265results about "Floats" patented technology

A craft includes 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.

The invention relates to the technical field of unmanned aerial vehicles, in particular to an emergency slow descent device for an unmanned aerial vehicle. According to the emergency slow descent device for the unmanned aerial vehicle, emergency slow descent can be conducted on the unmanned aerial vehicle under the condition that the unmanned aerial vehicle is powered off, meanwhile, multiple falling protection is conducted on the unmanned aerial vehicle, and damage to the unmanned aerial vehicle is effectively reduced. An emergency slow descent device for an unmanned aerial vehicle comprises a vehicle body, vehicle arms, motors and the like. Four machine arms are evenly arranged on the machine body at intervals, and a motor is arranged on each machine arm. The arc-shaped electromagnet loses magnetism through power failure of the unmanned aerial vehicle, the parachute pops up and is opened, the parachute is opened to reduce the descending speed of the fuselage through air resistance, excessive damage caused by too high descending speed of the unmanned aerial vehicle is avoided, and therefore the unmanned aerial vehicle can be subjected to emergency slow descending when the unmanned aerial vehicle breaks down in the air; potential safety hazards are reduced by reducing the landing speed of the unmanned aerial vehicle.

The invention relates to a drag reduction and deicing structure of an ice surface rescue unmanned aerial vehicle and the ice surface rescue unmanned aerial vehicle, and discloses a deicing structure which is used for cleaning broken ice on an ice surface or a water surface through cooperation of an ice breaking cone and snow removing sawteeth, can reduce the sliding resistance of the unmanned aerial vehicle and improves the ice surface rescue efficiency. The ice breaking machine is characterized by being composed of a machine body, a machine frame, a machine frame head, a machine frame tail, a machine frame middle part, an ice breaking plate, an ice breaking cone, a hanging plate, an air cylinder, a fixing plate and a fixing block, the machine frame comprises the machine frame head, the machine frame tail and the machine frame middle part, the two ends of the machine frame middle part are correspondingly arranged at one end of the machine frame head and one end of the machine frame tail respectively, and the machine frame is arranged on the top face of the machine body. The machine body is of a hollow structure, the length of the machine body is smaller than that of the machine frame, the width of the machine body is smaller than that of the machine frame, fixing plates are correspondingly arranged on the two side faces of the machine body respectively, fixing blocks are correspondingly arranged on the two sides of the bottom face of the tail of the machine frame respectively, and one end of a hanging plate is arranged on the bottom faces of the fixing blocks.

A payload delivery device is an apparatus designed to facilitate the delivery of emergency items to a target location via aerial vehicles. The apparatus includes a base strap, a plurality of holder straps, and a plurality of cargo straps. The base strap serves as the central structure of the apparatus that supports the plurality of holder straps and the plurality of cargo straps. The plurality of holder straps includes several straps designed to retain a parachute and the devices necessary to facilitate the deployment of the parachute. The plurality of holder straps is also designed to facilitate the operation of the parachute while securing the parachute to the base strap. The plurality of cargo straps include several straps that secure the payload to the apparatus. The plurality of cargo straps can also be arranged to accommodate the shape and size of the payload to be delivered using the apparatus.

A throwing protection apparatus for an adaptive navigation situation awareness device based on ship pilotage comprises: a connecting apparatus, a landing buffer apparatus, a fixing apparatus, a pressing apparatus, a shell and a control apparatus; wherein a bottom of the shell is provided with an opening for the adaptive navigation situation awareness device to pass through; one end of the connecting apparatus is fixedly connected to an unmanned aerial vehicle, and the other end of the connecting apparatus is slidably connected to the shell; the adaptive navigation situation awareness device is arranged in the shell and is fixed by the fixing apparatus arranged on the shell; the pressing apparatus is mounted on the shell and is positioned above the adaptive navigation situation awareness device; the landing buffer apparatus is mounted outside the shell; and an air bag and a distance measuring sensor are fixedly mounted on the shell.

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.

The invention relates to an ice surface rescue unmanned aerial vehicle accumulated snow prevention structure and an ice surface rescue unmanned aerial vehicle, and discloses the snow prevention structure which can guide accumulated snow or crushed ice through cooperation of a conical top and an inclined-plane-shaped intercepting net, reduce attachment and accumulation of the accumulated snow or the crushed ice on the intercepting net, reduce abrasion of flying fan blades and improve the ice surface rescue efficiency. The device is characterized in that the device is composed of rack wings, air guide through holes, a conical top, inclined supporting rods, an intercepting net, a ring bottom, threads, thread grooves and fixing rings, the rack wings are correspondingly provided with the air guide through holes, the top faces of the rack wings are correspondingly provided with the fixing rings, the edges of the inner side faces of the fixing rings are connected with the edges of the air guide through holes, and the conical top is provided with the inclined supporting rods. A threaded groove is formed in the side face of the fixing ring, threads are formed in the inner side face of the ring bottom, the threads correspond to the threaded groove, the inner side face of the ring bottom is in threaded connection with the side face of the fixing ring in the mode that the threads are matched with the threaded groove, and the conical top is located over the air guide through hole.

The invention discloses a marine inspection unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles, the marine inspection unmanned aerial vehicle comprises an unmanned aerial vehicle main body, a mounting groove is formed in the outer side of the bottom of the unmanned aerial vehicle main body, a safety bag is mounted in the mounting groove, and water inlet cavities are uniformly formed in the outer side of the unmanned aerial vehicle main body; a reaction cavity and a transition cavity are formed in the unmanned aerial vehicle body. When the device is used, seawater quickly enters the reaction cavity and enters the closed guide channel along the communicating hole under the action of the water inlet cavity, and a first floating plate is matched to enable a sealing block to move upwards until the interior of the water inlet cavity is sealed, so that the seawater is prevented from entering the reaction cavity, and in the process, the seawater reacts in the reaction cavity; and the water inlet cavity is closed, so that the generated gas can only enter the transition cavity and is finally injected into the safety bag, the utilization rate of the gas is high, and the safety bag is fully opened, so that the safety of the unmanned aerial vehicle main body is ensured.

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 belongs to the technical field of unmanned aerial vehicles, and particularly relates to a multipurpose amphibious unmanned aerial vehicle which comprises an unmanned aerial vehicle body, a support and a connecting frame, and a supporting mechanism is mounted on the connecting frame; the flying mechanism is mounted on the bracket and comprises a flying part and a heat dissipation part; an air pump is installed at the bottom of the unmanned aerial vehicle body, and the exhaust end of the air pump is connected with an air conveying pipe. Wherein the supporting mechanism comprises an outer cylinder, the outer cylinder is installed on the connecting frame, inner cylinders are slidably connected to the two ends of the outer cylinder in an inserted mode, a control part is installed between the two inner cylinders, buoyancy parts are installed at the front end and the rear end of each inner cylinder, and limiting grooves are annularly distributed in the inner wall of the outer cylinder; through holes are further formed in the two ends of the limiting groove, and a blocking part is arranged on the inner cylinder. The unmanned aerial vehicle can show remarkable advantages in the aspects of improving flight efficiency, enhancing waterproof protection, improving use convenience and adaptability and the like.

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.

According to the ice surface rescue unmanned aerial vehicle supporting and positioning structure and the ice surface rescue unmanned aerial vehicle, a rotating motor drives a triangular wheel to rotate, so that the unmanned aerial vehicle can rapidly reach the water surface position where a person falling into water is located, and meanwhile slipping and rollover of the unmanned aerial vehicle on the ice surface and deviation of the unmanned aerial vehicle from a preset return route are reduced; and the ice surface rescue efficiency is improved through the position adjusting structure. The device is characterized in that the device is composed of a device body, a sliding plate, a sliding plate groove, a second screw, a motor containing groove, triangular wheels, a supporting shell, a fourth rotating shaft and a rotating motor, the sliding plate comprises two vertical sliding plates and two transverse sliding plates, the motor containing groove is formed in the middle of the device body, and the length of the motor containing groove is equal to the width of the device body; the motor containing groove is parallel to the transverse sliding plates and located between the two transverse sliding plates, one ends of supporting shells are correspondingly arranged on the two sides of the bottom of the motor containing groove respectively, and rotating motors are correspondingly arranged on the side faces of the supporting shells respectively.

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.

An amphibious aircraft includes two floats, each having a front hull and an elevated rear hull with a step between the two. Each float also has a retractable main landing gear with a main wheel. The step and the main wheel are placed strategically close to each other to provide readily controllable landings and takeoffs from water or land. To achieve such close placement of the step and the main wheel, a clearance notch in the front hull, near the step, provides space into which part of the main landing gear can extend when the main wheel descends to a deployed landing position. The size of the notch is sufficiently small to have an inconsequential effect on the front hull's ability to hydroplane. In some examples, a colored portion of the main landing gear protrudes above the float to provide a visual indication of when the main wheel is retracted.

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 invention discloses an unmanned aerial vehicle seaborne landing airbag, and belongs to the technical field of unmanned aerial vehicle landing, the unmanned aerial vehicle seaborne landing airbag comprises an airbag and an airbag inflation mechanism used for inflating gas into the airbag, the airbag inflation mechanism comprises a gas storage tank, a manual opening and closing valve, a high-pressure hose, an electromagnetic exhaust valve and an adapter, and the gas storage tank is fixedly connected to a vehicle body of an unmanned aerial vehicle; one end of the air storage tank is connected with the manual opening and closing valve, one end of the high-pressure hose is connected with the manual opening and closing valve through a first hose connector, the other end of the high-pressure hose is connected with the electromagnetic exhaust valve through a second hose connector, one end of the adapter is connected with the electromagnetic exhaust valve, and the other end of the adapter is connected with the air bag. The unmanned aerial vehicle is in control connection with the electromagnetic exhaust valve, and the air bag is located at the bottom of the vehicle body after pushing open the cabin cover of the unmanned aerial vehicle downwards in the using state. According to the unmanned aerial vehicle offshore landing airbag, the unmanned aerial vehicle can operate in a sea area and stably land to the sea surface, and the problem of offshore landing of the unmanned aerial vehicle is effectively solved.

The invention belongs to the technical field of parachutes, and relates to an unmanned aerial vehicle emergency recovery landing device which comprises a mounting box, hook-and-loop fasteners, a landing mechanism and a fixing mechanism, the hook-and-loop fasteners are connected to the two sides of the bottom of the mounting box, and the mounting box can be fixed to an unmanned aerial vehicle body through the hook-and-loop fasteners; a landing mechanism used for assisting the unmanned aerial vehicle body in landing is arranged in the mounting box, and a fixing mechanism used for fixing the landing mechanism in the mounting box is arranged in the mounting box. In the operation process of the unmanned aerial vehicle, if the explosion phenomenon occurs, the parachute can be opened, the falling speed of the unmanned aerial vehicle is buffered through the parachute, the situation that the unmanned aerial vehicle falls on the ground and is damaged is avoided, and economic losses caused when the air crash time of the unmanned aerial vehicle occurs are reduced.

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.