27 results about "Ducted propeller" patented technology

This invention relates to the field of marine propulsion device manufacturing, specifically a design method for a fully azimuth-controlled adjustable-pitch ducted propeller. This method extracts the basic parameters of the ship's main engine and existing rudder propeller, and establishes an integrated arrangement scheme to replace the fixed-pitch propeller with an adjustable-pitch propeller while maintaining the original power parameters unchanged. Based on the theoretical diagram of the fixed-pitch ducted propeller, a hydrodynamic calculation program is executed, introducing correction factors for increased shell diameter ratio and slightly reduced disk area ratio, and forcibly lowering the theoretical thrust coefficient by 5%, to obtain the corrected target open-water characteristic curve. The overall rotational characteristics of the fully azimuth-controlled rudder propeller are utilized to provide thrust for reversing and steering, strictly limiting the pitch adjustment authority to adaptability requirements for low-speed navigation and providing maximum drag under multiple operating conditions. A single-crank slider mechanism is configured inside the propeller hub as the core rotor component, and a three-dimensional spatial layout is completed. An electro-hydraulic integrated servo control system, dominated by a PLC and incorporating a dual-pump parallel architecture and a built-in hydraulic lock, is established. This significantly reduces the frequency and physical amplitude of the propeller blade rotation angle.

The invention provides a shaftless ducted thruster and an aircraft. The shaftless ducted thruster comprises a shell, an air floatation rotating paddle assembly, an air cooling duct and a lip air inlet duct structure. The air floatation rotating paddle assembly is arranged in the inner side of the shell, is provided with a rotatable shaftless paddle end and is used for providing propelling force in a rotating manner; the air cooling duct is arranged between the shell and the air flotation rotating paddle assembly and penetrates through the two ends of the shell; the lip air inlet channel structure is arranged at the end of the shell and used for guiding airflow to enter the air cooling duct in an accelerated mode, and heat dissipation is conducted on the air flotation rotating paddle assembly in the shell. According to the invention, the air cooling duct is arranged between the shell and the air floatation rotating paddle assembly, and the air flow flows through the air cooling duct at a high speed under the flow guide acceleration of the lip air inlet duct structure on the air flow, so that direct heat dissipation is carried out on a core heating part, and a through type high-speed heat dissipation flow channel is formed; the low-efficiency heat dissipation mode that heat is conducted from the inside to the shell for heat dissipation in a traditional structure is effectively improved.

The utility model belongs to building glass cleaning technical field, concretely is a kind of culvert propeller adsorption type cleaning robot, including robot body, the front and rear sides of robot body are symmetrically equipped with two groups of driving caterpillar belt, the right side of robot body is equipped with cleaning wheel cover, the inside rotation of cleaning wheel cover is equipped with cleaning roller, the utility model utilizes the culvert type propeller of top four corners, and the distance between robot and glass surface can be quickly regulated, effectively overcome the distance barrier caused by structure such as window sill plate, ensure that negative pressure suction cup and cleaning roller are closely attached to glass, the detection camera and radar of front and rear sides scan building elevation profile in real time, avoid window sill, corner and other barriers in advance, avoid collision and risk of missing.

The invention provides a ducted thruster thrust testing device and testing method. The thrust testing device comprises an air duct type mounting base, an axial linear moving platform, a ducted fan, an air inlet pipe, an air outlet pipe, an auxiliary fan and a pull pressure sensor assembly. The ducted fan comprises a ducted shell and a core assembly, the core assembly comprises a supporting guide vane, an impeller and a motor assembly, a linear cylindrical guide rail assembly is arranged between the supporting guide vane and the ducted shell, and the thrust value of the core assembly can be independently measured through the arrangement of the linear cylindrical guide rail assembly. The thrust value of the core assembly is compared with the overall thrust value of the ducted fan, and the influence of the ducted shell on the thrust is evaluated; if the overall thrust value is larger than the thrust value of the core assembly, it is indicated that the thrust of the ducted shell is increased; if the overall thrust value is smaller than the thrust value of the core assembly, it shows that the duct shell causes energy loss.

The invention discloses a butterfly-shaped unmanned aerial vehicle with high flight stability and a use method thereof, and relates to the technical field of unmanned aerial vehicles. The unmanned aerial vehicle comprises an unmanned aerial vehicle body, a propelling assembly is arranged at the bottom of the unmanned aerial vehicle body, and a connecting assembly is arranged at the top of the propelling assembly and located at the bottom of the unmanned aerial vehicle body. The propelling assembly can capture the posture change of the aircraft body caused by strong wind in real time through the balance sensor on one side of the top of the shell, signals are synchronously fed back to a transmission system, a bevel gear, a worm gear and a worm are driven by a motor to be rapidly linked, the angle of a ducted propeller is adjusted in time to generate reverse counteracting force, and impact of the strong wind on the aircraft body is rapidly neutralized; inclination, yawing or deviation of the aircraft body caused by strong wind is effectively restrained, it is ensured that the aircraft body can still keep a stable flight state in a complex strong wind environment, the stress directions of the ducted propellers can be accurately adjusted according to the strong wind from different directions, and propulsive force can effectively resist the aircraft body from the corresponding side.

The present application provides a ducted propeller, belonging to the field of ducted propellers, comprising a duct, a ring, a hub, a fixed blade and a movable blade; the ring is arranged to rotate on the axis in the duct; the hub is arranged to rotate on the axis in the duct; the fixed blade rotates synchronously with the ring; the movable blade rotates synchronously with the hub, and moves forward and backward along the axis of the hub relative to the hub and has a first position and a second position; when the movable blade is in the first position, the fixed blade and the movable blade are in the same rotation plane; when the movable blade is in the second position, the fixed blade and the movable blade are in two radial planes respectively. The present application sets the movable blade of the shafted propeller to move axially, and combines the fixed blade of the shaftless propeller which can be controlled independently to stop rotating, so that the two different working modes can be switched flexibly, and the rotating blade of the shaftless propeller is designed as a variable structure, which is directly converted into the front stator of the duct after stopping, realizing the functional reuse of a single component.

This invention discloses a fixed-type aerodynamic performance-selective ducted propeller shaft structure for land-to-air aircraft. The fixed-type structure includes a central main shaft, at least one first rotor, at least one second rotor, at least one third rotor, a first duct corresponding to each of the first rotors, a second duct corresponding to each of the second rotors, and a third duct corresponding to each of the third rotors. The first rotors are fixedly mounted on the central main shaft. The first duct is fitted around the outer periphery of the first rotor. The second rotor is loosely fitted onto the central main shaft, and its second blade is fixedly connected to the second duct. The third rotor is fixedly connected between the central main shaft and the third duct. This fixed-type structure uses the duct and rotor as equivalent to a pump wheel, a turbine, and a guide wheel, respectively, thereby achieving different aerodynamic performances to meet different aerodynamic and lift requirements, thus enabling selection of aerodynamic performance.

The application provides a cross-domain vehicle and a navigation method, and belongs to the technical field of cross-domain vehicles.The vehicle comprises a catamaran main body, a composite propulsion module and a semi-submersible floating body structure, the catamaran main body is provided with an underwater propeller, and the catamaran main body is connected with the semi-submersible floating body structure;the top of the semi-submersible floating body structure is provided with a foldable rotor system, the foldable rotor system is connected with a rotor engine, and is retracted and closely attached to the vehicle body in the water entry or underwater stage, so as to reduce fluid resistance; the composite propulsion module comprises a front anti-torsion ducted propeller and a tail pitch ducted propeller which are installed on the semi-submersible floating body structure.The application effectively solves the problems that the traditional water navigation tool and the aerial vehicle have single functions and are difficult to efficiently cooperate in a complex environment, realizes water-air amphibious autonomous switching and attitude stable control, and provides a multifunctional and efficient operation platform for the fields of ocean exploration, emergency rescue and cross-domain logistics.

This invention proposes a ducted propeller, comprising a tube body, a propeller body, and protruding units. At least one groove is formed on the inner wall of the tube body. The propeller body is disposed within the tube body and located at one end of the tube body. The groove is spirally arranged around the central axis of the tube body. Several protruding units are continuously and uniformly arranged within the groove along its spiral line. Adjacent protruding units are connected end-to-end. By forming a spiral-shaped groove on the inner wall of the tube body, the propeller wake is rectified. As the wake flows towards the outlet at the free end of the tube body, the circumferential velocity component of the wake gradually decreases under the action of the groove. This results in the circumferential velocity component at the wake outlet being significantly smaller than that at the wake inlet, thereby improving propulsion efficiency and reducing noise.

The present application belongs to the technical field of copper alloy, and particularly relates to a wear-resistant and corrosion-resistant high-manganese copper alloy and a preparation method thereof, characterized by the following composition by weight percentage (wt.%): Mn: 20% to 35%, Al: 5% to 7%, Ni: 10% to 14%, and the balance of Cu and inevitable impurities, with the total percentage of all impurities being not more than 0.5%, and the content of any one of Pb, Sn, Si, Zn, P and S being not more than 0.1%. The preparation method comprises the following steps: 1) batching; 2) smelting; 3) pouring; and 4) solid solution treatment, to obtain the wear-resistant and corrosion-resistant high-manganese copper alloy. The present application has the following beneficial effects: innovative alloy composition, tensile strength up to 585 MPa, yield strength up to 296 MPa, hardness up to 305 HV, friction coefficient as low as 0.43, corrosion current density as low as 3.95 x 10 ‑6 A / cm 2 , and excellent comprehensive performance, and can be widely applied to pump bodies, valve bodies, pipelines, propellers and other parts in marine environments and other occasions with high requirements for wear resistance and corrosion resistance.

The application provides a movable post-stator duct propeller, which comprises a pipe body, an inflow end and an outflow end at two ends respectively, a propeller body arranged in the pipe body and provided with a propeller blade, and a stator arranged on the inner wall of the pipe body and located between the propeller body and the outflow end, wherein the end of the propeller blade towards the stator is a trailing edge, the trailing edge has the ability to be elastically deformed by heating or cooling, and the end of the trailing edge towards the stator rotates around the pipe body in the radial direction; the end of the stator towards the propeller blade is a leading edge, the leading edge has the ability to be elastically deformed by heating or cooling, and the end of the leading edge towards the propeller blade rotates around the pipe body in the radial direction; the trailing edge of the propeller blade and the leading edge of the stator can simultaneously deform and deflect, which helps the inflow angle of the propeller blade and the post-stator to be zero to form an ideal hydrodynamic state, and the trailing edge of the propeller blade and the leading edge of the stator simultaneously deflect, which solves the problem that only the leading edge of the stator deflects and needs to deflect a large angle.

The application provides a cross-domain vehicle combining a ducted propeller group and a rotor unmanned aerial vehicle and a navigation method, and belongs to the technical field of cross-domain vehicles.The cross-domain vehicle comprises six groups of circumferentially uniformly distributed ducted propellers, which comprise clockwise rotating ducted propellers and counterclockwise rotating ducted propellers; the clockwise rotating ducted propellers and the counterclockwise rotating ducted propellers are alternately arranged; the bottom of the ducted propeller is mounted on a circular base; the ducted propeller is connected with a cylindrical structure through a transverse connecting beam; a rotor unmanned aerial vehicle system is mounted on the cylindrical structure; and a flight control device and two groups of battery systems are mounted in the cylindrical structure.The vehicle integrates water surface navigation and air flight functions, realizes the operation requirements such as rapid and stable navigation on the water surface, smooth take-off and ascent into the air and safe landing on the water surface through fine regulation and control of the coordinated work of the ducted propeller group and the rotor unmanned aerial vehicle, realizes lightweight while ensuring the structural strength, and guarantees the stability and environmental adaptability of the vehicle.

The application discloses a variable-structure multi-duct vertical take-off and landing aircraft and a control method thereof. The aircraft comprises a fuselage, wings fixed on both sides of the fuselage, and a V-shaped tail wing fixed at the tail of the fuselage. The wings comprise fixed wings connected with the fuselage and rotatable wings connected with the fixed wings. At least one ducted propeller thrust unit is arranged on the rotatable wings. During the rotation of the rotatable wings around the fixed wings, the rotatable wings have a first position for keeping the aircraft in a horizontal flight mode, a second position for keeping the aircraft in a vertical take-off and landing flight mode, and an intermediate transition position for a transition flight mode. The root of the V-shaped tail wing is rotatably connected to the tail of the fuselage. The rotatable wings and the V-shaped tail wing are connected through a synchronous motion mechanism, and the opening angle of the V-shaped tail wing is synchronously adjusted during the rotation of the rotatable wings around the fixed wings. The application can realize vertical take-off and landing and cruising in a fixed-wing mode, and can switch the flight mode during flight.

Aircraft with a fuselage (12) and two wings (14, 16) arranged on opposite sides of the fuselage (12), wherein the wings (14, 16) each comprise at least one ducted propeller (22, 24) and each comprise at least one adjustable elevon (40, 42, 44, 46), wherein the ducted propellers (22, 24) are activatable at least in a vertical flight phase and the elevons (40, 42, 44, 46) are pivotable about a rotational axis (D) at least between a first position and a second position, wherein the elevons (40, 42, 44, 46) in the second position enclose a larger angle (a) to a horizontal plane than in the first position, wherein the elevons (40, 42, 44, 46) are adjusted to the second position in the vertical flight phase.

The invention provides a distributed power stern rudder system for an underwater vehicle. The distributed power stern rudder system comprises a stern rudder, a ducted propeller assembly, a driving motor and a control unit arranged in a boat body. The stern rudders adopt an X-shaped design and are divided into four groups which are uniformly distributed in the circumferential direction of the stern contraction section, so that a multi-degree-of-freedom control configuration with four control surfaces working cooperatively is formed; the four groups of ducted propeller assemblies are respectively matched and correspondingly mounted at the tips of the four groups of stern rudders; each group of guide pipe paddle assembly comprises a guide pipe, an upper stator, a lower stator, a motor mounting sleeve, a flow guide cover, a propeller, a driving motor and a mechanical sealing part; the driving motor is electrically connected with the control unit, the power output end of the driving motor extends out of the axial outer side of the motor mounting sleeve, and the propeller is mounted at the extending end in a matched mode. According to the novel distributed power tail vane design, the conception is reasonable, the yawing moment can be provided in the static state, the yawing moment can also be provided at different navigational speeds, and navigation thrust can also be provided.

In a method for designing the duct and propeller of a ducted fluid propeller, an example embodiment is a ducted fluid-propeller system with a propeller coupled with an electrical generator, the propeller surrounded by at least one annular airfoil (duct). A method for designing a duct and propeller involves calculating 2D CFD of duct-airfoil coordinates and calculating 3D CFD of duct-airfoil and propeller models, as well as calculating 3D CFD actuator-disk duct and propeller-model designs. The method also involves creating scaled duct models along with modified propeller models for scale-model testing and for creating full-scale duct and propeller models and validating full-scale duct and propeller designs.

This invention discloses a ducted rotor drive system and a ducted rotor for unmanned aerial vehicles (UAVs), belonging to the field of ducted rotor technology. The motor system includes an annular housing, a rotor, an oil supply assembly, and a stator. The housing has internal grooves, and the rotor slides along a slide rail within the groove via a slider, replacing large-diameter rolling bearings to achieve weight reduction. A U-shaped upper oil baffle and a C-shaped lower oil baffle, combined with the rotor's hook edge, achieve frictionless oil sealing. The slide rail is composed of guide rail units spliced ​​together, with pre-reserved oblique joints to accommodate thermal expansion and reduce operational impact. This invention constructs a closed-loop circulating oil circuit, enabling the recovery and filtration of lubricating oil under complex attitude conditions. This invention eliminates central hub obstruction, improves aerodynamic efficiency, and balances lightweight design, low friction, and long-term lubrication, ensuring motor electrical safety, extending service life, and is suitable for use with ducted rotors for UAVs.

According to the ducted motor controller, the ducted electric drive assembly and the ducted thruster, the cylindrical shell is adopted by the controller to be matched with the flow guide cover, and ducted wind resistance is remarkably reduced; the circuit boards in the controller are axially stacked, the circuit boards are connected through the welding terminals, the conductive columns or the linear beams, the power switch devices are installed in a wall-attached mode, the vibration resistance, the EMC interference resistance and the heat dissipation effect are good, and the performance requirements needed by the hovercar are met.

The application discloses an anti-icing channel propeller and belongs to the technical field of ship and ocean engineering equipment. The anti-icing channel propeller comprises an inlet section, a first curved section, a curved connection section, a second curved section and an outlet section which are sequentially connected, a propeller is arranged in the outlet section, the shape of the first curved section is variable, a curvature adjusting device is arranged on the first curved section, the curvature adjusting device is used for adjusting the curvature of the first curved section, an inertia locking cavity is further arranged in the first curved section, and the inertia locking cavity is used for making high inertia ice blocks collide and break. Through the collaborative design of the curvature adjusting device and the inertia locking cavity, the application realizes smooth flow guiding in an ice-free area and active deformation interception in an ice area, thereby completely solving the structural conflict between propelling efficiency and anti-icing capability and greatly improving the all-weather survival capability and economic benefits of a polar ship.

The application provides a front stator movable conduit propeller, which comprises a pipe body, an inflow end and an outflow end at two ends respectively, a propeller body arranged in the pipe body and provided with a propeller blade, and a stator arranged on the inner wall of the pipe body and located between the propeller body and the inflow end, wherein the end of the propeller blade towards the stator is a leading edge, the leading edge has the ability to be elastically deformed by heating or cooling, and the end of the leading edge towards the stator rotates around the pipe body in the radial direction; the end of the stator towards the propeller blade is a trailing edge, the trailing edge has the ability to be elastically deformed by heating or cooling, and the end of the trailing edge towards the propeller blade rotates around the pipe body in the radial direction; the leading edge of the propeller blade and the trailing edge of the stator can simultaneously deform and deflect, which helps the inflow angle of the propeller blade and the front stator to be zero to form an ideal hydrodynamic state, and the simultaneous deflection of the leading edge of the propeller blade and the trailing edge of the stator solves the problem that only the trailing edge of the stator needs to deflect a large angle.

The invention discloses a flying and diving combined robot for water area rescue and salvage. The flying and diving combined robot is characterized by comprising a duct propeller flying driving device (100), a flying carrier structure (200), a diving robot (300), an intelligent control system (400) and a final assembly (500). The mechanisms and the systems are reasonably combined to form a novel water area rescue and salvage robot. Through the ducted propeller flying device, the submerged robot is quickly conveyed to the position above a water area needing operation, and then the submerged robot is put down. The diving robot dives and swims on the water surface and underwater to find a target through manual control or autonomous searching, and rescue and salvage tasks are completed. The water area rescue salvage working efficiency can be greatly improved, and a new technical scheme is provided for water area personal safety protection and water disaster rescue.

The present application relates to a deformable ducted propeller structure, which duct is composed of a leading edge, a trailing edge, an airfoil base, a leading edge control device and a trailing edge control device. The leading edge has a certain flexibility, and through the action of the leading edge control device, the leading edge can be elongated while slightly becoming sharp and narrow or shortened while slightly becoming round and blunt, so as to realize the adjustment of the length of the duct and the shape of the leading edge profile. Through the action of the trailing edge control device, the trailing edge can be deflected around the airfoil base, so as to realize the adjustment of the angle of the duct expansion section. The present application is conducive to further improving the aerodynamic performance under the condition of meeting the weight limit, and is suitable for the performance requirements in different flight stages.

The invention provides a ducted propeller with adjustable spectrum characteristics and a spectrum characteristic regulation and control method thereof, and belongs to the field of propellers, the ducted propeller comprises a conduit, a propeller hub, blades and a jet mechanism, the propeller hub is arranged in the center of the conduit; the blades are axially distributed on the propeller hub around the guide pipe and axially rotate relative to the guide pipe along with the propeller hub, and gaps are reserved between blade tips of the blades and the inner wall of the guide pipe; a plurality of jet holes are formed in the inner wall of the guide pipe around the axial direction of the guide pipe and jet towards the gap at the same time; the jet mechanism is used for inputting jet media into the jet holes; jet flow is jetted to the gap between the blade tip and the inner wall of the guide pipe through the jet flow mechanism, gap flow is directly interfered, line spectrum noise superposition at the blade frequency is reduced, radiation noise of a propulsion system can be remarkably reduced, the method is particularly suitable for the high-navigational-speed working condition of a ship, the sound stealth performance is improved, and the ship is prevented from being recognized by sonar.

The utility model discloses a balloon tube apron hovercraft which comprises a hull, a balloon tube apron, an engine assembly, a ducted propeller and a rudder, the engine assembly, the ducted propeller and the rudder are all arranged on the hull, the ducted propeller is located at the rear end of the hull, and the engine assembly is in transmission connection with the ducted propeller. The rudder is arranged behind the ducted propeller, the ducted propeller is used for providing advancing propulsive force and blowing part of airflow into the bag barrel apron so as to provide cushion lifting force, the bag barrel apron comprises a skirt bag and a plurality of barrel-shaped skirt fingers, the skirt bag wraps and is fixed to the periphery of the ship body in the circumferential direction of the ship body, and the barrel-shaped skirt fingers are arranged in the skirt bag. The cylindrical skirt fingers are evenly distributed at the bottom of the skirt bag in the circumferential direction of the skirt bag, the cylindrical skirt fingers are communicated with the skirt bag, and the sizes of the cylindrical skirt fingers are gradually reduced from top to bottom. The bag barrel apron hovercraft can be guaranteed to have good obstacle crossing ability and certain buoyancy, and the safety performance of the bag barrel apron hovercraft is greatly improved.

The application provides a flow control device and method for improving the efficiency of a ducted fan propulsion, comprising a duct and a ducted propeller device; an annular duct is arranged on the outer periphery of the ducted propeller device; the duct comprises a blowing flow channel, a blowing port, a suction port, a suction flow channel and a gas source device; the blowing port is arranged on the inner surface of the duct, that is, the upper surface of the duct airfoil, and is close to the leading edge of the duct airfoil; the suction port is arranged on the upper surface of the duct airfoil and is away from the leading edge of the duct airfoil; the application introduces a cooperative jet active flow control on the ducted fan, greatly improves the overall propulsion efficiency of the ducted fan, improves the wind resistance of the ducted fan, and enhances the controllability of the ducted fan.

The invention discloses an aerodynamic design method of a variable-pitch blade of a ducted fan, which comprises the following steps of: firstly, quickly designing the blade based on a blade element momentum theory and an eddy current theory of a ducted propeller, including hovering condition design and forward flying condition design; the blades meeting the design requirements can be obtained by calculating fluid dynamics (CFD) correction and iteration for two to three times, and the final blades of the ducted fan are obtained through comprehensive hovering and forward flight two-point optimization design, so that the aerodynamic performance of the ducted fan vertical take-off and landing aircraft under the working conditions of vertical take-off and landing / hovering and cruising is considered.

This invention discloses a ducted rotor for unmanned aerial vehicles (UAVs) and its manufacturing process, belonging to the technical field of ducted rotors for UAVs. The invention includes a shell and a rotor. The rotor includes an inner annular wall, the lower part of which protrudes outward to form an outer annular wall, forming a Z-shaped structure between the inner and outer annular walls. Permanent magnets are circumferentially laid on the inner side of the outer annular wall. A stator is connected to the shell and placed inside the outer annular wall, corresponding to the permanent magnets. It also includes several rotor blades, circumferentially connected to the inner annular wall at equal intervals. This invention employs a Z-shaped rotor structure and a carbon fiber integrated molding process. The resistance to torsion is no longer solely based on the rotor's axial thickness, but rather on a right-angled triangular diagonal support formed by the height and radial difference, reducing the possibility of loosening and breakage at rotor connection points.