An assembly in a marine vessel includes a unit arranged in a water tight chamber opening in a hull of a vessel, wherein the unit is adapted to extend into the water below the vessel when at a mounted position. A connection path between an inside and an outside of the vessel is provided with a sealing system and the sealing system divides the connection path into an outside connection path portion and an inside connection path portion. The assembly includes a gas inlet system opening to the outside connection path portion.

A fluid check valve for use in an aircraft fluid handling system having a confined surrounding structure where a first distance is defined between a fluid duct and the surrounding structure where the design of the fluid check valve is configured to facilitate removal of a first flange and the flow duct by moving the first flange and flow duct a second distance that is less than the first distance. The check valve is offset into the upstream side of a second flange to provide the reduction in the distance that the first flange has to be displaced to remove the first flange and flow duct from the check valve. A first alternate configuration of the fluid check valve utilizes rotational stops attached to the downstream surface of the flow flaps and in a second alternate embodiment configuration, rotational stops extend upstream from the flow flaps.

An annular seal for use in a fluid conveyance system that is subject to a high voltage event includes a center core having a generally tubular shape, the core having a circumferentially projected cross-section that is defined by inner and outer core radial surfaces, and core axial surfaces that are opposite one another. The sidewalls each have a generally tubular shape and a circumferentially projected cross-section that is defined by inner and outer sidewall radial surfaces, and first and second sidewall axial surfaces that are opposite one another. The first sidewall is attached along one of its axial surfaces to one of the core axial surfaces, and the second sidewall is attached along one of its axial surfaces to the other of the core axial surfaces. The center core has an electrical resistance that is less than an electrical resistance of each of the first and second sidewalls.

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. In other embodiments of the invention, the airship of the present invention can be used to dramatically reduce the cost of transportation of freight, the cost of passenger transportation, and to save on the area required for landing at the points of loading/unloading and embarkation/debarkation. And in another embodiment, the airship of the present invention can be used for transporting water and food to areas where needed. In another embodiment, the ship can be equipped with solar cells.

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 hybrid water storage system for an aircraft includes separate variable volumes for respectively storing/holding potable water and gray water occupying a common container. The hybrid water storage system is generally configured to draw potable water from a first variable volume in order to provide fresh water to one or more aircraft appliances (e.g., sinks, showers, ice-makers, etc.), and the used potable water (i.e., the potable water that is collected in drains from the aircraft appliances), referred to herein as gray water, is routed to a second variable volume that occupies the same container as the first variable volume.

A hybrid water storage system for an aircraft includes separate variable volumes for respectively storing/holding potable water and gray water occupying a common container. The hybrid water storage system is generally configured to draw potable water from a first variable volume in order to provide fresh water to one or more aircraft appliances (e.g., sinks, showers, ice-makers, etc.), and the used potable water (i.e., the potable water that is collected in drains from the aircraft appliances), referred to herein as gray water, is routed to a second variable volume that occupies the same container as the first variable volume.

Outflow valve (OFV) assemblies including non-metallic frames and enhanced attachment features are provided. In embodiments, the OFV assembly includes a non-metallic frame to which at least one valve door is pivotally mounted. The non-metallic frame may, in turn, include a generally rectangular frame body, a central opening through the frame body, an outer peripheral flange extending around at least a portion of the frame body. Frame attachment interfaces are distributed or spaced around the outer peripheral flange of the non-metallic frame. The frame attachment interfaces include fastener openings and elevated platform regions, which project from an inboard side of the outer peripheral flange and through which the fastener openings extend. Base plates seat against the elevated platform regions. Fasteners engage the base plates and extend through the fastener openings to an outboard side of the outer peripheral flange to attach the OFV assembly to an aircraft fuselage.

A lighter than air craft having an airframe that has at least one tank in the airframe for holding compressed or liquid hydrogen or helium and at least one compartment in the airframe holding an inflatable bladder. The inflatable bladder can be inflated with hydrogen or helium gas from the first tank. There is a vent in the compartment allowing air to exit the compartment when the bladder is inflated and allowing air to enter the compartment when the bladder is deflated. Inflating and deflating the bladder partially controls buoyancy of the craft. Inflating bladders in compartments fore and aft controls pitch and trim.

Outflow valve (OFV) assemblies including non-metallic frames and enhanced attachment features are provided. In embodiments, the OFV assembly includes a non-metallic frame to which at least one valve door is pivotally mounted. The non-metallic frame may, in turn, include a generally rectangular frame body, a central opening through the frame body, an outer peripheral flange extending around at least a portion of the frame body. Frame attachment interfaces are distributed or spaced around the outer peripheral flange of the non-metallic frame. The frame attachment interfaces include fastener openings and elevated platform regions, which project from an inboard side of the outer peripheral flange and through which the fastener openings extend. Base plates seat against the elevated platform regions. Fasteners engage the base plates and extend through the fastener openings to an outboard side of the outer peripheral flange to attach the OFV assembly to an aircraft fuselage.