Knuckle bearing hinged bolt and aircraft flap driving system with same

Abstract

The utility model belongs to the technical field of mechanical transmission, and relates to a knuckle bearing hinge bolt and an aircraft flap driving system with the same. The knuckle bearing hinge bolt comprises a hexagonal head bolt (2), a pressure oil injection nozzle (1), a plug (3) and a hexagonal groove type nut (7). The hexagonal head bolt (2) is provided with a blind hole (21) extending in the axial direction, an opening of the blind hole (21) is plugged through a plug (3), the other end of the blind hole (21) is communicated with a through hole (22) extending in the radial direction, and the end, away from the plug (3), of the hexagonal head bolt (2) is provided with external threads used for being connected with a hexagonal groove type nut (7) so that the hexagonal head bolt (2) can be fixed to an inner hole of a hydraulic actuator cylinder knuckle bearing. The through hole (22) is aligned with an oil groove between the inner ring and the outer ring of the knuckle bearing, a threaded hole (23) communicated with the blind hole (21) is machined in the bolt head in the radial direction, and the threaded hole (23) is in threaded connection with a pressure oil injection nozzle (1). The mechanical transmission hinge pair can be lubricated more conveniently.

Description

Technical Field

[0001] The present application belongs to the field of mechanical transmission technology, and in particular relates to a joint bearing hinge bolt and an aircraft flap drive system having the same. Background Art

[0002] In the mechanical transmission rod system composed of rocker arms, tie rods, supports, etc., in order to compensate for the errors in parts manufacturing and on-machine installation, the rod head end of the tie rod usually adopts a spherical bearing earring bolt type, and the rocker arm fork ear and the tie rod rod head spherical bearing usually adopts a spherical bearing hinge bolt assembly type composed of a hinge bolt, a washer, a hexagonal slot nut, a cotter pin, etc.; in addition, in the system where the control surface is driven to rotate around a fixed axis by a hydraulic actuator, the spherical bearing hinge bolt assembly type is usually used between the fixed end spherical bearing of the hydraulic actuator and the fixed support, and between the movable end of the hydraulic actuator and the control joint of the control surface.

[0003] In order to meet the needs of mechanical transmission articulated motion pairs, the joint bearing articulated bolt assembly, which is composed of articulated bolts, washers, hexagonal slot nuts, cotter pins, etc., must meet two requirements in terms of lubrication and maintenance: first, it should ensure sufficient grease lubrication between the inner and outer rings of the joint bearing to reduce the friction torque and ensure the movement flexibility of the motion pair; second, lubrication maintenance should be easy to implement; third, it should meet the lubrication maintenance interval requirements.

[0004] The traditional solution is: the bolts, washers, hexagonal slot nuts, and cotter pins of the spherical bearing hinge bolt assembly are all standard parts, and maintenance personnel use a brush to apply grease to the spherical bearing hinge bolt assembly.

[0005] Traditional torsion bar solutions have the following problems: First, the hinged bolt assembly lacks a dedicated lubrication channel, and the brush can only apply grease to the outer surface of the hinged bolt assembly, making it difficult to reach between the inner and outer rings of the bearing, thus defeating the purpose of lubrication maintenance. Second, lubrication maintenance cannot be easily implemented, nor can it meet the required lubrication maintenance intervals. Furthermore, even if a grease nozzle is installed, since the pressure grease nozzle is threaded onto the end face of the bolt head, a pressure grease gun can only inject grease from the end face of the bolt head. Due to space constraints on the aircraft, this is often impossible to implement with the hinged bolt assembly installed, rendering the grease channel useless. Utility Model Content

[0006] In order to solve at least one of the above technical problems, the present application designs a joint bearing hinge bolt and an aircraft flap drive system having the same, so as to solve the problems of difficulty in lubricating the joint bearings in the mechanical transmission hinge parts and difficulty in ensuring the lubrication maintenance cycle intervals.

[0007] In a first aspect, the present application provides a joint bearing hinge bolt, which mainly includes a hexagonal head bolt, a pressure oiling nozzle, a plug and a hexagonal slot nut;

[0008] Among them, the hexagonal head bolt has a blind hole extending in the axial direction, the blind hole has an opening at the bolt head and is sealed by a plug, and the other end is connected to a through hole extending radially along the hexagonal head bolt. The hexagonal head bolt has an external thread at the end away from the plug, which is used to connect with the hexagonal slot nut to fix the hexagonal head bolt to the inner hole of the hydraulic actuator joint bearing, and align the through hole with the oil groove between the inner and outer rings of the joint bearing. A threaded hole connecting to the blind hole is radially processed at the bolt head, and the threaded hole is threadedly connected to the pressure oil injection nozzle.

[0009] Preferably, the through hole is provided at an axial middle position of the hexagonal head bolt, and the distance that the blind hole extends axially from the open end to the bottom exceeds the middle position of the hexagonal head bolt.

[0010] Preferably, the hexagonal head bolt is machined from 30CrMnSiNi2A hexagonal bar.

[0011] Preferably, the hexagonal head bolt is subjected to heat treatment, surface phosphating and then coated with 7253 extreme pressure grease.

[0012] Preferably, a step is machined at the blind hole opening of the hexagonal head bolt to achieve an interference fit with the plug.

[0013] Preferably, the plug is machined from LY12-CZ rod.

[0014] Preferably, the plug is surface-treated by yellow anodizing.

[0015] Preferably, a washer is provided between the hexagonal head bolt and the hexagonal slot nut, and a cotter pin passing through the radial locking hole of the hexagonal slot nut is installed on the other side of the hexagonal slot nut.

[0016] The second aspect of the present application provides an aircraft flap drive system, including a first hydraulic actuator, a second hydraulic actuator and the above-mentioned joint bearing hinge bolts, the fixed-end joint bearings of the first hydraulic actuator and the second hydraulic actuator are respectively connected to the first fixed support assembly and the second fixed support assembly on the aircraft through the joint bearing hinge bolts, and the movable-end joint bearings of the first hydraulic actuator and the second hydraulic actuator are respectively connected to the first flap fixed rocker arm and the second flap fixed rocker arm on the aircraft through the joint bearing hinge bolts, and after the joint bearing hinge bolts are installed, the axis of the pressure oiling nozzle extends obliquely upward.

[0017] The invention has the advantages of simple structure, good manufacturing processability, good installation and disassembly maintenance, long service life, low use cost, etc. The invention has the advantages of convenient lubrication of mechanical transmission articulated pairs, sufficient lubrication, and meeting the requirements of lubrication maintenance intervals. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic structural explosion diagram of a preferred embodiment of the spherical bearing hinge bolt of the present application.

[0019] Figure 2 For this application Figure 1 Schematic diagram of the hexagonal head bolt structure of the embodiment shown.

[0020] Figure 3 For this application Figure 1 Schematic diagram of the internal opening of the hexagonal head bolt in the illustrated embodiment.

[0021] Figure 4 This is a structural diagram of the aircraft flap drive system of this application.

[0022] Among them, 1-pressure oil injection nozzle, 2-hexagonal head bolt, 21-blind hole, 22-through hole, 23-threaded hole, 3-plug, 4-double ear, 5-spherical bearing earring bolt, 6-washer, 7-hexagonal slot nut, 8-cotter pin;

[0023] 10- articulated bearing hinge bolt, 11- first hydraulic actuator, 12- second hydraulic actuator, 13- first fixed support assembly, 14- second fixed support assembly, 15- first flap fixed rocker arm, 16- second flap fixed rocker arm. DETAILED DESCRIPTION

[0024] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the implementation of this application will be described in more detail below in conjunction with the drawings in the implementation of this application. In the drawings, the same or similar numbers throughout represent the same or similar elements or elements with the same or similar functions. The described implementation is a part of the implementation of this application, not all of the implementations. The implementation described below with reference to the drawings is exemplary and is intended to be used to explain this application, and should not be understood as a limitation on this application. Based on the implementation in this application, all other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The implementation of this application is described in detail below in conjunction with the drawings.

[0025] The first aspect of the present application provides a joint bearing hinge bolt, such as Figure 1-Figure 3 As shown, it mainly includes: a hexagonal head bolt 2, a pressure oil injection nozzle 1, a plug 3 and a hexagonal slot nut 7;

[0026] Among them, the hexagonal head bolt 2 has a blind hole 21 extending in the axial direction. The blind hole 21 has an opening at the bolt head and is sealed by a plug 3. The other end is connected to a through hole 22 extending radially along the hexagonal head bolt 2. The hexagonal head bolt 2 has an external thread at the end away from the plug 3, which is used to connect with the hexagonal slot nut 7 to fix the hexagonal head bolt 2 to the inner hole of the hydraulic actuator joint bearing and align the through hole 22 with the oil groove between the inner and outer rings of the joint bearing. A threaded hole 23 connecting to the blind hole 21 is radially processed at the bolt head, and the threaded hole 23 is threadedly connected to the pressure oil nozzle 1.

[0027] The hexagonal bolt 2 of this application is a machined part, the pressure oil nozzle 1 is a HB4-71 standard part, and the plug 3 is a machined part. Figure 3 , HB4-71 standard pressure oiling nozzle 1 is tightened and installed on the side of the bolt head of the hexagonal head bolt 2 with M6-5H / 5h6h thread; the outer cylindrical surface of the machined plug 3 and the inner hole perpendicular to the end face of the bolt head are interference fit according to φ4H8 / x8 to realize the plugging process from the end face of the bolt head.

[0028] Maintenance personnel can use a pressure grease gun to inject 7253 extreme pressure grease from the pressure grease nozzle 1 of HB4-71. The grease enters the middle part of the bolt rod along the blind hole 21 along the axial direction of the hexagonal head bolt 2 and the through hole 22 perpendicular to the axial direction of the bolt, and then enters between the inner and outer rings of the joint bearing through the oil groove between the inner and outer rings of the joint bearing, forming a complete lubrication path. This application solves the problem of difficulty in lubrication maintenance at the mechanical transmission articulated joint due to the difficulty in injecting grease between the inner and outer rings of the joint bearing.

[0029] In some optional embodiments, the through hole 22 is provided at the axial middle position of the hexagonal head bolt 2 , and the distance that the blind hole 21 extends axially from the open end to the bottom exceeds the middle position of the hexagonal head bolt 2 .

[0030] In this embodiment, reference Figure 3 The depth of the blind hole 21 exceeds half of the length of the hexagonal head bolt 2, that is, the depth of the blind hole 21 along the axis of the bolt exceeds the axis of the through hole 22 perpendicular to the axis of the bolt. The blind hole 21 can store a certain amount of grease, which gradually overflows from the blind hole 21 during the operation of the articulated motion pair and enters the middle of the bolt polished rod, thereby achieving the lubrication maintenance cycle interval requirements of the articulated motion pair.

[0031] In some optional embodiments, the hexagonal head bolt 2 is machined from 30CrMnSiNi2A hexagonal bar.

[0032] In some optional embodiments, the hexagonal head bolt 2 is heat-treated, surface-phosphated, and then coated with 7253 extreme pressure grease.

[0033] In this embodiment, the heat treatment pressure of the hexagonal head bolt 2 is σb=1670±100 MPa; after the surface treatment HL (phosphating), 7253 extreme pressure grease is coated on the outer surface to achieve the purpose of corrosion protection.

[0034] It should also be noted that compared with ordinary standard parts, the hexagonal head bolt 2 has been optimized in terms of external dimensions. This mainly means that the thickness of the bolt head has been increased to 11 mm, so that an M6-5H internal threaded hole can be machined on the side of the bolt head, so that after being threadedly connected to the HB4-71 pressure oiling nozzle 1, the hole margin requirements can still be met. The middle of the hexagonal head bolt 2 is the polished rod part. The diameter size of the polished rod is φ19.05, which is consistent with the inner hole diameter size of the hydraulic actuator joint bearing (model 1836), and the tolerance band of the polished rod diameter is f7; the length size of the polished rod of the hexagonal head bolt is consistent with the thickness size of the inner ring of the joint bearing; the external thread size diameter of the hexagonal head bolt is slightly smaller than the polished rod diameter size, and the closest specification is M18×1.5-6h; through the above design measures of the outer profile size of the hexagonal head bolt, the small gap between the bolt polished rod and the inner ring of the joint bearing is achieved when the articulated bolt assembly is installed, ensuring that the joint bearing articulated bolt of this application can be easily inserted into the joint bearing, and large diameter thread is used to ensure the strength of the threaded connection while reducing the radial clearance.

[0035] In some optional embodiments, a step is machined at the blind hole opening of the hexagonal head bolt 2 to achieve an interference fit with the plug 3 .

[0036] In this embodiment, Figure 3 As shown, a step with a diameter of φ4H8 and a depth not exceeding the axis of the M6-5H internal thread is machined at the center of the bolt head end, so that the bolt head end face and the plug 3 can be assembled by interference fit to achieve process plugging.

[0037] In some optional embodiments, the plug 3 is machined from LY12-CZ bar stock. In this embodiment, the outer cylindrical diameter of the plug 3 is φ4x8, and the axial dimension of the outer cylindrical surface of the plug 3 matches the depth of the inner hole of the bolt head end face, ensuring a φ4H8 / x8 interference fit with the inner hole of the bolt head end face, ensuring a flush fit between the plug end face and the bolt head end face.

[0038] In some optional embodiments, the plug 3 is surface-treated by yellow anodizing (DYGF). This embodiment can reduce the potential difference between the plug material LY12 and the hexagonal head bolt material 30CrMnSiNi2A, thereby achieving the purpose of corrosion protection.

[0039] In some optional embodiments, a washer 6 is provided between the hexagonal head bolt 2 and the hexagonal slot nut 7 , and a cotter pin 8 passing through a radial locking hole of the hexagonal slot nut 7 is installed on the other side of the hexagonal slot nut 7 .

[0040] The second aspect of the present application provides an aircraft flap drive system, including a first hydraulic actuator 11, a second hydraulic actuator 12 and the above-mentioned joint bearing hinge bolt 10, the fixed end joint bearings of the first hydraulic actuator 11 and the second hydraulic actuator 12 are respectively connected to the first fixed support assembly 13 and the second fixed support assembly 14 on the aircraft through the joint bearing hinge bolt 10, and the movable end joint bearings of the first hydraulic actuator 11 and the second hydraulic actuator 12 are respectively connected to the first flap fixed rocker arm 15 and the second flap fixed rocker arm 16 on the aircraft through the joint bearing hinge bolt 10. After the joint bearing hinge bolt 10 is installed, the axis of the pressure oil nozzle 1 extends obliquely upward.

[0041] refer to Figure 4 The flap drive system of a certain type of aircraft adopts a hydraulic actuator drive form. A flap on one side is driven by two hydraulic actuators. Both ends of the two hydraulic actuators corresponding to each flap are installed with the joint bearing hinge bolts 10 of the present application. Figure 1 The hydraulic actuator is equipped with spherical bearing eyebolts 5 at both ends, with internal bearings. Two ears 4 are provided at the end of the fixed support assembly or the flap-mounted rocker arm, which are hinged to the spherical bearing eyebolts 5. When the hydraulic actuator is at its initial length, the flap is at zero degrees. When the hydraulic actuator outputs displacement based on its initial length and the dimension between the two hinge centers extends, the two hydraulic actuators drive the flap-mounted rocker arm to deflect around the flap's fixed rotation axis.

[0042] In this embodiment, reference Figure 1 The piston rod at the movable end of the hydraulic actuator is connected to the spherical bearing earring bolt 5 by internal and external threads. The initial relative position of the spherical bearing earring bolt 5 and the piston rod can be adjusted to achieve the initial length adjustment of the hydraulic actuator. After adjustment, it is locked by the locking device to achieve the zero-degree step difference requirement of the initial installation of the hydraulic actuator flap. In addition, when the spherical bearing hinge bolt 10 of the present application is used as an assembly part for overall installation, it is necessary to ensure that the axis of the pressure oiling nozzle is installed obliquely upward, and the maintenance personnel can use a pressure oiling gun to inject 7253 extreme pressure grease from the HB4-71 pressure oiling nozzle. The grease enters the middle of the bolt polished rod along the hexagonal head bolt, and then enters between the inner and outer rings of the joint bearing through the oil groove between the inner and outer rings of the joint bearing, forming a complete lubrication path, which solves the problem of difficulty in lubrication maintenance caused by the difficulty in injecting grease between the inner and outer rings of the joint bearing at the mechanical transmission articulated joint. Since the depth of the blind hole 21 along the axis of the bolt exceeds the axis of the through hole 22 perpendicular to the axis of the bolt, the blind hole 21 can store a certain amount of grease, which gradually overflows from the blind hole 21 during the operation of the articulated motion pair and enters the middle of the bolt polished rod, thereby meeting the lubrication maintenance cycle interval requirements of the articulated motion pair.

[0043] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. A joint bearing hinge bolt, characterized in that: It comprises a hexagonal head bolt (2), a pressure oil injection nozzle (1), a plug (3) and a hexagonal slot nut (7); The hexagonal head bolt (2) has a blind hole (21) extending in the axial direction. The blind hole (21) has an opening at the bolt head and is sealed by a plug (3). The other end is connected to a through hole (22) extending radially along the hexagonal head bolt (2). The hexagonal head bolt (2) has an external thread at the end away from the plug (3) for connecting with a hexagonal slot nut (7) to fix the hexagonal head bolt (2) to the inner hole of the hydraulic actuator joint bearing and make the through hole (22) align with the oil groove between the inner and outer rings of the joint bearing. A threaded hole (23) connected to the blind hole (21) is processed radially at the bolt head. The threaded hole (23) is threadedly connected to the pressure oil injection nozzle (1).

2. The spherical bearing hinge bolt according to claim 1, characterized in that: The through hole (22) is arranged at the axial middle position of the hexagonal head bolt (2), and the distance of the blind hole (21) extending axially from the open end to the bottom exceeds the middle position of the hexagonal head bolt (2).

3. The spherical bearing hinge bolt according to claim 1, characterized in that: The hexagonal head bolt (2) is machined from 30CrMnSiNi2A hexagonal bar.

4. The spherical bearing hinge bolt according to claim 1, characterized in that: The hexagonal head bolt (2) is subjected to heat treatment, surface phosphating and then coated with 7253 extreme pressure grease.

5. The spherical bearing hinge bolt according to claim 1, characterized in that: The blind hole opening of the hexagonal head bolt (2) is processed with a step to achieve interference fit with the plug (3).

6. The spherical bearing hinge bolt according to claim 1, characterized in that: The plug (3) is machined from LY12-CZ rods.

7. The spherical bearing hinge bolt according to claim 1, characterized in that: The plug (3) is surface-treated by yellow anodizing.

8. The spherical bearing hinge bolt according to claim 1, characterized in that: A washer (6) is provided between the hexagonal head bolt (2) and the hexagonal slot nut (7), and a cotter pin (8) passing through a radial locking hole of the hexagonal slot nut (7) is installed on the other side of the hexagonal slot nut (7).

9. An aircraft flap drive system, characterized in that: It comprises a first hydraulic actuator (11), a second hydraulic actuator (12) and a joint bearing hinge bolt (10) as described in any one of claims 1 to 8, wherein the fixed end joint bearings of the first hydraulic actuator (11) and the second hydraulic actuator (12) are respectively connected to the first fixed support assembly (13) and the second fixed support assembly (14) on the machine through the joint bearing hinge bolt (10), and the movable end joint bearings of the first hydraulic actuator (11) and the second hydraulic actuator (12) are respectively connected to the first flap fixed rocker arm (15) and the second flap fixed rocker arm (16) on the machine through the joint bearing hinge bolt (10), and after the joint bearing hinge bolt (10) is installed, the axis of the pressure oiling nozzle (1) extends obliquely upward.

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