An aero wind power generation apparatus includes: a drone unit including drone wings configured to make the aero wind power generation apparatus move and hover and a sensor unit configured to detect information for controlling the aero wind power generation apparatus; a buoyancy generation unit connected to the drone unit and including a side cover configured to open or close and a balloon provided inside the side cover, wherein the buoyancy generation unit is configured to enable injection of gas into or release of the gas from the balloon; and a power generation unit connected to the buoyancy generation unit and including a rotating unit with a plurality of blades, a blade control unit of adjusting the state of the blades, and a motor unit of converting kinetic energy transferred from the rotating unit into electrical energy.

An aero wind power generation apparatus includes: a drone unit including drone wings configured to make the aero wind power generation apparatus move and hover and a sensor unit configured to detect information for controlling the aero wind power generation apparatus; a buoyancy generation unit connected to the drone unit and including a side cover configured to open or close and a balloon provided inside the side cover, wherein the buoyancy generation unit is configured to enable injection of gas into or release of the gas from the balloon; and a power generation unit connected to the buoyancy generation unit and including a rotating unit with a plurality of blades, a blade control unit of adjusting the state of the blades, and a motor unit of converting kinetic energy transferred from the rotating unit into electrical energy.

A method of creating aeronautical lift is described which uses a fast voltage electrostatic force to rapidly simultaneously move the top and bottom surfaces of a lifting device downward, followed by a slow voltage electrostatic force to slowly simultaneously return the top and bottom surfaces to their original positions. This cyclic movement reduces downward air pressure on the top surface of the lifting device and increases air pressure on the bottom surface of the lifting device, thus producing aeronautical lift.

A method of creating aeronautical lift is described which uses a fast voltage electrostatic force to rapidly simultaneously move the top and bottom surfaces of a lifting device downward, followed by a slow voltage electrostatic force to slowly simultaneously return the top and bottom surfaces to their original positions. This cyclic movement reduces downward air pressure on the top surface of the lifting device and increases air pressure on the bottom surface of the lifting device, thus producing aeronautical lift.

A system for an unmanned aerial vehicle can include an altitude control system, which further includes a compressor assembly, a valve assembly, and an electronics assembly. The compressor assembly may include a driveshaft and a bearing assembly configured to rotate the driveshaft. The driveshaft may be formed from a first material and a compressor housing may be formed from a second material. The first and second materials may have different rates of thermal expansion. A dynamic preloading mechanism, such as a flexible plate, may be provided within the compressor assembly to exert a preloading force on the bearing assembly. Throughout the duration of the flight of the unmanned aerial vehicle, the preloading mechanism can continually compensate for differences in rates of thermal expansion between the first and second materials throughout.

A system for an unmanned aerial vehicle can include an altitude control system, which further includes a compressor assembly, a valve assembly, and an electronics assembly. The compressor assembly may include a driveshaft and a bearing assembly configured to rotate the driveshaft. The driveshaft may be formed from a first material and a compressor housing may be formed from a second material. The first and second materials may have different rates of thermal expansion. A dynamic preloading mechanism, such as a flexible plate, may be provided within the compressor assembly to exert a preloading force on the bearing assembly. Throughout the duration of the flight of the unmanned aerial vehicle, the preloading mechanism can continually compensate for differences in rates of thermal expansion between the first and second materials throughout.

Systems and methods related to deployable hydrogen reactors are described. In some embodiments, a system (e.g., a balloon system) may include a reaction chamber immersed in a body of water. By permitting a flow of water from the body of water into the reaction chamber, a reaction between a reactant and the water may be carried out to produce one or more lifting gases (e.g., hydrogen gas), which can be employed to subsequently inflate and launch the system in an automated fashion.

Systems and methods related to deployable hydrogen reactors are described. In some embodiments, a system (e.g., a balloon system) may include a reaction chamber immersed in a body of water. By permitting a flow of water from the body of water into the reaction chamber, a reaction between a reactant and the water may be carried out to produce one or more lifting gases (e.g., hydrogen gas), which can be employed to subsequently inflate and launch the system in an automated fashion.

An unmanned aerial vehicle (“UAV”) having an envelope and a drone body capable of delivering packages is disclosed. Methods for utilizing UAVs to deliver packages and systems for housing UAVs are also disclosed. In one aspect, a UAV includes a dual cavity envelope having an ellipsoid shape with a first internal cavity and a second internal cavity, the first internal cavity configured to hold a lighter than air gas, the second internal cavity configured to hold a heated gas, and a drone body attached to and located below the dual cavity vertical envelope.

An unmanned aerial vehicle (“UAV”) having an envelope and a drone body capable of delivering packages is disclosed. Methods for utilizing UAVs to deliver packages and systems for housing UAVs are also disclosed. In one aspect, a UAV includes a dual cavity envelope having an ellipsoid shape with a first internal cavity and a second internal cavity, the first internal cavity configured to hold a lighter than air gas, the second internal cavity configured to hold a heated gas, and a drone body attached to and located below the dual cavity vertical envelope.