An example method for launching a high-altitude balloon includes securing a launch collar around a balloon envelope to form a choke point separating an upper portion of the balloon envelope from a lower portion of the balloon envelope. The balloon envelope is structurally secured to a launch platform via a tether that is coupled to the launch collar. The launch collar is configured such that release of the launch collar from the choke point releases the balloon envelope from the launch platform.

Non-conductive films for constructing lighter than air balloons are provided. A non-conductive film may include multiple layers of gas barrier polymers. An outer surface printable layer and an interior heat or ultrasonically sealable layer may also be included. Each gas barrier film may include multiple (e.g., from 3 to approximately 75) barrier layers. A gas barrier core has a nano-layer structure. A gas barrier core may also include a biodegradable film or a bio-based film. A non-conductive film may include a metal layer for enhancing gas barrier properties. The metal layer may be discontinuous. The metal layer may be conductive and coated with an insulating top coat.

Non-conductive films for constructing lighter than air balloons are provided. A non-conductive film may include multiple layers of gas barrier polymers. An outer surface printable layer and an interior heat or ultrasonically sealable layer may also be included. Each gas barrier film may include multiple (e.g., from 3 to approximately 75) barrier layers. A gas barrier core has a nano-layer structure. A gas barrier core may also include a biodegradable film or a bio-based film. A non-conductive film may include a metal layer for enhancing gas barrier properties. The metal layer may be discontinuous. The metal layer may be conductive and coated with an insulating top coat.

Hydrogen is delivered from a first location to a second location by an airship, such as a lighter-than-air ship. The hydrogen may be produced at the first location and the second location is where the hydrogen is needed. Once produced, the hydrogen is then loaded onto the airship. In one approach, a hydrogen storage compartment in the airship is filled with hydrogen. After the airship has arrived at the second location, the hydrogen is retrieved and may be stored at the second location for use as an energy source.

A method of controlling an aero wind power generation device, includes take-off preparation process of preparing for take-off of the aero wind power generation device; a gas injection process of injecting gas into a buoyancy generation unit of the aero wind power generation device; a take-off process of taking off the aero wind power generation device using a drone unit and the buoyancy generation unit of the aero wind power generation device; and a charging process of charging a battery connected to the aero wind power generation device using the aero wind power generation device.

A method of controlling an aero wind power generation device, includes take-off preparation process of preparing for take-off of the aero wind power generation device; a gas injection process of injecting gas into a buoyancy generation unit of the aero wind power generation device; a take-off process of taking off the aero wind power generation device using a drone unit and the buoyancy generation unit of the aero wind power generation device; and a charging process of charging a battery connected to the aero wind power generation device using the aero wind power generation device.

The subject of the present invention relates to a floating platform (10) for launching a space rocket (100) from high altitude comprising a support structure (20) for suspending the space rocket (100) and which support structure (20) can be releasably connected to the space rocket (100), one or more hydrogen or helium filled balloons (30) fixed to the support structure (20), one or more rigid-walled tanks (12) and a compressor module (40) connected to the one or more balloons (30) and rigid-walled tanks (12) for delivering at least a portion of the hydrogen or helium stored in the balloons (30) into the one or more rigid-walled tanks (12), said one or more balloons (30) are dimensioned to lift the floating platform (10) and the space rocket (100) connected thereto, characterized in that the floating platform (10) comprises a hydrogen or helium-filled, preferably cigar-shaped rigid-walled balloon (35) which is releasably connected to the support structure (20) and secured to the top of the space rocket (100) and which is suitable for connecting the space rocket (100) to the support structure (20). The invention further relates to a method for launching a rigid-walled balloon (35) into space.

The subject of the present invention relates to a floating platform (10) for launching a space rocket (100) from high altitude comprising a support structure (20) for suspending the space rocket (100) and which support structure (20) can be releasably connected to the space rocket (100), one or more hydrogen or helium filled balloons (30) fixed to the support structure (20), one or more rigid-walled tanks (12) and a compressor module (40) connected to the one or more balloons (30) and rigid-walled tanks (12) for delivering at least a portion of the hydrogen or helium stored in the balloons (30) into the one or more rigid-walled tanks (12), said one or more balloons (30) are dimensioned to lift the floating platform (10) and the space rocket (100) connected thereto, characterized in that the floating platform (10) comprises a hydrogen or helium-filled, preferably cigar-shaped rigid-walled balloon (35) which is releasably connected to the support structure (20) and secured to the top of the space rocket (100) and which is suitable for connecting the space rocket (100) to the support structure (20). The invention further relates to a method for launching a rigid-walled balloon (35) into space.

Provided is a flight vehicle operating method including: mooring a flight vehicle to a mooring unit by a cable; reducing a weight of the flight vehicle, increasing the flotage of the flight vehicle, or increasing the flotage of the flight vehicle while reducing the weight of the flight vehicle, by using a first flotation adjuster; floating the flight vehicle at a suitable altitude in the air; increasing the weight of the flight vehicle, reducing the flotage of the flight vehicle, or reducing the flotage of the flight vehicle while increasing the weight of the flight vehicle, by using a second flotation adjuster or a propelling unit of the flight vehicle; and releasing the connection between the flight vehicle and the mooring unit and withdrawing the cable.

Provided is a flight vehicle operating method including: mooring a flight vehicle to a mooring unit by a cable; reducing a weight of the flight vehicle, increasing the flotage of the flight vehicle, or increasing the flotage of the flight vehicle while reducing the weight of the flight vehicle, by using a first flotation adjuster; floating the flight vehicle at a suitable altitude in the air; increasing the weight of the flight vehicle, reducing the flotage of the flight vehicle, or reducing the flotage of the flight vehicle while increasing the weight of the flight vehicle, by using a second flotation adjuster or a propelling unit of the flight vehicle; and releasing the connection between the flight vehicle and the mooring unit and withdrawing the cable.