112 results about "Ducted propeller" patented technology

The invention relates to a miniature electric ducted propeller type intelligent unmanned aerial vehicle, which consists of a ducted casing, a bracket, a coaxial counter propeller, a fairing, a battery, a motor, a driving control circuit and a microcontroller. The machine body has a dish-shaped appearance; and the ducted casing is arranged outside a rotor wing to eliminate flight safety threat caused by the traditional structure of the exposed rotor wing and improve the working efficiency of the propeller. The aerial vehicle adopts a design of the coaxial counter double-rotor wing, cancels the inertial rotation of the machine body without a tail rotor wing, saves materials and expands the operating space. The propeller is driven by the motor; the motor is under the servo control of the driving control circuit; and the horizontal motion of the aerial vehicle in the air is implemented by a deflectable guide plate below the propeller in a matching mode. In addition, a multi-azimuth convenient slot is formed inside the ducted casing of the aerial vehicle for mounting and detaching various sensors at any time; and the microcontroller comprehensively processes information fed back by each sensor and performs autonomous flight control according to a task.

The invention relates to the field of air-ground dual-dwelling vehicle technology, in particular to a longitudinal-line-type dual-culvert vertical-lifting air-ground vehicle. The vehicle comprises a vehicle body, a driving cabin and vehicle wheels that are arranged on the vehicle body; the front end and the rear end of the vehicle body are respectively provided with a ducted propeller; each ducted propeller comprises a culvert, an airscrew and a bracket; the rotation shaft of the airscrew is arranged vertically; the airscrew is provided with an automatic inclining device; two airscrews are driven to rotate reversely by an engine of the vehicle body; the vehicle can be driven on road by the vehicle wheels and can realize vertical lifting and flying by the lifting force provided by the rotation of two vertical ducted propellers; the flying, landing, suspending, heading, withdrawing and rotating are realized by adjusting the rotation speed difference of the two ducted propellers and/or the elevation of the oars; the controllability is good and the structure is simple; the culverts protect the airscrews and the passerby simultaneously and avoid the passerby from being harmed by the airscrews, thus having high safety performance.

The invention relates to a multi-ducted-propeller variable wing electric air vehicle, and belongs to the field of aviation devices. During taking-off, landing and parking, wings and a horizontal tail wing can be folded on a body; after the air vehicle lifts off, the wings and the horizontal tail wing are unfolded, multiple inclinable-rotating ducted propellers are symmetrically distributed in the front and the back of the wings and on horizontal planes, below the wings and the horizontal tail wing, at the left side and the right side of the body. With adopting of the layout, the air vehicle can vertically take off and land and also can fast fly horizontally, the occupied area is reduced during vertical taking-off and landing and parking, and the speed and the airborne period are increased during horizontal flying. The taking-off and landing processes are safe and reliable, and the flying attitude is smooth and steady. The air vehicle can be made into a manned air vehicle or an unmanned aerial vehicle.

A turbine engine including two contrarotating unducted propellers of an upstream propeller and a downstream propeller, with a power turbine mounted axially between the two propellers, the turbine including an outer rotor constrained to rotate with the upstream propeller and an inner rotor driving rotation of an inlet shaft of a step-down gearbox, the gearbox includes an outlet shaft driving rotation of the rotor of the upstream propeller and an outlet shaft driving rotation of the downstream propeller.

The invention discloses a double ducted-propeller electric manned aircraft capable of taking off and landing vertically, and belongs to the field of aviation products. The aircraft comprises an aircraft chamber, double ducted-propeller power systems and a control platform, wherein lateral wings with vertical planes are fixedly and integrally arranged on two sides of the aircraft chamber; the ducted-propeller power systems are arranged at the front end and the rear end of the aircraft chamber and are connected with the lateral wings respectively; a self-balancing mechanism is arranged on the lateral wing on one side; a duct rotating mechanism is arranged on the lateral wing on the other side; the self-balancing mechanism and the duct rotating mechanism are both connected with the ducted-propeller power systems; and the control platform and a battery pack are arranged in the aircraft chamber. The invention further provides a realization method for the aircraft, which adopts the rotation of propellers to generate pushing force, realizes left and right automatic balancing as well as forward and backward rotation of ducts by matching the self-balancing mechanism and the duct rotating mechanism, realizes the vertical taking off, landing and advancing of the aircraft by combining the wing-type streamline design of the aircraft chamber, makes full use of the efficiency of a motor, saves energy and is safer.

The invention discloses an under-actuated spherical underwater robot with flexible movement. The novel spherical underwater robot mainly comprises a ducted propeller mechanism with linear propulsion, a horizontal plane flywheel steering mechanism, a vertical plane pendulum pitching mechanism and a compression resistant sealing spherical shell structure. The robot is provided with the novel steering mechanism, so that the robot can realize no-radius turning in water; the design of the single propeller meets the requirements on low production cost and high running efficiency; a circular transparent shell with a supporting frame can resist certain deep water pressure, and also can be convenient for an internally installed sensor to detect water area information; the robot can be used as a carrier of reconnaissance equipment, aquatic and underwater operation systems and communication systems to perform various near sea operation tasks which cannot be completed by human being directly.

The invention provides an electric aircraft with a plurality of ducted propellers, telescopic wing and telescopic aircraft body, which belongs to the field of air materials. According to the invention, the wing comprises a plurality of embedded wing sections; during taking off, landing and parking, the tail parts of the wing and the aircraft body can retract; after liftoff, the tail parts of the wing and the aircraft body are unfolded; and the plurality of ducted propellers capable of tilting are symmetrically distributed in front of and behind the wing and on left and right sides of the aircraft body. Through adoption of the layout, the aircraft can vertically take off and land and can also rapidly fly in a flat way; the floor area is reduced during vertical take off and landing and parking; and during flat flight, the plurality of ducted propellers can tilt for 90 degrees so that the flying speed and airborne period are increased. The takeoff and landing process is safe and reliable and the flight attitude is stable. The invention can be made into manned aircrafts and can be also made into unmanned aerial vehicles.

The aircraft incorporates a single ducted propeller. The fuselage Bridges over the ducted propeller assembly, and is shaped in a way that the incoming air can smoothly flow into the propeller area. The duct has an aerodynamically shaped frontal area, and an aft extension, which forms the tail section. The wings are attached to the side of the duct. The ducted propeller assembly also contains louvers, which run span wise, to redirect the outgoing air in horizontal direction. During vertical take-off or landing, the propeller has a horizontal plane of rotation, after take-off the whole craft entirely tilts forward approximately 26 degrees to transition into horizontal wing born flight. During vertical flight, the aircraft is controlled by control louvers installed inside the ducted propeller assembly in the propeller slipstream.

The invention, which relates to the field of hovering fore-measuring technology of the unmanned aerial vehicle, provides an aerodynamic characteristic testing stand for a ducted coaxial dual-rotor unmanned aerial vehicle, so that problems of the existing motor thrust testing technique are solved. The aerodynamic characteristic testing stand comprises an external testing platform bracket, an internal adjustment support, a ducted propeller system and a measurement display system. The external testing platform bracket and the internal adjustment support are three-dimensional frames; and the internal adjustment support is fixed inside the external testing platform bracket by flat springs. According to the invention, because straight cantilever type springs are arranged at the same direction, the minimum stiffness plane is easy to bend; with a resistance strain type transducer, displacement during testing is small; because of different flat spring installation and fixation ways, displacement at a certain direction can be restricted and the freedom degree of the sensor measuring direction can be kept; and to-be-measured information generated by the system is transmitted to the sensor and data reading and recording are carried out by a display system, so that different test objectives are achieved.

A variable ducted propeller comprises a propeller and a duct which sleeves the periphery of the propeller, wherein the duct comprises a fixed tube section and a movable tube section, which are connected with each other in series in an axial direction of the propeller; the fixed tube section is positioned at the front end of the duct; the movable pipe section is formed by connecting a plurality of blades with wing-shaped sections in series in a circumferential direction; the blades are rotatably connected with the end surface of the fixed tube section; a hydraulic control lever is hinged on the outer wall surface of each blade; push levers of the hydraulic control levers are hinged with the blades; push lever seats of the hydraulic control levers are hinged with the outer wall surface of the fixed tube section; and the axial directions of the hydraulic control levers are parallel to a bus of the duct. According to the invention, high propelling efficiency under two different working conditions of low advance operation and high speed voyage can be ensured.

The invention relates to a vectored thrust ducted propeller. The vectored thrust ducted propeller comprises a screw propeller and a duct cylinder body, wherein the screw propeller can rotate to generate air currents and the duct cylinder body surrounds the screw propeller; a first rotating piece, a second rotating piece and a blocking piece which are arranged in an air current deflection mechanism are respectively and directly derived from a part of a duct body; a complete duct is jointly formed by the first rotating piece, the second rotating piece, the blocking piece and the duct cylinder body part. Under the driving of a speed reducing motor, a rotation driving shaft is rotated, so that the first rotating piece and the second rotating piece are driven to rotate to expected positions; the blocking piece moves forward and backward along a sliding groove formed in the duct cylinder body to prevent the air currents from flowing out of the right side of the duct, and the blocking piece is matched with the first rotating piece and the second rotating piece so that the air currents can flow out of the remained empty part formed after the first rotating piece is rotated; therefore, the whole system bears lateral force which is reversed to the air currents. According to the vectored thrust ducted propeller disclosed by the invention, the thrust direction of a ducted fan is substantially changed, large enough lateral force is provided for an aircraft to balance the reaction torque of a main rotor, so that the residual thrust in the axial direction of the aircraft is as small as possible, and more suitable for the aircraft of the type to ascend and descend perpendicularly and hang in the air.

The invention provides a sea and air amphibious propeller. The propeller comprises a ducted propeller stator, air propellers, air propeller rotors, ducted propellers and ducted propeller rotors, wherein a group of magnets is fixed on the air propeller rotors and the ducted propeller rotors respectively, the air propeller rotors and the ducted propeller rotors rotate coaxially and are nested to thesame ducted propeller stator, and two coils corresponding to the air propeller rotors and the ducted rotors respectively are embedded into the ducted propeller stator. The air propellers are used foraerial propulsion, water propellers are used for underwater propulsion, and the both can work independently. During underwater propulsion, the air propellers are folded back and rotated at a lower speed to eliminate the resistance to the air propellers, and the shaftless ducted propellers work to generate propulsion. In the air, the air propellers are unfolded and rotate to generate propulsion, and the ducted propellers assist the operation. The shaftless ducted propellers have good propulsion performance under water, the air propellers are suitable for working in the air, and the air propellers are combined with the shaftless ducted propellers to realize efficient propulsion and free switching under water and in the air.

The invention discloses a flexible aggressive mechanical octopus and aims at providing a flexible aggressive mechanical octopus which is capable of realizing a plurality of different operations underwater and suitable for both civil use and military use. The flexible aggressive mechanical octopus comprises a flexible shell and a battery, wherein the flexible shell is provided with a controller which is respectively connected with a satellite positioning module and a vacuum chuck; the flexible shell is further provided with an electric ejector connected with the controller; the ejection orifice of the electric ejector runs through the flexible shell which is connected with a ducted propeller; the vacuum chuck is arranged on the surface of the flexible shell; and the battery supplies power to the flexible aggressive mechanical octopus. As the octopus can be adsorbed to the surface of a target by the chuck and attacks by ejecting corrosive liquid through an ejector, the flexible aggressive mechanical octopus disclosed by the invention is suitable for the field of maritime military.

The invention provides a method for simulating an inland river pushing fleet, which includes: determining the coordinate origin of the fleet coordinate system and the center of gravity of the fleet according to the fleet parameters; combining the coordinate origin and the center of gravity into one point to obtain the simplified four-freedom of the fleet degree motion equation; calculate the inertial force and viscous hydrodynamic force of the ship according to the length of the pusher and barge, the width of the pusher and barge, the draft of the barge and pusher, and the square coefficient of the ship; calculate the fleet according to the inertial hydrodynamic force and viscous hydrodynamic force of the ship The additional mass of the propeller; calculate the thrust of the propeller and the rudder force of the ship according to the rotational speed, diameter, advance speed, wake coefficient and thrust coefficient of the ducted propeller; substitute the additional mass, propeller thrust and rudder force into Runge Kuta to calculate the ship The acceleration and speed of the fleet; the simulator simulates the navigation of the real inland river pushing fleet according to the acceleration and speed of the fleet. The invention regards the pusher boat and the barge as one ship, fully considers the influence factors of the inland river environment, and realizes the simulation of the inland river pusher fleet.

The invention discloses a four-ducted propeller powered fixed-wing unmanned aerial vehicle capable of achieving vertical take-off and landing, and belongs to the field of unmanned aerial vehicles. Thefour-ducted propeller powered fixed-wing unmanned aerial vehicle capable of achieving vertical take-off and landing comprises a structural unit, power units and a flight control and avionic unit, wherein the structural unit comprises a fuselage, wings, control planes and tail supporting rods; the fuselage is positioned at a central position of the whole unmanned aerial vehicle; four wings are fixed to the fuselage; the adjacent wings of the four wings form included angles of 90 degrees; the power units are arranged on the tips of the four wings; the control planes are arranged on the four wings; the tail supporting rod is arranged on each wing; each power unit comprises four sets of ducted propellers; a set of ducted propeller is arranged on each wing; the flight control and avionic unitis mounted inside the inner cavity of the fuselage. The unmanned aerial vehicle system has relatively low overall power redundancy and relatively high using efficiency, and can achieve vertical take-off and landing, fixed-point hover in the air and efficient cruise and level flight.

The invention aims to provide a bionic propeller. The bionic propeller comprises a blade. A guiding edge portion of the blade is of a concave-convex front edge structure, and a blade tip of the blade is of a sawtoothed structure. The concave-convex front edge structure comprises fourteen protruding nodes, the sizes of the protruding nodes sequentially decrease from the middle of the guiding edge portion to two sides, a smooth transition effect is achieved from the protruding nodes to the blade tip and the blade, and tangent planes at a convex position and a concaved position of each protruding node are both shaped like wing tangent planes. The sawtoothed structure comprises four sawteeth, the sawteeth are distributed in a region of 17 degrees to 25 degrees from the edge to the center line of the blade, inward sawtooth concaves and outward sawtooth cusps are formed in the blade tip of the blade, and the projection of each sawtooth is an isosceles triangle. The bionic propeller enables a boundary separation region on the surface of the blade to be obviously reduced relative to a standard blade, so a stalling angle is increased; the bionic propeller can make full use of the power of a main engine under various working conditions, reduce waste of the power of main engines of a conventional propeller and a ducted propeller, reduce generated cavitation noise, and improve the utilization efficiency of ship energy.

The invention relates to a dual-rotor coaxial helicopter with wing-shaped rotors, and the helicopter belongs to B64C 27/04. helicopters according to international patent technology classification. The general layout adopts a mashup design of a dual-rotor coaxial helicopter and a fixed wing aircraft with preposed canard wings. An elevator is preposed, and horizontal wings and ailerons for lateral control are disposed at the rear. A control surface that is responsible for yaw control is positioned behind ducted propellers that are disposed at the rear and used for providing thrust. Fans are arranged below the fuselage on the left and the right so as to retreat or horizontally and slightly adjust the fuselage hovering position or make the fuselage revolve. Due to the wing shape change, when an engine encounters in-flight shut-down, the helicopter continuously suffers height loss, so that air and the rotors interact to convert the potential energy of the helicopter into kinetic energy, which makes the rotors continue to rotate according to the rotation direction of the engine during working hours. Consequently, a lifting force can be generated, and fall can be changed to a safe landing. The helicopter provided in the invention can solve or improve the problems of small speed, short flying range, low flight height, great vibration and noise, poor reliability, high cost and use fee in helicopters in active service.

The invention relates to a novel ducted amphibious submersible device, belongs to the technical field of submersible devices and aims at solving a monotonous function problem in the prior art. The device includes a device body, wings symmetrically arranged at the two sides of the device body, an empennage arranged at the rear part of the upper end of the device body, tail thrusters symmetrically arranged at the two sides of the rear part of the lower end of the device body, two ducted propeller mechanisms arranged in the device body, two steering mechanisms arranged on an upper shell of the device body, a battery pack, a power source adjuster, an electronic speed controller group and a main controller. The wings are of rotatable structures; the upper ends of ducted housings of the ducted propeller mechanisms are in contact with the upper shell of the device body, and ducted propeller blades of the ducted propeller mechanisms are parallel to the horizontal plane; the two steering mechanisms correspond to the two ducted propeller mechanisms respectively and are used for adjusting the force output directions of the two ducted propeller mechanisms; the battery pack, the power source adjuster, the electronic speed controller group and the main controller are fixedly arranged in the device body, the battery pack is connected with the power source adjuster through a power line, and the power source adjuster is connected with the electronic speed controller group; the main controller controls running of the whole submersible device.

The invention relates to the technical field of medical instruments and discloses an implant-type blood flowing pump with a self-suspended shaft. In the implant-type blood flowing pump, a rotor comprises a hollow cylindrical steel magnet (5) and built-in blades fixed in the steel magnet (5); the rotor is directly arranged in the middle of a stator; the stator is neither directly nor indirectly connected with the rotor through a bearing; the rotor automatically separated form the inner wall of the stator during rotating and is in a suspended state. As the bearing and a magnetic suspension control system are not adopted, the size of the implant-type blood flowing pump is smaller and the weight of the implant-type blood flowing pump is lighter, the implant-type blood flowing pump does not stop rotating when a mechanical failure occurs to the bearing, so that the reliability is higher, and the formation of thrombus in the position of the bearing is avoided. The implant-type blood flowing pump adopts a serial structure that the built-in blades (8) are in the front and the external blades (9) are in the rear; the tangent planes of the blades adopt the modes of the wings of a marine ducted propeller, so that the implant-type blood flowing pump can ensure that blood smoothly branches in and passes through main vessels and branch vessels.

The invention discloses an integral ducted propeller. The integral ducted propeller comprises a duct, a propeller and a fairing, wherein the propeller comprises a propeller hub and at least two blades; the fairing is fixed on the propeller hub; and two ends of the blades are connected to the propeller hub and the duct separately. The blades and the duct of the integral ducted propeller are directly connected, so that the impulse noise is further reduced, the induced drag is reduced, deformation of the blades is smaller, the integral ducted propeller has a higher aerodynamic effect and the work efficiency of the propeller is improved.

The invention discloses a ducted propeller aircraft, wherein a lift system formed by ducted coaxial twin propellers is used as a main lift surface of the aircraft, so as to overcome the weight of theself-structure and the hanging load. Four ducted propellers located around the control surface can be used to control the yaw pitch and roll of the vehicle through the differential speed of the propeller. At the same time, they can also provide part of the lift for the aircraft. Compared with some existing ducted fan vehicles controlled by control rudder surface, it has the advantages of simple and reliable control, high control efficiency and good stability.

The invention provides a bevel-gear-transmission torque self-balancing shaftless ducted fan or propeller blades for an aircraft. The bevel-gear-transmission torque self-balancing shaftless ducted fancomprises a duct cylinder frame, at least one set of reverse shaftless fans or the shaftless propeller blades, and transmission mechanisms; the reverse shaftless fans or the shaftless propeller bladesand the transmission mechanisms are mounted in the duct cylinder frame; and the transmission mechanisms are connected with the reverse shaftless fans or the shaftless propeller blades through gears to form the shaftless ducted fan or the shaftless ducted propeller blades. According to the bevel-gear-transmission torque self-balancing shaftless ducted fan or propeller blades, the structure is simple, and mounting and using are convenient; and the bevel-gear-transmission torque self-balancing shaftless ducted fan or propeller blades are suitable for being used for the current aircraft which isapplied increasingly and widely, and especially suitable for a manned aircraft requiring low noise and high lift or thrust and having self-balancing torque.

The invention discloses a novel embedded ducted propeller driven blade which comprises a blade part, an embedded ducted propeller and a blade root connector, wherein the embedded ducted propeller is arranged at a blade tip of the blade part; the blade root connector is arranged at a blade root of the blade part; the blade root connector is connected with a main rotor shaft; the embedded ducted propeller comprises vanes, a fairing, a hub and an embedded duct; the hub is arranged in the center of the embedded duct; the fairing is arranged at the top end of the hub; the vanes are distributed in an annular space formed by the embedded duct and the hub; one end of each vane is connected with the hub; the other ends of the vanes are slidingly connected with a slide rail circumferentially arranged on an inner wall of the embedded duct; the hub is internally provided with a driving device; and the vanes are driven by the driving device to rotate. According to the novel embedded ducted propeller driven blade, a complicated and cumbersome mechanical transmission system and a reactive torque system can be cancelled; the weight efficiency of a helicopter is improved; the rotor performance is improved at the same time; and vibration and noise are inhibited.

The invention relates to An all terrain vehicle integrated electric ducted propeller propulsion system which includes a motor housing, end caps are fixedly connected to both ends of the motor housing,A shaft is arranged in that motor housing, a motor rotor is arranged on the outer rear of the rotating shaft, the motor rotor is matched with the motor stator installed in the motor casing, one end of the rotating shaft is protruded from the end cover and connected with the propeller, a rotating seal structure and a first bearing are arranged at the matched position of the rotating shaft and theend cover, and the other end of the rotating shaft is connected with a resolver through a second bearing; The motor stator is connected with a driving controller and a propulsion motor through a powersupply line and a signal control line. because double-propeller arrangements are arranged on the two sides of the all-terrain vehicle, the propeller speed is controlled by a propulsion motor and a drive control, and the steering of the all-terrain vehicle is realized by utilizing the differential speed of the propeller speeds of the left and right sides, the accessory parts such as the steering rudder plates and the like which are required in the past are omitted, the weight of the all-terrain vehicle is reduced, and the reliability of the whole vehicle is improved.