83results about "Floats" patented technology

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.

The invention relates to a water surface floating type flying water pump system for large-flow long-time operation, and belongs to the technical field of special operation unmanned aerial vehicles and fluid conveying. The system integrates a multi-rotor flying platform, a buoyancy stabilizing device, a large-flow water pump module, a high-strength flexible water conveying pipeline and an intelligent control system. The core of the system is that the system can land on an open water surface, stable floating is achieved through the buoyancy stabilizing device, and a water inlet of the water pump module is submerged into water to directly pump water. By means of the floating water taking mode, the flying platform does not need to hover during operation, energy consumption is greatly reduced, ultra-long operation time is achieved, the limitation of the liquid carrying amount of the unmanned aerial vehicle is broken through, and continuous high-flow water pumping can be conducted through a high-power water pump. The system supports independent operation of a single device or networking collaborative operation of multiple devices, dynamically distributes water supply tasks, can be used as an aerial extension arm of a ground fire fighting truck, and is mainly applied to emergency rescue scenes such as high-rise building fire fighting and forest fire fighting.

The utility model relates to the technical field of unmanned aerial vehicles, in particular to an amphibious rescue unmanned aerial vehicle which comprises a water dwelling assembly and an air dwelling assembly. The amphibious rescue unmanned aerial vehicle comprises an amphibious rescue unmanned aerial vehicle body and an air-dwelling assembly, the amphibious rescue unmanned aerial vehicle body comprises a first storage shell, a second storage shell and an inflatable air cushion connected with the first storage shell and the second storage shell, the amphibious rescue unmanned aerial vehicle body is inflated to unfold the inflatable air cushion to form an amphibious form after making contact with the water surface, and the air-dwelling assembly comprises a first wing connected to the first storage shell. The first wing is connected to the first storage shell, the second wing is connected to the second storage shell, propeller assemblies are arranged at the two ends of the first wing and the two ends of the second wing, and the first wing and the second wing are switched to be of a cross structure to form an air-dwelling form. According to the amphibious rescue unmanned aerial vehicle disclosed by the utility model, the unmanned aerial vehicle shares a set of wing and propeller assemblies with changeable forms in an air-dwelling form and a water-dwelling form, so that the amphibious rescue unmanned aerial vehicle can play the maximum effect when flying and sailing in water, the purpose of rapid rescue is achieved, the rescue manpower is effectively saved, and the water rescue time is shortened.

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.

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.

The application discloses a low-altitude unmanned aerial vehicle with a protection function, and relates to the field of unmanned aerial vehicles.The unmanned aerial vehicle comprises a main body, paddle blades connected to the ends of four supporting arms of the main body, a chassis fixedly connected to the bottom of the main body, a shell fixedly connected to the bottom of the main body and inside the chassis, a camera main body fixedly connected to the inside of the shell, four bidirectional elastic connection structures eccentrically arranged between the shell and the inner side of the chassis, horizontal rotating blocks and vertical rotating blocks, horizontal link blocks elastically connected to the inner side of the chassis, and vertical link blocks elastically connected to the outer surface of the shell.The bidirectional elastic connection structures can make the related components adaptively rotate along the impact direction, efficiently convert the concentrated impact force from different directions into the rotary motion of the mechanism around the rotating supporting point, and realize the direction guidance and dispersion of the impact force.

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.

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.

The invention discloses an unmanned aerial vehicle surveying and mapping device for a mine goaf, and relates to the technical field of unmanned aerial vehicle surveying and mapping, the unmanned aerial vehicle surveying and mapping device comprises an unmanned aerial vehicle supporting base, fixing frames are symmetrically mounted at the bottom of the unmanned aerial vehicle supporting base, buffer airbags and camera modules are arranged below the fixing frames, and the buffer airbags are symmetrically arranged on the two sides of the buffer airbags; the unmanned aerial vehicle surveying and mapping device for the mine goaf further comprises a multi-scene dynamic adjusting mechanism and a multi-angle adjusting mechanism. The multi-angle adjusting mechanism is linked with a third servo motor through a second servo motor, a V-shaped oblique angle swing block and a driving rod, so that multi-degree-of-freedom accurate adjustment of the camera module is realized. And in cooperation with stable supporting of the damping ring and the U-shaped frame, the shaking phenomenon in the shooting process is remarkably restrained, and it is guaranteed that images are clear and stable. The mechanism is further integrated with a damping air bag and a double-damping-seat structure, the influence of flight vibration on the camera module is further isolated, and it is ensured that high-quality image data can still be obtained in a high-dynamic environment.

The invention relates to a buoyancy system, intended to be connected to a structure of an aircraft comprising roll stabilization means comprising at least one floating mat, intended to be deployed on a water surface to reduce a rolling motion of the aircraft.

This utility model discloses a surface water sampling device based on a drone, relating to the field of surface water sampling technology. It includes two portal frames, with a crossbeam between the lower ends of the two portal frames. A connecting seat is provided between the lower ends of the two portal frames and the crossbeam, and the portal frames are fixedly connected to the crossbeam via the connecting seat. Protective sleeves are provided at both ends of the crossbeam and on the outside of the portal frames. Floating blocks are provided on the two portal frames and above the connecting seat. Mounting plates are provided between the upper sides of the two portal frames, with both ends of the mounting plates engaging with the portal frames. A mounting groove is provided in the middle of the two mounting plates. The drone floats on the water surface via the floating blocks, avoiding the instability of the drone hovering on the water surface, resulting in higher accuracy of water stratification sampling and reducing the risk of the drone falling into the water.

This invention relates to the field of unmanned aerial vehicle (UAV) technology, and more particularly to a UAV for inspecting enclosed space facilities. The technical problem of this invention is to provide a UAV capable of protecting itself during the inspection of enclosed space facilities. The technical solution is as follows: A UAV for inspecting enclosed space facilities includes a UAV body, a support frame, a protective frame, a camera, an emergency stop switch, an air pump, etc.; the support frame is located at the bottom of the UAV body, and protective frames are symmetrically located on both sides of the UAV body, front and back, to protect the UAV's fan blades and prevent them from colliding with the inner wall of the pipe. A camera is located at the top of the UAV body, and an emergency stop switch is located on the upper right side of the support frame. This invention uses an air pump to inflate an airbag, allowing the airbag to expand and enabling the UAV body to float on the water surface when it falls into the water.

(DE) The present invention relates to a transport drone with a main body having a wing at its upper part and a transport compartment at its lower part, through which a transport object, for example a car, can be inserted and removed forwards and backwards; and a buoyancy element with several tubes connected to the lower part of the main body and which are inflatable and deflatable by means of air pressure. In this configuration, the tubes, which expand and contract by means of air pressure, are connected along the lower perimeter of the main body. By means of the sequential expansion and contraction of the tubes, the drone can not only land on the water surface by means of the buoyancy force, but also, if it tips over on the water surface, hover above the water surface by means of the sequential expansion and contraction of the tubes, thus preventing it from falling into the water.

The invention relates to the technical field of unmanned aerial vehicle safety protection, provides an emergency floating device for an underground mine unmanned aerial vehicle and the underground mine unmanned aerial vehicle, and discloses the emergency floating device for the underground mine unmanned aerial vehicle. The inner sleeve is vertically arranged, sliding threads are arranged on the outer side face of the inner sleeve, the inner sleeve is coaxially and fixedly installed on an output shaft of the driving mechanism, the inner sleeve is coaxially sleeved with the outer sleeve, the outer sleeve is fixedly installed on a shell of the driving mechanism, the inner side face of the sliding assembly is matched with the sliding threads, and the outer side face of the sliding assembly is attached to the inner side face of the outer sleeve. The floating plates coaxially surround the inner sleeve, one end of each connecting rod is hinged to the corresponding sliding assembly, and the other end of each connecting rod is hinged to the corresponding plate assembly hinge piece in the corresponding floating plate. The underground mine unmanned aerial vehicle can float on the muddy water surface, and the conditions that a circuit is short-circuited, a sensor loses efficacy, a motor and a propeller are damaged, and equipment is completely scrapped are avoided.

This invention discloses an amphibious variable aircraft based on a float and propulsion system, relating to the field of aircraft technology. It includes a main fuselage and wings connected to both sides of the main fuselage. A power nacelle is located in the middle section of the wings, and a float mechanism is located at the end of the wings away from the main fuselage. The float mechanism includes floats, a tilting component on the outside of the floats, and a water intake / discharge component inside the floats. A tail fin is located at the tail of the main fuselage, and a horizontal stabilizing plate is mounted on the tail fin. This invention employs the aforementioned amphibious variable aircraft based on a float and propulsion system, using a tilting float design. The float mechanism's shape is identical to the aircraft's airfoil, reducing ineffective weight while ensuring the aircraft can quickly complete water intake / discharge operations, and its simple structure facilitates maintenance.

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.

The invention relates to the technical field of ground effect aircrafts, in particular to a tilt rotor type vertical take-off and landing ground effect aircraft. Comprising a fuselage, gull-shaped wings are symmetrically arranged on the two sides of the fuselage, empennages are arranged on the rear portion of the fuselage, winglets are arranged at the side ends, away from the fuselage, of the gull-shaped wings, and buoys are arranged below the joints of the gull-shaped wings and the winglets; the multi-rotor synchronous tilting mechanism penetrates through the gull-shaped wings and the interior of the fuselage. By arranging the tilting rotors and the gull-shaped wings with the small aspect ratio, more stable airflow distribution can be formed in the flight process, the flight response is good under various meteorological conditions on the sea, and during low-speed flight, the design of the gull-shaped wings can effectively reduce the induced resistance of the wings and increase the lift force, so that the stability and maneuverability of the aircraft are improved.

The present invention relates to a drone for transportation, comprising: a main body having a wing part formed at the upper part thereof and a transportation space formed at the lower part thereof in a penetrating manner such that a vehicle-like object to be transported can enter and exit in the front-rear direction; and a buoyancy part coupled to the lower end of the main body, the buoyancy part having a plurality of tube bodies coupled thereto, the tube bodies being expanded and contracted by air pressure. According to the structure, in addition, expansion and contraction pipe bodies driven by air pressure are combined on the periphery of the lower portion of the main body, the pipe bodies conduct expansion and contraction movement in sequence, the ship can stably float on the water surface by means of buoyancy, when the ship overturns, the pipe bodies can expand and contract in sequence, and therefore the ship automatically floats upwards and breaks away from the water surface, and the water immersion accident is effectively avoided.

The present invention relates to an air-land-water flight vehicle. Within a main frame, the front and rear ends of an upper frame are provided with propeller compartments for placement of folding propeller assemblies, a parachute compartment being provided between the folding propeller compartments; the front section of a lower frame is provided with a control cabin for piloting and loading of passengers and cargo, two sides of the middle rear section of the lower frame are provided with wing compartments for placement of retractable folding wing assemblies, two rear sides of the rear section of the lower frame are respectively provided with storage compartments, an integrated compartment being provided between the storage compartments, and a balloon compartment for placement of a balloon deployment and retraction system is provided below the middle of the lower frame; the folding propeller assemblies are mounted on the main frame, the retractable folding wing assemblies are symmetrically mounted on two sides at the rear of the main frame by means of connecting structures, and traveling wheels are provided below the main frame. The air-land-water fight vehicle has a compact structure, can travel and park on land and water and can perform vertical take-off and landing on land and water, and can change the form in mid-air; the flight vehicle is an electric flight vehicle that maintains long endurance with a certain payload, and ensures safe flight.

The present invention relates to an autonomous multifunctional inspection and rescue quadcopter drone system. The proposed drone system features an adaptive design for operation in multiple environments, wherein the system employs robust carob fiber frame, with a top protective cage, a bottom floats for water landing and floating capability, and advanced sensor suits, and artificial intelligence capabilities, wherein the advance sensor suits include LiDAR, thermal camera, and RGB camera, and wherein the AI capabilities allow the drone to performing autonomous navigation, and fault detection, which significantly enhance efficiency and safety in inspection and rescue operations. The proposed drone system has reduced operational costs and complexity, enhanced safety and reliability during inspections, and faster and more effective emergency response capabilities.

The invention relates to the technical field of unmanned aerial vehicles, and discloses an offshore application unmanned aerial vehicle adopting a multi-rotor structure, which comprises a shell, connecting frames are symmetrically and slidably connected to the lower end of the shell front and back, and rotors driven by servo motors are fixedly connected to the left and right ends of the two connecting frames through short shafts; the short shaft is sleeved with a floating block which enables the unmanned aerial vehicle to float horizontally when the unmanned aerial vehicle falls into water. And a driving unit for driving the two connecting frames to synchronously slide left and right in a reciprocating manner when falling into water so as to change the overall gravity center of the unmanned aerial vehicle is connected in the shell. The marine application unmanned aerial vehicle adopting the multi-rotor structure can effectively solve the problems that in the prior art, in the overturning and resetting process after a multi-rotor unmanned aerial vehicle falls into water, the multi-rotor unmanned aerial vehicle only depends on the differential speed of rotors on the two sides to conduct overturning, so that the influence of factors such as sea condition fluctuation and fuselage attitude deviation is large, and the situation that overturning power is insufficient or the attitude is out of control often occurs; and the turning-over failure probability is high.

A seaplane is configured to land and take off in the water and includes a hull or fuselage including a cabin configured for transporting people and / or cargo, a main wing connected to the hull or fuselage in a mid-section thereof, and a tail portion disposed at a rear section of the hull or fuselage, wherein the tail portion includes a first tail element and a second tail element that form a V-tail and further wherein the first tail element and the second tail element carry a first propeller and a second propeller, respectively.

The application relates to an amphibious aircraft float, a stamping die and a manufacturing method. The amphibious aircraft float is in the shape of a hull and is hot-stamped from a thermoplastic composite material composed of a thermoplastic resin and reinforcing fibers. The stamping die comprises an upper die, a lower die, a positioning device and a blank clamping device, the opposite surfaces of the upper die and the lower die are provided with male and female structures which are complementary to each other, the positioning device is fixed on the lower die, and the blank clamping device is used for clamping a blank to be stamped and is positioned by the positioning device so that the blank is positioned and supported directly above the female structure. The manufacturing method comprises the following steps: providing a stamping die, preparing a blank, heating the blank, hot-stamping and edge trimming. The amphibious aircraft float has the advantages of high strength, fatigue resistance, impact resistance and damage tolerance.

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 provides a helicopter emergency floating system, which comprises an emergency floating switch board 10, a floating control box 20, a gas cylinder system 30, an electromechanical management computer 40, a speed / height detector 50, a main total distance rod float inflation switch 60, a secondary total distance rod float inflation switch 70 and a water immersion sensor 80, wherein the emergency floating switch board 10, the main total distance rod float inflation switch 60 and the secondary total distance rod float inflation switch 70 are connected with the floating control box 20; the floating control box 20 is connected with the gas cylinder system 30, the electromechanical management computer 40, the speed / height detector 50 and the water immersion sensor 80 respectively; the electromechanical management computer 40 is connected with an emergency lifesaving positioning system 401, a key position self-destruction system 402, a rotor brake system 403, an engine 404, a weapon control board 405 and an engine fire extinguishing system 406 respectively; and the weapon control board 405 is connected with a weapon hanging rack 4051 and an inert explosive system 4052.

The invention relates to the technical field of unmanned aerial vehicle auxiliary equipment, in particular to a device for automatically floating an unmanned aerial vehicle after falling into water. The device comprises a light shell, a water-soluble fixing material, a reaction bag and an air bag, the reaction bag is arranged in the light shell and directly or indirectly communicated with the air bag, and the light shell is sealed and fixed through the water-soluble fixing material and can be fixed to the top of the unmanned aerial vehicle through a gum layer. When the whole unmanned aerial vehicle falls into water, the water-soluble adhesive tape is dissolved, the light shell is automatically opened, a water body and reactants in the reaction bag are subjected to chemical reaction, gas is released, the air bag is rapidly inflated, and therefore the unmanned aerial vehicle is driven to float. The structure is simple in design and clear in reaction starting condition, external energy supply is not needed, the unmanned aerial vehicle can rapidly float after falling into water through an electronic sensor and a mechanical structure, and the safety and recovery efficiency of the unmanned aerial vehicle are remarkably improved.

The application discloses an amphibious unmanned aerial vehicle landing gear structure and relates to the technical field of unmanned aerial vehicle landing gears.The amphibious unmanned aerial vehicle landing gear structure comprises a ring-shaped frame installed on the main body of the unmanned aerial vehicle, connecting rods fixed on the two sides of the ring-shaped frame, mounting seats fixed at the bottom ends of the connecting rods, hollow bottom frames installed on the mounting seats, and the two hollow bottom frames are symmetric about the center of the ring-shaped frame.The application is provided with an arc-shaped extension piece, a propeller assembly and other structures, can control the arc-shaped rack movement according to the requirement, and further control the arc-shaped extension piece to extend from the end of the hollow bottom frame.Because the end of the hollow bottom frame is an arc-shaped structure of a quarter of a circle, the shape of the arc-shaped extension piece is adapted to the arc-shaped extension piece.When the arc-shaped extension piece extends, the end of the hollow bottom frame cooperates with the arc-shaped extension piece to form a C-shaped structure.At this time, the four propeller assemblies are in the working position, and the unmanned aerial vehicle can run on the water surface based on the control of the four propeller assemblies.

The invention relates to an emergency flotation system for aircraft (1), in particular one that can be attached to the landing gear or fuselage of a helicopter, comprising at least two inflatable floats (2, 2a, 2b), each extending in a longitudinal direction and spaced apart in a horizontal direction transversely, in particular perpendicularly to the longitudinal direction, wherein the respective floats (2, 2a, 2b) have a polygonal cross-sectional shape between their ends when inflated, perpendicular to their longitudinal direction. The invention also relates to an aircraft, in particular a helicopter, which has an emergency flotation system according to one of the preceding claims on its landing gear or fuselage, in particular wherein the longitudinal direction of the floats (2, 2a, 2b) is aligned parallel to the longitudinal axis or transversely, in particular perpendicularly to the longitudinal axis of the aircraft (1).

The invention relates to the technical field of unmanned aerial vehicles, in particular to a reconnaissance unmanned aerial vehicle capable of flexibly residing, which comprises a fuselage main body, a reconnaissance camera is arranged on the side surface of the fuselage main body, and two groups of foldable undercarriages are arranged on the fuselage main body. Each foldable undercarriage comprises two fixed supporting pipes which are arranged in parallel and a supporting frame which is horizontally arranged, and the upper ends of the fixed supporting pipes are hinged to the fuselage main body; during flight, the pneumatic swing mechanism drives the fixed supporting pipe to be attached to the fuselage main body, the telescopic arm retracts into the fixed supporting pipe, air resistance is reduced, flight efficiency is improved, meanwhile, an exposed structure is prevented from colliding with an obstacle, and equipment safety is guaranteed; and during residence, the fixed supporting pipe automatically expands, the telescopic arm synchronously extends out, the supporting span is expanded, the ground or water surface landing stability is improved, the problems that an existing unmanned aerial vehicle support is tedious in operation and poor in adaptability are solved, automatic folding and telescopic integration of an undercarriage is achieved, and the unmanned aerial vehicle can adapt to flight and residence scenes without manual intervention.