A system including a spine portion that is configured to run from top end and a bottom end of a kite. A cross-spar segment having a first end portion and a second end portion that runs from wingtip to wingtip of said kite. A cover part, in which the cover part comprise a fabric made of at least one of a nylon and a cloth. A tail section. A first flight operative system disposed on one end portion of the cross-spar segment. A second flight operative system disposed on another end portion of the cross-spar segment.

The disclosure relates to an unmanned aerial vehicle, wherein a fuel cell system component provides a structural component of the vehicle. In some instances propulsion modules affixed to wings are oriented so as to provide airflow to plates of a fuel cell via air inlets for each fuel cell provided at the forward surface of each wing, a fuel cell system component forming a portion of the body and wherein the air inlets are unblocked during flight, each propulsion module is configured to provide air as an oxidant to a fuel cell via the air inlets.

An aircraft propulsion system comprises a propulsor an electric motor coupled to the propulsor. The electric motor comprises a surface mounted permanent magnet electric machine comprising a rotor mounted radially inward of a stator. A Motor Diameter Ratio (MDR) is defined as an inner diameter (D.sub.stator,in) of the motor stator in metres divided by an outer diameter (D.sub.stator,out) of the motor stator in metres. The MDR of the electric motor stator is within 10% of the value given by the equation:

[00001]${\mathrm{MDR}=0.83\times (\frac{\mathrm{Torq}ue}{L_{active}}\times \frac{1}{U_{\mathrm{fan},\mathrm{tip}}})}^{0.08}$ where: T is the maximum torque rating of the electric motor in kilonewton metres; L.sub.active is the active length of the motor stator in metres; and U.sub.tip is the tip speed of the propulsor at the maximum rated torque of the electric motor in metres per second.

In the described embodiments, the MDR is less than 1.

A multicopter includes: a support; rotors supported by the support; an electrical equipment that supplies power for rotationally driving the rotors; a circuitly that controls a flight of an airframe by individually adjusting a rotor speed of each of the rotors; and a cooling unit that cools the electrical equipment. The cooling unit includes a heat exchanger, a refrigerant circulating through the heat exchanger and the electrical equipment, and a pump that circulates the refrigerant.

A wireless power receiver coil is attached to a landing gear of a drone. The wireless power receiver coil is closer to the drone when the landing gear is in a retracted position and farther away from the drone when the landing gear is in an extended position. A length of the wireless power receiver coil may be the same length when the landing gear is in the retracted position and in the extended position. The wireless power receiver coil may be in a first orientation when the landing gear is in the retracted position and the wireless power receiver coil may be in a different orientation when the landing gear is in the extended position. The wireless power receiver coil may have a first shape when the landing gear is in the retracted position and may have a second shape when the landing gear is in the extended position.

Certain exemplary embodiments can provide an AirBox constructed to receive deliveries from a drone. The AirBox can comprise an automatically openable lid; and a wireless receiver that is constructed to receive data concerning a delivery from the drone. The automatically openable lid can open to receive the delivery from the drone.

The present invention provides an unmanned aerial vehicle (100) comprising: a flight system (4) for producing thrust to manoeuvre the unmanned aerial vehicle (100). The flight system (4) comprises: one or more flight rotors (42) defining a plane passing through each flight rotor and a thrust direction generally perpendicular to the plane; and one or more electric motor (44) for driving the one or more flight rotors (42). The unmanned aerial vehicle (100) further comprises: a cargo area for coupling to or receiving a load (200); and a load system (6) for providing thrust additional to the thrust provided by the flight system (4) to thereby lift a load attached to the connection point. The load system (6) comprises: a first gas turbine propulsion system; and a controller configured to control the flight system (4) and load system (6).

The battery thermal management system includes a battery pack, a circulation subsystem, and a heat exchanger. The system can optionally include a cooling system, a reservoir, a de-ionization filter, a battery charger, and a controller.

Stations for a drone are described as well as a monitoring system that is configured to monitor a property using one or more drones. The drone is launched from a docking station and configured to navigate the property to perform operations to monitor the property. The docking station is located at an area of the property. The docking station includes a landing surface that is parallel to a particular area of the property that supports the docking station. A positioning surface of the docking station slopes toward the landing surface. The positioning surface, including its slope, is configured to receive the drone and guide the drone toward the landing surface.

A multi-axis amphibious copter for flying and cruising at high speeds. The multi-axis amphibious copter includes six propulsion points i.e., four propellors oriented vertically, a coaxial rotor oriented vertically, and a mini turbine thruster on the rear of the aircraft body and configured to propel the multi-axis amphibious copter forward. The multi-axis amphibious copter can land and take off vertically from congested places and can fly at cruising speeds.