16results about "Seaplanes" patented technology

The application provides a smart adaptive ground effect vehicle, a flight control method and device, and relates to the technical field of vehicle control. The method initializes the ground effect vehicle according to a preset initialization program to control the ground effect vehicle in a shipborne maneuvering mode, and adjusts the ground effect vehicle from the shipborne maneuvering mode to a preset mode in response to a mode switching instruction. Meanwhile, when an emergency instruction is received, a preset emergency processing program is used to control the power gradient of the ground effect vehicle to descend and the hydrofoil to be in a safe water landing attitude, so that the initialization establishes a safe base state, the mode switching realizes multi-scene adaptation, the emergency disposal ensures flight safety, and the adaptability, stability and safety of the ground effect vehicle in a multi-working-condition scene are improved.

The application discloses a multi-mode water-air cross-medium aircraft based on a bionic airfoil, which comprises a shell, first to third carbon plates, a power module, a fairing, a ballast module, a gliding module, a battery module and a control module; the power module comprises four power units; the gliding module comprises two gliding units which are symmetrically arranged on the two sides of the shell. The application controls the difference between the gravity and the buoyancy of the cross-medium aircraft by storing and draining water through the ballast module; the power module provides power for flying or sliding underwater; when sliding underwater, the two gliding units work in cooperation with the power module, and can adapt to more complex underwater environments. The application has the multi-mode motion capabilities of aerial flight, underwater gliding and strong water ejection, and has a simple structure and is easy to maintain.

The present Invention of Air Cycling Aircraft is a double cycling mechanism or double mono wheel bikes whose mechanism is designed for locking in and out should one cyclist desire to take a rest. The double cycling system also ensures long cycling distances. The system mainly comprises a fuselage, wheels, double cycling structures or mono wheel bikes, linear wheel, twin arm gearbox, propeller shaft and propeller. The invention mainly addresses cycling structures, navigation or steering system, cycling friction, and high speed. Motion transmission system is developed into three stages, primary, secondary and advanced stage, to enable the twin arm gearbox to generate more than 2,000 rpm and transmit to the propeller. The present invention the new Air Cycling Aircraft is environmentally compliant and can be used for leisure flying, passenger and air sporting.

The present application relates to a kind of ground effect wing ship longitudinal coefficient estimation method and its aerodynamic characteristic analysis system, belong to the technical field of ground effect wing ship. It covers preliminary design ground effect wing ship scheme, design and manufacture wind tunnel model, obtain data by 3 times variable flight height test, and utilize these data to deduce the mathematical expression of ground effect wing ship longitudinal aerodynamic coefficient, estimate the longitudinal aerodynamic characteristic in any flight height state by the mathematical expression of ground effect wing ship longitudinal aerodynamic coefficient, to simplify test procedure, reduce test number. The present application significantly reduces the workload of model blowing test by combining theoretical analysis with a small amount of test data, shortens the research and development cycle, reduces the consumption of funds. At the same time, the method can accurately obtain the key partial derivative and relative ground effect height in the stability calculation of ground effect wing ship, improve the design efficiency and accuracy, and has important promoting effect on the development and application of ground effect wing ship technology.

This invention relates to the field of aerodynamic component technology, and in particular to a wing spoiler device for a ground effect vehicle (GEV). The wing spoiler device for a GEV includes: a base, a movable flap, the front end of which is hinged to the front of the base, and the rear end of which is fixed to the rear of the base via an adjusting fastener passing through a pre-set first adjusting and fixing hole. The spoiler device is mounted above the front wing of the GEV via the base, so that when the incoming airflow passes over the upper wing surface, it obstructs the downwash airflow converging at the trailing edge of the wing, generating vortices inside the spoiler device to reduce the lift of the upper wing surface and increase the ground effect ratio of the lower wing surface, thereby suppressing the aerodynamic center of gravity shift of the GEV. The advantages of this invention are its simple structure, low manufacturing cost, and the elimination of the need for active control components such as servos or other transmission electronic devices. It also features a robust structure, better adaptability to harsh water environments, reduced safety hazards, and extended service life of the aircraft.

This invention relates to a low-altitude spacecraft capable of both amphibious takeoff and landing, belonging to the field of low-altitude aircraft technology. The invention increases the contact area between the hull and water by combining a flat hull bottom with a horizontal hull section, effectively improving the stability of the spacecraft during water navigation. Simultaneously, an arc-shaped hull lifting section is incorporated. During takeoff and as the spacecraft ascends, water flow is diverted along the arc structure, creating a dynamic water pressure difference above and below the hull, generating an upward lifting force to counteract water drag. Combined with the ground effect, this enhances the lift coefficient, helping the hull quickly rise above the water and complete takeoff. Furthermore, the invention employs a multi-layered, multi-wing layout structure, which, during operation, can generate a high lift coefficient through a power superposition effect, producing an excellent thrust-to-weight ratio and ensuring stable flight of the spacecraft.

The application discloses a delta wing water-air cross-medium amphibious robot, and relates to the technical field of robots, which comprises a fuselage, a water power device, an underwater power device and a lifting device, the fuselage comprises a delta wing and a tail wing, the water power device, the underwater power device and the lifting device are all connected to the delta wing, the delta wing is triangular and has a front tip, the tail wing is connected to a rear side of the delta wing opposite to the front tip, the water power device is used for providing water surface navigation power for the delta wing water-air cross-medium amphibious robot, the underwater power device is used for providing underwater navigation power for the delta wing water-air cross-medium amphibious robot, and the lifting device is used for providing lifting power for the delta wing water-air cross-medium amphibious robot. The fuselage can be thinner, the displacement weight is reduced, the stability of underwater navigation is improved, the delta wing can increase the lift during flight, the cross-medium margin factor is improved, and the working efficiency during cross-medium is improved.

A firefighting float plane (10) having a fuselage (112), one or more wings (110), two floats (114, 116), a water scoop (120, 122) associated with each float for filling a water tank (300) of the firefighting float plane, and systems and / or methods for deploying the water scoops to prevent (and / or mitigate the effects of) asymmetric deployment and / or retraction of the water scoops.

The present Invention of Air Cycling Helicopter is a double cycling system with independent speeds. The mechanism is designed for locking in and out should one cyclist prefer to take a rest. The system comprises fuselage double mono wheel bikes, motion transmission mechanism, twin arm gearbox, vertical shaft, rotors and skis. The mono wheel bikes and the motion transmission system, which is developed into three stages, primary, secondary and advanced stage, transmit more than 1,800 rpm to the rotors. The present invention of Air Cycling Helicopter is environmental friendly and revolutionary in helicopter manual flying. The principal use of the present invention is for leisure flying and Air sporting.

This invention relates to the field of unmanned rescue equipment technology, and discloses a fully electric amphibious unmanned rescue boat with an adaptive stabilization structure, including a manta ray hull, a composite keel assembly, a dual-mode vector power assembly, an ejection handrail assembly, a towing assembly, a dual-light spherical gimbal, and a main control module. The manta ray hull, in conjunction with hydrodynamic stabilizing fins, reduces drag; the composite keel assembly bears the lift load generated by the dual-mode vector power assembly; the main control module receives image data collected by the dual-light spherical gimbal and performs visual recognition, activating micro-electromagnetic pins to release the handrails, and controlling the ejection of lifebuoys and high-strength towing ropes from high-pressure cold air micro-cylinders; the waterproof shell on the outside of the ship's data black box module and the internal resin potting layer prevent moisture from entering the interior and disperse mechanical vibration energy, ensuring the safe recording of core operational data.

This utility model relates to the field of aircraft water load flight test technology, specifically to a large amphibious aircraft with a multi-point fiber optic sensing system for water load and its application. The system consists of several fiber optic sensors, with several fiber optic sensor arrays distributed on the aircraft's belly. Each sensor is connected to the aircraft's access port via a separate fiber optic pigtail, and then connected to armored fiber optic cables via fiber optic flanges and internal data acquisition equipment. This utility model can realize large-scale, multi-point real-time measurement of water load on amphibious aircraft. By utilizing fiber optic sensors and fiber optic signal transmission, it improves the measurement system's resistance to electromagnetic interference, high temperature, impact, high humidity, and high salinity, meeting the requirements of onshore and offshore aircraft testing.

This invention provides a variable-layout biomimetic cross-medium unmanned aerial vehicle and method based on a folding wing, comprising a blended hull, a foldable wing, a Y-shaped tail, and a biomimetic buoyancy system. The foldable wing is installed at the intersection of the forward main structure and the aft main structure of the blended hull. The foldable wing is capable of being folded in half, has an adjustable dihedral angle, and can be rotated. The variable-layout biomimetic cross-medium unmanned aerial vehicle and method based on a folding wing provided by this invention features a wing mechanism design that allows the wing to fold and conform to the fuselage shape in underwater navigation, forming another underwater vehicle shape. This design also maintains the lightweight, flexible, and structurally strong nature of the wing mechanism. This invention enables simultaneous underwater, surface, and air navigation capabilities, and can switch layouts multiple times across water and air media.

An airborne vehicle having a body section; a main wing extending from the body section configured to generate aerodynamic lift, the main wing having one or more main wing control surfaces; and a tail assembly extending from the body section aft of the main wing. The tail assembly having a first tail member and a second tail member substantially parallel to each other. The first tail member having one or more control surfaces and the second tail member having one or more flap surfaces selectively deployable between a retracted position and an extended position. The flap surfaces being configured to increase a surface area and / or camber of the second tail member in the extended position.

The application provides a surface effect and hydrodynamic coupling water surface taking-off and landing aircraft configuration and relates to the technical field of amphibious aircrafts. The application discloses a surface effect and hydrodynamic coupling water surface taking-off and landing aircraft configuration, which relates to the technical field of amphibious aircrafts and comprises a fuselage, a sliding surface for water surface sliding being arranged at the bottom of the fuselage, floats being arranged at the two sides of the wing, and a tail wing being further arranged behind the fuselage. The float is composed of an upper profile body and a lower profile body, the upper profile body and the lower profile body are connected through PET rubber, the drainage depth of the lower profile body is controlled by controlling the lifting movement of the lower profile body, and then the buoyancy and stability of the aircraft body during the water surface taking-off and landing process are adjusted. The application can greatly reduce the windward area and aerodynamic resistance during cruising flight through the deformable design of the float structure, further improves the lateral stability in the static state and the taking-off state, and the increased float buoyancy is beneficial to promoting the drag reduction under the fuselage and the wing, so that the aircraft is more easily separated from the water surface.