32 results about "Folding propeller" patented technology

The invention provides a water-air two-domain self-adaptive state switching efficient propelling folding propeller, which comprises a propeller hub, a propeller blade, a propeller blade, a propeller blade and a propeller blade, the N fixed paddles are uniformly distributed on the side wall of the cylinder in the circumferential direction; the inner sides of the fixed paddles are fixedly connected with the outer surface of the side wall of the cylinder; the fixed blades are arranged along the water pushing direction; the outer side of the fixed paddle is bent upwards, and a connecting plate is arranged at the end part of the outer side; the N folding and unfolding paddles are correspondingly mounted at the outer ends of the fixed paddles, and each folding and unfolding paddle comprises a blade and a root ring fixedly connected with the root of the blade; the N rotating joints comprise pin shafts, and the pin shafts penetrate through the connecting holes and the root ring; wherein N is greater than or equal to 3; when the propeller hub rotates and is located above the water surface, the folding and unfolding blades are unfolded under the action of centrifugal force; and when the paddle is located below the water surface, the folding and unfolding paddle is folded under the action of water resistance. The efficient propelling folding paddle has sufficient propelling power in water and is high in water-air transition efficiency. The invention also provides an unmanned aerial vehicle equipped with the efficient propelling folding paddle.

The utility model discloses a folding paddle assembly and an unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles. The folding paddle assembly comprises a paddle blade, a paddle clamp, a wear-resistant part and an elastic part, the paddle blade comprises a mounting part and a main body part connected with the mounting part, the mounting part is rotationally connected to the paddle clamp, the wear-resistant part is clamped between the paddle clamp and the mounting part, and the elastic part is elastically supported between the wear-resistant part and the paddle clamp; a limiting structure is arranged at the position, close to the mounting part, of the main body part; when the paddle rotates relative to the paddle clamp, the limiting structure can abut against the paddle clamp so as to limit the rotation range of the paddle. According to the folding paddle assembly, the paddles are convenient to install, rotation of the paddles can be achieved without adjusting the locking force of the paddle clamps, the locking force is high and firm, and the problems that the paddles are prone to vibration and screws are loosened in the using process of the unmanned aerial vehicle are solved.

1. Name of the design product: Folding Propeller Protective Cover (5.2 inches). 2. Use of the design product: Prevent the propeller from being damaged and increase the propeller thrust at the same time. 3. Design key points of the design product: Lies in the shape. 4. Picture or photo that best shows the design key points: Perspective view 1.

1. Name of the product in this design: Paddle Clip (HEPF30). 2. Purpose of this design: For the fixed installation of folding propeller blades. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: 3D view 1.

The invention discloses a multi-rotor manned flight simulator based on a Stewart platform, and belongs to the technical field of rotor unmanned aerial vehicles. The multi-rotor manned flight simulator based on the Stewart platform comprises a rotor unmanned aerial vehicle body, the rotor unmanned aerial vehicle body comprises a rack, first servo motors and folding propellers, and four sets of servo motors are symmetrically and fixedly distributed on the side face of the rack; the three-degree-of-freedom parallel mechanism comprises a fixed platform, a movable platform and driving branch chains, the fixed platform is fixedly connected to the lower side of the rack, and the fixed platform and the movable platform are hinged through a plurality of driving branch chains; the driving branch chain comprises a second servo motor, a ball screw and a telescopic rod. The second servo motor is fixedly connected to the lower side of the fixed platform and connected with the ball screw through a coupler. And the manned cabin is rotationally connected to the lower portion of the movable platform and used for bearing passengers, and the stability and riding comfort of the cabin are remarkably improved by means of the active control characteristic of the Stewart platform.

The present invention provides a dual-rotor water-air amphibious drone with a wing-like electric eel structure, comprising a main body assembly, wherein the main body assembly includes a triangular bracket, a fuselage body, an electric eel drive mechanism, a rotating connector, a U-shaped slot, a wing-like electric eel structure, and a load platform. By arranging the wing-like electric eel structure on both sides of the fuselage body, the present invention enables the drone to enter and exit the water without an underwater propeller or mode switching. Furthermore, the structure has low motion energy consumption, enabling the drone to operate for long periods of time. The drone can flexibly switch between air and water modes, while also having superior performance such as ultra-quietness, high endurance, and high efficiency. The present invention utilizes a dual-rotor structure composed of a waterproof brushless motor, an output shaft, and a folding propeller assembly, and achieves attitude control through a front-to-back mounted tilt mechanism. The tilt mechanism deflects the rotor, and different tilt directions and tilt speeds can achieve different attitudes and movements, thereby enhancing attitude stability and motion control.

The invention relates to the technical field of ship propeller testing, in particular to an integrated testing device for a foldable propeller, which comprises a hollow propeller hub with a plurality of mounting holes uniformly distributed in the surface along the circumferential direction, and a folding device for the propeller is arranged in the hollow propeller hub. The folding device is correspondingly connected with blades extending out of the hollow propeller hub through each mounting hole, an energy recovery device integrally connected with the folding device is arranged in the propeller hub transition section, and the propeller hub transition section is connected with a load testing device through a fixing frame transition section. The propeller folding device, the load testing device and the energy recovery device are integrated into a whole, the trim angle of the folding propeller is adjustable, hydrodynamic testing is carried out in different tilt angle states, and the hydrodynamic testing range is widened. In the propelling process of the propeller, kinetic energy is converted into electric energy and stored, energy recovery and power generation are achieved, and the application potential and value of the foldable propeller are greatly expanded.

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 invention relates to an electric short-distance take-off and landing double-wing aircraft which comprises an aircraft body, wings and a lift augmentation power assembly. The wings comprise an upper wing, a lower wing and a vertical fin, one ends of the upper wing and the lower wing are connected through the vertical fin, the upper wing and the lower wing are equal in chord length, and the ratio of the chord length to the distance between the upper wing and the lower wing is 0.8; the high lift power assembly comprises a folding propeller, a driving motor and a slotted flap. The range extending power system comprises a variable pitch propeller, a fuel engine, a motor, a power conversion unit and a storage battery; the folding propellers are mounted at the front edges of the wings; the fuel engine is connected with the variable-pitch propeller, and the motor is connected with the variable-pitch propeller and the power conversion unit. Compared with the prior art, performance breakthrough is achieved through oil-electricity hybrid power; on the premise of not excessively increasing the extension length of the wings, the lift force is directly increased by increasing the total area of the wings through the double-layer wings, and the infiltration area of the aircraft is reduced by adopting the canard wings to carry out large-attack-angle longitudinal control.

The utility model provides a high-aspect-ratio vertical take-off and landing fixed-wing unmanned aerial vehicle easy to store, which comprises a vehicle body, canards arranged on the left side and the right side of the front part of the vehicle body respectively, main wings arranged on the two sides of the rear part of the vehicle body respectively, ailerons arranged on the rear sides of the main wings, and vertical wings arranged on the upper side and the lower side of the rear part of the vehicle body respectively. A folding propeller adjacent to the aircraft body is arranged on the front side of the main wing, and the section, away from the aircraft body, of the main wing can be folded and retracted in a swinging mode twice and can be unfolded. The section, away from the aircraft body, of the aileron and the section, corresponding to the main wing, of the aileron can synchronously achieve swing folding and unfolding, and the section, away from the aircraft body, of the vertical wing can be folded in the direction of the main wing and can be unfolded. On the basis that the unmanned aerial vehicle is small in occupied space after being folded and stored, the unfolding length of the main wing can be increased, then the aspect ratio of the unmanned aerial vehicle can be increased, and the cruising ability of the unmanned aerial vehicle can be improved by increasing the aspect ratio of the unmanned aerial vehicle.

The invention relates to a lifting body single-motor contra-rotating propeller helicopter, which belongs to the technical field of helicopters, and comprises a double-wing same-motor-shaft propeller mechanism, the double-wing same-motor-shaft propeller mechanism comprises a helicopter middle shaft, a parachute launching mechanism and a cabin, lifting body wings are arranged at the lower parts of the two sides of the cabin, and a lifting adjusting mechanism is arranged at the tail part of the cabin; a counter-rotating motor is arranged on a middle shaft of the helicopter; the parachute launching mechanism comprises a parachute bag, a parachute and an interlayer high-pressure air bag are arranged in the parachute bag, the parachute is provided with a first inflatable flexible framework, and the first inflatable flexible framework is connected with a high-pressure air cylinder; the lifting adjusting mechanism comprises an elevator, and a propelling device is arranged on the elevator. The helicopter has the beneficial effects that 1, the contra-rotating motor can realize the direction adjustment of the helicopter; 2, the inflatable flexible framework of the parachute is quickly inflated, so that the safety of the helicopter is ensured; and 3, the problem of heavy-load flight is solved by overlapping the fan-shaped blades of the reverse folding propellers and the ducted fan.

The invention discloses a high-speed helicopter rotor mode conversion mechanism which comprises a main shaft, a propeller hub fixedly arranged on the main shaft in a sleeving mode and a plurality of rotor modules evenly arranged in the circumferential direction of the propeller hub, each rotor module comprises a folding propeller hub rotationally connected with the propeller hub and a propeller clamping piece connected with the folding propeller hub through a universal cross shaft, and the propeller clamping pieces are used for fixing propeller blades; a folding base sleeves the propeller clamping piece, an auxiliary connecting rod is hinged to the folding base, a main connecting rod is hinged to the other end of the auxiliary connecting rod, the main connecting rod is hinged to the propeller hub, the folding driving module drives the main connecting rod to rotate relative to the propeller hub and drives the propeller clamping piece to rotate relative to the folding propeller hub, and folding of the propeller blades is achieved; the folding propeller hub is fixedly connected with a variable-pitch block, the steering engine drives the folding propeller hub to rotate relative to the propeller hub through the connecting rod structure and the variable-pitch block, and variable pitch of the propeller blades is achieved. The universal joint is added to separate the folding function and the pitch changing function, the folding function and the pitch changing function do not influence each other, the propeller pitch can still be adjusted to the position with small resistance in the folding process, and the folding difficulty is greatly reduced.

The invention discloses an umbrella-shaped folding ground effect aircraft which comprises an umbrella-shaped folding propeller made of flexible materials or rigid materials, a main driving device is installed on propeller blades, and blade connecting and fixing rings supported by elastic frameworks are arranged on the outer sides of the propeller blades, or rigid multi-wing centrifugal machine fan-shaped blade connecting and fixing rings are arranged on the inner sides and the outer sides of the propeller blades. The connecting and fixing ring blade is provided with a groove type jet engine nozzle or an electric rotor wing type auxiliary driving device, the multi-wing centrifugal machine fan-shaped blade connecting and fixing ring is conical, the conical centrifugal machine fan-shaped blade connecting and fixing ring is connected with a turbine pump or a center shaft, and the propeller blade is connected with an upper tray and a lower tray of the center shaft through an umbrella type framework. A turbine pump or other energy supply devices are installed on the center shaft, a safety air bag is arranged on the lower portion of the lower tray, the center shaft is connected with a load cabin, a tail vane of the load cabin is a telescopic rod, and a pushing device for controlling the direction such as a jet engine or an electric rotor wing is installed at the tail of the telescopic rod.

The present invention relates to a propeller device of an airborne mobile body, which is arranged to fold the propeller when the airborne mobile body falls, thereby preventing additional accidents caused by fragments resulting from the propeller hitting the ground, and enabling the propeller to be reused by unfolding the folded propeller after the airborne mobile body lands.

The invention belongs to the technical field of aircrafts, and particularly relates to a folding propeller with conformal propeller blades and propeller hubs, which is characterized in that the center-of-gravity position of each propeller blade is set, and the mass of each single propeller blade and the distance from the center-of-gravity of each propeller blade to the rotation center are designed; the aerodynamic force thrust and the component force in the negative direction of the normal of the centripetal force of the propeller blade are equal and opposite in direction, so that the blade deformation caused by the thrust is compensated, the center line of the propeller blade can coincide with the rotating plane, and at the moment, the propeller blade and the propeller hub form a complete integrated propeller. According to the folding propeller, the appearance and the structure of the propeller blades are designed, so that the gravity center deviates from a rotating plane and deviates towards the thrust direction by a certain distance, the axial aerodynamic force and the axial component force of centrifugal force borne by the propeller blades during rotation are balanced, the folding propeller is in a design point state during working, the efficiency of the propeller is improved, and the propeller is more stable during rotation.

The invention relates to the field of paddle forming molds, in particular to a folding propeller paddle forming mold and a using method thereof.The forming mold comprises an upper mold base and a lower mold base, multiple sets of cavities are formed in the upper end of the lower mold base side by side, and each set of cavities comprises a pair of paddle cavities arranged in a central symmetry mode; the blade cavities in each group are communicated through a first channel, a second channel is arranged on the surface of the lower die base, control bases used for controlling the opening and closing states between the first channel and the second channel are arranged at the two ends of the second channel, a connecting channel is arranged in the center of each control base, and one end of each connecting channel is communicated with the corresponding first channel. Multiple groups of paddles can be synchronously formed, the hot press forming efficiency is improved, the forming process is based on the same molten flowing resin, it is guaranteed that the forming environments of the left paddle and the right paddle are the same, then it is guaranteed that the structural strength of the left paddle and the structural strength of the right paddle are highly consistent, and the situation that use is affected due to the paddle strength difference is avoided.

The application discloses a dual-speed-ratio water-air dual-purpose power device, which mainly comprises a power input device, a rotating speed switching device and a paddle. The power input device provides power in a high rotating speed and low torque state under different media, and the rotating speed switching device converts the power input into torque meeting the requirement of the medium under different media through a one-way bearing and a planetary reduction mechanism. When the power unit is in the air, the planetary reduction mechanism loses the effect, the output of the rotating speed switching device is equal to the rotating speed and torque of the power input device, when the power unit is in the water, the planetary reduction mechanism operates, the output rotating speed of the rotating speed switching device is less than the rotating speed of the power input device, and the output torque of the rotating speed switching device is greater than the torque of the power input device. The output shaft of the rotating speed switching device drives a passive folding propeller to provide power, and the passive folding propeller is passively stretched and folded according to the rotating speed and the different media, so that the efficiency under different media is ensured.

A propeller with folding blades for the propulsion of a mobile vehicle inside a fluid is provided having a movement mechanism rotatable around a central rotation axis of the propeller; and a plurality of blades. Each blade has a root end connected to the movement mechanism by a gear to allow the movement of the blade from an opening position to a closed position and vice versa, wherein in the closed position the plurality of blades are configured to form a continuous solid in the form of a spindle wherein a leading edge of a first blade (S′) is configured to osculate a trailing edge of a second blade following the first blade (S′) in such a way as to form a continuous surface between the first blade (S′) and the second blade (S″).

A propeller folding device for an aerial vehicle that unfolds or folds propeller blades according to the flight state of the aerial vehicle. The propeller blades are efficiently used according to the flight state of the aerial vehicle. The energy efficiency and ferry range of the aerial vehicle are improved.

Foldable propeller for air mobility, wherein the foldable propeller includes: a shaft (100) with a hub (500) at an upper end section of the shaft (100); Blades (700), each of which is attached to the hub (500) via a rotating shaft (710) in order to be rotated with the hub (500) or to be rotated relative to the hub (500); a movable section (300) which is slidably mounted on the shaft (100); and a link arrangement (900) with a plurality of links (910, 920, 930, 940) connecting the movable section (300) and the vane blades (700) and enabling the vane blades (700) to be rotated around the hub (500) while the movable section (300) slides along the shaft (100) such that the vane blades (700) are folded towards each other or folded away from each other, wherein the plurality of members (910, 920, 930, 940) comprises a first member (910) and a second member (920), and wherein a first end section of the first member (910) is pivotably connected to the movable section (300) and a first end section of the second member (920) is pivotably connected to a point on the shaft (100) between the movable section (300) and the hub (500).

The invention discloses a driving device for a folding propeller of an unmanned aerial vehicle, and relates to the technical field of propellers, the driving device comprises blades, a first folding assembly, a second folding assembly and a propeller arm folding mechanism, the first folding assembly comprises a rotating shaft, an H-shaped frame, a mounting block, a lower clamping arm and an upper clamping arm, and the blades are fixedly mounted between the upper clamping arm and the lower clamping arm; a first folding driving part is arranged between the lower clamping arm and the H-shaped frame; the first folding driving part drives the paddle to be adjusted from a horizontal state to a vertical state; the second folding assembly comprises a mounting flange and a clamping cylinder, a second folding driving part is arranged between the clamping cylinder and the mounting flange, and the second folding driving part drives the rotating shaft to be adjusted to the horizontal state from the vertical state; the paddles are sequentially adjusted to be in the vertical state and the horizontal state through the first folding assembly and the second folding assembly, then the paddles are combined with the paddle arm folding mechanism to be recycled to the edge of the rack, and finally the space occupancy rate after the paddles are folded is further reduced through the dislocation mechanism.

The invention relates to a folding propeller assembly and an unmanned aerial vehicle. The folding propeller assembly comprises a propeller clamp and a propeller, the paddle is rotatably clamped between the paddle clamps so as to selectively have a folding position and an unfolding position; the adjusting assembly is arranged between the paddle and the paddle clamp and is used for dynamically adjusting the clamping force of the paddle clamp to the paddle; wherein the adjusting assembly comprises a hollow air bag structure, and the hollow air bag structure is used for providing elastic clamping force for the paddle; or the adjusting assembly comprises a magnetic piece, and the magnetic piece is used for providing magnetic clamping force for the paddle. According to the technical scheme, the rotating friction force of the paddles can be adjusted in a unified mode through the folding paddle assembly.

The invention discloses folding propeller machining equipment and a machining process based on an unmanned aerial vehicle, and belongs to the technical field of machine tool machining, the folding propeller machining equipment comprises a machine tool, the machine tool is provided with a spindle head and a fixing tool, the bottom of the spindle head is provided with a tool bit, and the spindle head is further provided with a damping mechanism. In the machining process, the clamping head synchronously moves along with the tool bit, when the fixing tool rotates, the clamping head can guarantee the clamping effect on the propeller, dynamic clamping close to the tool bit in the propeller machining process is achieved, the fixing and supporting effects on a propeller machining area are improved, vibration is reduced, and the machining efficiency is improved. Meanwhile, through the elastic force of a spring between a telescopic seat and a rotating seat and the elastic force of a spring between a first sliding block and a main shaft head, vibration generated during machining of the propeller clamped by the clamping head can be further restrained and reduced through the damping effect, and vibration generated in the milling machining process of the propeller is effectively reduced; and the overall machining precision and the product quality are improved.

The invention provides an automatically-unfolded folding propeller and an unmanned aerial vehicle, the automatically-unfolded folding propeller comprises a propeller body and a torsion component, the propeller body comprises a fixed propeller base and propeller blades, the propeller blades are fixed in the fixed propeller base, the torsion component comprises a torsion spring assembly, and the torsion spring assembly is fixed in the fixed propeller base. The torsional spring assemblies are arranged at the two ends of the fixed propeller base and connected with the propeller blades, stop blocks are arranged at the roots of the propeller blades, a baffle matched with the stop blocks is arranged on one side of the fixed propeller base, and when the automatic unfolding folding propeller is in an automatic unfolding state, the stop blocks are connected with the baffle in an abutting mode. The concealment is good, and the universality is high.

The utility model discloses an aircraft folding type propeller mechanism and an aircraft. The aircraft folding type propeller mechanism comprises a rotating shaft, a driving part, a first propeller, a second propeller and a limiting assembly. The driving piece is connected with one end of the rotating shaft; the first propeller comprises a first propeller hub and a first propeller blade which are connected, the first propeller hub is fixedly connected to the rotating shaft, and a thrust groove is formed in the side, away from the driving piece, of the first propeller hub; the second propeller comprises a second propeller hub and a second propeller blade which are connected, the second propeller hub is movably arranged on the rotating shaft in a sleeving mode and located on the side, away from the driving piece, of the first propeller hub, the second propeller hub is provided with a thrust block extending into the thrust groove in a protruding mode, and the thrust block and the thrust groove are matched to enable the second propeller blade to be in a folded state or an unfolded state relative to the first propeller blade; the limiting assembly is arranged on the rotating shaft and located on the side, away from the first propeller hub, of the second propeller hub. According to the folding propeller mechanism of the aircraft, the resistance of the aircraft in the flight process is reduced, and the flight performance of the aircraft is improved.

1. Name of the Design Product: Folding Propeller Blade (5.2 inches). 2. Use of the Design Product: Provide forward power for ships or water products by rotation. 3. Design Key Points of the Design Product: Lies in the shape. 4. Picture or Photograph that Best Illustrates the Design Key Points: 3D View 1.

The utility model relates to the technical field of testing devices, and discloses a simple folding propeller tension and power testing device which comprises a first fixing frame and a second fixing frame, the top end of the first fixing frame is provided with a tension tester, the inner side of the first fixing frame and the inner side of the second fixing frame are fixedly connected with transverse plates, and the transverse plates are fixedly connected with the first fixing frame and the second fixing frame. A plurality of folding assemblies are arranged between the side end of the bottom of the first fixing frame and the side end of the bottom of the second fixing frame, the top end of each folding assembly is provided with a limiting assembly used for fixing the corresponding folding assembly, and a translation assembly is arranged between the side end of the top of the first fixing frame and the side end of the top of the second fixing frame. According to the propeller tension and power testing device, through the arrangement of the folding assembly, the limiting assembly and the translation assembly, folding of the propeller tension and power testing device is achieved, the overall size of the testing device is reduced, the propeller tension and power testing device is convenient to carry by people, and the working efficiency is improved.

The present application discloses a foldable propeller mechanism for an aircraft and an aircraft. The foldable propeller mechanism for an aircraft includes a rotating shaft, a driving member, a first propeller, and a second propeller; the driving member is connected to one end of the rotating shaft; the first propeller includes a first hub and a first blade connected to each other, the first hub being fixedly connected to the rotating shaft, a thrust groove being provided on the side of the first hub facing away from the driving member, the bottom of the thrust groove having a first thrust surface arranged at an angle; the second propeller includes a second hub and a second blade connected to each other, the second hub being movably sleeved on the rotating shaft and located on the side of the first hub facing away from the driving member, a thrust block protruding from the side of the second hub facing the first hub and extending into the thrust groove, the thrust block and the thrust groove cooperating to enable the second blade to be in a folded state or an unfolded state relative to the first blade. The above-mentioned foldable propeller mechanism for an aircraft reduces the resistance of the aircraft during flight and improves the flight performance of the aircraft.

The present application relates to the field of paddle forming die, especially to a folding propeller paddle forming die and its using method, the forming die comprises an upper die seat and a lower die seat, the upper end of the lower die seat is provided with multiple groups of cavities side by side, each group of cavities comprises a pair of center-symmetrically arranged paddle cavities, the paddle cavities of each group are communicated through a first channel, the surface of the lower die seat is provided with a second channel, the two ends of the second channel are provided with control seats for controlling the opening and closing state between the first channel and the second channel, the control seat is provided with a connecting channel in the center, and one end of the connecting channel is communicated with the first channel. The present application can realize the synchronous forming of multiple groups of paddles, improve the efficiency of hot pressing forming, and ensure that the forming environment of the left paddle and the right paddle is the same based on the same molten flowing resin, thereby ensuring that the structural strength of the left paddle and the right paddle remains highly consistent, and avoiding the influence on use due to the strength difference of the paddles.

1. Name of the product in this design: Flat Paddle Mount (Dynamic Balance Adjustment Folding Mount). 2. Purpose of this design: An adjustable, dynamically balanced, folding propeller mount for model aircraft. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: 3D rendering 1.