42 results about "Folding propeller" patented technology

The invention provides a dual-rotor water-air amphibious unmanned aerial vehicle with a plume-like electric eel structure, which comprises a main body assembly, and the main body assembly comprises a triangular bracket, a fuselage main body, an electric eel driving mechanism, a rotary connecting piece, a U-shaped clamping groove, the plume-like electric eel structure and a load platform. According to the unmanned aerial vehicle, the line-like electric eel structures are arranged on the two sides of the fuselage main body, so that the unmanned aerial vehicle can enter and exit water without an underwater propeller or mode switching, and the structures are low in movement energy consumption, so that the unmanned aerial vehicle has the capability of working for a long time and can be flexibly switched between an air mode and a water mode; meanwhile, the system has excellent performances such as ultra-silence, high endurance and high efficiency; according to the invention, the attitude control is realized through a double-rotor structure consisting of the waterproof brushless motor, the output shaft and the folding propeller assembly and through the tilting mechanisms which are mounted front and back, the tilting mechanisms enable the rotors to deflect, different attitudes and motions can be realized through different tilting directions and tilting speeds, and the attitude stability and the motion control are enhanced.

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.

The utility model provides a locking quick-release assembly and an unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles. The locking quick-release assembly comprises a fixing piece, the fixing piece comprises a first fixing part and a second fixing part fixedly connected with the first fixing part, a first containing groove is formed in the side face of the first fixing part, and a second containing groove communicated with the first containing groove is formed in the side face of the second fixing part; the inner wall of the first containing groove is used for wrapping the side face of the base, a buckle is arranged on a groove opening of the first containing groove and used for being connected with the side face of the base in a clamped mode so that the first fixing part can be fixed to the base, and the inner wall of the second containing groove is used for wrapping the side face of the folded propeller so that the propeller can be prevented from rotating and unfolding. The locking quick-release assembly can lock the arms of the unmanned aerial vehicle body and the folded propellers at the same time, so that the carrying convenience and efficiency of the unmanned aerial vehicle body are remarkably improved. While the stability and the safety are ensured, the convenience of mounting and dismounting is also obviously optimized, and the manufacturing cost is reduced.

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 present invention relates to an amphibious and airborne aircraft, wherein the main support is divided into an upper frame, and propeller compartments for placing a folding propeller assembly are provided at the front and rear ends of the upper frame, and a parachute compartment is provided between the folding propeller compartments; a control room for driving and carrying passengers and cargo is provided at the front section of the lower frame, and wing compartments for placing a telescopic folding wing assembly are provided at the two sides of the middle and rear sections of the lower frame, and storage rooms are provided at the rear of the two sides of the rear section of the lower frame, and a comprehensive room is provided between the storage rooms, and an airbag room for placing an airbag retracting and releasing system is provided in the middle below the lower frame; the folding propeller assembly is installed on the main support; the telescopic folding wing assembly is symmetrically installed on both sides behind the main support through a connecting structure, and running wheels are provided below the main support. The structure is compact, can travel and park on the ground and water, can take off and land vertically on the ground and water, can be deformed in the air, and is an electric aircraft with a certain load, long endurance, and safe flight.

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 disclosure provides an electric propulsor. The electric propulsor has a propeller having a hub and blades extending from the hub. The blades are movable along respective flapping axes between a deployed position and a stowed position. The electric propulsor also has an actuator and an electric motor coupled with the hub and arranged to rotatably drive the propeller. Further, the electric propulsor has one or more processors configured to: receive an input indicating an azimuthal position of the blades; control the electric motor to align the blades with a target azimuthal position based at least in part on the input; and with the blades of the propeller arranged at the target azimuthal position, cause the actuator to translate a control rod coupled thereto and with the hub to actively fold or unfold the blades along the respective flapping axes of the blades.

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.

An unmanned aerial vehicle including a propeller blade and a central hub. The propeller blade includes a hole, and a connector located at a root of the propeller blade, the connector including a projection and a shoulder. The central hub includes an opening configured to receive the projection; a portion of a face, wherein the shoulder engages with the portion of the face in a first rotational position of the propeller blade and holes. The holes of the propeller blade and the central hub are concentric so that the propeller blade is movably connected to the central hub via the holes.

The utility model relates to the technical field of four-rotor aircrafts, in particular to a transverse folding type four-rotor aircraft which comprises a main machine body, the main machine body is provided with two vertically-through channels, the end of each channel is provided with a sliding arm in a matched mode, and the end, corresponding to the center of the main machine body, of each sliding arm is provided with a control head; a sliding arm control panel is arranged in the center of the main machine body and provided with control sliding rails corresponding to the control heads. Each rotor arm is hinged to the free end of the sliding arm, the free end of each rotor arm is vertically provided with an undercarriage, the top end of each undercarriage is provided with a folding paddle, each rotor arm is internally provided with a rotor motor, and each rotor motor is electrically connected with the flight control module. In the contraction state, the undercarriage of the aircraft is attached to the edge of the main machine body, and the folding paddles are attached to the adjacent rotor arms, so that the aircraft is stored, the occupied space is small, and convenience is provided for transportation and use.

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 utility model belongs to the technical field of unmanned aerial vehicle propeller manufacturing equipment, and particularly relates to a carbon fiber composite material folding propeller forming mold which is characterized in that an upper mold and a lower mold are detachably connected, and mold lifting grooves are formed in the upper mold and the lower mold; an upper section mold cavity is formed in the upper mold, a lower section mold cavity is formed in the lower mold, a glue flowing groove matched with the lower section mold cavity is formed in the lower mold, a reserved mold taking hole is formed in the lower mold, and a movable pin shaft is arranged in the reserved mold taking hole; the upper mold and the lower mold are matched to form a joint line, the edge height of the mold cavity of the lower mold is not higher than that of the joint line, a glue overflowing seam is generated, and the glue overflowing seam is communicated with the interior of the glue flowing groove, the interior of the upper section mold cavity and the interior of the lower section mold cavity.

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.