The present invention relates to a hydrogen recycling flight system and flight method, the hydrogen recycling flight system including: a flight fuselage which has at least one pair of wings at each of both sides of a body; a hydrogen gas balloon which is air-tightly connected to the flight fuselage; a hydrogen fuel cell which is connected with the hydrogen gas balloon and is installed outside or inside the flight fuselage; and a secondary battery which is charged with electricity generated from the hydrogen fuel cell, electricity generated from a solar cell provided at an outer peripheral portion of the flight fuselage, or electricity of an external power network, in which by using a switch, the hydrogen fuel cell is switched to a water electrolysis device or the water electrolysis device is switched to the hydrogen fuel cell, the hydrogen recycling flight system includes: a water tank which stores water generated from the hydrogen fuel cell; the water electrolysis device which electrolyzes the stored water; a switch control device which switches functions of the hydrogen fuel cell and the water electrolysis device; and a high-pressure gas barrel which high-pressure stores hydrogen gas and oxygen gas generated in the water electrolysis device, and the flight fuselage flies by controlling the volume of the hydrogen gas balloon that is flotation power of a flight vehicle by an operation of the hydrogen fuel cell or the high-pressure gas barrel.

A vacuum lighter than air vehicle (VLTAV) includes a rigid frame of rods connected together to form a hexakis icosahedron. A membrane skin covers the rigid frame and defines therewith a vessel configured to hold an internal vacuum that allows the vessel to float in the air. The plurality of rods and membrane skin have weights and dimensions that result in a neutral and/or positive buoyancy for the vessel while preventing geometric instability.

An aerial vehicle (1) in which forward motion is developed by changing the position of the buoyancy centre and the position of the centre of gravity of the aerial vehicle (1). The aerial vehicle (1) has an envelope (12) which is a body of revolution about a central axis (X-X). The envelope (12) comprises a film and contains a lighter than air gas and wings (13, 14) one each extending laterally either side of the envelope (12).

An aerial vehicle (1) in which forward motion is developed by changing the position of the buoyancy centre and the position of the centre of gravity of the aerial vehicle (1). The aerial vehicle (1) has an envelope (12) which is a body of revolution about a central axis (X-X). The envelope (12) comprises a film and contains a lighter than air gas and wings (13, 14) one each extending laterally either side of the envelope (12).

A lighter-than-air airship has an exoskeleton constructed of spokes and hubs to create a set of connected hexagrams comprised of isosceles triangles wherein the spokes flex and vary in length to produce the slope of said airship's surface. In one embodiment, the exoskeleton connects to a nose cone that includes a cockpit cabin for controlling the airship's operation from a single location that can be physically separated from the exoskeleton in response to catastrophic events and for autonomous and/or remotely piloted operation. An improved means is also provided for landing and unloading cargo, and through use of unmanned aerial vehicles in another embodiment, the airship is configured for remote pickup, transport, delivery and return of payloads such as packages. In yet another embodiment, the airship provides a communications platform for beam form transmission and satellite signal relay, including in combination with the foregoing disclosed attributes.

The present invention is a variable geometry aircraft that is capable of morphing its shape from a symmetric cross-section buoyant craft to an asymmetric lifting body and even to a symmetric zero lift configuration. The basic structure is a semi rigid airship with movable longerons. Movement of the longerons adjusts the camber of the upper and/or lower surfaces to achieve varying shapes of the lifting-body. This transformation changes both the lift and drag characteristics of the craft to alter the flight characteristics. The transformation may be accomplished while the craft is airborne and does not require any ground support equipment.

A system for transporting hydrogen from where it can be economically made to where it is most needed using airships. Green technologies can be used to generate electricity near to the primary energy sources. This electricity can then be used to produce hydrogen directly from water. Hydrogen can be delivered using an airship in which the hydrogen gas can also be used for generating lift, providing propulsion energy and serving ancillary needs. The ship can be equipped with solar cells that generate electricity that can be used to make hydrogen from water, and can be used to power the ship's propulsion system.

A system for transporting hydrogen from where it can be economically made to where it is most needed using airships. Green technologies can be used to generate electricity near to the primary energy sources. This electricity can then be used to produce hydrogen directly from water. Hydrogen can be delivered using an airship in which the hydrogen gas can also be used for generating lift, providing propulsion energy and serving ancillary needs. The ship can be equipped with solar cells that generate electricity that can be used to make hydrogen from water, and can be used to power the ship's propulsion system.

The invention relates to an aircraft having a supporting structure (12) and a shell (10) that can be filled with a gas and which is tensioned by the supporting structure (12). According to the invention, said supporting structure (12) comprises a plurality of rod or tube-shaped sections (24-30) which define a circular, oval or polygonal main clamping plane for the shell (10).

The invention relates to an aircraft having a supporting structure (12) and a shell (10) that can be filled with a gas and which is tensioned by the supporting structure (12). According to the invention, said supporting structure (12) comprises a plurality of rod or tube-shaped sections (24-30) which define a circular, oval or polygonal main clamping plane for the shell (10).