Described herein are features for a high altitude lighter-than-air (LTA) system and associated methods. The LTA may include a super-pressure balloon (SPB) and/or a zero-pressure balloon (ZPB). The SPB may include two, three, four or more chambers. There may be more than one SPB. The SPB may use a compressor to provide a variable amount of ballast air by pumping in or expelling out ambient air. The zero-pressure balloon (ZPB) may be attached with the multi-chamber SPB. The ZPB may provide lift for the system. The SPB may include lifting gas and ballast air to provide both lifting and descent functions. The SPB may have an internal barrier separating a lift gas compartment from a variable ballast air compartment.

This invention relates to a thermal hydrogen generator and a process and system for generating hydrogen gas, more specifically to a process and system for generating hydrogen gas by thermally decomposing a metal hydride.

This invention relates to a thermal hydrogen generator and a process and system for generating hydrogen gas, more specifically to a process and system for generating hydrogen gas by thermally decomposing a metal hydride.

A laminated load ring for a balloon assembly includes a plurality of ring stacking units stacked one on top of the other. Each of the ring stacking units can include a main body having a central opening, a plurality of arms, and at least one weld line. The plurality of arms may each extend away from the main body around a circumference of the main body. The at least one weld line can be formed on the main body. The plurality of arms of the plurality of ring stacking units may be aligned with one another. The weld line of each of the plurality of ring stacking units may be offset from the weld line of a directly adjacent ring stacking unit in a direction extending around the circumference of the laminated load ring.

A laminated load ring for a balloon assembly includes a plurality of ring stacking units stacked one on top of the other. Each of the ring stacking units can include a main body having a central opening, a plurality of arms, and at least one weld line. The plurality of arms may each extend away from the main body around a circumference of the main body. The at least one weld line can be formed on the main body. The plurality of arms of the plurality of ring stacking units may be aligned with one another. The weld line of each of the plurality of ring stacking units may be offset from the weld line of a directly adjacent ring stacking unit in a direction extending around the circumference of the laminated load ring.

Disclosed are an unmanned aerial vehicle (UAV) having a buoyancy apparatus and an attitude control method thereof, in which the buoyancy apparatus is coupled to the UAV to reduce the energy consumption of rotors such that the time of staying in the air is extended, enabling a long flight, and in which the buoyancy apparatus absorbs the impact energy and reduces the falling speed to thereby ensure sufficient safety for the UAV.

Disclosed are an unmanned aerial vehicle (UAV) having a buoyancy apparatus and an attitude control method thereof, in which the buoyancy apparatus is coupled to the UAV to reduce the energy consumption of rotors such that the time of staying in the air is extended, enabling a long flight, and in which the buoyancy apparatus absorbs the impact energy and reduces the falling speed to thereby ensure sufficient safety for the UAV.

A rechargeable drone apparatus or arrangement is provided. The rechargeable drone device includes a series of sensors configured to receive information about a user and transmit the information to a computing system configured to assess the information collected from the drone device and a set of securable compartments configured to maintain samples or medications, wherein the series of securable compartments are configured to be openable by an approved individual.

A rechargeable drone apparatus or arrangement is provided. The rechargeable drone device includes a series of sensors configured to receive information about a user and transmit the information to a computing system configured to assess the information collected from the drone device and a set of securable compartments configured to maintain samples or medications, wherein the series of securable compartments are configured to be openable by an approved individual.

A cover for a rawinsonde balloon includes a cover main body with an inner surface forming inner space and an outer surface. The rawinsonde balloon is inserted into the inner space of the cover main body. Further, the cover includes an inlet, positioned at a preliminary free end of the cover main body, for allowing the rawinsonde balloon to be inserted into the inner space and the cover additionally includes an inlet control member for controlling a size of the inlet and fixing a controlled size of the inlet. Furthermore, the cover includes a plurality of basic cover fixing members formed or located respectively at a plurality of basic preliminary fixed ends on the outer surface.