Abstract: A system and method for aerial traffic management of unmanned aerial vehicles (UAVs) are provided. The method includes receiving at least a navigation request from a first UAV of a plurality of UAVs, wherein the navigation request specifies at least a waypoint; determining whether the waypoint is clear; sending an instruction the first UAV to hover at a specified position until the waypoint is clear, when the received waypoint is not clear; locking the waypoint, when the received waypoint not clear; and instructing the first UAV to navigate to the received waypoint.

Abstract: A system and method for safely terminating navigation of an unmanned aerial vehicle (UAV). A method includes generating a navigation plan for the UAV, the UAV including a propulsion system, wherein the navigation plan includes at least a start point, an end point, and a virtual three-dimensional (3D) tunnel connecting the start and end points; and configuring the UAV to execute the navigation plan by navigating from the start point to the end point, wherein the UAV is configured such that the UAV executes the navigation plan by navigating from the start point to the end point, wherein the UAV is further configured such that the UAV terminates navigation by terminating power to the propulsion system of the UAV and deploying a failsafe, wherein the UAV is configured to terminate navigation when the UAV is outside of the 3D tunnel.

Abstract: A multirotor aircraft that includes a chassis, vertical rotors, foldable wings, and a means for deploying and folding the foldable wing. The foldable wing is attached to the chassis and the means for deploying and folding the foldable wing is designed to deploy and open the foldable wing from a folded and closed state to a deployed and opened state, and vice versa. The gravity center of the folded wing in a folded and closed state is near and close to the gravity center of the multirotor aircraft, and by that enabling to fold and close the foldable wing when hovering, landing and during takeoff and to deploy and open it when flying forward.

Abstract: A multirotor aircraft that includes a chassis, three or more vertical rotors, one or more free wings and on ore more fixed horizontal rotor. The free wing is attached to the chassis by an axial connection so that the angle of the free wing is changed relative to the chassis according the flow of air over the free wing. The fixed horizontal rotor enables the multirotor aircraft to lower and climb while flying forward at a stable horizontal pitch of the chassis.

Abstract: A system and method for safely terminating navigation of an unmanned aerial vehicle (UAV). A method includes generating a navigation plan for the UAV, the UAV including a propulsion system, wherein the navigation plan includes at least a start point, an end point, and a virtual three-dimensional (3D) tunnel connecting the start and end points; and configuring the UAV to execute the navigation plan by navigating from the start point to the end point, wherein the UAV is configured such that the UAV executes the navigation plan by navigating from the start point to the end point, wherein the UAV is further configured such that the UAV terminates navigation by terminating power to the propulsion system of the UAV and deploying a failsafe, wherein the UAV is configured to terminate navigation when the UAV is outside of the 3D tunnel.

Abstract: A system and method for safely terminating navigation of an unmanned aerial vehicle (UAV). A method includes generating a navigation plan for the UAV, the UAV including a propulsion system, wherein the navigation plan includes at least a start point, an end point, and a virtual three-dimensional (3D) tunnel connecting the start and end points; and configuring the UAV to execute the navigation plan by navigating from the start point to the end point, wherein the UAV is configured such that the UAV executes the navigation plan by navigating from the start point to the end point, wherein the UAV is further configured such that the UAV terminates navigation by terminating power to the propulsion system of the UAV and deploying a failsafe, wherein the UAV is configured to terminate navigation when the UAV is outside of the 3D tunnel.

Abstract: A system and method for safely terminating navigation of an unmanned aerial vehicle (UAV). A method includes generating a navigation plan for the UAV, the UAV including a propulsion system, wherein the navigation plan includes at least a start point, an end point, and a virtual three-dimensional (3D) tunnel connecting the start and end points; and configuring the UAV to execute the navigation plan by navigating from the start point to the end point, wherein the UAV is configured such that the UAV executes the navigation plan by navigating from the start point to the end point, wherein the UAV is further configured such that the UAV terminates navigation by terminating power to the propulsion system of the UAV and deploying a failsafe, wherein the UAV is configured to terminate navigation when the UAV is outside of the 3D tunnel.

Abstract: A payload release device, a payload release assembly including a payload release device, and methods for arming a payload release device. A payload release device includes a member and a button. The member has a top portion, a bottom portion, and a middle portion. The middle portion has an aperture defining a bottom edge, a first upwardly sloping edge, and a second upwardly sloping edge, wherein each upwardly sloping edge is upwardly sloping with respect to the bottom edge. The button has a top surface and is at least partially disposed in the aperture, wherein the button is depressed toward the first upwardly sloping edge when force is applied thereto, wherein the button raises toward the second upwardly sloping edge when at least a portion of the force applied to the button is released, and wherein the second upwardly sloping edge is parallel with the top surface of the button.

Abstract: A system and method for securing delivery of an autonomous vehicle. The method includes determining visual features of a captured image of a current location of the autonomous vehicle, the captured image generated by an image sensor communicatively coupled with the autonomous vehicle; retrieving location coordinates of the current location of the autonomous vehicle from a positioning sensor communicatively coupled with the autonomous vehicle; matching the visual features of the captured image to reference data associated with the location coordinates; and determining if the current location is the final destination. In some embodiments, the method further includes matching a verification code present within the captured image to a reference verification code, where the verification code is a two-dimensional visual code previously associated with the final destination.

Abstract: A multirotor aircraft that includes a chassis, three or more vertical rotors, one or more free wings and one or more fixed horizontal rotor. The free wing is attached to the chassis by an axial connection so that the angle of the free wing is changed relative to the chassis according the flow of air over the free wing. The fixed horizontal rotor enables the multirotor aircraft to lower and climb while flying forward at a stable horizontal pitch of the chassis.

Abstract: A method for passive aerial cord release mechanisms and an aerial cord release mechanism for an aerial vehicle (AV). A method includes determining a retracting force to be applied to a winch of an aerial vehicle (AV), wherein the determined retracting force is a force required to retract a cord to be coiled around the winch within the AV, and the cord is temporarily coupled to the winch, such that an external force exceeding a predetermined threshold causes decoupling between the cord and the winch.

Abstract: A multirotor aircraft that comprises a body, at least three motors and at least one wing that is connected to the body. The wing is designed to be folded and unfolded during flight of the multirotor aircraft and designed to change during the flight a low-drag creation position to a lift creation position, and vice versa. At least one motor has a greater motor power than another motor and the distance from the strong motor to the center of gravity of the multirotor aircraft is shorter than the distance from the another motor to the center of gravity. The wing is positioned in the geometric area between the motors.

Abstract: A multirotor aircraft that includes a chassis, at least three engines that are equipped with propellers, and one or more axial free wings that are connected to the chassis by axial connections. The leading edges of the one or more axial free wings are designed to face constantly same direction when the multirotor flying, and the attack angles of the one or more axial free wings are designed to be changed relatively to the chassis due to flow of air over the one or more axial free wings.

Abstract: A method and system for optimizing drone delivery efficiency. The method includes determining an optimal intermediate location for a UAV based on historical payload delivery data related to a payload carried by the UAV, wherein the distance between the optimal intermediate location and each of a group of potential recipient devices is less than a predetermined threshold; causing the UAV to navigate to the optimal intermediate location; sending, to each potential recipient device having a probability of requesting the payload carried by the UAV which exceeds a predetermined threshold, a notification indicating the payload carried by the unmanned aerial vehicle; receiving, from a first potential recipient device of the potential recipient devices, a request to deliver the payload; and causing the UAV to navigate from the optimal intermediate location to a location of the first potential recipient device when the request to deliver the payload is received.

Abstract: A multirotor aircraft that includes a chassis, at least three engines that are equipped with propellers, and one or more axial free wings that are connected to the chassis by axial connections. The leading edges of the one or more axial free wings are designed to face constantly same direction when the multirotor flying, and the attack angles of the one or more axial free wings are designed to be changed relatively to the chassis due to flow of air over the one or more axial free wings.

Abstract: A system and method for dynamically operating a drone safety system of a delivery drone. The method includes: receiving at least one terrain map; receiving a delivery request, wherein the delivery request includes a destination location and a delivery time; analyzing the received at least one terrain map and the delivery request to generate a navigation plan, wherein the navigation plan include a plurality of segments, wherein each of the plurality of segments include at least source coordinates, destination coordinates, an operation instruction to operate a drone safety system in case of failure of a delivery drone; and sending the navigation plan to the delivery drone for execution of the navigation plan at least in case of failure of the delivery drone.

Abstract: An apparatus and method for centralized control of a vehicle.

Abstract: A system and method for aerial traffic management of unmanned aerial vehicles (UAVs) are provided. The method includes receiving at least a navigation request from a first UAV of a plurality of UAVs, wherein the navigation request specifies at least a waypoint; determining whether the waypoint is clear; sending an instruction the first UAV to hover at a specified position until the waypoint is clear, when the received waypoint is not clear; locking the waypoint, when the received waypoint not clear; and instructing the first UAV to navigate to the received waypoint.

Abstract: A multirotor aircraft that includes a chassis, vertical rotors, foldable wings, and a means for deploying and folding the foldable wing. The foldable wing is attached to the chassis and the means for deploying and folding the foldable wing is designed to deploy and open the foldable wing from a folded and closed state to a deployed and opened state, and vice versa. The gravity center of the folded wing in a folded and closed state is near and close to the gravity center of the multirotor aircraft, and by that enabling to fold and close the foldable wing when hovering, landing and during takeoff and to deploy and open it when flying forward.

Abstract: A multirotor aircraft that includes a chassis, at least three engines that are equipped with propellers, and one or more axial free wings that are connected to the chassis by axial connections. The leading edges of the one or more axial free wings are designed to face constantly same direction when the multirotor flying, and the attack angles of the one or more axial free wings are designed to be changed relatively to the chassis due to flow of air over the one or more axial free wings.