Automatic pitch-adjustable propeller adjustment component and assembly method

Abstract

A propeller adjustment component capable of automatically adjusting pitch and an assembly method thereof, wherein the hub seat of the propeller adjustment component capable of automatically adjusting pitch can be rotatably connected to a central shaft, the side of the hub seat is evenly distributed with two or more mounting holes, an angle adjustment component is arranged in the hub seat, a blade component can be rotatably mounted at the mounting hole through the angle adjustment component, and the axis of the mounting hole intersects the axis of the central shaft perpendicularly. The present invention does not require perforating a power system or a main shaft, can directly match the installation method of an existing propeller, has the characteristics of few parts, easy processing, low manufacturing cost, and maintenance-free.

Description

Technical Field

[0001] The invention belongs to the technical field of aviation and shipbuilding, and in particular relates to a propeller regulating component and an assembly method. Background Art

[0002] Propellers are commonly used in aviation, navigation and other fields. The main shaft of the power system rotates, driving the blades to rotate through the transmission system. The inclined surface of the blades moves the fluid to generate thrust by reaction, making the aircraft or ship move forward. A propeller is generally composed of multiple spiral blades and a hub, also known as a propeller.

[0003] When the propeller blade speed is fixed, the corresponding forward speed is different, resulting in different thrusts, so the power of the power system cannot be used to the maximum efficiency. Therefore, in areas with high propeller efficiency and strong maneuverability, variable pitch propeller devices are used, such as helicopter main propellers. The adjustable pitch propeller adjusts the blade pitch in real time, so that the propeller can achieve the best power output effect under different working conditions.

[0004] The general propeller adjustment assembly usually includes an adjustment rod, a transmission assembly and a control device. For example, the main propeller of a helicopter needs to be installed with an adjustment rod on the outside of the main shaft, which not only generates more air resistance, but also cannot be completely sealed, and is not suitable for use on ship propellers in underwater working environments. Some ships and fixed-wing aircraft variable pitch propeller mechanisms require a through hole to be set in the middle of the main shaft. The through hole runs through the entire main shaft, and bearings, adjustment rods, forks and transmission assemblies are set in the through hole. The adjustment rod is controlled by a complex structure such as a hydraulic adjustment device or an electric adjustment device to achieve blade pitch adjustment. Due to the high strength of the main shaft design, the middle perforation processing is difficult, and the through hole in the center of the shaft will reduce the strength of the shaft, requiring the diameter of the shaft to be increased, resulting in an increase in weight. The transmission control systems such as the electronic control system and the gearbox system have complex structures, high failure rates, and high manufacturing costs, which greatly increase the management difficulty and use cost of machinery and equipment. Summary of the invention

[0005] The purpose of the present invention is to solve the technical problems existing in the prior art and to provide an automatically adjustable pitch propeller adjustment component. The present invention does not require drilling holes on the power system or the main shaft, can directly match the installation method of the existing propeller, has the characteristics of few parts, easy processing, low manufacturing cost, and maintenance-free.

[0006] Another object of the present invention is to provide a method for assembling an automatically adjustable pitch propeller adjustment assembly.

[0007] The technical solution of the present invention is: an automatically adjustable pitch propeller adjustment component, the middle part of the hub seat can be rotatably connected to the central axis, the side of the hub seat is evenly distributed with more than two mounting holes, the hub seat is provided with an angle adjustment component, the blade assembly can be rotatably mounted at the mounting hole through the angle adjustment component, and the axis of the mounting hole intersects the axis of the central axis perpendicularly.

[0008] The blade assembly includes a blade and a blade chuck, the blade is mounted on the outside of the blade chuck, the blade chuck is a rotating body, and an eccentric cylindrical boss is eccentrically arranged on the end face inside the blade chuck; the angle adjustment assembly includes a nut (i.e., a polygonal nut) threadedly connected to the external thread in the middle of the central shaft, and there are more than two adjustment grooves around the nut corresponding to each blade assembly one by one; the eccentric cylindrical boss of each blade chuck is inserted in each adjustment groove.

[0009] The eccentric cylindrical boss of each blade chuck is inserted into each adjustment groove through a slider sleeve; the slider sleeve and the adjustment groove are clearance-matched; there are also small bosses around the nut that are parallel to the axial positioning surface of the blade chuck, and the plane where the small bosses are located is parallel to the central axis of the nut, and the number of small bosses corresponds one-to-one to the adjustment groove.

[0010] The center shaft is a stepped shaft, and a fixing hole is provided in the center of the center shaft for installing the center shaft bolt after being connected to the main shaft; the center shaft is rotatably connected to the center hole of the hub seat via an axial bearing, and an adjusting screw is sleeved in the middle of the center shaft, and the thread of the outer circle of the adjusting screw forms the outer thread in the middle of the center shaft; the purpose of setting the adjusting screw is to increase the versatility of the center shaft parts, and changing the pitch and stroke here can be achieved by simply replacing the small part of the adjusting screw, and the processing cost is lower.

[0011] The lower part of the adjusting screw is inserted into the notch at the waist of the central shaft through the lower gasket, and the upper gasket used for limiting the stroke of the nut is sleeved on the central shaft at the upper end of the adjusting screw; the adjusting screw, the lower gasket and the upper gasket are all located in the propeller hub seat;

[0012] The propeller hub seat is divided into two parts, the upper propeller hub seat and the lower propeller hub seat are both provided with a center hole for coaxial assembly, and the upper / lower propeller hub seat is evenly divided into two or more semicircular grooves in the circumferential direction; when the upper and lower propeller hub seats are relatively combined, each semicircular groove is combined into a plurality of complete mounting holes;

[0013] The axial bearing includes a tapered roller bearing installed at the center hole of the lower hub seat and an ultra-thin bearing installed at the center hole of the upper hub seat. The large diameter outer circle of the central shaft is matched with the inner diameter of the tapered roller bearing, and the inner diameter of the ultra-thin bearing is sleeved on the small diameter of the central shaft.

[0014] The blade clamp has a notch on the outside of the blade clamp, and the blade fixing end of the blade is mounted on the notch on the blade clamp of the blade clamp; a radial bearing is mounted near the inner side of the outer wall of the blade clamp, and the outer ring of the radial bearing cooperates with the mounting hole; the radial bearing is a blade clamp thrust combination bearing, and a blade clamp sliding bearing is mounted on the outside of the blade clamp thrust combination bearing. The blade clamp sliding bearing plays a radial supporting role for the blade clamp and has a certain sealing role. The sliding bearing has a larger contact area than the needle bearing and can withstand greater impact caused by radial vibration.

[0015] The middle part of the slider sleeve is a cylindrical cavity, and the outer side of the slider sleeve is a quadrangular prism structure. The slider sleeve is made of wear-resistant material.

[0016] The blade assembly includes a blade and a blade clamp, and the blade is installed on the outside of the blade clamp; the angle adjustment assembly is a nut threadedly connected to the external thread in the middle of the central shaft, and the periphery of the nut is connected to the blade assembly via a transmission connecting rod assembly.

[0017] A flexible connecting piece is provided between the central shaft and the hub seat.

[0018] The flexible connecting member includes a coil spring, which is accommodated in a hub pressure cover; the hub pressure cover is installed on the hub seat; a positioning hook is respectively provided on the inner ring and the outer ring of the coil spring, and the positioning hook of the outer ring of the coil spring is fixed in the outer groove of the hub pressure cover; the positioning hook of the inner ring of the coil spring is directly inserted into the positioning groove at the upper end of the central shaft; or the positioning hook of the inner ring of the coil spring is inserted into the positioning groove of the locking nut connected to the upper end of the central shaft, and the locking nut connected to the external thread of the upper end of the central shaft is placed outside the hub seat; the lower end of the locking nut abuts against the axial bearing at the center hole of the upper hub seat.

[0019] A method for assembling an automatically pitch-adjustable propeller adjustment assembly comprises the following steps:

[0020] 1) Obtain the maximum torque parameter torque value n of the main shaft of the power equipment;

[0021] 2) Select the spring parts whose elastic deformation torque and effective number of turns include this torque value n;

[0022] 3) The middle part of the hub seat can be rotatably connected to the central axis, and there are more than two mounting holes on the side of the hub seat. There is an angle adjustment component in the hub seat. The blade assembly can be rotatably installed at the mounting hole through the angle adjustment component. The axis of the mounting hole intersects the axis of the central axis perpendicularly;

[0023] 4) A flexible connector is provided between the central shaft and the hub seat, and the flexible connector includes a coil spring, which is accommodated in the hub gland; the hub gland is placed on the hub seat; a positioning hook is provided on the inner and outer rings of the coil spring, respectively, and the positioning hook of the inner ring of the coil spring is inserted into the positioning groove at the upper end of the central shaft; the positioning hook of the outer ring of the coil spring is fixed in the outer groove of the hub gland;

[0024] 5) Specific setting method of the preload force of the coil spring: rotate the hub gland in the direction of the preload spring until the rotational torque brings the maximum torque value of the main shaft of the power equipment, and then reverse the number of turns m to obtain the preload force F of the coil spring, so that the hub gland is fixed to the hub seat through the gland bolts; the number of turns required for the corresponding center shaft to rotate when the nut of the angle adjustment assembly moves from the initial state to the target position along the middle external thread of the center shaft is m1, m= m1. When the torque difference between the main shaft of the power equipment and the hub seat is greater than the preload force F of the coil spring, the rotational torque first compresses the coil spring until it is compressed to the limit of the coil spring, and after the nut of the angle adjustment assembly moves to the limit position, the torque is transmitted to the hub seat. At this time, the propeller blades rotate with the hub seat, and the process of coil spring compression is the process of the blade pitch changing from the maximum pitch state to the minimum pitch state.

[0025] When the blade pitch needs to be locked at any position, remove the flexible connector and the hub gland, fix the lower hub seat of the hub seat and then rotate the center shaft. The blade chuck rotates along the mounting hole of the hub seat, and the blade pitch changes accordingly. When the blade pitch reaches the target pitch, stop rotating the center shaft, connect the middle part of the distance piece with the center shaft key or with the locking nut key on the center shaft, and align the mounting hole on the outside of the distance piece with the hole position of the hub seat, connect the distance piece to the hub seat and lock it, and the pitch locking is completed.

[0026] The first aspect of the present invention proposes a propeller adjustment component that can automatically adjust the pitch according to the load; the second aspect proposes a method for setting the propeller pitch adjustment torque; the present invention realizes that in the automatic variable pitch mode, at any speed of the main shaft, the propeller will automatically and steplessly adjust the pitch to achieve maximum output efficiency; when the pitch needs to be fixed, the pitch is quickly fixed to meet the needs of a fixed-pitch propeller.

[0027] According to the functional requirements of the first aspect of the present invention, the automatic pitch-adjustable propeller adjustment assembly includes: a central shaft, which looks like a stepped shaft, has an external thread on the small diameter side, a positioning groove on the middle shaft shoulder, and a fixing hole in the center of the shaft; the propeller hub seat is divided into an upper and lower part, the upper propeller hub seat and the lower propeller hub seat are both provided with a central hole for assembly with the central shaft, and the upper and lower propeller hub seats are both provided with a plurality of semicircular grooves equally divided in the circumferential direction, and the diagram of the present invention shows 3 semicircular grooves, but is not limited to three, and the upper and lower propeller hub seats are relatively merged so that the semicircular grooves are combined into a plurality of complete circular holes; a polygonal nut is arranged in the propeller hub seat, has a threaded interior, and has a small boss and a rectangular groove on the outer side; an adjustment The screw is provided with a center hole and is installed on the center shaft. A positioning groove is provided at the shaft end, and the outer circle is a thread that cooperates with the inner thread of the polygonal nut; the lower gasket of the adjusting screw has a center through hole that cooperates with the outer diameter of the center shaft, and bosses are provided on both end faces, which are respectively connected with the center shaft shoulder positioning groove and the adjusting screw positioning groove; the locking nut has an inner thread connected with the outer thread of the center shaft, one end is provided with a positioning groove perpendicular to the axis, and the maximum outer diameter part is the spline shaft; the coil spring has a diameter-direction bent positioning hook provided on the inner and outer rings respectively, and the inner ring positioning hook is inserted into the locking nut positioning groove; the hub pressure cover has a mounting hole provided on a part of the outer circumference, and the hollow circular cavity inside is used to place the coil spring. The blade chuck is a stepped shaft with a slot. The slot is used to clamp the blade, and the blade and the chuck are fixed together by bolts. An eccentric cylindrical boss is provided at the large diameter end of the chuck; the slider is a rectangular block with a central circular through hole part. The inner hole cooperates with the eccentric cylindrical boss of the blade chuck and can rotate, and the rectangular block can slide in the rectangular groove of the polygonal nut; the distance piece has a spline hole in the center, which can cooperate with the spline shaft of the locking nut, and is a plate-mounted part with a circumferentially processed mounting hole.

[0028] According to the first aspect of the present invention, the pitch-adjustable propeller adjustment assembly can automatically adjust the pitch of the propeller, and the following actions are performed: the center shaft is connected to the main shaft of the power machine through the fixing hole of the center shaft, and the three parts of the lower hub seat, the lower gasket of the adjusting screw, and the adjusting screw are installed axially in sequence, so that the bosses at the upper and lower ends of the lower gasket of the adjusting screw are respectively placed in the positioning grooves of the center shaft and the adjusting screw.

[0029] Slider sleeves are separately installed on multiple blade chucks. The diagram of the present invention shows three, but is not limited to three. Then the slider sleeve is placed in the rectangular groove of the polygonal nut so that the end face of the blade chuck is in full contact with the small boss of the polygonal nut, ensuring that each side of the polygonal nut has a corresponding blade chuck assembly. Then the above assemblies are placed in the upper hub seat so that the outer circle of the blade chuck is placed in the semicircular groove of the hub seat, and the inner spiral hole of the polygonal nut is coaxial with the center hole of the upper hub seat.

[0030] Install the upper propeller hub seat assembly equipped with the blade chuck into the center shaft along the axial direction. When the polygonal nut contacts the adjusting screw, it needs to be screwed in and installed in the direction of the spiral line until the end faces of the upper propeller hub seat fit together with the lower propeller hub seat and all the blade chucks fall into the semicircular groove of the lower propeller hub seat.

[0031] On the outside of the upper hub seat, screw the lock nut onto the center shaft, and then insert the inner ring positioning tongue-shaped hook of the coil spring into the positioning groove of the lock nut. The hub gland covers the outside of the coil spring, and fixes the outer ring positioning tongue-shaped hook of the coil spring into the outer groove of the hub gland.

[0032] When the automatic pitch-adjustable propeller adjustment assembly according to the embodiment of the present invention works, the main shaft of the device drives the central shaft of the device to rotate, and the torque is transmitted to the coil spring through the locking nut installed on the central shaft. At this time, if the resistance of the propeller is less than the torque of the main shaft, the propeller will rotate synchronously with the main shaft. At this time, the pitch of the propeller is the largest. The diagram of the present invention shows that the maximum pitch of the propeller top is 45° with the horizontal plane, but it is not limited to this angle, so as to achieve the maximum efficiency during high-speed cruising; the present invention automatically adjusts the blade pitch according to the wind resistance on the blade without increasing the mass of the moving parts, so that the projection area of ​​the blade in the vertical forward direction is set to the minimum, thereby reducing the speed change resistance of the main shaft, increasing the speed and improving the efficiency. When the power equipment of the traditional propeller increases the torque output instantly, commonly known as refueling, the main shaft speed cannot be increased immediately due to the resistance of the propeller during acceleration, resulting in the speed of the power equipment cannot be quickly increased to the high torque speed, resulting in a decrease in acceleration efficiency. The decrease in acceleration efficiency will bring two problems: 1. It takes more kinetic energy to reach the predetermined speed and consumes more fuel; 2. It takes longer time to reach the predetermined speed, and the maneuverability decreases. For example, an airplane requires a longer takeoff taxi runway. The resistance that the main shaft bears during the acceleration process comes from the following two points: 1. The mass of the moving parts, among which the mass of the propeller blade is the largest. The larger the mass, the greater the inertia, and the greater the kinetic energy required to change from low speed to high speed; 2. The projection area of ​​the blade perpendicular to the forward direction. The larger the projection area, the greater the wind resistance. The forward direction of the blade is changing, such as an airplane: the airplane does not move, and the concentric circles of the forward direction of the blade rotate; when the airplane is gliding at low speed on the ground, the forward direction of the blade moves in the direction of a small pitch spiral; when the airplane is flying quickly in the air, the forward direction of the blade moves forward in the direction of a large pitch spiral. The resistance generated by the above superposition will make the acceleration curve of the main shaft a slow climbing curve, so it takes a longer time to achieve the increase in speed. The present invention can absorb the instantaneous increase in the speed of the main shaft by the coil spring under this working condition of sudden acceleration, because the coil spring plays a role in making the hub seat and the central axis into a flexible state that can rotate relative to each other, and can realize the function of automatic return. Automatic return means that due to the acceleration process, the center shaft overcomes the force of the coil spring, and the coil spring will be compressed. At this time, the center shaft will rotate earlier than the hub seat, and the blades will change from a large pitch state to a small pitch state. At this time, the projected area of ​​the blade rotation direction is reduced. When the rotational resistance is reduced, the rotation speed of the blade and the hub seat gradually synchronizes with the center shaft. Under the action of the energy released by the coil spring, the hub seat will rotate faster than the center shaft, and the pitch of the blade will automatically recover from a small pitch state to a large pitch state.The coil spring automatically returns to its original state when it is not subjected to the external force of the main shaft, that is, the blade presents a large pitch angle state. Therefore, when the central shaft is driven by the main shaft to speed up, the central shaft overcomes the coil spring torque and rotates in advance, and drives the adjusting screw to rotate. At this time, the polygonal nut in the hub seat moves linearly along the axis along the spiral line of the adjusting screw. When the polygonal nut moves, the eccentric cylindrical boss of the blade chuck is driven to move in the axial direction through the slider sleeve in the rectangular groove. Since the hub chuck limits the direction of linear movement in the semicircular grooves of the upper and lower hub seats, it can only achieve rotational movement along the axis of the semicircular groove. Therefore, when the eccentric cylindrical boss of the blade chuck moves up and down, the blade chuck completes the coaxial rotational movement along the semicircular groove. The thread length of the adjusting screw is greater than the effective length and thickness of the polygonal nut thread. The difference in length determines the stroke of the polygonal nut that can be lifted and lowered, thereby also determining the range of the controllable rotation angle of the blade chuck in the semicircular groove. The diagram of the present invention shows that the minimum pitch of the top of the blade is 3°, but it is not limited to this angle, and the maximum torque during acceleration can be achieved. The automatic pitch-adjusting propeller adjustment assembly automatically adjusts the propeller pitch according to the torque and rotational resistance when working, and can automatically and continuously adjust without intervention, just like a CVT gearbox. This invention improves the efficiency of the propeller mechanism. On the basis of realizing the conventional variable blade pitch function, it eliminates the complex hydraulic and electrical adjustment devices, has a compact structure with fewer parts, optimizes the propeller installation space, and saves manufacturing costs. Since the automatic adjustment mechanism can be completely sealed and maintenance-free, it can be used in any environment.

[0033] According to the first aspect of the present invention, the automatic pitch-adjusting propeller adjustment assembly also includes a fixing bolt between the propeller blade and the blade clamp, which is used to position the blade in the notch of the blade clamp and keep it stable, while also satisfying the function of rapid blade replacement. When the blade clamp rotates along the axis of the central axis together with the hub seat, the blade can be driven to rotate together; when the blade clamp rotates along the axis of the semicircular groove, the blade is driven to adjust the pitch angle. A combined bearing is provided between the blade clamp and the semicircular groove of the hub seat to reduce the friction resistance during the pitch angle adjustment process.

[0034] According to the first aspect of the present invention, an automatic pitch-adjustable propeller adjustment assembly is provided, and bearings are respectively provided between the central shaft and the lower propeller hub seat and the upper propeller hub seat, the inner diameter of the bearing is in contact with the central shaft, and the outer diameter is in contact with the propeller hub seat, and a circular hole matching the size of the bearing is provided at the corresponding position of the propeller hub seat, so as to realize the relative rotation between the central shaft and the propeller hub seat and meet the axial positioning requirements.

[0035] According to the first embodiment of the present invention, the automatic pitch-adjustable propeller adjustment assembly is connected by bolts in the middle of the upper and lower hub seats, and the hub gland and the upper and lower hub seats are also connected by through bolts.

[0036] According to the first embodiment of the present invention, the pitch-adjustable propeller adjustment assembly can be automatically adjusted. One end of the adjusting screw is the adjusting screw lower gasket, and the other end is provided with the adjusting screw upper gasket. The distance between the upper and lower gaskets is set to the effective stroke of the polygonal nut. Therefore, if the angle range of the automatic pitch adjustment needs to be changed, it can be achieved by simply increasing or decreasing the length of the adjusting screw and the thickness of the upper and lower gaskets. Therefore, the present invention is very easy to match the needs of various pitch range adjustment working conditions and is widely applicable.

[0037] The method for setting the propeller pitch adjustment torque according to the second embodiment of the present invention comprises an adjustment device and the above-mentioned automatic pitch adjustment propeller adjustment assembly. The torque setting mainly depends on the position of the hub gland during installation and the pre-tightening torque of the coil spring. Operation method: 1. First obtain the maximum torque parameter of the main shaft of the power equipment; 2. Select the coil spring part with elastic deformation including the maximum torque; 3. Put the coil spring into the inner ring of the hub cover, and insert the tongue-shaped hook (i.e., positioning hook) of the outer ring of the coil spring into the positioning groove of the hub cover; 4. After aligning the positioning hook of the inner ring of the coil spring with the positioning groove of the locking nut, merge the gap between the hub cover and the upper hub seat. Merging means buckling the hub seat cover on the hub seat, fitting seamlessly; 5. Clamp the torque wrench on the hexagonal boss on the outside of the hub cover, rotate the hub cover in the direction of pre-tightening the coil spring until the rotational torque brings the maximum torque value of the main shaft of the power equipment, and then reverse the corresponding number of turns. The value of this turn is the number of threads of the adjusting screw minus the number of threads of the polygonal nut; 6. Use the gland bolt to pass through the hub cover mounting hole to completely fix it to the upper and lower hub seats, and the torque adjustment is completed.

[0038] The method for setting the propeller pitch adjustment torque described in the present invention has at least the following beneficial effects: by matching the original power system and selecting a coil spring with appropriate strength, a larger selection and adjustment space is achieved; whether the center shaft is installed on the main shaft does not affect the setting of the torque, there is no limitation on the working space, and the implementation is more convenient; during the adjustment process, a torque wrench is used to accurately apply the torque, and the adjusted torque position is maintained by using the installation hole position of the hub gland, which can achieve micro-adjustment capability and meet the purpose of setting various power output curve characteristics. The adjustment method is easy to implement, the operation steps are simple and reliable, and it has good controllability and stability.

[0039] The present invention can also achieve the locking of the pitch at any position. According to the device for locking the pitch at any position of the embodiment of the third aspect of the present invention, when a fixed-pitch propeller needs to be used for operation under specific working conditions, such as when used as a fixed-speed blower or a water pump, the installation of a matching positioning piece can easily complete the locking of the propeller pitch at any position. The method of use is to remove the hub pressure cover and the coil spring; rotate the hub seat to adjust the pitch of the propeller and reach the required state; align the spline hole of the positioning piece with the spline shaft outside the locking nut; fix the positioning piece to the hub seat with bolts, and the installation is completed. At this time, under the action of the connecting piece, the center shaft and the hub seat are effectively connected, and no relative rotation will occur, so the propeller pitch is locked. The pitch locking method is simple and efficient, with few and reliable operating steps, and is easy to implement with few tools. It has good controllability and stability, and further expands the application scenarios and scope of application of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] The above and / or additional aspects and advantages of the present invention will become apparent and easily understood from the description of the embodiments in conjunction with the following drawings, in which:

[0041] Figure 1 An exploded view of an automatic pitch-adjustable propeller adjustment assembly of the present invention;

[0042] Figure 2 It is an exploded view of the "paddle clamp" assembly of the present invention;

[0043] Figure 3 An exploded view of the "central axis" component of the present invention;

[0044] Figure 4 This is a schematic diagram of the detailed features of the "screw" part;

[0045] Figure 5 for Figure 4 Stereoscopic image of

[0046] Figure 6 This is a schematic diagram of the detailed features of the "lower gasket" part;

[0047] Figure 7 for Figure 6 Stereoscopic image of

[0048] Figure 8 This is a schematic diagram of the detailed features of the "polygonal nut" part;

[0049] Fig. 9 This is a schematic diagram of the detailed features of the "blade chuck" part;

[0050] Fig.10 It is one of the three-dimensional images of the lower propeller hub seat;

[0051] Fig.11 This is the second stereoscopic view of the lower propeller hub seat;

[0052] Fig.12 It is one of the cross-sectional views of the present invention;

[0053] Fig.13 This is the second cross-sectional view of the present invention;

[0054] Fig.14 This is a schematic diagram of the propeller pitch being adjusted to the limit state;

[0055] Fig.15 This is the second schematic diagram of the propeller pitch being adjusted to the limit state;

[0056] Fig.16 This is a schematic diagram of the appearance of the present invention in a state where the pitch can be automatically adjusted;

[0057] Fig.17 This is a schematic diagram of the appearance of the present invention in a locked pitch state;

[0058] Fig.18 It is a schematic diagram of the assembly of the coil spring, hub gland, lock nut and center shaft;

[0059] Fig.19 for Fig.18 A partial enlarged view of

[0060] Reference numerals: center axis 100; center axis waist notch 101; center axis thread 102; center axis bolt 200; tapered roller bearing 300; lower propeller hub seat 400; upper semicircular groove 401 of lower propeller hub seat; lower gasket 500; upper plane boss 501 of lower gasket; lower plane boss 502 of lower gasket; blade 600; blade fixed end 601; adjusting screw 700; end notch 701 of adjusting screw; polygonal nut 800; rectangular groove 801; small boss 802; inner thread 803 of polygonal nut; upper gasket 900; upper propeller hub seat 1000; super Thin bearing 1100; hub seat bolt 1200; locking nut 1300; coil spring 1400; hub pressure cover 1500; spacer 1600; cover bolt 1700; fairing 1800; propeller clamp sliding bearing 1900; propeller clamp thrust combination bearing 2000; blade clamp 2100; eccentric cylindrical boss 2101; notch 2102 on blade clamp; large hole 2103 on blade clamp; small hole 2104 on blade clamp; axial positioning surface 2105 of blade clamp; slider sleeve 2200; large propeller clamp bolt 2300; small propeller clamp bolt 2400. DETAILED DESCRIPTION

[0061] Embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and cannot be understood as limiting the present invention.

[0062] In the description of the present invention, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical axis", "horizontal axis" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention. In addition, features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0063] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0064] refer to Figure 1 , is an automatic pitch-adjustable propeller adjustment assembly of the present invention, including a center shaft 100, which is a stepped shaft structure, used to connect with the main shaft of the power system. The main shaft referred to in the present invention is a tapered shaft with an internal threaded hole, so the figures are all shown in the tapered shaft connection scheme, but are not limited to this connection method. The center shaft is a hollow shaft that is thick at the bottom and thin at the top. The following description is uniformly agreed that the small outer diameter points upward, the large outer diameter points downward, and the axis of the center shaft 100 is a vertical axis. The top of the center shaft 100 has an external thread 102, and the middle has a positioning notch 101. The fixing hole is used to install the center shaft bolt 200 after connecting with the main shaft. The main shaft refers to the rotating shaft connected to the present invention from a power device such as an engine or an electric motor. The function of the center shaft bolt 200 is to connect the present invention with the rotating shaft output by the power device.

[0065] The outer circle of the first step at the lower part of the central shaft 100 is matched with the inner diameter of the tapered roller bearing 300 for installation. The central shaft 100 penetrates the central hole from the bottom of the lower propeller hub seat 400 from bottom to top until the outer diameter of the tapered roller bearing 300 is placed in the lower annular groove of the lower propeller hub seat 400 to achieve radial positioning. The lower gasket 500 is sleeved on the small diameter end of the central shaft 100 and pushed downward along the vertical axis until the flat boss 501 on the lower gasket is stuck in the notch 101 at the waist of the central shaft to achieve synchronous rotation. After installation, it is ready for use.

[0066] refer to Figure 2 , assemble the blade clamp assembly, install the blade clamp thrust combination bearing 2000 and the blade clamp sliding bearing 1900 in the horizontal axial order on the blade clamp 2100, and install the blade clamp thrust combination bearing 2000 and the blade clamp sliding bearing 1900 at the three mounting holes on the side of the hub seat to meet the minimum movement resistance and appearance size. Then insert the blade fixing end 601 of the blade 600 into the notch 2102 on the blade clamp of the blade clamp 2100, so that the large hole on the blade fixing end 601 is aligned with the large hole 2103 on the blade clamp, and the small hole on the blade fixing end 601 is aligned with the small hole 2104 on the blade clamp, take the blade clamp large bolt 2300 and insert it into the large hole 2103 on the blade clamp in the vertical axis direction and lock it, take the blade clamp small bolt 2400 and insert it into the small hole 2104 on the blade clamp in the vertical axis direction and lock it, and the blade connection is completed. Connect the other blades in the same way and ensure that the directions of the blades are consistent.

[0067] refer to Figure 3-13, assemble the pitch adjustment motion assembly, take the adjusting screw 700, the adjusting screw 700 is coaxial with the central axis 100, and is connected through the lower gasket 500, so that the notch 701 on the end face of the adjusting screw is screwed into the internal thread 803 of the polygonal nut 800 in the downward vertical axis direction, and the notch is kept just screwed out of the position. Slide the slider cover 2200 on the eccentric cylindrical boss 2101 on the blade chuck, and then insert the slider cover 2200 into the rectangular groove 801 outside the polygonal nut. The slider cover 2200 is a wear-resistant material with a circular hole in the center and a rectangular outside. The outer rectangular height of the slider sleeve 2200 is basically equal to the height of the rectangular groove 801. The bottom of the eccentric cylindrical boss 2101 is chamfered. When the slider sleeve 2200 is sleeved on the eccentric cylindrical boss 2101, the end of the eccentric cylindrical boss 2101 is placed in the slider sleeve 2200. The outer end of the slider sleeve 2200 is clearance-matched with the bottom of the eccentric cylindrical boss 2101. The inner end of the slider sleeve 2200 corresponds to the bottom of the rectangular groove 801. The slider sleeve 2200 can slide left and right in the rectangular groove 801. After adjusting the direction, the end face of the blade chuck 2100 is completely in contact with the small boss 802 on the outer side of the polygonal nut. When the polygonal nut rotates on the central axis, the friction force will produce a rotation movement with the same trend, which effectively prevents the polygonal nut from rotating with the central axis and improves the transmission accuracy of the moving parts. The other several blade clamp assemblies are assembled in the same way and placed around the polygonal nut 800 on the same horizontal plane, with the blade clamp 2100 facing inward and the blades 600 facing outward in a radial shape. The adjustment slot 801 is a rectangular slot.

[0068] Pick up all the blade clamp components at the same time, and move the polygonal nut 800 to the small diameter end of the central shaft 100. Put the polygonal nut 800 on the central shaft 100 along the vertical axis direction, push it downward until the blade clamp thrust combination bearing 2000 falls into the upper semicircular groove 401 of the lower propeller hub seat, and adjust the screw end face notch 701 to clamp the two sides of the flat boss 501 on the lower gasket. Put the upper gasket 900 and the upper propeller hub seat 1000 on the central shaft 100 in sequence, and at this time the semicircular groove of the upper propeller hub seat 1000 is facing downward. Push them down together and make the upper propeller hub seat 1000 fit completely with the lower propeller hub seat 400, install and lock the propeller hub seat bolt 1200, and then the assembly drawing of the upper propeller hub seat 1000 and the lower propeller hub seat 400 is referred to as the propeller hub seat, and the semicircular groove axis is referred to as the horizontal axis. Take the ultra-thin bearing 1100 and put it on the small diameter of the central shaft 100, and push it into the center hole of the upper propeller hub seat 1000. After locking nut 1300 is screwed into central shaft thread 102 and locked, installation is completed. At this moment, both axial and radial directions of central shaft 100 have been positioned, and the single can rotate in the propeller hub seat.

[0069] At this working state, the central shaft 100 is rotated alone, and the support of the tapered roller bearing 300 and the ultra-thin bearing 1100 is excessive, and the hub seat may not rotate with it. However, after the central shaft 100 is rotated, the positioning of the central shaft waist notch 101 and the lower plane boss 502 of the lower gasket in the direction of rotation will drive the lower gasket 500 to rotate synchronously; similarly, the upper plane boss 501 of the lower gasket and the end face notch 701 of the adjusting screw are positioned in the direction of rotation, and the adjusting screw 700 will rotate synchronously. Since the adjusting screw 700 cooperates with the polygonal nut internal thread 803 of the polygonal nut 800, when the adjusting screw 700 rotates, the polygonal nut 800 will move up and down along the axis direction of the spiral line. Since the slider sleeve 2200 constrains the two parts, the rectangular groove 801 on the outer side of the polygonal nut and the eccentric column-shaped boss 2101 on the blade chuck in the up and down directions, the eccentric column-shaped boss 2101 on the blade chuck will obtain the force of moving in the same direction when the polygonal nut 800 moves. At the same time, the outer diameter of the blade clamp thrust combination bearing 2000 is covered by the semicircular groove 401 on the hub seat, and cannot move up and down, but can only rotate along the horizontal axis. Therefore, when the polygonal nut 800 moves, the eccentric column-shaped boss 2101 on the blade clamp will rotate along the axis of the thrust combination bearing 2000, that is, the horizontal axis, and the slider sleeve 2200 outside the eccentric column-shaped boss 2101 on the blade clamp will slide synchronously in the rectangular groove 801 of the polygonal nut 800, and always keep connected and limit the movement stroke of the eccentric column-shaped boss 2101 on the blade clamp. By continuously rotating the central axis 100, the blade clamp 2100 will continue to rotate along the horizontal axis, that is, the pitch adjustment is in progress. When the polygonal nut rotates on the central axis, it will produce a rotation movement with the same trend due to the action of friction. The complete contact between these two places can eliminate the gap between the parts, effectively prevent the polygonal nut from rotating with the central axis, and improve the transmission accuracy of the moving parts. One of the two places is the large plane of the blade clamp in the direction of the columnar platform, that is, the axial positioning surface 2105 of the blade clamp, and the other is the top surface of the small boss 802 of the polygonal nut. Fig.14 , 15 , until the polygonal nut 800 contacts the upper gasket 900, and the blade clamp 2100 reaches the limit position of pitch adjustment. The pitch adjustable range shown in the figure is that the angle between the lower plane of the blade 600 and the horizontal plane is between 3° and 45°, and the pitch adjustment range that can be achieved by the present invention is not limited to this. Continuously rotating the central shaft 100, after reaching the limit position of pitch adjustment, it will drive the hub seat to rotate together, and the blade 600 will rotate along the vertical axis together with the positive sleeve mechanism.

[0070] In the figure of the present invention, the internal thread 803 of the polygonal nut is a right-handed thread. When the central axis rotates clockwise at any time, the hub seat 400 does not move, and the polygonal nut 800 will move upward. The eccentric column-shaped boss 2101 on the blade clamp is set to the left side of the axis of the blade clamp thrust combination bearing 2000. Therefore, when the polygonal nut 800 moves upward, the eccentric column-shaped boss 2101 on the blade clamp will deflect upward with the slider sleeve 2200 at the same time, and the blade clamp 2100 also rotates clockwise along the horizontal axis. In summary, if the angle and direction of the pitch adjustment are to be changed, it is only necessary to control the angular velocity difference and rotation direction between the central axis 100 and the hub seat. Therefore, whether it is a thrust propeller or a pull propeller, it is only necessary to match the appropriate spiral rotation direction of the internal thread 803 of the polygonal nut and the direction of the eccentric column-shaped boss 2101 on the blade clamp during assembly. The present invention has a simple structure, is easy to assemble, is convenient to adjust, and is suitable for various types of propeller propulsion devices.

[0071] refer to Figure 1 , including all the parts involved in the method for setting the pitch adjustment torque of a propeller of the present invention, the coil spring 1400 is installed in the countersunk hole of the hub gland 1500, and the outer ring tongue of the coil spring 1400 is hooked in the positioning groove of the outer ring of the hub gland 1500 to ensure that they cannot rotate relative to each other. The inner ring tongue of the coil spring 1400 is hooked in the notch in the center of the locking nut 1300 to ensure that they cannot rotate relative to each other. Reference Figure 8 , use the cover bolts 1700 to completely fix the hub gland 1500, the upper hub seat 1000 and the lower hub seat 400. At this time, rotate the central shaft 100. If the torque is less than the preload force of the coil spring 1400, the rotational torque will be directly transmitted to the hub seat through the coil spring 1400, and the propeller blade 600 will rotate with the hub seat, and the pitch will not change; on the contrary, if the torque is greater than the preload force of the coil spring 1400, the rotational torque will cause the coil spring 1400 to deform elastically, and the angular velocity of the central shaft 100 and the hub seat will differ. The central shaft 100 will rotate an angle first and then the hub seat will start to rotate, and the aforementioned pitch adjustment action will occur. The blade 600 will automatically adjust the pitch until the torque of the central shaft 100 is balanced with the torque of the coil spring 1400 after compression, and the hub seat will rotate synchronously with the central shaft 100. It can be seen that the pitch adjustment torque can be set by only changing the preload force of the coil spring 1400.

[0072] The specific setting method of the preload force of the coil spring 1400 is to select the coil spring 1400 part whose elastic deformation torque and effective number of turns include this torque value by obtaining the maximum torque parameter of the main shaft of the power machine, put the coil spring into the inner ring of the hub gland 1500, and insert the positioning tongue-shaped hook of the outer ring of the coil spring 1400 into the positioning groove of the hub gland 1500, align the positioning tongue-shaped hook of the inner ring of the coil spring 1400 with the positioning groove of the center of the locking nut 1300, and close the gap between the hub gland 1500 and the upper hub seat 1000. Use a scaled torque wrench to clamp the hexagonal boss on the outside of the hub gland 1500, rotate the hub gland 1500 in the direction of preloading the coil spring 1400 until the rotation torque reaches the maximum torque parameter value of the main shaft, and use the torque wrench to rotate the hub gland 1500. As the deformation of the coil spring increases, the torque wrench will display the force value, and then reverse the adjustment screw 700 to work. Reverse retraction means that, for example, when a torque wrench is used to rotate clockwise at any time, the coil spring is tightened, and the reverse direction is the action of rotating counterclockwise; for example, the number of working turns is used to adjust the pitch of the blade from the minimum pitch state of 3° to the maximum pitch state of 45°, and the central axis 100 will rotate ≈1.33 turns. This 1.33 turns is the number of working turns, which is determined by the pitch of the thread on the adjusting screw 700 and the distance between the upper gasket 900 and the lower gasket 500. The smaller the thread pitch, the greater the number of working turns, and the greater the distance between the two gaskets, the greater the number of working turns. This turn value is the number of turns m obtained by subtracting the inner thread 803 of the polygonal nut from the number of turns of the adjusting screw 700. The number of turns m determines the reaction speed of the present invention when performing automatic pitch adjustment of the blade, which is somewhat similar to the number of gears on a car gearbox. The more working turns, the more gears, and the fewer working turns, the fewer gears. A power system with high torque can use fewer working turns, and a power system with low torque or low horsepower needs to match a mechanism with more working turns. Finally, the cover bolt 1700 is passed through the installation hole of the hub gland 1500 to completely fix it to the hub seat, and the torque adjustment is completed. The purpose of the reverse retraction number is to ensure that when the center shaft 100 reaches the maximum torque operation, the propeller blade 600 pitch just reaches the ideal small pitch position during acceleration ( Fig.15 3° position).

[0073] In the initial state of the invention, the propeller blades are at the large pitch state 45° position. When the torque difference between the power main shaft and the hub seat is greater than the preload force of the coil spring 1400, the rotational torque first compresses the coil spring 1400 until it is compressed to the coil spring limit or the polygonal nut contacts the upper gasket, and then transmits the torque to the hub seat. At this time, the propeller blades 600 rotate with the hub seat, and the pitch of the blades changes from a large pitch to a small pitch angle during the coil spring compression process. The pitch adjustment torque sets the target. When the central shaft rotates with high torque, the propeller blade 600 is at a small pitch angle, which can quickly increase the speed and achieve high engine speed and high torque, just like a car gearbox shifting to a low gear to climb a slope. When the propeller-propelled machine enters a fast moving state, the rotational resistance of the blade 600 is reduced. Under the action of the reverse torque of the coil spring 1400, the hub seat and the central shaft 100 will tend to be the same. When the torque difference between the main shaft and the hub seat is less than the compression deformation force of the coil spring 1400, the coil spring will release energy, which will push the hub seat to accelerate and drive the polygonal nut to rotate until the polygonal nut contacts the lower gasket. The process of the coil spring releasing energy is the process of the pitch of the blade changing from a small pitch to a large pitch angle. The propeller blade 600 automatically changes to a large pitch state to rotate during the adjustment of the pitch change mechanism, achieving low engine speed and high efficiency, just like a car gearbox shifting to a high gear and running at high speed. The automatic pitch adjustment process is automatically completed by relying on the torque setting of the coil 1400, the rotation speed of the center shaft 100, the forward speed of the machine, the resistance of the propeller blades 600, the load conditions, etc. No manual intervention is required during operation. Just like a CVT continuously variable transmission, the pitch adjustment is completed automatically throughout the entire process from the start of the center shaft 100 to the complete stop of the machine.

[0074] refer to Figure 1, including a device for locking the pitch at any position according to the third aspect of the present invention, the spacing piece 1600 is a plate-like structure, the center of which is a spline hole, which matches the spline shaft of the outer diameter of the locking nut 1300, and there are multiple positioning holes near the outer circle, which can be integrated with the hub seat by the cover bolt 1700. As mentioned above, the pitch adjustment is achieved by the angular velocity difference between the central shaft 100 and the hub seat. When the central shaft 100 and the hub seat are effectively fixed so that there is no angular velocity difference between them, the pitch locking can be achieved. The pitch locking operation method at any position is to remove the upper cover bolt 1700, the hub pressure cover 1500, and the coil spring 1400 of the present invention in sequence, fix the lower hub seat, manually rotate the central shaft 100, rotate the blade clamp 2100 horizontally, and change the pitch of the blade 600 accordingly. When the target pitch is reached, stop the rotation of the central shaft 100, put the spline hole of the spacer 1600 on the spline shaft of the locking nut 1300, and align the mounting hole on the outside of the spacer 1600 with the hole position of the upper hub seat 1000, connect the spacer 1600 with the hub seat with the cover bolt 1700 and lock it, and the pitch locking is completed. The pitch locking function is realized with fewer disassembly and assembly parts, simple and efficient operation, and fast switching can be achieved. Fig.16 This is a schematic diagram of the working state of the automatic pitch adjustment. Fig.17 This is a schematic diagram of the appearance of the working state with the pitch locked. It can be used in working conditions that require constant speed and constant fluid delivery, such as wind tunnel test equipment, blowers, water pumps, etc., and can cover almost all the use environments of fixed pitch propeller thrusters.

[0075] Fig.18 , 19 In the figure, the coil spring 1400 is accommodated in the hub pressure cover 1500, the hub pressure cover 1500 is installed on the hub seat, the outer ring positioning hook 1401 of the coil spring 1400 is fixed in the outer groove of the hub pressure cover 1500; the inner ring positioning hook 1402 of the coil spring 1400 is inserted into the positioning groove of the locking nut 1300 connected to the upper end of the central shaft 100.

[0076] The technical solution of the present invention has been disclosed by the preferred embodiments as above. Those skilled in the art should be aware that any changes and modifications made without departing from the scope and spirit of the present invention disclosed by the claims attached to the present invention are within the protection scope of the claims of the present invention.

Claims

1. An automatic pitch-adjustable propeller adjustment assembly, characterized in that: The middle part of the hub seat is rotatably connected to the central shaft (100), the side of the hub seat is evenly distributed with two or more mounting holes, an angle adjustment assembly is arranged in the hub seat, the blade assembly is rotatably mounted at the mounting hole through the angle adjustment assembly, and the axis of the mounting hole intersects the axis of the central shaft perpendicularly; The blade assembly comprises a blade (600) and a blade chuck (2100), wherein the blade (600) is mounted on the outside of the blade chuck (2100), the blade chuck (2100) is a rotating body, and the eccentric cylindrical boss (2101) is eccentrically arranged on the end surface of the inner side of the blade chuck (2100); the angle adjustment assembly comprises a nut threadedly connected to the external thread in the middle of the central shaft (100), and the periphery of the nut has more than two adjustment grooves (801) corresponding to each blade assembly one by one; the eccentric cylindrical boss (2101) of each blade chuck (2100) is inserted at each adjusting groove (801); the nut is a polygonal nut (800); the eccentric cylindrical boss (2101) of each blade chuck (2100) is inserted into each adjusting groove (801) via a slider sleeve (2200); the slider sleeve (2200) and the adjusting groove (801) are clearance-matched; the nut is also provided with a small boss (802) in parallel contact with the axial positioning surface (2105) of the blade chuck around the nut, the plane where the small boss (802) is located is parallel to the central axis of the nut, and the number of the small bosses (802) corresponds one-to-one to the adjusting groove (801); A flexible connection piece is provided between the central shaft (100) and the propeller hub seat; The flexible connecting member comprises a coil spring (1400), and the coil spring (1400) is accommodated in a propeller hub pressure cover (1500); the propeller hub pressure cover (1500) is mounted on the propeller hub seat; The pitch adjustment method is as follows: the central shaft (100) is rotated, and the positioning of the central shaft waist groove (101) and the lower plane boss (502) of the lower gasket in the rotation direction will drive the lower gasket (500) to rotate synchronously; similarly, the upper plane boss (501) of the lower gasket and the end face groove (701) of the adjusting screw are positioned in the rotation direction, and the adjusting screw (700) will rotate synchronously; since the adjusting screw (700) cooperates with the polygonal nut internal thread (803) of the polygonal nut (800), when the adjusting screw (700) rotates, the polygonal nut (800) will move up and down along the axis direction of the spiral line; since the slider sleeve (2200) is aligned with the adjusting groove (801) on the outer side of the polygonal nut, and the offset on the blade clamp The two parts of the core column boss (2101) are constrained in the up and down directions, so when the polygonal nut (800) moves, the eccentric column boss (2101) on the blade chuck will obtain a force moving in the same direction; when the polygonal nut (800) moves, the eccentric column boss (2101) on the blade chuck will rotate along the horizontal axis, and the slider sleeve (2200) outside the eccentric column boss (2101) on the blade chuck will synchronously slide in the adjustment groove (801) of the polygonal nut (800) and always maintain connection and limit the movement stroke of the eccentric column boss (2101) on the blade chuck; by continuously rotating the central shaft (100), the blade chuck (2100) will continue to rotate along the horizontal axis; The specific method for setting the preload force of the coil spring (1400) is as follows: by obtaining the maximum torque parameter of the main shaft of the power machine, select the coil spring (1400) part whose elastic deformation torque and effective number of turns include this torque value, place the coil spring into the inner ring of the hub cover (1500), and insert the positioning tongue-shaped hook of the outer ring of the coil spring (1400) into the positioning groove of the hub cover (1500), align the positioning tongue-shaped hook of the inner ring of the coil spring (1400) with the positioning groove in the center of the locking nut (1300), and close the gap between the hub cover (1500) and the upper hub seat (1000); use a graduated torque wrench to rotate the hub cover (1500) in the direction of the preloaded coil spring (1400) until the rotational torque reaches the maximum torque parameter value of the main shaft, and use the torque wrench to rotate the hub cover (1500). As the deformation of the coil spring increases, the force value will be displayed on the torque wrench, and then the adjustment screw (700) is reversed and the working number of turns is adjusted; In the initial state, the propeller blades are in the large pitch state position. When the torque difference between the power main shaft and the hub seat is greater than the preload of the coil spring (1400), the rotational torque first compresses the coil spring (1400) until it is compressed to the coil spring limit or the polygonal nut contacts the upper gasket, and then transmits the torque to the hub seat. At this time, the propeller blades (600) rotate with the hub seat. During the coil spring compression process, the pitch of the blades changes from a large pitch to a small pitch angle. The pitch adjustment torque sets the target. When the center shaft rotates with high torque, the propeller blades (600) are at a small pitch angle. When the propeller-propelled machine When the device enters a rapid moving state, the rotational resistance of the blade (600) is reduced. Under the action of the reverse torque of the coil spring (1400), the hub seat and the central axis (100) tend to be the same. When the torque difference between the main shaft and the hub seat is less than the compression deformation force of the coil spring (1400), the coil spring releases energy, which pushes the hub seat to accelerate and drives the polygonal nut to rotate until the polygonal nut contacts the lower gasket. The process of the coil spring releasing energy is the process of the pitch of the blade changing from a small pitch to a large pitch angle. The propeller blade (600) automatically changes to a large pitch state and rotates during the adjustment of the pitch change mechanism.

2. The automatic pitch-adjustable propeller adjustment assembly according to claim 1, characterized in that: The central shaft (100) is a stepped shaft, and a fixing hole for installing a central shaft bolt (200) connected to the main shaft is provided at the center of the central shaft (100); the central shaft (100) is rotatably connected to the central hole of the hub seat via an axial bearing, and an adjusting screw (700) is sleeved in the middle of the central shaft (100), and the thread of the outer circle of the adjusting screw (700) forms an external thread in the middle of the central shaft (100); The lower part of the adjusting screw (700) is inserted into the notch (101) at the waist of the central shaft through the lower gasket (500), and the upper gasket (900) for limiting the stroke of the nut is sleeved on the central shaft (100) at the upper end of the adjusting screw (700); the adjusting screw (700), the lower gasket (500), and the upper gasket (900) are all located in the propeller hub seat; The propeller hub seat is divided into an upper and lower part, the upper propeller hub seat (1000) and the lower propeller hub seat (400) are both provided with a central hole, and the upper / lower propeller hub seat is equally divided into more than two semicircular grooves in the circumferential direction; when the upper and lower propeller hub seats are relatively combined, the semicircular grooves are combined into a plurality of complete mounting holes.

3. The automatic pitch-adjustable propeller adjustment assembly according to claim 1, characterized in that: The blade clamp (2100) has a blade clamp notch (2102) on its outer side, and the blade fixing end (601) of the blade (600) is mounted on the blade clamp notch (2102) of the blade clamp (2100); A radial bearing is installed on the outer wall of the blade chuck (2100) near the inner side, and the outer ring of the radial bearing is matched with the mounting hole; The middle part of the slider sleeve (2200) is a cylindrical cavity, and the outer side of the slider sleeve (2200) is a quadrangular prism-shaped structure.

4. The automatic pitch-adjustable propeller adjustment assembly according to claim 1, characterized in that: A positioning hook is provided on the inner ring and the outer ring of the coil spring (1400), respectively. The positioning hook on the outer ring of the coil spring (1400) is fixed in the outer groove of the hub pressure cover (1500); the positioning hook on the inner ring of the coil spring (1400) is directly inserted into the positioning groove at the upper end of the central shaft (100); or the positioning hook on the inner ring of the coil spring (1400) is inserted into the positioning groove of the locking nut (1300) connected to the upper end of the central shaft (100), and the locking nut (1300) connected to the outer thread of the upper end of the central shaft (100) is placed outside the hub seat; the lower end of the locking nut (1300) abuts against the axial bearing at the center hole of the upper hub seat (1000).

5. A method for assembling the automatic pitch control propeller adjustment assembly according to claim 1, characterized in that: The following steps are included: 1) Obtain the maximum torque parameter torque value n of the main shaft of the power equipment; 2) Select the spring (1400) part whose elastic deformation torque and effective number of turns include this torque value; 3) The middle of the hub seat is rotatably connected to the central shaft (100), and the side of the hub seat is evenly distributed with two or more mounting holes. The hub seat is provided with an angle adjustment assembly, and the blade assembly is rotatably mounted at the mounting hole through the angle adjustment assembly, and the axis of the mounting hole intersects the axis of the central shaft perpendicularly; 4) A flexible connection member is provided between the central shaft (100) and the hub seat, the flexible connection member comprising a coil spring (1400), the coil spring (1400) being accommodated in a hub pressure cover (1500); the hub pressure cover (1500) being placed on the hub seat; a positioning hook is provided on the inner ring and the outer ring of the coil spring (1400), respectively, the positioning hook of the inner ring of the coil spring (1400) being inserted into the positioning groove at the upper end of the central shaft (100); the positioning hook of the outer ring of the coil spring (1400) being fixed in the outer groove of the hub pressure cover (1500); 5) Method for setting the preload force of the coil spring (1400): rotate the hub cover (1500) in the direction of the preloaded coil spring until the rotational torque reaches the maximum torque value of the main shaft of the power equipment, and then reverse the number of turns m to obtain the preload force F of the coil spring (1400), so that the hub cover (1500) is fixed to the hub seat; when the nut of the angle adjustment assembly moves from the initial state to the target position along the middle external thread of the center axis (100), the corresponding number of turns of the center axis (100) required is m1, m= m1.

6. The assembly method according to claim 5, characterized in that: When the pitch of the blade (600) needs to be locked at any position, remove the flexible connector and the hub gland (1500), fix the lower hub seat of the hub seat and then rotate the central shaft (100), the blade clamp (2100) rotates along the mounting hole of the hub seat, and the pitch of the blade (600) changes accordingly. When the pitch of the blade (600) reaches the target pitch, stop rotating the central shaft (100), key the middle part of the spacing piece (1600) to the central shaft (100) or key the locking nut (1300) on the central shaft (100), connect the spacing piece (1600) to the hub seat and lock it, and the pitch locking is completed.

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