Patents
Literature
128results about "Seaplanes" patented technology
Efficacy Topic
Property
Owner
Technical Advancement
Application Domain
Technology Topic
Technology Field Word
Patent Country/Region
Patent Type
Patent Status
Application Year
Inventor
aircraft
The present invention relates to a vertical take-off and landing (VTOL) aircraft featuring a central fuselage and at least two power units. Each power unit is connected to at least two separate lifting rotors via transmission lines, ensuring that each power unit is linked to at least two rotors diametrically opposed relative to the centre of gravity of the aircraft. The lifting rotors might be driven by power transmission lines of hydrostatic type. The power units on either side might be housed in separate pods which might be incorporated into the main fuselage or arranged as separate pods. These separate pods might also function as floats / pontoons for the aircraft to land, take-off and manoeuvre on water.
Owner:SEAHORSE AIR LTD +1
Amphibious aircraft fly-by-wire flight control system and working method
PendingCN121404495AWith power amplificationActuated personallyFlight control modesControl electronics
The invention belongs to the technical field of amphibious aircraft flight control, and discloses an amphibious aircraft fly-by-wire flight control system and a working method, a cockpit control device is connected with and controls a normal instruction sensor and a backup instruction sensor, the normal instruction sensor transmits a signal to an actuator control electron, and the backup instruction sensor transmits a signal to the actuator control electron; the actuator control electronics and the flight control computer transmit signals mutually, the actuator control electronics and the actuator control module transmit signals mutually, and the actuator control electronics further receive signals of the external signal sensor, the direct angular rate sensor, the flap position sensor and the flight control mode switch; the backup command sensor transmits the signal to the backup flight control computer, and the backup flight control computer transmits the signal to the actuator control module; the actuator control module is connected with and controls the actuator, and the angular displacement sensor is arranged on the actuator and transmits collected signals to the actuator control module. The problem that a current fly-by-wire flight control system is not matched with amphibious aircraft cross-medium application is solved.
Owner:AVIC GENERAL HUANAN AIRCRAFT IND CO LTD
4-pylon evtol wig
An aerial and preferably marine vehicle intended to operate in its principal mode near the surface of water or land employing the Wing-in-Ground Effect (WIG) and capable to take-off and land vertically (VTOL) by means of thrust vectoring, which vehicle has a wing arranged at the lowermost part of the fuselage, propulsion units comprising four rotatable pylons extending transversely in pairs on both sides of the upper part of the fuselage, four elongated nacelles mounted on the outer tips of said pylons, which nacelles contain electric motors (E) and provided with propellers at their extremities, so that the rotation of the pylons results in turning the nacelles and thrust of propellers from substantially vertical, ensuring take-off and landing, to substantially horizontal providing a flight mode, retractable hydroskis for emergency landing on water, while said propulsion units and said wing are spaced apart vertically and horizontally and do not overlap.
Owner:ORLOV SERGEY A
Tailstock type overwater vertical take-off and landing fixed-wing unmanned aerial vehicle
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a tailstock type overwater vertical take-off and landing fixed-wing unmanned aerial vehicle which can float and park on the water surface, can vertically take off to leave the water and is switched into a fixed-wing mode for cruising and level flight. The unmanned aerial vehicle comprises a four-rotor support buoy and a wing body fusion body fixed to the upper portion of the four-rotor support buoy, small wing type buoys are arranged on wing tips of the two sides of the wing body fusion body respectively, and lifting ailerons capable of deflecting up and down are arranged on the rear edges of wings on the two sides of the wing body fusion body respectively. And four motor rotor propeller propelling devices are uniformly arranged at the tip part of the four-rotor bracket buoy.
Owner:CHINA SPECIAL TYPE FLIER RES INST
Providing Feedback on a Mode Transition of a Craft
A craft is provided with a lever that can control the power / speed of the craft and semi-automatically transition the craft in various modes of operation. This makes control of the craft somewhat similar to control of a boat, thereby bringing a maritime flight control experience to a wing-in-ground effect vehicles, hydrofoiling vessels, seagliders, and seaplanes. Further, various audio, visual, and / or haptic devices in the cockpit can provide alerts / feedback to the operator on the use of the lever and mode transitions.
Owner:REGENT CRAFT INC
Fixed wing type cross-domain aircraft capable of self-adaptive load replacement
The invention discloses a fixed wing type cross-domain aircraft capable of realizing self-adaptive load replacement, belongs to the technical field of cross-domain aircrafts, and is used for a water-air double-domain operation cross-domain aircraft. Comprising an aircraft body, a main wing, an aileron, a tail assembly, a vertical take-off and landing support, a vertical take-off and landing rotor wing, a fixed wing propeller, an underwater propeller, a load replacement device and a control module. The control module comprises a decision making system, a telemetering communication system, a state sensing system, an underwater water surface load replacement system, a water surface four-rotor vertical take-off and landing control system, an air fixed-wing cruise control system and an underwater vehicle control system. According to the fixed wing type cross-domain aircraft, through collaborative innovation of a multi-mode power system and self-adaptive buoyancy control, the dynamic characteristic adaptation problem in cross-domain navigation is solved, and the fixed wing type cross-domain aircraft has the vertical take-off and landing capacity, the air cruising capacity and the underwater maneuvering capacity.
Owner:QINGDAO INNOVATION & DEV CENT OF HARBIN ENG UNIV +1
Large seaplane integrated with distributed electric propulsion technology and propulsion method
PendingCN120902954APower plant arrangements/mountingAircraft stabilisationAttitude control systemWave disturbance
The invention discloses a large seaplane integrated with a distributed electric propulsion technology and a propulsion method, and relates to the technical field of seaplane. Comprising a fuselage, a left wing and a right wing are arranged on the two sides of the fuselage respectively, and a V-shaped hull is arranged at the lower end of the fuselage; and a T-shaped empennage is arranged at the tail part of the fuselage. Through the synergistic effect of the design of the V-shaped ship body and the distributed propulsion system, the whole ship body makes contact with the water surface to provide sufficient buoyancy at the low speed, only the main sliding face makes contact with the ship body to form an air layer at the high speed, and the air film drag reduction effect of a propeller at the bottom of the ship body is matched, so that the water resistance is reduced by 35%-50%, and the draft is reduced by 40%-60% along with speed increase; the problems that a traditional seaplane is large in water resistance and difficult to leave water are effectively solved, meanwhile, the left buoy and the right buoy are in linkage with the attitude control system, wave disturbance can be counteracted in real time, the transverse inclination angle is controlled within 1 degree, the wave resistance is improved to be capable of coping with waves with the height of 1.5 m, and the defects that a traditional seaplane is poor in wave resistance and has strict requirements for taking-off and landing water areas are overcome.
Owner:NANCHANG HANGKONG UNIVERSITY
Control method, device and equipment for water-air cross-medium robot
PendingCN121143408AVehicle position/course/altitude controlSeaplanesControl objectiveControl engineering
The invention relates to a method, a device and equipment for controlling a water-air cross-medium robot, and aims to design a special control distribution algorithm aiming at the possible contradiction among a plurality of control targets in the sliding process, such as the possible demand conflict between depth keeping and speed adjusting. A plurality of control targets are decomposed into specific tasks and are distributed to different actuators (such as tail vanes or side wings) for execution, so that effective cooperative control of depth, speed and attitude is realized.
Owner:NAT UNIV OF DEFENSE TECH
Hydrofoil equipped seaglider takeoff
A craft comprises a hull, a wing, a hydrofoil, and a control system. The wing is configured to generate upwards aero lift as air flows past the wing to facilitate wing-borne flight of the craft. The hydrofoil is configured to generate upwards hydrofoil lift during a first mode of operation as water flows past the hydrofoil to facilitate hydrofoil-borne movement of the craft through the water. While the craft is hydrofoil-borne, the control system is configured to determine the upwards aero lift generated by the wing. The control system is further configured to control the hydrofoil to generate downwards hydrofoil lift to counteract the upwards aero lift generated by the wing that maintains the hydrofoil at least partially submerged in the water while the determined upwards aero lift is below a threshold lift.
Owner:REGENT CRAFT INC
Hydrofoil Takeoff and Landing with Multiple Hydrofoils
A craft comprises at least one hull, at least one wing configured to generate upwards acro lift as air flows past the at least one wing to facilitate wing-borne flight of the craft, at least one retractable hydrofoil configured to generate upwards hydrofoil lift during a first mode of operation as water flows past the at least one hydrofoil to facilitate hydrofoil-borne movement of the craft through the water, and a control system that comprises data storage having instruction code stored thereon that causes the control system to during a takeoff operation when the craft is accelerating through the water and is supported by the at least one hydrofoil, control the at least one hydrofoil to generate downwards hydrofoil lift that maintains the at least one hydrofoil submerged at a predetermined hydrofoil depth threshold below the water surface; and when the craft reaches a takeoff condition, cause the least one retractable hydrofoil to release the craft from the water to facilitate wing-borne flight of the craft.
Owner:REGENT CRAFT INC
Winglet control surfaces and methods for use therewith
Various control surfaces are disclosed that can cause a side force along a lateral axis running through a center of mass of a craft when the control surfaces are deployed in a same direction. The side force can be created without creating a yawing moment on the craft. The control surfaces can be on a winglet of the craft. Also disclosed are a split-flap control surface and stand-alone ailerons.
Owner:REGENT CRAFT INC
Seaplane with attachable float frame comprising auxiliary fuel tanks
A seaplane float frame apparatus with extra fuel storage, and a method of installing, comprising: 1) a middle section housing at least one auxiliary fuel storage tank; and 2) two opposing side panels affixed to the middle section, extending outward from about 45-60-degrees from the parallel, each of the two opposing side panels comprising a bottom flat edge fit-able to a float (e.g., carbon composite). The middle section further comprises a fuel pump and a fuel line attached to the auxiliary fuel storage tank(s) and to a main fuel tank within an airplane fuselage-engine. Electrical components enable the pilot, or automatedly as needed, to pump fuel from the frame's tanks. The two opposing side panels comprise triangular shaped cutouts to reduce the float frame's weight and drag, and a built-in steps, a bar, and non-skid coating on the floats to assist in climbing safely into / out of the cockpit.
Owner:CUB CRAFTERS INC
Wing in ground effect (WIGE) vessel
PCT designated stageWO2025260095A1FloatsFuel systems for specific fuelsStructural engineeringMechanical engineering
A waterborne vessel includes a fuselage, at least one forward wing coupled to the fuselage, at least one rearward wing coupled to the fuselage and aft of the at least one forward wing, a first pontoon positioned and coupled to a port side of the fuselage, a second pontoon positioned and coupled to a starboard side of the fuselage, and a tail assembly coupled to the fuselage and aft of the at least one rearward wing. The tail assembly includes at least one rudder. The vessel further includes at least one propulsive element coupled to the fuselage and configured to generate airflow toward the tail assembly.
Owner:SEA CHEETAH CORP
System and method for speed reduction, turning and resistance reduction of amphibious aircraft during water surface sliding
The invention belongs to the technical field of aircraft design, and discloses an amphibious aircraft water surface sliding speed reduction, turning and resistance reduction system and method.The system comprises two water baffles, and the two water baffles are arranged on the two sides of a hull structure below an aircraft waterline respectively and located between an aircraft belly fault step and a tail fault step; when the opening angle is small, the two water baffles form an air cavity at the rear portion through the ventilation effect to form the drag reduction effect, when the opening angle is large, the two water baffles reduce the exciting force caused by vortex falling, and the two water baffles are embedded in a groove of the rear fuselage when being forbidden to conform to the overall shape of the aircraft. The water baffles are innovatively arranged on the two sides of the hull structure of the seaplane, resistance or turning torque or a resistance reduction air cavity can be generated by changing the hydrodynamic shape of the seaplane when the seaplane slides on water, and the sliding process of the seaplane is controlled.
Owner:AVIC GENERAL HUANAN AIRCRAFT IND CO LTD
Triphibian unmanned aerial vehicle
The invention relates to the technical field of unmanned aerial vehicles, in particular to a water-land-air triphibian unmanned aerial vehicle which comprises a water-land-air unmanned aerial vehicle body and further comprises a positioning assembly, unmanned aerial vehicle blades are arranged at the top of the water-land-air unmanned aerial vehicle body, an underwater propeller is arranged on the rear side of the bottom of the water-land-air unmanned aerial vehicle body, and propeller blades are arranged on the back face of the underwater propeller. A working box is fixedly connected to the middle of the bottom of the water-land-air unmanned aerial vehicle body, the positioning assembly comprises first supporting springs, the first supporting springs are fixedly connected to the left side and the right side of the bottom in the working box, and a lifting shell is fixedly connected to the top ends of the first supporting springs. When the body of the water-land-air unmanned aerial vehicle makes contact with the water surface, the elastic arc-shaped plates make contact with the water surface and expand outwards, the contact area between the elastic arc-shaped plates and the water surface is increased, the weight of the body is dispersed, the local pressure is remarkably reduced, the unmanned aerial vehicle is prevented from sinking, the expanded elastic connecting plates form a structure similar to a hydrofoil, transverse stability is provided, and the rollover risk caused by waves is effectively resisted.
Owner:HENAN CHAOZHUN INFORMATION TECHNOLOGY CO LTD
Hull-borne maneuvering of craft with distributed propulsion systems
While hull-home and operating in a heading adjustment mode, the control system of the disclosed craft receives indications of a target craft heading and an observed craft heading. Embodiments include determining that the difference in heading is above a threshold, determining an adjusted wing-affixed control setting for affecting a change in the observed heading of the craft based on at least (a) sensed environmental conditions, (b) the initial wing- affixed control setting, (c) the target craft heading, and (d) the observed craft heading; and operating wing-affixed control element(s) according to the adjusted wing-affixed control setting to change the observed heading of the craft to the target craft heading. After determining that the heading difference is not above the threshold heading difference, the wing-affixed control setting is adjusted to forgo affecting further change in the observed heading of the craft.
Owner:REGENT CRAFT INC
Integrated design of a lightweight fuel transfer system and method for a seaplane
The present application belongs to the field of aircraft fuel system, and relates to a kind of integrated design light weight fuel transfer system and method of seaplane. Including Ⅰ, Ⅱ, Ⅲ, Ⅳ, Ⅴ, Ⅵ oil tank on the wing of the aircraft, pressure refueling connector, pressure refueling control valve, oil level controller, pressure refueling control panel, oil pump, low oil level signal. One oil pump integrates the flow of oil transfer system and the flow of emergency oil discharge system two working states, maximally reduces the number of pump;Pressure refueling pipeline, oil transfer pipeline, emergency oil discharge pipeline are integrated designed, reduce the number of pipeline;Thirdly, the low oil level signal of oil tank and the low oil level signal of oil quantity measuring system are shared designed during oil transfer and emergency oil discharge, the on-off control of oil transfer system and the on-off control of pressure refueling are shared designed, the on and off of oil transfer are controlled by pressure refueling control valve, reduce the setting of oil transfer cut-off valve.
Owner:AVIC GENERAL HUANAN AIRCRAFT IND CO LTD
Intelligent self-adaptive ground effect vehicle, flight control method and device
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.
Owner:YONGKANG ZHANXING AEROSPACE TECHNOLOGY CO LTD
Attitude-adjustable hydrofoil and trans-medium vehicle
PendingCN122211516ASeaplanesHydrodynamic/hydrostatic featuresMarine engineeringStructural engineering
Owner:PEKING UNIV +1
Bionic flapping wing aircraft capable of efficiently converting air and water dual modes
The invention discloses an air-water bimodal efficient conversion bionic flapping-wing air vehicle and a control method thereof, and relates to the technical field of bionic flapping-wing air vehicles, the air-water bimodal efficient conversion bionic flapping-wing air vehicle comprises an air vehicle body, a mounting column is arranged in a storage groove, a fourth servo motor is fixedly connected to the upper surface in the mounting column, and an electric push rod is connected to the upper surface of a first support. Compared with the prior art, the wing folding device has the advantages that an electric push rod is started to pull a clamping block to be separated from a first clamping groove, a first servo motor drives a second support to rotate, a fourth servo motor drives a first support to rotate, wing folding storage is achieved, conversion of the wing form between an underwater streamline form and an air efficient flight form is achieved, and the space requirement for compact storage is met; a second servo motor can be started to drive a rotating disc to rotate, a protective cover rotates along with the rotating disc, an opening in a mounting column is blocked through the protective cover, the underwater streamline wing form is achieved, and the resistance of the device advancing in water can be reduced.
Owner:KUNMING UNIV OF SCI & TECH
A method for longitudinal control of a water take-off and landing of an amphibious aircraft
The present application belongs to the water surface take-off and landing control technology field of water surface aircraft, and particularly relates to a kind of amphibious aircraft water surface take-off and landing longitudinal control method.The present application determines the corresponding elevator deflection angle of the aircraft when sliding at the median pitch angle at different speeds through flight test, and when taking off, the corresponding relationship of the flight test speed, median pitch angle and elevator deflection angle is used to draw the elevator control rate curve of the aircraft during the take-off process respectively, so as to obtain the elevator control rate of the aircraft during the take-off process on the static water surface and wave water surface;when landing, the pilot gradually brings the rod after the aircraft touches the water, so that the elevator deflection angle is in the minimum state of the maximum available deflection angle combination until the aircraft completes the deceleration on the water surface.The present application effectively solves the unstable influence caused by the interference of the wave water surface on the take-off and landing of the amphibious aircraft, and improves the take-off and landing safety.
Owner:CHINA SPECIAL TYPE FLIER RES INST
Air-land-water integrated unmanned aerial vehicle
The utility model discloses an air-land-water integrated unmanned device which comprises a seat body, a flying mechanism arranged on the upper portion of the seat body, a land walking mechanism arranged on the lower portion of the seat body, an underwater driving unit arranged on the rear portion of the seat body, and a storage battery and a control unit arranged in the seat body. The flying mechanism comprises a plurality of arms, a concave area is arranged on the upper portion of a base, a plurality of driving mechanisms are mounted on the base, a first motor is mounted at one end of each arm, a first propeller is fixedly connected to a rotating shaft of each first motor, and the other end of each arm is connected to one driving mechanism. The driving mechanism can drive the vehicle arms to rotate so that the vehicle arms and the first propellers can be located in the sunken areas or the vehicle arms can be unfolded outwards. A water tank, a gas tank, a water pump and a gas pump are arranged on the seat body; a piston is arranged in the middle in the water tank; the water pump communicates with the water tank through a waterway pipeline; the air pump communicates with the air tank and the water tank through an air channel pipeline. And first and second electromagnetic gate valves are respectively arranged on the waterway pipeline and the gas pipeline. The utility model has the advantages of compact structure, stable operation under various working conditions, and wide application range.
Owner:FENGRUN (ZHANGZHOU) INTELLIGENT TECHNOLOGY CO LTD
Multimode water-air cross-medium aircraft based on biomimetic airfoil
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.
Owner:NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
Cross-medium variable tilt rotor aircraft and control method thereof
The invention discloses a cross-medium variable tilt rotor aircraft and a control method thereof, and relates to the technical field of cross-medium aircrafts. Comprising a fuselage, front rotor units, a tail tilting rotor assembly, main wing units and wing unfolding and folding mechanisms, wherein the front rotor units are arranged on high-position mounting platforms on the two sides of the fuselage and are in bilateral symmetry; the tail tilting rotor assembly is arranged at the tail end of the fuselage and can rotate around a transverse tilting shaft; the main wing units are in bilateral symmetry and can be folded; the buoyancy adjusting unit and the control system are arranged in the fuselage. Through collaborative design of fuselage bionic integration, the composite rotors, the variable main wings, active buoyancy adjustment and closed-loop control, the traditional single propulsion bottleneck is broken through, cross-medium adaptation, consideration of take-off and landing and cruising efficiency and smooth transition are achieved, multi-scene adaptation is achieved, and breakthrough support is provided for engineering application.
Owner:SOUTHWEAT UNIV OF SCI & TECH
Air cycling aircraft
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.
Owner:LEBANON THADDAEUS
Wing-in-ground effect vehicle
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.
Owner:REGENT CRAFT INC
Estimation method of longitudinal coefficients of ground effect vehicles and its aerodynamic characteristics analysis system
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.
Owner:CHINA SHIP SCIENTIFIC RESEARCH CENTER
Water take-off and landing solar aircraft with wave power generation function
The invention provides a water take-off and landing solar aircraft with wave power generation, which comprises wings, solar panels laid on the upper surfaces of the wings, and storage batteries arranged in the wings; a fuselage forming a cabin for carrying a driver and passengers; the buoy is used for assisting the airplane to take off and land on the water surface; the propeller power motors are installed below the wings and used for pushing blades of the propeller power motors to supply power to the storage battery through wind power when the airplane stops on the water surface; the flexible wave power generation devices are symmetrically distributed below the outer sides of the wings, and when the aircraft floats on the water surface, the flexible wave power generation devices are in a spread state and charge a storage battery in the aircraft with waves as power; when the airplane is ready to take off and land or fly, the airplane is rolled up and rotated to be recycled by the motor; the empennage is used for controlling pitching and yawing of the aircraft; and the foldable solar power generation device is arranged between the two buoys on the rear sides of the wings, and when the airplane floats on the water, the airplane is in a spread state and performs photovoltaic power generation through solar energy.
Owner:XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA