A precision landing system is described for an unmanned aerial vehicle (UAV). The system may include one or more anchors configured for placement in proximity to a landing zone, a tag configured for securement to the UAV where the tag wirelessly communicates with at least three or more of the anchors. A controller may be configured to fly the UAV towards a centerline axis defined through a first airspace zone at a first altitude above the landing zone while descending towards the first altitude and then fly the UAV towards the centerline axis defined through a second airspace zone at a second altitude which is below the first altitude while descending towards the second altitude, and finally to fly the UAV towards the centerline axis defined through a third airspace zone at a third altitude which is below the second altitude while descending towards the landing zone.

A portal and method for a drone to transit from one side of door to the other. The portal having an opening for each side of the door and having at least two levels, and a temporary landing area. The portal structure with no moving parts that allows the drone to transit the door.

A landing system for a fixed-wing unmanned aerial vehicle (UAV), the system comprising a parachute arranged in a parachute compartment that is secured to a fuselage tail section, and suspension lines for securing to the fuselage are fixed in four points on a fuselage lower part symmetrically relative to the UAV's center of gravity. The parachute compartment interacts with a detachment mechanism secured on a bulkhead of the tail section and comprises pins that are hinged to rods secured on a central rotatable disc coupled to at least one servomotor by means of a spring-loaded rod, the pins are mounted in guides, free ends of the pins fit into corresponding holes along a parachute compartment perimeter. The system further comprises an airbag coupled to an impeller and arranged in an onboard compartment that is arranged in a fuselage upper part and closed with a hinged hatch cover.

Rotorcraft including a fuselage and at least three rotor system arms each having a rotor system. Each rotor system includes a mast having at least two rotor blades and an electric rotor motor. At least one rotor system arm includes a support mechanism for pivotally supporting a floating mast about at least one pivot axis whereby the floating mast is tillable relative to a fiducial tilt position. The floating mast has a controllable cyclic rotor blade pitch. A mast tilt measurement mechanism provides a mast tilt feedback signal regarding a measured tilt position of a floating mast relative to its fiducial tilt position. A flight control system continuously controls the at least three electric rotor motors and the floating masts cyclic rotor blade pitch in response to a desired input maneuver and its mast tilt feedback signal.

Rotorcraft including a fuselage and at least three rotor system arms each having a rotor system. Each rotor system includes a mast having at least two rotor blades and an electric rotor motor. At least one rotor system arm includes a support mechanism for pivotally supporting a floating mast about at least one pivot axis whereby the floating mast is tillable relative to a fiducial tilt position. The floating mast has a controllable cyclic rotor blade pitch. A mast tilt measurement mechanism provides a mast tilt feedback signal regarding a measured tilt position of a floating mast relative to its fiducial tilt position. A flight control system continuously controls the at least three electric rotor motors and the floating masts cyclic rotor blade pitch in response to a desired input maneuver and its mast tilt feedback signal.

Examples relate to uncrewed aerial vehicles (UAVs) and methods for controlled descent during control tier failures. A computing device may initially detect a control tier failure at an UAV. In some examples, the UAV includes a fuselage, a pair of wings extending outwardly from the fuselage, and a pair of stabilizers arranged in a V-shape configuration. Each stabilizer has a control surface that is adjustable relative to a fixed portion of the stabilizer. Based on detecting the control tier failure at the UAV, the computing device may adjust the control surface of each stabilizer from a first angle to a second angle relative to the fixed portion of the stabilizer. By adjusting the angle between the control surfaces and fixed portions of one or both stabilizers, the UAV may induce a deep stall maneuver that can enable a controlled descent of the UAV.

Examples relate to uncrewed aerial vehicles (UAVs) and methods for controlled descent during control tier failures. A computing device may initially detect a control tier failure at an UAV. In some examples, the UAV includes a fuselage, a pair of wings extending outwardly from the fuselage, and a pair of stabilizers arranged in a V-shape configuration. Each stabilizer has a control surface that is adjustable relative to a fixed portion of the stabilizer. Based on detecting the control tier failure at the UAV, the computing device may adjust the control surface of each stabilizer from a first angle to a second angle relative to the fixed portion of the stabilizer. By adjusting the angle between the control surfaces and fixed portions of one or both stabilizers, the UAV may induce a deep stall maneuver that can enable a controlled descent of the UAV.

A landing system for a fixed-wing unmanned aerial vehicle (UAV), the system comprising a parachute arranged in a parachute compartment that is secured to a fuselage tail section, and suspension lines for securing to the fuselage are fixed in four points on a fuselage lower part symmetrically relative to the UAV's center of gravity. The parachute compartment interacts with a detachment mechanism secured on a bulkhead of the tail section and comprises pins that are hinged to rods secured on a central rotatable disc coupled to at least one servomotor by means of a spring-loaded rod, the pins are mounted in guides, free ends of the pins fit into corresponding holes along a parachute compartment perimeter. The system further comprises an airbag coupled to an impeller and arranged in an onboard compartment that is arranged in a fuselage upper part and closed with a hinged hatch cover.

A landing system for a fixed-wing unmanned aerial vehicle (UAV), the system comprising a parachute arranged in a parachute compartment that is secured to a fuselage tail section, and suspension lines for securing to the fuselage are fixed in four points on a fuselage lower part symmetrically relative to the UAV's center of gravity. The parachute compartment interacts with a detachment mechanism secured on a bulkhead of the tail section and comprises pins that are hinged to rods secured on a central rotatable disc coupled to at least one servomotor by means of a spring-loaded rod, the pins are mounted in guides, free ends of the pins fit into corresponding holes along a parachute compartment perimeter. The system further comprises an airbag coupled to an impeller and arranged in an onboard compartment that is arranged in a fuselage upper part and closed with a hinged hatch cover.

A rotorcraft including a fuselage and two diagonally opposite counter-rotating pairs of rotor systems mounted on the fuselage wherein each rotor system has a mast configured to have at least two rotor blades attached thereto and an electric motor coupled to the mast for driving the mast whereupon the at least two rotor blades act as a rotating rotor disc. Each rotor system of the two diagonally opposite counter-rotating pairs of rotor systems having an individually controllable collective rotor blade pitch and an individually controllable cyclic rotor blade pitch.