Tail rotor pitch control device and helicopter

Abstract

This invention relates to the field of helicopter technology, and discloses a tail rotor pitch control device and a helicopter. The tail rotor pitch control device includes: a transmission engagement with the tail rotor shaft and a pitch-changing component of the tail rotor; a control bearing, including an outer bearing ring and an inner bearing ring, the inner bearing ring being assembled and connected to the control shaft and rotating together with the control shaft; a booster control stick assembly, assembled and connected to the outer bearing ring; and a temperature detection component, disposed on the booster control stick assembly, with the detection end of the temperature detection component contacting the outer bearing ring. This invention changes the assembly method of the control bearing, giving the booster control stick assembly installation space for mounting the temperature detection component. By placing the temperature detection component in a corresponding position to directly contact the outer bearing ring, the temperature of the outer bearing ring can be detected accurately in real time. Simultaneously, the temperature detection component can transmit the measured information to the helicopter's monitoring system. When a preset temperature is reached, a timely warning can be issued and the operator notified, improving flight safety.

Description

Technical Field

[0001] This invention relates to the field of helicopter technology, specifically to a tail rotor pitch control device and a helicopter. Background Technology

[0002] The tail rotor is a crucial component of a helicopter's tail section. During flight, the reaction torque from the rotor's rotation causes the helicopter to rotate in the opposite direction. The thrust or pull generated by the tail rotor counteracts this rotation, achieving directional stability. The direction can be controlled by altering the tail rotor's thrust or pull. A tail rotor typically consists of tail blades, a tail hub, and a pitch control mechanism. The tail blades are connected to the tail hub and have rotating surfaces; the tail hub is the intermediate component connecting the tail blades to the tail drive system and tail control system; the tail rotor pitch control mechanism can change the tail rotor's thrust or pull by altering its pitch angle.

[0003] Currently, the control shaft of existing tail rotor pitch control mechanisms is typically connected to the booster control lever inside the fuselage via a control bearing. The control shaft rotates along with the tail rotor. Under the action of the booster, the booster control lever can move axially and drive the control shaft to move, thereby achieving the change of tail rotor pitch angle. As helicopters operate for extended periods, the control bearing of existing tail rotor pitch control mechanisms is prone to seizing. The control shaft becomes fixed as the control bearing seizes, preventing the tail rotor pitch control mechanism from functioning properly and potentially leading to catastrophic failure. Summary of the Invention

[0004] In view of this, the present invention provides a tail rotor pitch control device and a helicopter to solve the safety hazard caused by the long-term operation of the control bearing of the existing tail rotor pitch control mechanism.

[0005] In a first aspect, the present invention provides a tail rotor pitch control device, comprising: a control shaft, which is driven to rotate by the tail rotor shaft and the tail rotor pitch control component, the control shaft being adapted to be driven to rotate by the tail rotor shaft, the control shaft being adapted to move along its own axial direction and drive the pitch control component to rotate, thereby changing the pitch angle of the blade; a control bearing, comprising an outer ring and an inner ring, the inner ring being assembled and connected to the control shaft and rotating together with the control shaft; a booster control lever assembly, which is assembled and connected to the outer ring of the bearing, the booster control lever assembly being adapted to drive the control bearing to move axially, thereby driving the control shaft to reciprocate; and a temperature detection component, disposed on the booster control lever assembly, the detection end of the temperature detection component contacting the outer ring of the bearing.

[0006] Beneficial effects: By assembling the inner ring of the bearing with the control shaft and the outer ring of the bearing with the booster control stick assembly, and by changing the assembly method of the control bearing and the structure of the booster control stick, the booster control stick assembly has installation space for assembling a temperature detection component. By placing the temperature detection component in the corresponding position on the booster control stick assembly to directly contact the outer ring of the bearing, the temperature of the outer ring of the bearing can be detected in real time and accurately. At the same time, the temperature detection component can transmit the measured information to the helicopter's monitoring system. When the preset temperature is reached, an early warning can be issued in a timely manner and the operator can be notified, improving the safety of the flight process and effectively solving the safety hazard problem of the control bearing of the existing tail rotor pitch mechanism operating for a long time.

[0007] In one optional embodiment, the booster lever assembly includes a lever and a connecting plate. The connecting plate is assembled and connected to the outer ring of the bearing. The lever is connected to the connecting plate and drives the connecting plate to move. The connecting plate is provided with a mounting groove for mounting a temperature detection component, and the opening of the mounting groove faces the outer ring of the bearing.

[0008] Beneficial effects: The booster lever assembly has a simple and reliable structure. It can reliably fit with the end face of the bearing outer ring through the connecting plate. Since the connecting plate is relatively large while the temperature detection component is usually small, the installation slot will not significantly affect the overall structural strength of the connecting plate, so that the booster lever assembly can still work stably and reliably.

[0009] In one alternative embodiment, the temperature detection assembly includes a temperature sensor and a connecting wire. The temperature sensor is connected to the helicopter's monitoring system via the connecting wire. The temperature sensor is disposed in a mounting slot, and the detection end of the temperature sensor contacts the outer ring of the bearing through the opening of the mounting slot.

[0010] Beneficial effects: The structure is simple and reliable, and the signal transmission process of the connecting line is more stable and faster, which can reduce the delay in the detection process.

[0011] In one alternative embodiment, connecting ears are formed on both sides of the temperature sensor, and a mounting groove is provided at the position of the connecting ears. The connecting ears are assembled and connected to the connecting groove by fastening components.

[0012] Beneficial effects: This connection method is simple and reliable, easy to assemble and disassemble, and the force is more even after assembly. In addition, it can avoid the problem of decreased temperature measurement accuracy caused by the temperature sensor's detection end becoming loose during operation.

[0013] In one optional embodiment, the connecting plate is provided with an oil hole for conveying lubricating oil, the mounting groove is located near the oil hole, and the connecting wire passes through the oil hole and connects to the temperature sensor.

[0014] Beneficial effects: The connecting wire can be directly threaded through the oil hole on the connecting plate. The structure is simple and reliable, and there is no need to open a separate threading hole, which can effectively avoid affecting the structural strength of the connecting plate.

[0015] In one alternative embodiment, the joystick has a through hole for the connecting wire to pass through.

[0016] Beneficial effect: After the connecting wire comes out of the oil hole, it can be directly inserted into the inside of the control lever without taking up space outside the control lever.

[0017] In one optional embodiment, the connecting plate has a connecting hole inside, one end of which communicates with the through hole and the other end forms a through outlet. The connecting wire passes through the through hole, the connecting hole and the corresponding oil hole in sequence, and is connected to the temperature sensor.

[0018] Beneficial effects: The connection hole is closer to the oil hole, which reduces the length of the connection cable exposed outside the control lever, improving the reliability and stability of the connection cable.

[0019] In one optional embodiment, the connecting plate is further provided with a locking structure at the position corresponding to the through-hole. The connecting wire is fixed to the connecting plate by the locking structure. The locking structure has a locked state that fixes the connecting wire to the through-hole, and an unlocked state that allows the connecting wire to be pulled along the through-hole.

[0020] Beneficial effects: The locking structure can fix the position of the connecting wire at the outlet, preventing the exposed connecting wire from moving or shaking at will, reducing the possibility of friction between the connecting wire and external components, and improving the service life of the connecting wire.

[0021] In one optional embodiment, the control lever is provided with a sealing element at one end near the control bearing and at the other end away from the control bearing. The sealing element is used to block the through hole. The sealing element away from the control bearing is provided with a through hole for the connecting wire to pass through. And / or, the tail rotor pitch control device also includes a casing and a bearing bushing. The outer ring of the bearing is engaged with the inner wall of the casing through the bearing bushing. The bearing bushing abuts against the connecting plate through a locking assembly, and the connecting plate abuts against the outer ring of the bearing to lock the outer ring of the bearing. The locking structure is a locking screw. The connecting plate is provided with a locking screw hole near the through hole. The locking screw passes through the locking screw hole and fixes the connecting wire.

[0022] Beneficial effects: By sealing the opening of the through hole with a sealing component, the connecting wires running through the through hole can be protected from interference by external objects. It can also prevent foreign objects from entering the bearing through the through hole, thereby improving the reliability of the working process.

[0023] Secondly, the present invention also provides a helicopter, comprising: a fuselage; a tail rotor assembly disposed at the tail of the fuselage; a tail gear reducer disposed at the tail of the fuselage for driving the tail rotor assembly to rotate; and the aforementioned tail rotor pitch control device disposed inside the tail gear reducer and assembled and connected to the tail rotor assembly. Attached Figure Description

[0024] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0025] Figure 1 This is a cross-sectional schematic diagram of a tail rotor pitch control device according to an embodiment of the present invention;

[0026] Figure 2 for Figure 1 A partially enlarged schematic diagram of the tail rotor pitch control device shown;

[0027] Figure 3 for Figure 1 A three-dimensional schematic diagram of the engagement between the booster control lever assembly and the control bearing of the tail rotor pitch control device;

[0028] Figure 4 for Figure 1 A three-dimensional schematic diagram of the connecting disc of the tail rotor pitch control device.

[0029] Explanation of reference numerals in the attached figures:

[0030] 1. Control shaft; 101. Locking nut;

[0031] 2. Operating bearing; 201. Bearing outer ring; 202. Bearing inner ring;

[0032] 3. Booster control lever assembly; 301. Control lever; 3011. Through hole; 302. Connecting plate; 3021. Mounting slot; 3022. Connecting slot; 3023. Oil hole; 3024. Connecting hole; 3025. Locking screw hole; 303. Sealing component;

[0033] 4. Temperature detection component; 401. Temperature sensor; 4011. Connecting ear; 402. Connecting cable;

[0034] 5. Locking structure; 6. Casing; 7. Bearing bushing; 8. Locking assembly; 801. Locking nut; 802. Locking ring; 803. Retaining ring. Detailed Implementation

[0035] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0036] The following is combined with Figures 1 to 4 The following describes embodiments of the present invention.

[0037] In related technologies, the seizure of the control bearing is mainly caused by the continuous rise in temperature of the control bearing during long-term rotation, which leads to volume expansion and wear. However, the control bearing is usually located inside the pitch control assembly, and its location is relatively concealed. Existing tail rotor pitch control mechanisms make it difficult to arrange detection structures to directly detect the operating status of the bearing. Related technologies generally use indirect means to monitor whether the control bearing is peeling off or damaged. Typically, a magnetic debris detector is installed at the bottom of the tail reducer oil sump. By monitoring the metal debris generated inside the tail reducer, the bearing's usage is indirectly monitored. However, this method has a large lag or delay and cannot promptly grasp the operating status of the control bearing.

[0038] According to an embodiment of the present invention, a tail rotor pitch control device is provided, comprising: a control shaft 1, a control bearing 2, a booster control lever assembly 3, and a temperature detection assembly 4. The control shaft 1 is driven to rotate by the tail rotor shaft and the tail rotor pitch control element. The control shaft 1 is adapted to move along its own axial direction and drive the pitch control element to rotate, thereby changing the pitch angle of the blade. The control bearing 2 includes an outer bearing ring 201 and an inner bearing ring 202. The inner bearing ring 202 is assembled and connected to the control shaft 1 and rotates together with the control shaft 1. The booster control lever assembly 3 is assembled and connected to the outer bearing ring 201. The booster control lever assembly 3 is adapted to drive the control bearing 2 to move axially, thereby driving the control shaft 1 to reciprocate. The temperature detection assembly 4 is disposed on the booster control lever assembly 3 and connected to the helicopter's monitoring system. The detection end of the temperature detection assembly 4 contacts the outer bearing ring 201 and continuously detects the temperature of the outer bearing ring 201.

[0039] The tail rotor pitch control device of this embodiment connects the inner bearing ring 202 to the control shaft 1 and the outer bearing ring 201 to the booster control stick assembly 3. By changing the assembly method of the control bearing 2 and the structure of the control stick, the booster control stick assembly 3 has an installation space for mounting the temperature detection component 4. By placing the temperature detection component 4 at the corresponding position of the booster control stick assembly 3 to directly contact the outer bearing ring 201, the temperature of the outer bearing ring 201 can be detected in real time and accurately. At the same time, the temperature detection component 4 can transmit the measured information to the helicopter's monitoring system. When the preset temperature is reached, an early warning can be issued in time and the operator can be notified, improving the safety of the flight process and effectively solving the safety hazard problem of the control bearing of the existing tail rotor pitch control mechanism working for a long time.

[0040] It should be noted that the pitch control component of the tail rotor blade is a fork-shaped component; the control shaft 1 is connected to the tail rotor shaft via a spline or a flat key, and the control shaft 1 is connected to the fork-shaped component via a spline or a flat key.

[0041] In related technologies, the inner ring 202 of the bearing is typically fitted onto a bearing housing connected to the booster control stick assembly or directly mounted on the booster control stick, while the outer ring 201 of the bearing is assembled and connected to the inner hole of the pitch control shaft. This arrangement makes it difficult to install a temperature detection structure inside the control stick due to its relatively thin overall size. Furthermore, because the booster actuator cylinder is mounted outside the control stick, this structure cannot accommodate the connection wires of the temperature sensor to the helicopter's monitoring system. Additionally, the temperature detection structure would occupy some space inside the control stick, significantly reducing its structural strength. Therefore, the assembly method of the control bearing 2 in related technologies cannot accommodate an additional temperature detection structure, thus making it impossible to directly obtain the temperature information of the control bearing 2.

[0042] When the temperature of the control bearing 2 reaches the preset warning temperature, it means that the control bearing 2 cannot be lubricated or cooled. The monitoring process of the tail rotor pitch control bearing by the magnetic debris detection signal device usually has a delay. The metal debris generated at the position of the pitch control bearing needs to flow continuously through a complex flow path before it can reach the bottom of the tail rotor oil sump and be monitored by the magnetic debris detection signal device. This monitoring process has obvious delay and lag. It is usually monitored one hour or even longer after the pitch control bearing peels off. When the magnetic debris detection signal device obtains information and issues an alarm at this time, the warning information has exceeded the optimal warning time. At this time, the control bearing may already be in a state of impending failure, which will affect the safety of tail rotor pitch control.

[0043] In this embodiment, the tail rotor pitch control device changes the assembly method of the control bearing 2 and the structure of the booster control lever assembly 3. The booster control lever assembly 3 is assembled and connected to the outer ring 201 of the bearing. During operation, the outer ring 201 of the bearing only moves along the axial direction and does not rotate. Since the booster control lever assembly 3 is closer to the outside and does not need to be nested with the control bearing 2, it can form a space for arranging the temperature detection component 4. Therefore, the temperature of the control bearing 2 can be obtained simply and effectively through the temperature detection component 4, solving the problem of difficulty in directly obtaining the temperature of the control bearing 2 in related technologies.

[0044] In this embodiment, the booster lever assembly 3 includes a lever 301 and a connecting plate 302. The connecting plate 302 is assembled and connected to the outer ring 201 of the bearing. The lever 301 is connected to the connecting plate 302 and drives the connecting plate 302 to move. The connecting plate 302 is provided with a mounting groove 3021 for mounting the temperature detection component 4. The opening of the mounting groove 3021 faces the outer ring 201 of the bearing. The booster lever assembly 3 has a simple and reliable structure. It can reliably cooperate with the end face of the outer ring 201 of the bearing through the connecting plate 302. Since the connecting plate 302 is relatively large and the temperature detection component 4 is usually small, the mounting groove 3021 will not significantly affect the overall structural strength of the connecting plate 302, so that the booster lever assembly 3 can still work stably and reliably.

[0045] Specifically, such as Figure 3 and Figure 4 As shown, the mounting groove 3021 is disposed on the outer peripheral surface of the connecting plate 302. The temperature detection component 4 is disposed in the mounting groove 3021 and can be directly hidden inside the connecting plate 302, which can avoid interference between the temperature detection component 4 and surrounding components.

[0046] In this embodiment, the temperature detection component 4 includes a temperature sensor 401 and a connecting line 402. The temperature sensor 401 is connected to the helicopter's monitoring system via the connecting line 402. The temperature sensor 401 is disposed in the mounting groove 3021. The detection end of the temperature sensor 401 contacts the outer ring 201 of the bearing through the opening of the mounting groove 3021. The structure is simple and reliable. The signal transmission process of the connecting line 402 is more stable and faster, which can reduce the delay in the detection process.

[0047] Specifically, there are no restrictions on the size and specifications of the temperature sensor 401 and the arrangement of the connecting wire 402. The size and specifications of the temperature sensor 401 can be selected according to the actual size and specifications of the helicopter model. The connecting wire 402 can be arranged to extend along the outer wall of the connecting plate 302 and the control stick 301, or it can be installed inside the connecting plate 302 and the control stick 301.

[0048] Furthermore, during operation, the temperature sensor 401 is in direct contact with the outer ring 201 of the pitch control bearing 2, and outputs the resistance signal of the contact point to the helicopter's monitoring system through the connecting line 402 and converts it into a temperature signal, thereby realizing real-time monitoring of the temperature of the control bearing 2.

[0049] In this embodiment, connecting ears 4011 are formed on both sides of the temperature sensor 401, and a connecting groove 3022 is provided in the mounting groove 3021 corresponding to the position of the connecting ears 4011. The connecting ears 4011 are assembled and connected to the connecting groove 3022 by fastening components. This connection method is simple and reliable, easy to assemble and disassemble, and the force is more even after assembly. In addition, it can also avoid the problem of temperature measurement accuracy decreasing due to the loosening of the detection end of the temperature sensor during operation.

[0050] It is understood that, as an alternative implementation, the temperature sensor 401 can also be connected to the inner wall of the mounting groove 3021 by means of welding, snap-fitting, gluing, etc.

[0051] Specifically, such as Figure 3 As shown, the connecting ear 4011 can be placed into the corresponding connecting groove 3022. The connecting ear 4011 is provided with a through hole for fastening components to pass through, and the connecting groove 3022 is provided with a corresponding mating hole for fastening components to cooperate with.

[0052] In this embodiment, the connecting plate 302 is provided with an oil hole 3023 for conveying lubricating oil. The mounting groove 3021 is set close to the oil hole 3023. The connecting wire 402 passes through the oil hole 3023 and is connected to the temperature sensor 401. The connecting wire 402 can be directly passed through the oil hole on the connecting plate 302. The structure is simple and reliable, and there is no need to open a separate through hole, which can effectively avoid affecting the structural strength of the connecting plate 302.

[0053] The mounting groove 3021 is connected to the corresponding oil hole 3023. The oil hole 3023 can be used to transport lubricating oil and to pass through the connecting line 402. It is a multi-purpose hole that makes full use of the inherent structure on the connecting plate 302.

[0054] In addition, such as Figure 4 As shown, in order to deliver lubricating oil to the operating bearing 2 evenly and reliably, multiple oil holes 3023 are arranged circumferentially on the surface of the connecting plate 302, and the mounting groove 3021 is correspondingly set with one of the oil holes 3023.

[0055] Specifically, there are no specific limitations on the number and size of the oil holes 3023; they can be flexibly set according to requirements.

[0056] In this embodiment, the control lever 301 has a through hole 3011 for the connecting wire 402 to pass through. The connecting wire 402 is disposed inside the through hole 3011. After the connecting wire 402 passes through the oil hole 3023, it can be directly inserted into the inside of the control lever 301. The connecting wire 402 does not need to occupy the space outside the control lever 301. The control lever 301 can protect the connecting wire 402 and prevent the connecting wire 402 from colliding or rubbing with external components and failing.

[0057] Among them, such as Figure 1 As shown, the through hole 3011 extends along the axial direction of the control lever 301. Compared with a solid lever, this type of control lever 301 is lighter and more resistant to bending, providing protection for the connecting cable 402 while also improving its own performance.

[0058] In this embodiment, the connecting plate 302 is provided with a connecting hole 3024 inside. One end of the connecting hole 3024 is connected to the through hole 3011 and the other end forms a through outlet. The connecting line 402 passes through the through hole 3011, the connecting hole 3024 and the corresponding oil hole 3023 in sequence, and is connected to the temperature sensor 401. The connecting hole 3024 is close to the oil hole 3023, which can reduce the length of the connecting line 402 exposed outside the control shaft 1 and improve the reliability and stability of the connecting line 402. In addition, since the connection position between the connecting plate 302 and the control lever 301 has high strength, opening the connecting hole 3024 here has little impact on the overall strength of the control shaft 1.

[0059] Specifically, such as Figure 3 and Figure 4 As shown, in order to further reduce the impact of the connecting hole 3024 on the structural strength of the connecting plate 302, a protrusion is also provided at the corresponding position of the connecting plate 302. The connecting hole 3024 is located inside the protrusion, and the outlet is located at the end of the protrusion. The protrusion can enhance the local structural strength at the location of the connecting hole 3024, increase the wall thickness at the connecting hole 3024, and ensure that the connecting plate 302 can work stably and reliably.

[0060] In this embodiment, the connecting plate 302 is also provided with a locking structure 5 at the position corresponding to the through-hole. The connecting wire 402 is fixed to the connecting plate 302 through the locking structure 5. The locking structure 5 has a locked state that fixes the connecting wire 402 to the through-hole, and an unlocked state that allows the connecting wire 402 to be pulled along the through-hole. The locking structure 5 can fix the position of the connecting wire 402 at the through-hole, prevent the exposed connecting wire 402 from moving or shaking at will, reduce the possibility of friction between the connecting wire 402 and external components, and improve the service life of the connecting wire 402.

[0061] Specifically, the form of the locking structure 5 is not limited; it can be a locking nut, a snap-fit ​​structure, or a clamp, as long as it can fix the connecting line 402 at the outlet.

[0062] In this embodiment, the control lever 301 is provided with a sealing member 303 at one end near the control bearing 2 and at the other end away from the control bearing 2. The sealing member 303 is used to block the through hole 3011. The sealing member 303 away from the control bearing 2 is provided with a through hole for the connecting wire 402 to pass through. Since the control bearing 2 is provided with a through hole 3011, by blocking the opening of the through hole 3011 by the sealing member 303, it can be ensured that the connecting wire 402 passing through the through hole 3011 is not interfered with by external objects, and it can also prevent external objects from entering the control bearing 2 through the through hole 3011, thereby improving the reliability of the working process.

[0063] Specifically, there are no restrictions on the specific type and structure of the plugging component 303. It can be an internal hexagonal plug, an external hexagonal plug, a tapered thread plug, etc. Existing plug structures can be referenced, but it needs to be able to provide a through hole for the connecting wire 402 to pass through.

[0064] Furthermore, such as Figure 1 As shown, the sealing member 303, located away from the control bearing 2, not only has a through hole for the connecting wire 402 to pass through, but the location of the sealing member 303 is also filled with sealant to further improve the sealing performance of the end of the control lever 301 away from the control bearing 2, preventing foreign objects and rainwater from entering the control lever 301 through gaps. The sealing member 303 at the end of the control lever 301 near the control bearing 2 can effectively prevent oil and gas in the reducer from entering the control lever 301.

[0065] Additionally, it should be noted that, since the through hole 3011 of the control lever 301 needs to be machined starting from the end closest to the control bearing 2, the diameter of the through hole 3011 at the end closest to the control bearing 2 is larger than the diameter at the other end. In order to better seal the through hole 3011, the outer diameter of the sealing member 303 at the end closest to the control bearing 2 is larger than the outer diameter of the sealing member 303 away from the control bearing 2.

[0066] In this embodiment, the tail rotor pitch control device also includes a housing 6 and a bearing bushing 7. The outer ring 201 of the bearing is fitted with the inner wall of the housing 6 through the bearing bushing 7. The bearing bushing 7 abuts against the connecting plate 302 through the locking assembly 8, and the connecting plate 302 abuts against the outer ring 201 of the bearing to lock the outer ring 201 of the bearing. The locking structure 5 is a locking screw. The connecting plate 302 is provided with a locking screw hole 3025 near the outlet. The locking screw passes through the locking screw hole 3025 and fixes the connecting line 402. The structure is simple and reliable, and easy to assemble and manufacture. After the locking screw fixes the connecting line 402, it can prevent the connecting line 402 from continuously vibrating and shaking during operation, and prevent the connecting line from interfering with or wearing with other rotating parts.

[0067] Specifically, the locking assembly 8 includes a locking nut 801, a locking ring 802, and a retaining ring 803. The locking nut 801 is threadedly connected to the inner wall of the bearing bushing 7 and presses the connecting disc 302 against the end of the bearing inner ring 202. The locking ring 802 simultaneously abuts against the end faces of the locking nut 801 and the bearing bushing 7 to position the locking nut 801 and the bearing bushing 7 circumferentially. The retaining ring 803 engages with the side of the locking ring 802 away from the locking nut 801, effectively restricting the position of the locking ring 802 and preventing the locking nut 801 from loosening during operation.

[0068] In this embodiment, the control shaft 1 is assembled and connected to the inner ring 202 of the control bearing 2 via a locking nut 101.

[0069] According to an embodiment of the present invention, in another aspect, a helicopter is provided, comprising: a fuselage, a tail rotor assembly, a tail gearbox, and the aforementioned tail rotor pitch control device, wherein the tail gearbox and the tail rotor assembly are disposed at the tail of the fuselage, and the tail gearbox drives the tail rotor assembly to rotate; the tail rotor pitch control device is disposed inside the tail gearbox and is assembled and connected to the tail rotor assembly.

[0070] In this embodiment, the helicopter also includes necessary components such as the fuselage and tail rotor.

[0071] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. A tail rotor pitch control device, characterized in that, include: The control shaft (1) is driven to rotate by the tail rotor shaft and the pitch control component of the tail rotor. The control shaft (1) is adapted to move along its own axial direction and drive the pitch control component to rotate, thereby changing the pitch angle of the blade. The control bearing (2) includes an outer ring (201) and an inner ring (202), wherein the inner ring (202) is assembled and connected to the control shaft (1) and rotates together with the control shaft (1); The booster lever assembly (3) is assembled and connected to the outer ring (201) of the bearing. The booster lever assembly (3) is adapted to drive the control bearing (2) to move axially, so as to drive the control shaft (1) to move. A temperature detection component (4) is disposed on the booster lever assembly (3), and the detection end of the temperature detection component (4) is in contact with the outer ring (201) of the bearing; The booster lever assembly (3) includes a lever (301) and a connecting plate (302). The connecting plate (302) is assembled and connected to the outer ring of the bearing (201). The lever (301) is connected to the connecting plate (302) and drives the connecting plate (302) to move. The connecting plate (302) is provided with a mounting groove (3021) for the temperature detection assembly (4) to be installed. The opening of the mounting groove (3021) faces the outer ring of the bearing (201). The temperature detection component (4) includes a temperature sensor (401) and a connecting line (402). The temperature sensor (401) is connected to the monitoring system of the helicopter through the connecting line (402). The temperature sensor (401) is disposed in the mounting groove (3021). The detection end of the temperature sensor (401) contacts the outer ring (201) of the bearing through the opening of the mounting groove (3021). The connecting plate (302) is provided with an oil hole (3023) for conveying lubricating oil. The mounting groove (3021) is located close to the oil hole (3023). The connecting line (402) passes through the oil hole (3023) and is connected to the temperature sensor (401). The control lever (301) has a through hole (3011) inside for the connecting wire (402) to pass through, and the connecting wire (402) is disposed inside the through hole (3011); The connecting plate (302) has a connecting hole (3024) inside. One end of the connecting hole (3024) is connected to the through hole (3011) and the other end forms a through outlet. The connecting line (402) passes through the through hole (3011), the connecting hole (3024) and the corresponding oil hole (3023) in sequence, and is connected to the temperature sensor (401).

2. The tail rotor pitch control device according to claim 1, characterized in that, The temperature sensor (401) has connecting ears (4011) on both sides, and the mounting groove (3021) has a connecting groove (3022) corresponding to the position of the connecting ears (4011). The connecting ears (4011) are assembled and connected to the connecting groove (3022) by fastening components.

3. The tail rotor pitch control device according to claim 1, characterized in that, The connecting plate (302) is further provided with a locking structure (5) at the position corresponding to the through-hole. The connecting line (402) is fixed to the connecting plate (302) through the locking structure (5). The locking structure (5) has a locked state that fixes the connecting line (402) to the through-hole, and an unlocked state that allows the connecting line (402) to be pulled along the through-hole.

4. The tail rotor pitch control device according to claim 3, characterized in that, The control lever (301) has a sealing member (303) at one end near the control bearing (2) and at the other end away from the control bearing (2). The sealing member (303) is used to block the through hole (3011). The sealing member (303) away from the control bearing (2) has a through hole for the connecting wire (402) to pass through. And / or, the tail rotor pitch control device further includes a casing (6) and a bearing bushing (7), the outer ring of the bearing (201) is engaged with the inner wall of the casing (6) through the bearing bushing (7), the bearing bushing (7) is abutted against the connecting plate (302) through the locking assembly (8), and the connecting plate (302) is abutted against the outer ring of the bearing (201) to lock the outer ring of the bearing (201), the locking structure (5) is a locking wire, the connecting plate (302) is provided with a locking wire hole (3025) near the outlet, the locking wire passes through the locking wire hole (3025) and fixes the connecting line (402).

5. A helicopter, characterized in that, include: body; A tail rotor assembly is located at the tail of the fuselage; A tail gear reducer is located at the tail of the fuselage and drives the tail rotor assembly to rotate; The tail rotor pitch control device according to any one of claims 1 to 4 is disposed inside the tail gearbox and assembled and connected to the tail rotor assembly.

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