A structure equipped with a fuel cell system, wherein the structure comprises: a skirt configured to form an accumulation space between a bottom of the structure and the ground, an air supplier configured to supply off-gas, which is discharged from the fuel cell system, to at least one space selected from the group consisting of the accumulation space and an internal space of the skirt, and a pressure discharger configured to discharge pressure accumulated in the accumulation space to outside of the skirt from a lower end of the skirt, and wherein lift is imparted to the structure by supplying a predetermined amount of the off-gas from the air supplier to at least one space selected from the group consisting of the accumulation space and the internal space of the skirt.

A structure equipped with a fuel cell system, wherein the structure comprises: a skirt configured to form an accumulation space between a bottom of the structure and the ground, an air supplier configured to supply off-gas, which is discharged from the fuel cell system, to at least one space selected from the group consisting of the accumulation space and an internal space of the skirt, and a pressure discharger configured to discharge pressure accumulated in the accumulation space to outside of the skirt from a lower end of the skirt, and wherein lift is imparted to the structure by supplying a predetermined amount of the off-gas from the air supplier to at least one space selected from the group consisting of the accumulation space and the internal space of the skirt.

An example wing-in-ground effect vehicle includes (i) a main wing having main wing control surfaces; (ii) a tail having tail control surfaces; (iii) a blown-wing propulsion system arranged along the main wing or the tail; (iv) a retractable hydrofoil configured to operate in: (a) an extended configuration in which the retractable hydrofoil extends below a hull of the vehicle for submersion below a water surface and (b) a retracted configuration in which the retractable hydrofoil is retracted at least partially into the hull of the vehicle; and (v) a control system configured to maneuver the vehicle by (i) causing a change in orientation of the retractable hydrofoil when the retractable hydrofoil is operating in the extended configuration, and (ii) causing a change in orientation of the main wing control surfaces and tail control surfaces when the retractable hydrofoil is operating in the retracted configuration.

A lightweight gearbox control mechanism for air cushion vehicles provides change in direction of rotation for the vehicle lift fan and allows the gearbox to be used at port or starboard vehicle locations without the use of specialty tools.

A lightweight gearbox control mechanism for air cushion vehicles provides change in direction of rotation for the vehicle lift fan and allows the gearbox to be used at port or starboard vehicle locations without the use of specialty tools.

A rotor assembly for generating thrust for a vehicle. The rotor assembly includes a rotor hub and a plurality of rotor blade assemblies coupled to the rotor hub. Each rotor blade assembly includes a metallic bearing race, a composite rotor blade and a metallic coupling assembly. The composite rotor blade has a root section with a radially outwardly tapered outer surface. The metallic coupling assembly has a radially inwardly tapered inner surface that receives the radially outwardly tapered outer surface of the root section of the rotor blade therein to provide a centrifugal force seat for the rotor blade. The coupling assembly includes at least two circumferentially distributed coupling members. The coupling assembly is configured to couple the rotor blade to the bearing race and to provide a centrifugal force load path therebetween.

A rotor assembly for generating thrust for a vehicle. The rotor assembly includes a rotor hub and a plurality of rotor blade assemblies coupled to the rotor hub. Each rotor blade assembly includes a metallic bearing race, a composite rotor blade and a metallic coupling assembly. The composite rotor blade has a root section with a radially outwardly tapered outer surface. The metallic coupling assembly has a radially inwardly tapered inner surface that receives the radially outwardly tapered outer surface of the root section of the rotor blade therein to provide a centrifugal force seat for the rotor blade. The coupling assembly includes at least two circumferentially distributed coupling members. The coupling assembly is configured to couple the rotor blade to the bearing race and to provide a centrifugal force load path therebetween.

A rotor assembly for generating vehicle thrust. The rotor assembly includes a rotor hub with a plurality of rotor blade assemblies coupled thereto. Each rotor blade assembly includes a metallic bearing race, a composite rotor blade and a split collet assembly. The split collet assembly includes two circumferentially distributed collet members each having an inner inboard conical seat configured to mate with a radially outwardly extending conical feature of the bearing race and an inner outboard conical seat configured to mate with a radially outwardly extending conical feature of the rotor blade. The split collet assembly also includes an outer sleeve having an inner conical surface that mates with outer conical surfaces of the collet members to maintain the collet members in a circumferential orientation around the bearing race and the rotor blade such that the split collet assembly provides a centrifugal force load path therebetween.

The invention discloses a hovercraft using single ducted fan with vectoring propulsion, including a hull and a single ducted fan arranged on the hull, wherein the single ducted fan comprises barrel shaped shell and oar-blade component arranged in chamber of the shell, a first air outlet is disposed on one side of shell towards the tail end of the hull, diversion rudders enabling to block the first air outlet are disposed on the shell, two first air guide all connected with chamber of the shell is disposed on both sides of the shell, a second air outlet towards external of the single ducted fan is disposed on the first air guide, and the second air outlet and the first air outlet are arranged in reverse or with an included angle greater than 0 degree.

The invention discloses a hovercraft using single ducted fan with vectoring propulsion, including a hull and a single ducted fan arranged on the hull, wherein the single ducted fan comprises barrel shaped shell and oar-blade component arranged in chamber of the shell, a first air outlet is disposed on one side of shell towards the tail end of the hull, diversion rudders enabling to block the first air outlet are disposed on the shell, two first air guide all connected with chamber of the shell is disposed on both sides of the shell, a second air outlet towards external of the single ducted fan is disposed on the first air guide, and the second air outlet and the first air outlet are arranged in reverse or with an included angle greater than 0 degree.