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.

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 system uses existing pipelines, e.g., natural gas, oil, etc., to transport hydrogen to one or more distribution points. The disclosed hydrogen distribution system enables use of water, sewer, storm drain and other existing pipelines for local distribution. Hydrogen is produced from an energy source at a producing location. A safety pipe is located inside an existing pipeline configured to carry a first product and a hydrogen delivery line, configured to carry hydrogen, is placed inside the safety pipe such that a channel is formed between an exterior of the hydrogen delivery line and an interior of the safety pipe. Hydrogen is injected into the hydrogen delivery line and a sweeper gas is injected into the channel to purge any hydrogen that might be leaking from the hydrogen delivery line.

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 aircraft may include variable span, length, and camber. The variability of the structure and the flexible envelope allows the aircraft to adjust its aspect ratio along with the camber of the upper and/or lower surfaces to achieve varying shapes. This transformation changes both the lift and drag characteristics of the craft and may be accomplished while the craft is airborne.

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 aircraft may include variable span, length, and camber. The variability of the structure and the flexible envelope allows the aircraft to adjust its aspect ratio along with the camber of the upper and/or lower surfaces to achieve varying shapes. This transformation changes both the lift and drag characteristics of the craft and may be accomplished while the craft is airborne.

The VEHICLE WITH TRAVELING WAVE THRUST MODULE APPARATUSES, METHODS AND SYSTEMS include force or forces applied to an arc-like flexible sheet-like material to create a deformed crenated strip fin with strained-deformations. The strained-deformations take on a sinusoid-like form that express the internal energy state of the flexible sheet-like material after it has been configured into a crenated strip fin. After being incorporated into a mechanism with couplings that prevent the crenated strip fin from returning to its un-strained state, the strained-deformations persist. Actuators may be used to sequentially rotate vertebrae attached to the fins causing the travel of sinusoid-like deformations along the fins. The fin, fin actuator or actuators, power source and central controller may be incorporated into a thrust module. Two thrust modules coupled to a central body via roll actuators and flexible coupling members may form a vehicle with exceptional maneuverability.

The VEHICLE WITH TRAVELING WAVE THRUST MODULE APPARATUSES, METHODS AND SYSTEMS include force or forces applied to an arc-like flexible sheet-like material to create a deformed crenated strip fin with strained-deformations. The strained-deformations take on a sinusoid-like form that express the internal energy state of the flexible sheet-like material after it has been configured into a crenated strip fin. After being incorporated into a mechanism with couplings that prevent the crenated strip fin from returning to its un-strained state, the strained-deformations persist. Actuators may be used to sequentially rotate vertebrae attached to the fins causing the travel of sinusoid-like deformations along the fins. The fin, fin actuator or actuators, power source and central controller may be incorporated into a thrust module. Two thrust modules coupled to a central body via roll actuators and flexible coupling members may form a vehicle with exceptional maneuverability.

The technology relates to techniques for drogue deployment for a lighter than air (LTA) vehicle descent. A drogue deployment system for an LTA vehicle descent can include a drogue comprising a drogue parachute coupled to a carrier. A spring can be configured to launch the drogue from a launch tube directed outward from an apex of the LTA vehicle in an acute angle from a horizontal plane. A core can be placed around the launch tube and placed around the spring, the core compressing the spring and holding the spring in a compressed state prior to deployment, and a riser can couple the carrier to the envelope of the LTA vehicle. In some cases, the drogue deployment system can comprise two or more drogues, wherein intervals between the two or more drogues can be selected such that horizontal components of drogue deployment forces approximately cancel out.

A measurement system comprising a plurality of High-Altitude Pseudo Satellites (HAPS), comprising fixed wing HAPS, having a span loaded fixed wing, an aspect ratio greater than 15 and wing loading less than 6 kg/m2, and/or lighter than air HAPS, each HAPS carrying a plurality of lightweight dropsondes, each dropsonde including sensors and a transmitter, where the plurality of high-altitude pseudo satellites located in a geographical array over at least part an area of the earth. The dropsondes are deployed from the HAPS at predetermined times, such that the deployed dropsondes gathering sensed data after deployment, and the sensed data transmitted to the HAPS.

A measurement system comprising a plurality of High-Altitude Pseudo Satellites (HAPS), comprising fixed wing HAPS, having a span loaded fixed wing, an aspect ratio greater than 15 and wing loading less than 6 kg/m2, and/or lighter than air HAPS, each HAPS carrying a plurality of lightweight dropsondes, each dropsonde including sensors and a transmitter, where the plurality of high-altitude pseudo satellites located in a geographical array over at least part an area of the earth. The dropsondes are deployed from the HAPS at predetermined times, such that the deployed dropsondes gathering sensed data after deployment, and the sensed data transmitted to the HAPS.