A ground effect craft having a ground effect wing, a plurality of sponsons, and a control system is disclosed. The ground effect wing may include a fore ground effect wing and an aft ground effect wing. The ground effect wing may generate a stabilizing moment on at least one sponson to stabilize the ground effect craft. The plurality of sponsons may be dynamically coupled to the body. The plurality of sponsons may be dynamically coupled to each other. The dynamic coupling may permit the sponsons to move relatively independent of the body and each other, thereby stabilizing the ground effect craft. The ground effect craft may include a stabilizing wing.

A ground effect craft having a ground effect wing, a plurality of sponsons, and a control system is disclosed. The ground effect wing may include a fore ground effect wing and an aft ground effect wing. The ground effect wing may generate a stabilizing moment on at least one sponson to stabilize the ground effect craft. The plurality of sponsons may be dynamically coupled to the body. The plurality of sponsons may be dynamically coupled to each other. The dynamic coupling may permit the sponsons to move relatively independent of the body and each other, thereby stabilizing the ground effect craft. The ground effect craft may include a stabilizing wing.

The invention relates to a surfing arrangement (3) for mounting to underneath an aircraft (1), comprising at least a tank of a water collecting system (10), which arrangement (3) is configured for providing a gliding surface (7) on which said aircraft (1) may surf on water when having a moving speed higher than a predetermined value. The arrangement (3) comprises an elongated body (9), underneath which elongated body (9) the gliding surface (7) is situated, wherein the elongated body (9) is connectable to underneath an aircraft (1) by means of a linkage arm arrangement (23) arranged to a coupling element (25) configured to be coupled to the aircraft (1). The linkage arm arrangement (23) is, when the arrangement (3) is coupled to an aircraft (1), operational to vertically move the elongated body (9) between a raised position, in which raised position the gliding surface (7) is positioned above a lowermost contact point of a piece of a landing gear (5), and a lower position, in which lower position the gliding surface (7) is positioned underneath said lowermost contact point of the piece of said landing gear (5). Said movement of the elongated body (9) being selectively operational during flight of the aircraft (1). The invention further relates to an aircraft (1) comprising such a surfing arrangement (3).

A method of transporting cargo, a cargo transport system and an unmanned Wing In Ground Effect vessel (UWIG) for transporting the cargo. A wake up signal indicates assignment of a new delivery. The UWIG begins pre-flight, causes cargo to be transported to the UWIG, and causes the cargo loaded into UWIG storage compartments. Once loaded and the loaded UWIG is ready, the UWIG taxis, e.g., to the open sea. Environmentally sealed PAR thrust fans provide PAR thrust during takeoff. The UWIG flies to a delivery location where cargo is unloaded, and may be stored.

A vertical take-off and landing (VTOL) aircraft (100) having: a wing structure having right and left side forward wings (20, 22); and right and left side rearward wings (30, 32), each of the right side wings (20, 30) being connected, and each of the left side wings (22, 32) being connected in a box wing configuration; wherein each wing (20, 22, 30, 32) has a fixed leading edge (100) and at least one moveable trailing control surface (110), further wherein each wing (20, 22, 30, 32) has at least one motor pod (195), the motor pod (195) being pivotally mounted to an underside of the fixed leading edge (100), and fixedly secured to the trailing control surface (110).

The present invention relates to a multipurpose and long endurance Hybrid Unmanned Aerial Vehicle (HUAV) with the combined functions of a Vertical Take-off and Landing (VTOL) and a fixed wing operation. The HUAV may take-off and land vertically on both land and water, and perform a mid-air transition from a VTOL mode to a fixed wing mode. The HUAV includes an airframe, a fixed wing unit having at least one forward thrust motor, one or more VTOL units mounted on a tail boom, and a fuselage of the airframe. Each of the one or more VTOL units includes at least one VTOL motor, and a control unit configured to control on-board transition of the HUAV between the VTOL mode and the fixed wing mode by controlling at least one forward thrust motor and at least one VTOL motor.

The present invention relates to a multipurpose and long endurance Hybrid Unmanned Aerial Vehicle (HUAV) with the combined functions of a Vertical Take-off and Landing (VTOL) and a fixed wing operation. The HUAV may take-off and land vertically on both land and water, and perform a mid-air transition from a VTOL mode to a fixed wing mode. The HUAV includes an airframe, a fixed wing unit having at least one forward thrust motor, one or more VTOL units mounted on a tail boom, and a fuselage of the airframe. Each of the one or more VTOL units includes at least one VTOL motor, and a control unit configured to control on-board transition of the HUAV between the VTOL mode and the fixed wing mode by controlling at least one forward thrust motor and at least one VTOL motor.

A ground effect craft having a ground effect wing, a plurality of sponsons, and a control system is disclosed. The ground effect wing may include a fore ground effect wing and an aft ground effect wing. The ground effect wing may generate a stabilizing moment on at least one sponson to stabilize the around effect craft. The plurality of sponsons may be dynamically coupled to the body. The plurality of sponsons may be dynamically coupled to each other. The dynamic coupling may permit the sponsons to move relatively independent of the body and each other, thereby stabilizing the ground effect craft. The ground effect craft may include a stabilizing wing.

A ground effect craft having a ground effect wing, a plurality of sponsons, and a control system is disclosed. The ground effect wing may include a fore ground effect wing and an aft ground effect wing. The ground effect wing may generate a stabilizing moment on at least one sponson to stabilize the around effect craft. The plurality of sponsons may be dynamically coupled to the body. The plurality of sponsons may be dynamically coupled to each other. The dynamic coupling may permit the sponsons to move relatively independent of the body and each other, thereby stabilizing the ground effect craft. The ground effect craft may include a stabilizing wing.

The present disclosure relates to a secondary airfoil apparatus, system and method for improving lift, takeoff, landing and aerodynamic performance of a floatplane. The secondary airfoil can be integrated into the floatplane during manufacture, or retrofitted to an existing floatplane after manufacture. The secondary airfoil is itself of sufficient structural rigidity to withstand any and all forces added by the airfoil during floatplane operation. The secondary airfoil is fixedly attached between the floats of the floatplane, and are purposefully not attached to spreader bars that can exist typically between the floats. The secondary airfoil can be arranged at an optimal angle of incidence and vertical lift position relative to the primary airfoil, or wing of the aircraft, and relative to the floats center of gravity and drag for optimal maneuverability of the floatplane.