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 charging and storage system for a renewable energy transportation, may include a transportation configured to transfer renewable energy; and a cabin configured to charge and store the transportation, wherein the cabin includes a support portion for supporting the transportation, an accommodation portion formed in at least a part of the support portion to accommodate the transportation therein, and a charging unit provided in the accommodation portion to charge the transportation using the renewable energy, and wherein the transportation includes a body portion to be selectively inserted in the accommodation portion, and a wing portion coupled to the body portion to move the body portion.

A drone recharging station comprising a housing carried by a base; one or more photovoltaic panels carried by the housing; an electrical energy storage assembly located within the housing, the electrical energy storage assembly having an electrical input and an electrical output, wherein the or each photovoltaic panel is electrically connected to the electrical input of the electrical energy storage assembly; a drone receiving platform carried by the housing which is configured to receive thereon a drone; and a power coupling electrically connected to the electrical output of the electrical energy storage assembly, wherein the power coupling transfers electrical energy from the electrical storage assembly to a drone in use.

An unmanned aircraft system includes a flying wing airframe having leading and trailing edges with respective sweep angles. A thrust array is coupled to the airframe and includes first and second motor mounts each selectively rotatably coupled to the leading edge by a locking joint. Each motor mount has first and second propulsion assemblies coupled to respective first and second distal ends thereof. A power system is operably associated with the thrust array and is operable to provide power to each propulsion assembly. A flight control system is operably associated with the thrust array and is operable to independently control the speed of each propulsion assembly. In a flight configuration, each motor mount is locked substantially perpendicular with the leading edge by the respective locking joint. In a compact storage configuration, each motor mount is locked substantially parallel with the leading edge the respective locking joint.

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.

Embodiments relate to reconfigurable unmanned vehicles (100). Such vehicles (100) comprise a fuselage (102) presenting a bay (118) for receiving a plurality of components (120-128), each of the plurality of components (120-128) relating to a respective entity for at least one of flight control or operation of the unmanned vehicle (100). The bay (118) comprising a bus to support communications between at least two of the plurality of components (120-128), the plurality of components (120-128) comprising a controller to determine a configuration or presence of one or more than one component of the plurality of components (120-128) when coupled to the bus.

Embodiments relate to reconfigurable unmanned vehicles (100). Such vehicles (100) comprise a fuselage (102) presenting a bay (118) for receiving a plurality of components (120-128), each of the plurality of components (120-128) relating to a respective entity for at least one of flight control or operation of the unmanned vehicle (100). The bay (118) comprising a bus to support communications between at least two of the plurality of components (120-128), the plurality of components (120-128) comprising a controller to determine a configuration or presence of one or more than one component of the plurality of components (120-128) when coupled to the bus.

A system comprising: one or more Unmanned Aerial Vehicles (UAVs); and a UAV carrier configured to carry the UAVs from an origin to a destination; wherein the UAV carrier comprises a first controller configured to release the UAVs from the UAV carrier; and wherein each of the UAVs comprises: one or more motors configured to generate, directly or indirectly, a lift, lifting the UAV; and a second controller, configured to: activate at least one of the motors upon fulfilment of one or more conditions, thereby generating the lift, wherein after the release of the respective UAV and before the activation of the at least one motor of the respective UAV the motors of the respective UAV are inactive.

A UAV location management method for use with a flight management system is provided, where the method comprises providing a location for at least one unmanned aerial vehicle (UAV) for at least one of: landing, taking-off and loading, providing at least a first weight-sensitive UAV pad at the UAV location, assigning a gross weight limit to each UAV scheduled to take-off from the first weight-sensitive UAV pad, the gross weight limit being based on a safety factor and at least one of: (i) a characteristic of the UAV; (ii) a characteristic of a power source of the UAV; (iii) a scheduled flight path for the UAV; and (iv) a weather condition, monitoring a weight exerted on the first weight-sensitive UAV pad when the UAV is positioned on the UAV pad, and transmitting a halt-flight signal to the flight management system for the UAV where the weight exceeds the gross weight limit.

The unmanned aerial vehicle (UAV) includes detachable motor arms. In this way, the UAV may be conveniently stored and transported, rapidly assembled in the field, and repaired in the event of a crash. The motor arms are also configured to separate from the fuselage in the event of a crash. An example unmanned aerial vehicle comprises: a fuselage and two motor arms. Each motor arm is detachably secured to the fuselage by two mechanical connectors and comprises a tube having a rotary wing propulsion system on each end and an electrical connector, positioned between the two rotary wing propulsion systems, configured to conductively interface with an electrical connector in an underside of the fuselage. The two mechanical connectors detachably securing each motor arm to the fuselage are configured to facilitate the separation of that motor arm from the fuselage during a crash.