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.

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.

A hovercraft having a stealth function. The hovercraft includes at least: a hull in which a cabin is provided; a power generator provided on the hull and configured to supply a lifting force with which the hull is lifted and a propelling force with which the hull is propelled; a skirt provided at a lower portion of the hull and causes the hull to be lifted by the lifting force supplied by the power generator; an opening/closing louver assembly made up of a plurality of opening/closing louvers on air intakes formed in an outer surface of the hull; and a steering louver assembly made up of a plurality of rudder louvers that are rotated and opened/closed on a port and a starboard of a rear of the opening/closing louver assembly on the outer surface of the hull.

A hovercraft includes a lift air supply source having a dynamic air flow area in communication with a central lift air chamber to provide continuous air flow to the central lift air chamber and a static air flow area in communication with an inflatable skirt extending around a periphery of the hovercraft. Air flow from the static air flow area enters the skirt to replenish air leaking from the skirt. The static air flow area has less air flow than the dynamic air flow area. The static air flow area is located at a higher position than the dynamic air flow area to reduce the likelihood of water entering the inflatable skirt when the hovercraft is operated on water.

A hovercraft having a stealth function. The hovercraft includes at least: a hull in which a cabin is provided; a power generator provided on the hull and configured to supply a lifting force with which the hull is lifted and a propelling force with which the hull is propelled; a skirt provided at a lower portion of the hull and causes the hull to be lifted by the lifting force supplied by the power generator; an opening/closing louver assembly made up of a plurality of opening/closing louvers on air intakes formed in an outer surface of the hull; and a steering louver assembly made up of a plurality of rudder louvers that are rotated and opened/closed on a port and a starboard of a rear of the opening/closing louver assembly on the outer surface of the hull.

A hovercraft including imaginary longitudinal, transverse and vertical axes; a propulsion system (12), configured to generate airflow; a base (50) and, a skirt (13) wherein the skirt (13) further including air permeable regions (130) and at least two set of outflow nozzles (220); wherein the air permeable regions (130) and the set of outflow nozzles (20, 21) are in fluid communication; wherein each set of nozzles (20, 21) comprises, at least, one outflow nozzle (22), said outflow nozzle (22) including two opposing ends, a first end (221) and a second end (222); the hovercraft further including actuating means (30) suitable to control the opening of at least one end (221 or 222) of the nozzles (22) managing the passage of airflow through the end (221 or 222). The technical features and functionalities described herein are applicable to the field of hovercrafts. More particularly, to controllable outflow nozzles and controlling systems for hovercrafts.

A hovercraft including imaginary longitudinal, transverse and vertical axes; a propulsion system (12), configured to generate airflow; a base (50) and, a skirt (13) wherein the skirt (13) further including air permeable regions (130) and at least two set of outflow nozzles (220); wherein the air permeable regions (130) and the set of outflow nozzles (20, 21) are in fluid communication; wherein each set of nozzles (20, 21) comprises, at least, one outflow nozzle (22), said outflow nozzle (22) including two opposing ends, a first end (221) and a second end (222); the hovercraft further including actuating means (30) suitable to control the opening of at least one end (221 or 222) of the nozzles (22) managing the passage of airflow through the end (221 or 222). The technical features and functionalities described herein are applicable to the field of hovercrafts. More particularly, to controllable outflow nozzles and controlling systems for hovercrafts.

A control system of a hovercraft that includes one engine and one propulsion fan enclosed in a duct in which swivel side flaps are located is described. The control system includes, downstream of the duct, at least three rudders. Each of the rudders operates in the full range of angular position, regardless of the position of the swivel side flaps. A control method of such a hovercraft is also described.

A direction control device includes a housing, a wheel shaft supported by the housing, a wheel supported by the wheel shaft, a blade shaft supported by the housing, and a blade mounted on the blade shaft. The housing has a first side and a longitudinal axis. The wheel shaft has a wheel axis and is configured to extend beyond the first side outside the housing. The wheel has a rotational axis and is configured to rotate about the rotational axis. The blade shaft is configured to extend beyond the first side outside the housing.

The invention relates to a control system for an air cushion vehicle (400) for the purpose of improving maneuverability of the air cushion vehicle. The system includes four propeller towers (401-404), propellers installed at the propeller towers, and mounting seats for mounting the propeller towers to the air cushion vehicle. In the system, an edge portion (442) located closest to a side wall N of the air cushion vehicle in the mounting seat is located closer to the ground than an opposite edge portion (446) in relation to a pivot point in the mounting seat, providing a tilt (450) of the propeller in response to rotation of the mounting seat at the pivot point, and in response to the rotation of the mounting seat, the propeller tower directs an air flow (452) produced with the propeller over the side wall of the air cushion vehicle and, due to the tilt of the propeller, partly downwardly relative to a horizontal plane defined by the ground, the air flow exerting a force (462) that lifts the side wall of the air cushion vehicle upwardly from the ground.