glides to a point (T), at which same has entered a first space (CEP-1) required for landing or a wider second space (CEP-2) considered safe, and maintains lift and has minimized flight air resistance after passing through the point (T); a third control step (S3) of performing control so that lift is increased and performing control so that a nose cone is switched into an upward direction; and a fourth control step (S4) of performing control so that lift is gradually reduced, and controlling a second variable-pitch control device (122) so that thrust does not act on the aerial vehicle at the moment the aerial vehicle lands, and thus the present invention can vertically land while minimizing impact to be applied to the aerial vehicle.

Aircraft capable of vertical takeoff and landing, hovering, and efficient forward flight are described. An aircraft includes two side mounted tiltable proprotors and a central rotor disposed above the proprotors. The proprotors are tiltable between at least a horizontal position for forward flight and a vertical position for vertical or hovering flight. The central rotor may be powered for vertical and transitional flight modes and may turn by free autorotation during forward flight. The proprotors may be differentially tilted during vertical or hovering flight to counter torque effects of the central rotor. The central rotor may be foldable and/or easily detachable from the aircraft to facilitate storage and transportation. Left and right proprotors may provide both forward thrust and attitude control. Control inputs to left and right proprotors may be connected directly to an autopilot creating closed loop actuation using motor RPM feedback.

A multi-rotor unmanned aerial vehicle (UAV) includes a central body, a plurality of branch members connected to the central body, each branch member configured to support a corresponding actuator assembly, a communication module disposed within the central body and configured to establish a communication channel between the UAV and a remote device, and an indicator light disposed on one of the plurality of branch members. The indicator light is configured to indicate whether the communication channel is established.

A multi-rotor unmanned aerial vehicle (UAV) includes a central body, a plurality of branch members connected to the central body, each branch member configured to support a corresponding actuator assembly, a communication module disposed within the central body and configured to establish a communication channel between the UAV and a remote device, and an indicator light disposed on one of the plurality of branch members. The indicator light is configured to indicate whether the communication channel is established.

A passive elastic teeter bearing (3c) for an aircraft rotor (3b), including, rotatably arranged on an rotational axis (RA) of said rotor (3b), a teeter beam (3d), configured for attaching the rotor which has rotor blades, with the teeter beam being configured for performing a teetering motion, and having two pairs of first lugs (3j1, 3j2) arranged at opposite ends thereof at a distance with respect to the rotational axis; and a hub piece (3f) located below the teeter beam, the hub piece having two arms (3g1, 3g2) that extend outwardly in a radial direction, each having a second lug (3k) arranged at a distance with respect to said rotational axis. Each second lug is located between the two lugs of a respective pair of first lugs, and respective connecting pins (3n) pass through the first and second lugs on either side of the rotational axis. A pair of elastic bushings (3l1, 3l2) are arranged on each connecting pin between a first one of the first lugs and the second lug and between a second one of said first lugs and the second lug, respectively.

A delivery rotary-wing aircraft has a plurality of rotary wings, a central portion to which a plurality of arms for supporting the rotary wings are connected, a first mounting portion for loading a package, a second mounting portion which is located on the opposite side to the first mounting portion as viewed from the central portion, a first supporting member for coupling the first mounting portion with the central portion, and a connection portion between the central portion and the first supporting member. The center point of lift occurring in the rotary-wing aircraft with the rotation of the plurality of rotary wings and the center point of gravity of the rotary-wing aircraft coincide with the center point of the connection portion. The first supporting member is equipped with an adjustment mechanism for vertically downwardly extending the length of the first supporting member.

A delivery rotary-wing aircraft has a plurality of rotary wings, a central portion to which a plurality of arms for supporting the rotary wings are connected, a first mounting portion for loading a package, a second mounting portion which is located on the opposite side to the first mounting portion as viewed from the central portion, a first supporting member for coupling the first mounting portion with the central portion, and a connection portion between the central portion and the first supporting member. The center point of lift occurring in the rotary-wing aircraft with the rotation of the plurality of rotary wings and the center point of gravity of the rotary-wing aircraft coincide with the center point of the connection portion. The first supporting member is equipped with an adjustment mechanism for vertically downwardly extending the length of the first supporting member.