A design of unmanned helicopter rotor control

Abstract

The present application relates to the field of aircraft technology, in particular to a kind of unmanned helicopter rotor control device design, comprising: fixed seat, the fixed seat is connected with steering gear by unmanned aerial vehicle shell, adjusting piece is equipped on fixed seat, adjusting piece bottom end is connected with steering gear output end, adjusting piece is equipped with stationary ring, a plurality of top of upper anti-twist arm is hinged on stationary ring, the end of lower anti-twist arm is hinged on the bottom of upper anti-twist arm, the other end of lower anti-twist arm is hinged on the side wall of fixed seat, driving piece is equipped on fixed seat, to control the inclination of stationary ring, adjusting piece top end is connected with rotor, by setting up the anti-twist arm assembly of lower anti-twist arm and upper anti-twist arm, operator can make the control of unmanned helicopter more stable, reduce the idle stroke of control device.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, and in particular to a design of a rotor control component for an unmanned helicopter. Background Technology

[0002] The rotor control components of a drone are the parts that control the rotor speed, steering angle, and lift of the drone. By operating these components, precise control of the drone can be achieved, thereby ensuring its stability and flexibility during flight.

[0003] However, existing technologies still have shortcomings in application. For example, the linkage structure of a coaxial UAV tilter provided by patent number 202222170818.0 includes a main shaft and a pitch-changing assembly. The pitch-changing assembly includes a tilter and several sets of servos. The tilter includes a rotating ring, a fixed ring, and a deep groove ball bearing. The fixed ring is sleeved on the main shaft. The rotating ring is rotatably connected to the fixed ring through the deep groove ball bearing. The outer ring of the rotating ring is provided with a collective pitch component connected to the rotor. Each set of servos has a pitch-changing component connected to the fixed ring at its output end. The servos drive the pitch-changing component to move so that the fixed ring tilts or moves up and down along the main shaft. This device has an excessively large idle stroke and low stability. Summary of the Invention

[0004] This invention provides a design for a rotor control component of an unmanned helicopter to address the issues raised in the background art.

[0005] To achieve the above-mentioned objectives, the present invention provides the following technical solution: a design for a rotor control component of an unmanned helicopter, comprising: a fixed base, wherein the fixed base is connected to a servo motor via the UAV shell, an adjusting component is provided on the fixed base, the bottom end of the adjusting component is connected to the output end of the servo motor, a stationary ring is mounted on the adjusting component, the top ends of multiple upper anti-torsion arms are hinged to the stationary ring, the bottom ends of the upper anti-torsion arms are hinged to the ends of lower anti-torsion arms, the other ends of the lower anti-torsion arms are hinged to the side wall of the fixed base, a driving component is mounted on the fixed base to control the tilt angle of the stationary ring, and the top end of the adjusting component is connected to the rotor.

[0006] Preferably, the driving component includes a cylinder and a driving rod, with the bottom ends of multiple cylinders hinged to the fixed base, the cylinders being spaced apart from the lower anti-torsion arm, and the cylinder output end being hinged to the stationary ring via the driving rod.

[0007] Preferably, the adjusting component includes: a main shaft, a deep groove ball bearing, and a radial spherical bearing. The inner wall of the fixed seat is connected to the side wall of the main shaft through a rotating component. The bottom end of the main shaft is connected to the output end of the servo motor. A radial spherical bearing is mounted on the main shaft. A deep groove ball bearing is mounted on the bottom side wall of the radial spherical bearing. The side wall of the deep groove ball bearing is connected to the inner wall of the stationary ring.

[0008] Preferably, the adjusting component further includes a moving ring, wherein the top sidewall of the radial spherical bearing is connected to the inner wall of the moving ring, and the moving ring is arranged parallel to the deep groove ball bearing.

[0009] Preferably, the adjusting component further includes an upper torque arm and a lower torque arm, a retaining ring is mounted on the main shaft, the ends of multiple upper torque arms are hinged to the retaining ring, the other end of the upper torque arm is hinged to the top end of the lower torque arm, and the top end of the lower torque arm is hinged to the moving ring.

[0010] Preferably, the adjusting component further includes: a pitch control rod, the bottom ends of multiple pitch control rods are hinged to the moving ring, the pitch control rods are spaced apart from the upper torque arm, the top end of the pitch control rod is hinged to the rotor sidewall, and the rotor is mounted on the top of the main shaft.

[0011] Preferably, the rotor includes: a mounting base, a rotating shaft, and a rotor assembly. The mounting base is mounted on the top end of the main shaft, and the end of the rotating shaft is rotatably connected to the mounting base. The other end of the rotating shaft is connected to the rotor assembly, and the side wall of the rotor assembly is hinged to the top end of the pitch control rod.

[0012] Preferably, the rotor assembly includes: a blade, a bolt, and a transmission rod. The other end of the rotating shaft is connected to the end of the blade by a bolt. The end of the transmission rod is mounted on the side wall of the blade. The transmission rod is arranged parallel to the rotating shaft. The other end of the rotating shaft is hinged to the top of the pitch control rod.

[0013] Preferably, the rotating component includes a positioning ring, a driven ring, and a ball bearing. The inner wall of the fixed seat is connected to the side wall of the positioning ring. The inner wall of the positioning ring has a lubrication groove. The top wall of the lubrication groove is rotatably sealed to the top surface of the driven ring, and the bottom surface of the driven ring is rotatably sealed to the bottom wall of the lubrication groove. The lubrication groove and the side wall of the driven ring form a lubrication cavity, which is filled with lubricating oil. The driven ring is fitted onto the side wall of the main shaft. The side wall of the driven ring has multiple grooves. The end of the ball bearing is slidably connected in the grooves. The other end of the ball bearing is slidably engaged with an annular groove, which is formed on the inner wall of the lubrication groove.

[0014] Preferably, the top of the positioning ring is provided with an oil injection hole, the bottom end of the oil injection hole is connected to the top wall of the lubrication groove and is set towards the bottom wall of the lubrication groove, and a one-way valve is installed in the oil injection hole to prevent lubricating oil leakage.

[0015] The beneficial effects of this invention are as follows:

[0016] In the solution of the present invention:

[0017] By setting up an anti-torsion arm assembly consisting of a lower anti-torsion arm and an upper anti-torsion arm, the operator's control of the unmanned helicopter can be made more stable, and the idle travel of the control components can be reduced. Attached image description:

[0018] Figure 1 This is a schematic diagram of the main structure of the present invention;

[0019] Figure 2 This is a schematic diagram of the spindle mounting position according to the present invention;

[0020] Figure 3 This is an exploded view of the stationary ring, deep groove ball bearing, radial spherical plain bearing, and moving ring of the present invention;

[0021] Figure 4 This is a schematic diagram of the installation position of the upper torque arm of the present invention;

[0022] Figure 5 This is a schematic diagram of the rotor structure of the present invention;

[0023] Figure 6 This is a cross-sectional view of the rotating component of the present invention;

[0024] Figure 7 This is a schematic diagram showing the location of the oil injection hole in this invention;

[0025] Figure 8 This is a schematic diagram of the oil drain pipe structure of the present invention;

[0026] Figure 9 This is a schematic diagram of the installation position of the heat dissipation ring tube of the present invention;

[0027] Figure 10 This is a schematic diagram showing the location of the pressure-bearing surface in this invention.

[0028] The components include: fixed seat 1, lower anti-torsion arm 2, upper anti-torsion arm 3, stationary ring 4, adjusting component 5, cylinder 6, drive rod 7, main shaft 8, deep groove ball bearing 9, radial spherical bearing 10, moving ring 11, upper torque arm 12, lower torque arm 13, variable pitch rod 14, mounting seat 15, rotating shaft 16, rotor assembly 17, blade 18, bolt 19, transmission rod 20, positioning ring 21, driven ring 22, ball bearing 23, oil injection hole 24, oil drain pipe 25, heat dissipation ring pipe 26, oil inlet pipe 27, pump plate 28, guide shell 29, moving plate 30, pressure bearing surface 31, rack 32, connecting plate 33, and torsion spring 34. Detailed Implementation

[0029] The preferred embodiments of the present invention will be described below with reference to the accompanying drawings. It should be understood that the preferred embodiments described herein are for illustration and explanation only and are not intended to limit the present invention.

[0030] Example: Reference Figures 1-10A rotor control component design for an unmanned helicopter includes: a fixed base 1, a lower anti-torsion arm 2, an upper anti-torsion arm 3, a stationary ring 4, and an adjusting component 5. The fixed base 1 is connected to a servo motor via the UAV shell. The adjusting component 5 is mounted on the fixed base 1, with its bottom end connected to the servo motor output end. The stationary ring 4 is mounted on the adjusting component 5, and the top ends of multiple upper anti-torsion arms 3 are hinged to the stationary ring 4. The bottom ends of the upper anti-torsion arms 3 are hinged to the ends of the lower anti-torsion arms 2, and the other end of the lower anti-torsion arms 2 is hinged to the side wall of the fixed base 1. A driving component is mounted on the fixed base 1 to control the tilt angle of the stationary ring 4. The top end of the adjusting component 5 is connected to the rotor.

[0031] The principles and beneficial effects of the above scheme are as follows:

[0032] The drone shell is equipped with a fixed base 1. When the servo motor is activated, the output end of the servo motor rotates, causing the adjusting component 5 to rotate. The top ends of multiple upper anti-torsion arms 3 are hinged to the fixed ring 4. The bottom end of the upper anti-torsion arm 3 is hinged to the end of the lower anti-torsion arm 2. The other end of the lower anti-torsion arm 2 is hinged to the side wall of the fixed base 1. When it is necessary to adjust the rotor angle, the drive component is activated. The top end of the drive component drives the fixed ring 4 to move, and changes the angle between the fixed ring 4 and the fixed base 1. The fixed ring 4 drives the adjusting component 5 to move, and the adjusting component 5 causes the rotor to change the angle relative to the fixed base 1, so that the rotor generates a horizontal component force, thereby causing the rotor to fly forward and backward and left and right or to ascend and descend.

[0033] By setting up an anti-torsion arm assembly consisting of a lower anti-torsion arm 2 and an upper anti-torsion arm 3, the operator's control of the unmanned helicopter can be more stable, and the idle travel of the control components can be reduced.

[0034] The number of servo motors was reduced, lowering the production cost of the device.

[0035] The driving component includes a cylinder 6 and a driving rod 7. The bottom ends of multiple cylinders 6 are hinged to the fixed base 1. The cylinders 6 are spaced apart from the lower anti-torsion arm 2. The output end of the cylinder 6 is hinged to the stationary ring 4 through the driving rod 7.

[0036] The principles and beneficial effects of the above scheme are as follows:

[0037] Since multiple cylinders 6 are hinged on the fixed base 1, and the drive rod 7 connected to the output end of the cylinder 6 is hinged to the stationary ring 4, when it is necessary to control the movement direction or altitude of the unmanned helicopter, the cylinder 6 is activated to provide thrust or pull according to actual needs. The drive rod 7 connected to the output end of the multiple cylinders 6 changes the tilt angle of the stationary ring 4, thereby controlling the angle of the rotor connected to the adjusting component 5 and completing the change of flight state. By setting multiple cylinders 6 and the drive rod 7 connected to them to cooperate in changing the tilt angle of the stationary ring 4, the flight state of the unmanned helicopter is controlled, reducing the difficulty of flight attitude adjustment.

[0038] The bottom end of the cylinder 6 is hinged to the fixed base 1, and the drive rod 7 connected to the output end of the cylinder 6 is hinged to the stationary ring 4. When the tilt angle of the stationary ring 4 is changed, the extension and shortening of the drive rod 7 will not cause the drive component to jam.

[0039] At the same time, using cylinder 6 as the power source for changing the tilt angle of stationary ring 4 improves the efficiency of flight attitude adjustment and reduces the cost of device manufacturing.

[0040] The adjusting component 5 includes: a main shaft 8, a deep groove ball bearing 9, and a radial spherical bearing 10. The inner wall of the fixed seat 1 is connected to the side wall of the main shaft 8 through a rotating component. The bottom end of the main shaft 8 is connected to the output end of the servo motor. The radial spherical bearing 10 is mounted on the main shaft 8. The deep groove ball bearing 9 is mounted on the bottom side wall of the radial spherical bearing 10. The side wall of the deep groove ball bearing 9 is connected to the inner wall of the stationary ring 4.

[0041] The main shaft 8 is a tubular structure.

[0042] The principles and beneficial effects of the above scheme are as follows:

[0043] When the servo motor is activated, the main shaft 8 rotates synchronously because it is connected to the output end of the servo motor. A radial spherical bearing 10 is mounted on the main shaft 8, and a deep groove ball bearing 9 is mounted on the bottom side wall of the radial spherical bearing 10. The side wall of the deep groove ball bearing 9 is connected to the inner wall of the stationary ring 4. When the tilt angle of the stationary ring 4 changes, the stationary ring 4 drives the radial spherical bearing 10 to move via the deep groove ball bearing 9, thereby changing the tilt angle of the radial spherical bearing 10. Because the stationary ring 4 is subjected to the lower anti-torsion arm 2 and the upper anti-torsion arm... Due to the constraint of 3, the stationary ring 4 will not rotate synchronously with the spindle 8; since the inner wall of the fixed seat 1 is connected to the side wall of the spindle 8 through the rotating component, the rotating component can provide auxiliary stability for the rotation of the spindle 8 when the spindle 8 rotates, preventing it from swaying during rotation and improving the stability of the spindle 8 during rotation; since the spindle 8 is a tubular structure and the fixed seat 1 is concentrically set with the spindle 8, the parts are designed to be lightweight, ensuring structural strength while making the structure fit together tightly and the overall weight is lighter.

[0044] The adjusting component 5 further includes a moving ring 11, the top sidewall of the radial spherical bearing 10 is connected to the inner wall of the moving ring 11, and the moving ring 11 is arranged parallel to the deep groove ball bearing 9.

[0045] The principles and beneficial effects of the above scheme are as follows:

[0046] When the tilt angle of the radial spherical bearing 10 changes, it causes the rotating ring 11 connected to it to change its tilt angle.

[0047] The adjusting component 5 further includes an upper torque arm 12 and a lower torque arm 13. A retaining ring is installed on the main shaft 8. Multiple ends of the upper torque arms 12 are hinged to the retaining ring. The other end of the upper torque arm 12 is hinged to the top end of the lower torque arm 13. The top end of the lower torque arm 13 is hinged to the moving ring 11.

[0048] The principles and beneficial effects of the above scheme are as follows:

[0049] The main shaft 8 is hinged to the ends of multiple upper torque arms 12 via retaining rings. The retention rings reduce the difficulty of installing and disassembling the upper torque arms 12. The other end of the upper torque arm 12 is hinged to the top of the lower torque arm 13. The top of the lower torque arm 13 is hinged to the moving ring 11. While the moving ring 11 is rotating and adjusting its tilt angle, the rotation of the main shaft 8 can be transmitted to the moving ring 11 through the cooperation of the upper torque arms 12 and the lower torque arms 13.

[0050] Meanwhile, since the retaining ring, upper torque arm 12, lower torque arm 13 and moving ring 11 are connected in sequence, the moving ring 11 will not get stuck when the tilt angle changes.

[0051] The operating planes of the moving ring 11 and the stationary ring 4 are coplanar. By utilizing the ball center of the spherical bearing, the linear operation of the moving ring 11 during transmission can be guaranteed to the greatest extent. The rotation of the moving ring 11 will not be affected when the tilt angle is adjusted.

[0052] The rotation of the rotor blows airflow to the mounting points of the moving ring 11 and the stationary ring 4, and the flowing air reduces the heat generated by the deep groove ball bearing 9 and the radial spherical bearing 10 during rotation.

[0053] When the tilt angle of the stationary ring 4 is not adjusted, both the upper torque arm 12 and the lower anti-torsion arm 2 are perpendicular to the main shaft 8, ensuring the motion symmetry and precise and reliable constraint of the lower torque arm 13 and the upper anti-torsion arm 3, while also possessing good structural efficiency.

[0054] The adjusting component 5 further includes: a pitch rod 14, the bottom ends of multiple pitch rods 14 are hinged to the moving ring 11, the pitch rods 14 are spaced apart from the upper torque arm 12, the top end of the pitch rod 14 is hinged to the rotor sidewall, and the rotor is installed at the top of the main shaft 8.

[0055] The principles and beneficial effects of the above scheme are as follows:

[0056] When the tilt angle of the rotating ring 11 changes, the rotating ring 11 adjusts the angle of the rotor through the pitch control rod 14, thereby adjusting the flight attitude of the unmanned helicopter.

[0057] The rotor includes: a mounting base 15, a rotating shaft 16, and a rotor assembly 17. The mounting base 15 is mounted on the top end of the main shaft 8. The end of the rotating shaft 16 is rotatably connected to the mounting base 15. The other end of the rotating shaft 16 is connected to the rotor assembly 17. The side wall of the rotor assembly 17 is hinged to the top end of the pitch control rod 14.

[0058] The rotor assembly 17 includes: a blade 18, a bolt 19, and a transmission rod 20. The other end of the rotating shaft 16 is connected to the end of the blade 18 by the bolt 19. The end of the transmission rod 20 is mounted on the side wall of the blade 18. The transmission rod 20 is arranged parallel to the rotating shaft 16. The other end of the rotating shaft 16 is hinged to the top of the pitch control rod 14.

[0059] The principles and beneficial effects of the above scheme are as follows:

[0060] Mounting base 15 is located at the top of main shaft 8. The rotation of main shaft 8 drives rotating shaft 16 and winglets 18 in rotor assembly 17 to rotate. When the tilt angle of rotating ring 11 changes, multiple variable pitch rods 14 connected to it extend or shorten. The top of variable pitch rod 14 drives transmission rod 20 hinged to it to rotate around rotating shaft 16, thereby changing the tilt angle of winglets 18 connected to rotating shaft 16 and changing the flight attitude of unmanned helicopter. By setting winglets 18 to rotating shaft 16 through bolts 19, it is easy to quickly disassemble and install winglets 18, reducing the maintenance difficulty of the device. One end of rotating shaft 16 is rotatably connected to mounting base 15, and the other end of rotating shaft 16 is connected to winglets 18. Transmission rod 20 is installed on rotating shaft 16. Transmission rod 20 rotates rotating shaft 16 through variable pitch rod 14 hinged to it, thereby changing the tilt angle of winglets 18, simplifying the complexity of the device and making full use of the space between components.

[0061] The rotating component includes a positioning ring 21, a driven ring 22, and a ball bearing 23. The inner wall of the fixed seat 1 is connected to the side wall of the positioning ring 21. The inner wall of the positioning ring 21 has a lubrication groove. The top wall of the lubrication groove is rotatably sealed to the top surface of the driven ring 22, and the bottom surface of the driven ring 22 is rotatably sealed to the bottom wall of the lubrication groove. The lubrication groove and the side wall of the driven ring 22 form a lubrication cavity, which is filled with lubricating oil. The driven ring 22 is fitted onto the side wall of the main shaft 8. The side wall of the driven ring 22 has multiple grooves. The end of the ball bearing 23 is slidably connected in the grooves. The other end of the ball bearing 23 is slidably engaged with an annular groove, which is located on the inner wall of the lubrication groove.

[0062] The principles and beneficial effects of the above scheme are as follows:

[0063] When the servo drive drives the main shaft 8 to rotate, the positioning ring 21 and the driven ring 22 rotate in engagement to prevent the main shaft 8 from wobbling during rotation, reducing vibration within the device and preventing wear on components. By injecting lubricating oil between the positioning ring 21 and the driven ring 22, wear caused by relative rotation between the positioning ring 21 and the driven ring 22 is reduced. The driven ring 22 has multiple grooves on its side wall, and the ends of the balls 23 are slidably connected in the grooves. The other end of the balls 23 is slidably engaged with an annular groove, which is located on the inner wall of the lubrication groove. The grooves limit the movement of the balls 23 as they rotate relative to each other. The sliding engagement between the grooves and the annular groove improves the positioning effect of the balls 23 within the rotating parts, preventing them from shifting within the lubrication groove and improving the safety of the device during movement. The balls 23 can limit the distance between the positioning ring 21 and the driven ring 22, further improving the stability of the main shaft 8 during rotation.

[0064] The top of the positioning ring 21 is provided with an oil injection hole 24. The bottom end of the oil injection hole 24 is connected to the top wall of the lubrication groove and is set towards the bottom wall of the lubrication groove. A one-way valve is installed in the oil injection hole 24 to prevent lubricating oil leakage.

[0065] The principles and beneficial effects of the above scheme are as follows:

[0066] Lubricating oil is injected into the lubrication groove through the oil injection hole 24. The lubricating oil can lubricate the positioning ring 21 and the driven ring 22, and at the same time, the lubricating oil can lubricate the ball 23 to prevent it from wearing out. A one-way valve is installed in the oil injection hole 24 to prevent the lubricating oil that has been injected into the lubrication groove from leaking.

[0067] The bottom wall of the lubrication tank has a guide hole, and the top of the inner wall of the lubrication tank has a second guide hole. The guide hole is connected to the end of the oil drain pipe 25. The other end of the oil drain pipe 25 extends to the outside of the side wall of the fixed seat 1. One end of a plurality of heat dissipation ring pipes 26 is connected to the oil drain pipe 25. The heat dissipation ring pipes 26 are arranged longitudinally at equal intervals and are concentric with the fixed seat 1. The second guide hole is connected to the end of the oil inlet pipe 27. The end of the oil inlet pipe 27 is equipped with a check valve to prevent lubricating oil from flowing back into the oil inlet pipe 27. The end of the oil inlet pipe 27 located outside the side wall of the fixed seat 1 is connected to the other end of the plurality of heat dissipation ring pipes 26. The driven ring 22 is equipped with the end of a plurality of pump blades 28. The other end of the pump blades 28 is placed in the lubrication cavity.

[0068] The principles and beneficial effects of the above scheme are as follows:

[0069] When the spindle 8 rotates, the lubricating oil in the lubrication groove lubricates the positioning ring 21, the driven ring 22, and the balls 23, and absorbs the heat generated by friction between the parts. Multiple pump blades 28 are mounted on the driven ring 22, rotating synchronously with the driven ring 22 and the spindle 8. The rotation of the pump blades 28 pumps the working lubricating oil into the oil drain pipe 25. The end of the oil drain pipe 25 located outside the side wall of the fixed seat 1 is connected to the ends of multiple cooling ring pipes 26. Because the temperature of the oil drain pipe 25 entering the cooling ring pipes 26 is high, and the oil drain pipe 25... The lubricating oil in the end of the 5th end is affected by the rotation of the pump blade 28, so the oil pressure of the lubricating oil in the end of the oil drain pipe 25 is higher than that of the lubricating oil in the end of the oil inlet pipe 27, thus facilitating the circulation of the lubricating oil in the heat dissipation ring pipe 26; multiple heat dissipation ring pipes 26 are arranged equidistantly in the longitudinal direction, and the heat dissipation ring pipes 26 are concentrically arranged with the fixed base 1, so the lubricating oil can be quickly dispersed from the oil drain pipe 25 into multiple heat dissipation ring pipes 26, instantly increasing the heat dissipation area. When the lubricating oil comes into contact with the air and is simultaneously subjected to the airflow generated by the rotation of the blade 18, it can be rapidly cooled.

[0070] After cooling, the lubricating oil flows through the high-temperature lubricating oil pressure output by the oil drain pipe 25 to the other end of the heat dissipation ring pipe 26. Since the pressure in the oil inlet pipe 27 is lower than the pressure in the oil drain pipe 25, the lubricating oil after cooling can quickly flow back into the lubrication tank. By setting a check valve in the oil inlet pipe 27 to prevent the lubricating oil after cooling from flowing back into the heat dissipation ring pipe 26, the continuous supply of lubricating oil in the lubrication tank is maintained.

[0071] As the main shaft 8 rotates synchronously, the pump blades 28 circulate the lubricating oil. The lubricating oil provides a damping effect for the pump blades 28 during rotation. Therefore, when the main shaft 8 stops rotating, the rotational speed of the main shaft 8 can be reduced quickly, preventing the servo motor from continuously rotating under the inertia of the wing blades 18 and preventing the servo motor itself from being damaged due to continuous idling. At the same time, due to the existence of the damping effect, the servo motor can be prevented from rotating due to the action of flowing air on the wing blades 18 when the unmanned helicopter is not in operation. It can also prevent the wing blades 18 from rotating due to vibration during transportation, thereby reducing the number of fixing devices used when transporting the unmanned helicopter.

[0072] When the main shaft 8 is not rotating or is rotating, lubricating oil is injected into the lubrication groove, and a pump plate 28 is installed on the driven ring 22. Since the pump plate 28 is placed in the lubricating oil, both the top and bottom surfaces of the pump plate 28 are subjected to the pressure of the lubricating oil. Therefore, the lubricating oil can limit the pump plate 28, the driven ring 22 and the main shaft 8 in a certain longitudinal direction, preventing the main shaft 8 from impacting the output end of the servo motor due to longitudinal vibration during the transport of the unmanned helicopter. It can also prevent the main shaft 8 from impacting or pulling the output end of the servo motor when the unmanned helicopter is ascending or descending, thereby improving the service life of the servo motor.

[0073] The side wall of the oil drain pipe 25 is connected to the end of the guide shell 29. The guide shell 29 is set in the positioning groove on the side wall of the fixed seat 1. The other end of the guide shell 29 is placed inside the fixed seat 1. The oil drain pipe 25 and the guide shell 29 are slidably sealed with the moving plate 30. The top of the side of the moving plate 30 placed inside the oil drain pipe 25 is provided with a pressure bearing surface 31. The pressure bearing surface 31 is set towards the wing 18. The other side of the moving plate 30 is connected to a rack 32. The rack 32 is placed between the other end of the guide shell 29 and the main shaft 8. The rack 32 is meshed with a gear. The side of the gear is rotatably engaged with the connecting plate 33 through the second rotating shaft. The connecting plate 33 is installed in the fixed seat 1. The end of the torsion spring 34 is mounted on the connecting plate 33. The other end of the torsion spring 34 is connected to the side of the gear.

[0074] The movable plate 30 is made of copper.

[0075] The principles and beneficial effects of the above scheme are as follows:

[0076] When an unmanned helicopter operates in a low-temperature environment for an extended period, or under conditions of continuously decreasing temperature, the fluidity of the lubricating oil decreases. Simultaneously, the pressure of the lubricating oil in the guide hole of the oil drain pipe 25 decreases. Consequently, the pressure exerted on the bearing surface 31 at the end of the moving plate 30 by the lubricating oil discharged from the oil drain pipe 25 decreases. Under the action of the elastic potential energy of the torsion spring 34, the torsion spring 34 drives the gear to rotate clockwise. The gear drives the rack 32, which meshes with the rack, to move towards the oil drain pipe 25. The rack 32 then drives the moving plate 30 towards the oil drain pipe. 25. The pressure-bearing surface 31 at the end of the moving plate 30 blocks the oil drain pipe 25. After the blockage, the oil drain pipe 25 stops the lubricating oil from entering the lubrication tank through the heat dissipation ring pipe 26 and the oil inlet pipe 27. At this time, the lubricating oil with poor fluidity in the lubrication tank gradually heats up due to the rotation of the pump plate 28 and the friction between the parts. The fluidity of the lubricating oil increases again after the temperature rises. At the same time, the pressure of the lubricating oil in the guide hole of the oil drain pipe 25 increases, and the pressure on the pressure-bearing surface 31 increases. The moving plate 30 drives the rack 32 to move into the fixed seat 1. Strip 32 drives the gear to rotate counterclockwise, and torsion spring 34 returns to its original position, preparing for the next operation. The sealed fit between the moving plate 30 and the oil drain pipe 25 can promptly stop the circulation when the lubricating oil flow decreases, preventing wear of parts due to lubricating oil gaps in the lubrication groove. Since the moving plate 30 is made of copper, when the temperature of the lubricating oil in the lubrication groove rises, the moving plate 30 can assist in the heat transfer of the lubricating oil in the heat dissipation ring pipe 26 and increase the flow of lubricating oil in the heat dissipation ring pipe 26. The main shaft 8 has a tubular structure, which increases the contact area between the main shaft 8 and the driven ring 22, resulting in high heat transfer efficiency. When the lubricating oil in the lubrication groove heats up, some of the heat can be transferred through the main shaft 8 to the deep groove ball bearing 9 and the radial spherical plain bearing 10, thus assisting in heating the lubricating oil in these two components to a certain extent, improving the fluidity of the lubricating oil and preventing wear of the deep groove ball bearing 9 and the radial spherical plain bearing 10 due to insufficient lubricating oil fluidity.

[0077] Although embodiments of the present invention have been disclosed above, they are not limited to the applications listed in the specification and embodiments. They can be applied to various fields suitable for the present invention. Other modifications can be easily made by those skilled in the art. Therefore, without departing from the general concept defined by the claims and their equivalents, the present invention is not limited to the specific details and illustrations shown and described herein.

Claims

1. A design for a rotor control component of an unmanned helicopter, characterized in that, include: The fixed base (1) is connected to the servo motor through the UAV shell. The fixed base (1) is provided with an adjustment component (5). The bottom end of the adjustment component (5) is connected to the output end of the servo motor. The adjustment component (5) is equipped with a stationary ring (4). The top ends of multiple upper anti-torsion arms (3) are hinged to the stationary ring (4). The bottom end of the upper anti-torsion arm (3) is hinged to the end of the lower anti-torsion arm (2). The other end of the lower anti-torsion arm (2) is hinged to the side wall of the fixed base (1). The fixed base (1) is equipped with a drive component to control the tilt angle of the stationary ring (4). The top end of the adjustment component (5) is connected to the rotor. The driving component includes a cylinder (6) and a driving rod (7). The bottom ends of multiple cylinders (6) are hinged on the fixed base (1). The cylinders (6) are spaced apart from the lower anti-torsion arm (2). The output end of the cylinder (6) is hinged to the stationary ring (4) through the driving rod (7). The adjusting component (5) includes: a main shaft (8), a deep groove ball bearing (9) and a radial spherical bearing (10). The inner wall of the fixed seat (1) is connected to the side wall of the main shaft (8) through a rotating component. The bottom end of the main shaft (8) is connected to the output end of the servo motor. The radial spherical bearing (10) is mounted on the main shaft (8). The bottom side wall of the radial spherical bearing (10) is mounted with a deep groove ball bearing (9). The side wall of the deep groove ball bearing (9) is connected to the inner wall of the stationary ring (4). The adjusting component (5) further includes: a moving ring (11), the top sidewall of the radial spherical bearing (10) is connected to the inner wall of the moving ring (11), and the moving ring (11) is arranged parallel to the deep groove ball bearing (9); The adjusting component (5) further includes: an upper torque arm (12) and a lower torque arm (13). A retaining ring is installed on the main shaft (8). Multiple ends of the upper torque arm (12) are hinged to the retaining ring. The other end of the upper torque arm (12) is hinged to the top end of the lower torque arm (13). The top end of the lower torque arm (13) is hinged to the moving ring (11). The adjusting component (5) further includes: a variable pitch rod (14), the bottom ends of multiple variable pitch rods (14) are hinged on the moving ring (11), the variable pitch rods (14) are spaced apart from the upper torque arm (12), the top end of the variable pitch rod (14) is hinged to the rotor side wall, and the rotor is installed on the top end of the main shaft (8). The rotor includes: a mounting base (15), a rotating shaft (16) and a rotor assembly (17). The mounting base (15) is mounted on the top of the main shaft (8). The end of the rotating shaft (16) is rotatably connected to the mounting base (15). The other end of the rotating shaft (16) is connected to the rotor assembly (17). The side wall of the rotor assembly (17) is hinged to the top of the pitch control rod (14). The rotating component includes: a positioning ring (21), a driven ring (22), and a ball (23). The inner wall of the fixed seat (1) is connected to the side wall of the positioning ring (21). The inner wall of the positioning ring (21) has a lubrication groove. The top wall of the lubrication groove is rotatably sealed to the top surface of the driven ring (22). The bottom surface of the driven ring (22) is rotatably sealed to the bottom wall of the lubrication groove. The lubrication groove and the side wall of the driven ring (22) form a lubrication cavity. The lubrication cavity is filled with lubricating oil. The driven ring (22) is fitted on the side wall of the main shaft (8). The side wall of the driven ring (22) has multiple grooves. The end of the ball (23) is slidably connected in the groove. The other end of the ball (23) is slidably engaged with the annular groove. The annular groove is opened on the inner wall of the lubrication groove. The bottom wall of the lubrication tank has a guide hole, and the top of the inner wall of the lubrication tank has a second guide hole. The guide hole is connected to the end of the oil drain pipe (25). The other end of the oil drain pipe (25) extends to the outside of the side wall of the fixed seat (1). One end of a plurality of heat dissipation ring pipes (26) is connected to the oil drain pipe (25). The heat dissipation ring pipes (26) are arranged longitudinally at equal intervals. The heat dissipation ring pipes (26) are concentrically arranged with the fixed seat (1). The second guide hole is connected to the end of the oil inlet pipe (27). The end of the oil inlet pipe (27) is equipped with a check valve to prevent lubricating oil from flowing back into the oil inlet pipe (27). The end of the oil inlet pipe (27) placed outside the side wall of the fixed seat (1) is connected to the other end of the plurality of heat dissipation ring pipes (26). The driven ring (22) is equipped with the end of a plurality of pump blades (28). The other end of the pump blades (28) is placed in the lubrication cavity.

2. The design of a rotor control component for an unmanned helicopter according to claim 1, characterized in that, The rotor assembly (17) includes: a blade (18), a bolt (19) and a transmission rod (20). The other end of the shaft (16) is connected to the end of the blade (18) by the bolt (19). The side wall of the blade (18) is fitted with the end of the transmission rod (20). The transmission rod (20) is arranged parallel to the shaft (16). The other end of the shaft (16) is hinged to the top of the pitch control rod (14).

3. The design of a rotor control component for an unmanned helicopter according to claim 1, characterized in that, The top of the positioning ring (21) is provided with an oil injection hole (24). The bottom end of the oil injection hole (24) is connected to the top wall of the lubrication groove and is set towards the bottom wall of the lubrication groove. A one-way valve is installed in the oil injection hole (24) to prevent lubricating oil leakage.

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