The present disclosure pertains to an unmanned aerial vehicle system. Some exemplary implementations may include: a mounting frame (110) onto which at least a payload (30) is affixed; a plurality of fuel cell stacks (50) operable in a predefined configuration, each of the plurality of stacks (50) being in a separate package; one or more tanks (60) configured to supply hydrogen tot the plurality of stacks; a propulsion system (70, 80) configured to receive an out put power generated from the plurality of stacks (50); and a power controller (40) configured to couple the plurality of stacks in the predefined configuration.

A fuel cell system includes a fuel cell and a fuel system. The fuel cell includes a housing and a fuel cell stack positioned in the housing. The fuel cell stack is configured to produce an electrochemical reaction from a fuel and air to output electricity. The fuel system includes a fuel source, a fuel vaporizer, and fuel lines through which fuel flows from the fuel source to the fuel vaporizer and from the fuel vaporizer to the fuel cell stack. The fuel vaporizer includes a conductive tube through which the fuel flows, the conductive tube being in contact with the housing to conduct heat from the housing to the fuel to vaporize the fuel.

A fuel cell system includes a fuel cell and a fuel system. The fuel cell includes a housing and a fuel cell stack positioned in the housing. The fuel cell stack is configured to produce an electrochemical reaction from a fuel and air to output electricity. The fuel system includes a fuel source, a fuel vaporizer, and fuel lines through which fuel flows from the fuel source to the fuel vaporizer and from the fuel vaporizer to the fuel cell stack. The fuel vaporizer includes a conductive tube through which the fuel flows, the conductive tube being in contact with the housing to conduct heat from the housing to the fuel to vaporize the fuel.

Methods, apparatuses and systems for providing renewable energy powered, continuous geostationary orbital communications include arranging a plurality of renewable energy powered unmanned aerial vehicles (UAVs) having ground and air communication capabilities in a belt configuration around the earth, spacing apart the plurality of UAVs to provide intercommunication between at least neighboring ones of the plurality of UAVs, and positioning the plurality of UAVs in a relatively stationary location above the earth at a height of between 12 to 15 miles.

Methods, apparatuses and systems for providing renewable energy powered, continuous geostationary orbital communications include arranging a plurality of renewable energy powered unmanned aerial vehicles (UAVs) having ground and air communication capabilities in a belt configuration around the earth, spacing apart the plurality of UAVs to provide intercommunication between at least neighboring ones of the plurality of UAVs, and positioning the plurality of UAVs in a relatively stationary location above the earth at a height of between 12 to 15 miles.

A mobile emergency communication and vehicle propulsion power system, method, and apparatus for full-scale, clean fuel, electric-powered vehicles having a fuel cell module including a plurality of fuel cells working together to process oxidizers including gaseous oxygen from the atmosphere or local oxygen supply and fuels including gaseous hydrogen from liquid hydrogen, to collect electrons from the plurality of hydrogen fuel cells to supply voltage and current to and control an amount and distribution of electrical voltage or current for use in collecting and amplifying communications signals to function as a cell site repeater and for propulsion systems of the vehicle itself. The system can accordingly be deployed at a location to provide wireless communication functionality in remote areas or areas cut off due to natural disaster.

A drone equipped with fuel cell power pack capable of reducing weight by supplying power from a fuel cell while enabling long-term operation of a drone is provided. The drone equipped with fuel cell power pack may include a case including a wing part placed along an outer circumference of the case, a module frame placed in the case, a fuel cell unit placed in the module frame with a weight balance; and a gas tank mounted on the module frame and connected to the fuel cell unit. Because an overall weight balance of the fuel cell power pack itself can be maintained, even if it is integrally mounted inside the drone, the stable operation of the drone can be achieved.

Disclosed are systems and methods that utilize a solid hydrogen storage material, e.g., a metal hydride as a fuel source for operating a vehicle. Disclosed systems utilize the pressure of a hydrogen storage tank as a controlling factor for release of hydrogen from a solid hydrogen storage material. Disclosed systems are particularly beneficial for use with unmanned aerial vehicles.

Disclosed are systems and methods that utilize a solid hydrogen storage material, e.g., a metal hydride as a fuel source for operating a vehicle. Disclosed systems utilize the pressure of a hydrogen storage tank as a controlling factor for release of hydrogen from a solid hydrogen storage material. Disclosed systems are particularly beneficial for use with unmanned aerial vehicles.

An autonomous cargo delivery aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft includes a fuselage having an aerodynamic shape with a leading edge, a trailing edge and first and second sides. First and second wings are coupled to the fuselage proximate the first and second sides, respectively. A distributed thrust array includes a first pair of propulsion assemblies coupled to the first wing and a second pair of propulsion assemblies coupled to the second wing. A flight control system is operably associated with the distributed thrust array and configured to independently control each of the propulsion assemblies. The first side of the fuselage includes a door configured to provide access to a cargo bay disposed within the fuselage from an exterior of the aircraft with a predetermined clearance relative to the first pair of propulsion assemblies.