Unmanned aerial vehicles and frames thereof are disclosed. The unmanned aerial vehicle includes a frame and a control module. The frame includes a central frame, a first arm set, and a second arm set. Each of the first arm set and the second arm set includes a second arm assembly, a third arm assembly, and a first arm assembly. The first arm assembly is located between the second arm assembly and the third arm assembly. The first arm assembly includes a first rotor assembly. The second arm assembly includes a second rotor assembly. The third arm assembly includes a third rotor assembly. In an output direction of downward-propelling wind fields, one of a rotation plane of the first rotor assembly, a rotation plane of the second rotor assembly, and a rotation plane of the third rotor assembly is located at a different position from the other two.

The disclosure provides a monitoring system for live event, a computing device to use with the monitoring, and a computer program product that can be used to control the monitoring. In example, the monitoring system includes: (1) a control structure and a drone having a camera, wherein the drone is tethered to the control structure, and (2) a computing device having an integrated transceiver configured to receive an access signal and a processor configured to control operations of the drone and the camera, when having permission based on the access signal, to capture images from the camera.

According to an example aspect of the present invention, there is provided a drone station comprising a housing having a cavity, and a structure permeable to air and configured to be moved from a first position into a second position and reverse, wherein a platform for landing, storing and starting of a drone is provided by the structure within the cavity in the first position, and wherein an entry into the cavity or an exit out of the cavity through a ventral access is provided for the drone in the second position.

An unmanned aerial vehicle has a flight mode and a compact storage mode. The unmanned aerial vehicle includes an airframe having first and second wings with first and second pylons extending therebetween. A thrust array is coupled to the airframe including two propulsion assemblies coupled to each of the first and second wings. An electric power system is operably associated with the thrust array and operable to provide power to each propulsion assembly. A flight control system is operably associated with the thrust array and operable to independently control the speed of each propulsion assembly. In the flight mode, the first and second wings are substantially parallel with the vertical dimension therebetween at a maximum. In the compact storage mode, the first and second pylons are rotated relative to the first and second wings such that the vertical dimension between the first and second wings is at a minimum.

An aerial vehicle securing system for use with a base portion of an aerial vehicle, comprising: at least one substantially flat platform for supporting said base portion upon landing of the vehicle thereon; at least one magnetizable element configured to be integrated in one of said platform or base portion; at least one electropermanent magnet configured to be integrated in another one of said platform or base portion, said electropermanent magnet configured for generating a magnetic field, so that upon a distance between said base portion and said platform reaching a pre-determined value during the landing of the vehicle on the platform, said magnetic field is configured to cause magnetizable element to be attracted to at least said one electropermanent magnet; and a power supply module configured for generating an electric current to said at least one electropermanent magnet for selectively generating and cancelling said magnetic field.

A base module may be used to receive and house one or more unmanned aerial vehicles (UAVs) via one or more cavities. The base module receives commands from a manager device and identifies a flight plan that allows a UAV to execute the received commands. The base module transfers the flight plan to the UAV and frees the UAV. Once the UAV returns, the base module once again receives it. The base module then receives sensor data from the UAV from one or more sensors onboard the UAV, and optionally receives additional information describing its flight and identifying success or failure of the flight plan. The base module transmits the sensor data and optionally the additional information to a storage medium locally or remotely accessible by the manager device.

An unmanned aerial vehicle includes a central body and a plurality of arms extendable from the central body. Each of the plurality of arms is configured to support one or more propulsion units. Each of the plurality of arms is configured to transform between (1) a flight configuration in which the arm is extending away from the central body and (2) a compact configuration in which the arm is folded against the central body. At least one of the plurality of arms is configured to rotate about a first rotational axis and at least a portion of the at least one of the plurality of arms is configured to rotate about a second rotational axis not parallel to the first rotational axis.

An unmanned aerial vehicle (UAV), a stand for launching, landing, testing, refueling and recharging a UAV, and methods for testing, landing and launching the UAV are disclosed. Further, embodiments may include transferring a payload onto or off of the UAV, and loading flight planning and diagnostic maintenance information to the UAV.

An unmanned aircraft system operable for wing-borne lift in a flying wing orientation. The unmanned aircraft system includes an airframe having a leading edge, a trailing edge, first and second wingtips and a root chord. The airframe has an airfoil cross-section along chord stations thereof. A thrust array is coupled to the airframe including first and second motor mounts coupled to the leading edge respectively between the root chord and the first and second wingtips. The motor mounts each have first and second propulsion assemblies coupled to respective first and second distal ends thereof. The motor mounts each have a flight configuration substantially perpendicular with the leading edge forming a two-dimensional distributed thrust array such that the airframe extends outboard of the first and second motor mounts. The unmanned aircraft system includes an electric power system and a flight control system that are operably associated with the thrust array.

An unmanned aircraft system operable for wing-borne lift in a flying wing orientation. The unmanned aircraft system includes an airframe having a leading edge, a trailing edge, first and second wingtips and a root chord. The airframe has an airfoil cross-section along chord stations thereof. A thrust array is coupled to the airframe including first and second motor mounts coupled to the leading edge respectively between the root chord and the first and second wingtips. The motor mounts each have first and second propulsion assemblies coupled to respective first and second distal ends thereof. The motor mounts each have a flight configuration substantially perpendicular with the leading edge forming a two-dimensional distributed thrust array such that the airframe extends outboard of the first and second motor mounts. The unmanned aircraft system includes an electric power system and a flight control system that are operably associated with the thrust array.