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 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.

An air, sea and underwater tilt tri-rotor UAV capable of performing vertical take-off and landing. By the method for controlling a submerged floating device and a tilt tri-rotor device, the UAV is switched among the vertical take-off and landing mode, fixed wing mode, water surface sailing mode and underwater submerging mode.

In an embodiment, a system for air cooling in a wet environment includes a propeller coupled to a vehicle capable of at least one of: taking off from and landing on water. The system includes a battery configured to power the propeller, a float configured to hold the battery, and a flap in the float. The flap is configured to open in response to air pressure to permit airflow into the float to cool the battery.

An amphibious drone having a fuselage, a vertical tail, a wing and a take-off and landing device. The take-off and landing device is on the lower surface of the fuselage or the vertical tail or the wing. The take-off and landing device has a buoyancy unit and a power device, and the power device is capable of generating thrust to push the buoyancy unit to move. The take-off and landing device can be on the lower surface of the drone, and realizes the water support of the drone by symmetrically providing the take-off and landing device. At the same time, the take-off and landing device is further provided with a power device for pushing the drone to be started. The amphibious drone can take off and land by relying on the take-off and landing device, which can be disassembled to adapt to different usage conditions.

A low noise aircraft comprising a fuselage comprising a nose section, a cabin and a tail comprising an empennage, the profile of the fuselage tightening towards the tail, two wings mounted on opposite sides of the fuselage, two engines, each engine mounted on a pylon on a respective side of the fuselage, two propellers, each propeller joined to and positioned behind a respective the engine, at least one cabin door to access the cabin, and landing gear, wherein the engines are positioned above the wings, wherein the propellers are positioned at a rear end of each engine such that the propellers push the engines, and wherein the propellers are positioned behind the inhabitable zone of the cabin.

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.

A submergible aerial vehicle with one or more rotors, a body operatively connected to the one or more rotors, and a platform operatively connected to the body. The vehicle is configured to operate with one or more additional vehicles such that the platform of each vehicle connects together and forms a segment of an enlarged floating platform. The enlarged platform is configured to support an object above the water. The body includes a cavity that is able to be at least partially filled with fluid. The cavity causes the submergible aerial vehicle to be at least partially submerged in a body of water.

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.