116results about "Floats" patented technology

The invention belongs to the technical field of map photogrammetry, and discloses an unmanned aerial vehicle-based map photogrammetry device, which comprises a high-integration-level measurement camera, a floating mechanism arranged outside the measurement camera and a connecting frame arranged below the floating mechanism and used for being hung on the bottom surface of an unmanned aerial vehicle, the floating mechanism comprises a mounting cylinder vertically arranged outside the measuring camera, a group of mounting grooves formed in the outer surface of the mounting cylinder at equal intervals in the circumferential direction, and a floating shell hinged to the upper parts of inner cavities of the mounting grooves. Through cooperative design of the measuring camera and the floating mechanism, salvage and recovery of the measuring camera by an operator are realized, the recovery difficulty is reduced, the salvage efficiency of the measuring camera is improved, the time consumption is low, the cost is low, and the problems that the measuring camera and the unmanned aerial vehicle are heavy in weight and easy to sink into water are avoided. And an operator needs to dive into water to salvage and recover the fish, so that the recovery difficulty is high, the consumed time is long and the cost is high.

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 present invention comprises a system which includes a novel quick release thruster mount system using one or more removable elements allowing the thrusters to be removed quickly. The present invention also comprises a novel “float compartment centric” design where no wiring to the cockpit is necessary. Redundant power units are self-contained and protected. The novel design incorporates thrust force over the surface of the water rudders improving directional control. The rudder anti lift device ALPB allows the rudders to remain in the water while reverse or braking thrust is applied. Control and monitoring are done wirelessly from the safety of the cockpit reducing hazard while maneuvering to avoid prop strike hazards to pilot, persons or objects. The system offers the ability to maintain positive directional control while taxing downwind resisting the inherent weathervane forces, braking, and turning maneuvers unachievable with current methods. The system differs from any prior art due to the aft location of drive components, method for deployment, and the fact that the drive system does not mount directly to the float itself but rather the water rudders. These forces are marginal in comparison to what is needed when one takes into consideration the Moment and Arm location of the force and the smaller lightweight thrusters do more work with less effort.

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.

The utility model relates to the technical field of unmanned aerial vehicles, and discloses an overwater landing gear with an anti-skid structure for an unmanned aerial vehicle, which comprises a base, a supporting mechanism is arranged on the base, a first supporting column is fixedly mounted on one side of the outer wall of the base, and an inner supporting column is slidably connected in the first supporting column; the device comprises a base, a first supporting column is installed on one side of the base, an inner supporting column is slidably connected in the first supporting column, air bag feet are fixedly installed at the bottom of the inner supporting column, a threaded opening is formed in the base, a connecting column is in threaded connection with the lower portion of the threaded opening, and a supporting air bag is fixedly installed at the bottom of the connecting column. And in addition, the supporting air bag is in threaded connection with the lower portion of the base, and the stability of the whole unmanned aerial vehicle landing on the water surface is enhanced.

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.

The invention provides a float plane having a fuselage, a wing, and two floats mounted to the fuselage. In one group of embodiments, the float plane is a firefighting float plane that includes a water tank and a water scooping assembly. In another group of embodiments, the float plane includes a spreader bar suspension assembly. In certain embodiments, the float plane is a firefighting float plane that includes a water tank, a water scooping assembly, and a spreader bar suspension assembly.

(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 invention discloses a fire extinguishing helicopter adapting to complex water bodies and airspaces and a low-risk water taking method, and relates to the technical field of aviation fire fighting, the technical core is an overwater air bag floating-assisting water taking technology, and stable buoyancy is provided for the helicopter on the water surface and shaking is reduced by means of an air bag capable of being rapidly inflated / deflated at the bottom of a helicopter body; according to the rotor low-rotating-speed floating-assisting water taking technology, the rotor generates auxiliary buoyancy at the low rotating speed and cooperates with the air bag to further stabilize the posture of the helicopter on the water surface; a conformal water tank water storage and flight safety technology is adopted, and a water tank attached to a fuselage structure is used for carrying water, so that the negative influence on flight stability is eliminated, and the operation safety is improved. All the systems work cooperatively and are matched with a posture monitoring and control system, safety and high efficiency of the helicopter in the whole water taking, water carrying flight and fire extinguishing operation process are guaranteed, the operation reliability and fire extinguishing efficiency of the fire extinguishing helicopter in complex water and airspace environments are greatly improved, powerful technical support is provided for helicopter fire extinguishing application, and the application prospect is wide.

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 discloses an airbag device capable of both buffering and load reduction, as well as stable floating. The airbag device comprises a buffered object, an airbag assembly, and an inflatable assembly. The airbag assembly is arranged on the bottom surface of the buffered object, and the inflatable assembly is disposed on the buffered object and connected to the airbag assembly. The present invention combines the dual functions of landing buffering and floating on water. When on water, it can automatically switch from a buffering and load reduction state to a stable floating state. It has stronger environmental adaptability and can be widely used in drone recovery, heavy equipment airdrops, and landing and recovery of aerospace vehicles, greatly expanding the environmental adaptability of the buffering and load reduction airbag.

The invention provides a ground-effect conveyor adopting tilting wings, which belongs to the technical field of transportation equipment, and adopts a front-back tandem type double-wing aerodynamic layout, and the rear wings can integrally tilt, so that the distance between the rear edges of the rear wings and the water surface is adjusted, and finally the ground effect and the lift force adjustment are realized. Meanwhile, a hybrid power system, a retractable and foldable floating device and a distributed propelling system based on an embedded ducted fan are adopted, and high-speed maneuvering flight and rapid loading and releasing of equipment can be achieved on the basis of large load.

To provide a recovery device of an unmanned air vehicle which can recover the unmanned air vehicle even when the unmanned air vehicle becomes unable to fly.SOLUTION: A recovery device of an unmanned air vehicle of the invention includes: a wire which may be connected to an unmanned air vehicle; a wire take-up part; a connection part which connects the wire to the unmanned air vehicle; and a start part which starts a falling relaxation mechanism included in the unmanned air vehicle. The start part starts the falling relaxation mechanism when an abnormality occurs in flying of the unmanned air vehicle.SELECTED DRAWING: Figure 3

The present invention discloses a scanning device for preventing pixel offset for an aerial survey drone, specifically relating to the field of aerial survey technology. The device comprises a drone body, a camera, and a scanning module. Horizontal balance plates are provided on both sides of the drone body. A fixing plate is provided at the bottom end of the drone body. A longitudinal balance plate is provided at the bottom end of the fixing plate. The horizontal balance plate includes a storage tube, a central tube is provided inside the storage tube, a micro motor is fixedly provided at the front side of the storage tube, and a connecting groove is provided at the outer end of the storage tube. The present invention installs horizontal and longitudinal balance plates on the drone body, and adjusts the angle of the longitudinal balance plate according to the wind direction when wind blows, thereby reducing the force-bearing area of the horizontal and longitudinal balance plates in the wind. The wind force can also be used to hinder the swing of the horizontal and longitudinal balance plates, indirectly making the drone body more stable.

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.