A drilling device for an aircraft control rod

Abstract

The application discloses a drilling device for aircraft control pull rod, which comprises a circumferential synchronization mechanism and an axial synchronization mechanism, the circumferential synchronization mechanism comprises a worm gear assembly and two interval arranged workpiece mounting plates, one of the workpiece mounting plates is provided with a first clamping assembly for clamping the head of the aircraft control pull rod, the other workpiece mounting plate is provided with a second clamping assembly for clamping the shaft of the aircraft control pull rod, the worm gear assembly is used for driving the two workpiece mounting plates to move synchronously in the circumferential direction, the axial synchronization mechanism comprises a positioning pin for positioning the head of the aircraft control pull rod, a drill jig sleeve for cooperating with the shaft of the aircraft control pull rod to drill holes, and a synchronization guide assembly for synchronously moving the positioning pin and the drill jig sleeve in the axial direction. The application has the advantages of high working efficiency and high drilling precision.

Description

Technical Field

[0001] This invention relates to the field of machining technology, and in particular to a drilling device for aircraft control levers. Background Technology

[0002] The aircraft control stick is a core transmission component of the aircraft control system. Its function is to transmit the pilot's control commands (such as altitude and steering) to the actuators, thus requiring stringent precision in the hole machining. According to the drilling requirements, the control stick head needs to have two sets of holes drilled with their end faces aligned relative to the stick body. These two sets of holes have an axial distance relative to their end faces and a circumferential angular relative position. The existing two holes on the control stick head are needed for positioning before drilling into the stick body.

[0003] Currently, manual scribing and drilling, and fixed drilling templates are commonly used for machining. Manual scribing and drilling relies on the operator's experience, has large errors, low drilling accuracy, and requires individual clamping and positioning of the workpiece for each drilling operation, resulting in low efficiency. Fixed drilling templates are used by fixing the template to the end face of the tie rod, inserting a positioning pin into the fork lug hole, aligning the template with the workpiece, and then drilling through the template hole. However, the fixture is only suitable for a single size of workpiece, and redesign is required for different sizes. Furthermore, with the template fixed, the screw-in depth of the fork lug joint cannot be dynamically adjusted, resulting in poor concentricity. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to overcome the shortcomings of the prior art and provide a drilling device for aircraft control rods that is adapted to the drilling requirements of aircraft control rods, with high working efficiency and high drilling accuracy.

[0005] To solve the above-mentioned technical problems, the present invention adopts the following technical solution:

[0006] A drilling device for an aircraft control stick includes a circumferential synchronization mechanism and an axial synchronization mechanism. The circumferential synchronization mechanism includes a worm gear assembly and two spaced-apart workpiece mounting plates. One workpiece mounting plate has a first clamping assembly for clamping the head of the aircraft control stick, and the other workpiece mounting plate has a second clamping assembly for clamping the body of the aircraft control stick. The worm gear assembly drives the two workpiece mounting plates to move synchronously in the circumferential direction. The axial synchronization mechanism includes a locating pin for positioning the head of the aircraft control stick, a drill jig for drilling holes in conjunction with the body of the aircraft control stick, and a synchronization guide assembly for moving the locating pin and the drill jig synchronously in the axial direction.

[0007] As a further improvement to the above technical solution:

[0008] The worm gear assembly includes two pairs of spaced-apart and meshing worm gears and worms, with the two worms connected by a coupling, and the workpiece mounting plate connected to the worm gears.

[0009] The worm gear is a sector-shaped worm gear, with its outer arc surface meshing with the worm and its inner arc surface connected to the workpiece mounting plate.

[0010] The bottom of the workpiece mounting plate is provided with an outward protrusion, which is connected to the inner arc surface of the worm gear.

[0011] At least one end of the worm gear is provided with an operating handle.

[0012] The worm gear has support plates on both sides, and the support plates have a first arc-shaped track. The bottom of the workpiece mounting plate has rollers that cooperate with the first arc-shaped track.

[0013] The roller on at least one side is a V-shaped roller or a U-shaped roller.

[0014] The support plate is also provided with a second arc-shaped track, the bottom of the workpiece mounting plate is provided with a clamping plate, the clamping plate is provided with a rotatable and adjustable adjusting shaft, the adjusting shaft is provided with a roller bearing that is eccentrically matched with the adjusting shaft, and the outer ring of the roller bearing is in rolling contact with the lower surface of the second arc-shaped track.

[0015] The synchronous guide assembly includes a linear guide rail arranged along the axial direction, a slide plate on the linear guide rail, and the positioning pin and the drill jig sleeve respectively disposed on the slide plate.

[0016] The sliding plate is detachably connected to a positioning pin mounting plate and a drill jig mounting plate. The positioning pin is mounted on the positioning pin mounting plate, and the drill jig is mounted on the drill jig mounting plate.

[0017] Compared with the prior art, the advantages of the present invention are as follows:

[0018] 1. The drilling device for aircraft control levers of the present invention, by adjusting the circumferential synchronization mechanism, allows the drill jig sleeve to adapt to the circumferential angle between multiple holes, and by adjusting the axial synchronization mechanism, allows the drill jig sleeve to adapt to the axial distance between multiple holes, realizing the replication of multiple hole positions, high drilling accuracy, and eliminating the need to re-clamp and position the workpiece for each drilling operation, resulting in high work efficiency; circumferential synchronous movement is achieved through a worm gear mechanism, which is self-locking to prevent circumferential movement of the workpiece during drilling, reducing human error and ensuring high drilling accuracy.

[0019] 2. The drilling device for aircraft control levers of the present invention uses a sector-shaped worm wheel to satisfy the machining of two sets of holes. The sector-shaped worm wheel can save materials, reduce costs, and has a simple and compact structure.

[0020] 3. In the drilling device for aircraft control levers of the present invention, when the worm gear drives the workpiece mounting plate to rotate, the roller rolls on the first arc track, thereby achieving the support plate supporting both sides of the workpiece mounting plate, preventing the workpiece mounting plate from shaking during drilling, making the structure more stable and the drilling accuracy higher.

[0021] 4. The drilling device for aircraft control levers of the present invention has a first arc-shaped track that is engaged in the groove of a V-shaped roller, which can axially limit the workpiece mounting plate, prevent the workpiece from moving axially during drilling, constrain the drill bit path, and improve the concentricity of drilling.

[0022] 5. The drilling device for aircraft control levers of the present invention has the outer ring of the roller bearing abutting against the lower surface of the second arc-shaped track and the roller abutting against the upper surface of the first arc-shaped track, thereby limiting the vertical position of the workpiece mounting plate and preventing the workpiece from moving vertically during drilling. Due to the eccentric setting of the roller bearing, there is a certain gap between the roller bearing and the second arc-shaped track during installation, which facilitates installation. After installation, the height of the roller bearing edge can be adjusted by rotating the adjusting shaft so that the edge fits against the lower surface of the second arc-shaped track. Then, the adjusting shaft is locked with bolts to achieve clamping and limiting of the workpiece mounting plate. The structure is simple and reliable.

[0023] 6. The drilling device for aircraft control sticks of the present invention, through the modular setting of positioning pins and drill jigs, allows for quick replacement of positioning pins and drill jigs by disassembling and assembling positioning pin mounting plates and drill jig mounting plates, adapting to drilling requirements of different hole diameters. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the drilling device for aircraft control levers according to the present invention.

[0025] Figure 2 This is a schematic diagram of the drilling device for aircraft control levers of the present invention from another angle (workpiece mounting plate and some related components are not shown).

[0026] Figure 3 This is a cross-sectional view of the clamping plate in the drilling device for aircraft control levers of the present invention.

[0027] Legend: 1. Circumferential synchronization mechanism; 11. Worm gear; 12. Worm; 13. Workpiece mounting plate; 131. Outer protrusion; 132. Roller; 133. Clamping plate; 134. Adjusting shaft; 135. Roller bearing; 14. Coupling; 15. Operating handle; 2. Axial synchronization mechanism; 21. Locating pin; 22. Drill jig sleeve; 23. Synchronization guide assembly; 24. Slide plate; 25. Locating pin mounting plate; 26. Drill jig sleeve mounting plate; 31. Support plate; 311. First arc-shaped track; 312. Second arc-shaped track; 41. First clamping assembly; 42. Second clamping assembly; 91. Aircraft control lever head; 92. Aircraft control lever body. Detailed Implementation

[0028] The present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0029] In the description of this invention, it should be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0030] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0031] In this invention, unless otherwise explicitly specified and limited, the terms "assembly," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0032] like Figures 1 to 3As shown, the drilling device for the aircraft control stick in this embodiment includes a circumferential synchronization mechanism 1 and an axial synchronization mechanism 2. The circumferential synchronization mechanism 1 includes a worm gear assembly and two spaced-apart workpiece mounting plates 13. One workpiece mounting plate 13 is provided with a first clamping assembly 41 for clamping the head 91 of the aircraft control stick, and the other workpiece mounting plate 13 is provided with a second clamping assembly 42 for clamping the body 92 of the aircraft control stick. The worm gear assembly is used to drive the two workpiece mounting plates 13 to move synchronously in the circumferential direction. The axial synchronization mechanism 2 includes a positioning pin 21 for positioning the head 91 of the aircraft control stick, a drill jig sleeve 22 for drilling holes in cooperation with the body 92 of the aircraft control stick, and a synchronization guide assembly 23 for moving the positioning pin 21 and the drill jig sleeve 22 synchronously in the axial direction.

[0033] In this embodiment, the drilling device for the aircraft control lever is used to clamp and position the aircraft control lever head 91 and the aircraft control lever body 92 on two workpiece mounting plates 13 respectively. The circumferential synchronization mechanism 1 and the axial synchronization mechanism 2 are adjusted so that the positioning pin 21 is inserted into the first hole of the aircraft control lever head 91. Then, a drill bit is used to drill the first hole in the aircraft control lever body 92 through the drill jig sleeve 22. Then, the worm gear assembly drives the aircraft control lever head 91 and the aircraft control lever body 92 to move synchronously in the circumferential direction. The synchronization guide assembly 23 drives the positioning pin 21 and the drill jig sleeve 22 to move synchronously in the axial direction so that the positioning pin 21 is inserted into the second hole of the aircraft control lever head 91. Then, a drill bit is used to drill the second hole in the aircraft control lever body 92 through the drill jig sleeve 22. By repeating the above operation, multiple holes of the aircraft control lever head 91 can be replicated on the aircraft control lever body 92.

[0034] The drilling device for aircraft control sticks in this embodiment adjusts the circumferential synchronization mechanism 1 so that the drill jig sleeve 22 can adapt to the circumferential angle between multiple holes, and adjusts the axial synchronization mechanism 2 so that the drill jig sleeve 22 can adapt to the axial distance between multiple holes, realizing the replication of multiple hole positions, high drilling accuracy, and no need to re-clamp and position the workpiece for each drilling, resulting in high work efficiency; circumferential synchronous movement is achieved through a worm gear mechanism, which is self-locking to prevent circumferential movement of the workpiece during drilling, reducing human error and ensuring high drilling accuracy.

[0035] Furthermore, in this embodiment, the worm gear assembly includes two pairs of spaced-apart and meshing worm gears 11 and worms 12. The two worms 12 are connected by a coupling 14, and the workpiece mounting plate 13 is connected to the worm gears 11. The connection of the two worms 12 via the coupling 14 enables the two worm gears 11 to rotate synchronously by the same angle, thereby achieving synchronous rotation of the worm gears 11, the workpiece mounting plate 13 mounted on the worm gears 11, and the workpiece by the same angle. This results in a simple and reliable structure.

[0036] Preferably, in this embodiment, the transmission ratio between the worm gear 11 and the worm 12 is 50:1, which makes the rotation angle of the worm gear 11 change slowly when the worm 12 is rotated, and can more accurately control the rotation angle of the worm gear 11.

[0037] Furthermore, in this embodiment, the worm gear 11 is a sector-shaped worm gear. The outer arc surface of the worm gear 11 meshes with the worm 12, and the inner arc surface is connected to the workpiece mounting plate 13. Typically, the tie rod has two sets of holes, and the interval angle between the two sets of holes is always within 180°. Therefore, using a sector-shaped worm gear 11 can satisfy the machining of both sets of holes. The sector-shaped worm gear can save materials, reduce costs, and has a simple and compact structure.

[0038] Furthermore, in this embodiment, the bottom of the workpiece mounting plate 13 is provided with an outward protrusion 131, which is connected to the inner arc surface of the worm gear 11. By fitting the outward protrusion 131 to the inner arc surface of the worm gear 11, the workpiece mounting plate 13 and the worm gear 11 are connected surface to surface, resulting in better synchronization and stability when the workpiece mounting plate 13 and the worm gear 11 rotate together.

[0039] Furthermore, in this embodiment, at least one end of the worm gear 12 is provided with an operating handle 15. Rotating the operating handle 15 will cause the worm gear 12 to rotate, which is simple and reliable.

[0040] Furthermore, in this embodiment, support plates 31 are provided on both sides of the worm gear 12, and a first arc-shaped track 311 is provided on the support plates 31. The bottom of the workpiece mounting plate 13 is provided with rollers 132 that cooperate with the first arc-shaped track 311. When the worm gear 11 drives the workpiece mounting plate 13 to rotate, the rollers 132 roll on the first arc-shaped track 311, so that the support plates 31 support both sides of the workpiece mounting plate 13, preventing the workpiece mounting plate 13 from shaking during drilling, making the structure more stable and the drilling accuracy higher.

[0041] Furthermore, in this embodiment, at least one of the rollers 132 is a V-shaped roller. The first arc-shaped track 311 is engaged in the groove of the V-shaped roller, which can axially limit the workpiece mounting plate 13, prevent the workpiece from moving axially during drilling, constrain the drill bit path, and improve the concentricity of the drilling. Of course, in other embodiments, the roller 132 can also be a U-shaped roller.

[0042] Preferably, in this embodiment, one side of the roller 132 is a V-shaped roller, and the other side of the roller 132 is a cylindrical roller. The cylindrical roller only serves a supporting function to prevent processing difficulties and installation problems caused by axial transition positioning.

[0043] Furthermore, in this embodiment, the support plate 31 is also provided with a second arc-shaped track 312, the bottom of the workpiece mounting plate 13 is provided with a clamping plate 133, the clamping plate 133 is provided with a rotatable adjustable shaft 134, the adjustable shaft 134 is provided with a roller bearing 135 that is eccentrically matched with the adjustable shaft 134, and the outer ring of the roller bearing 135 is in rolling contact with the lower surface of the second arc-shaped track 312. The outer ring of the roller bearing 135 abuts against the lower surface of the second arc-shaped track 312, and the roller 132 abuts against the upper surface of the first arc-shaped track 311, thereby limiting the workpiece mounting plate 13 in the vertical direction and preventing the workpiece from moving vertically during drilling. Due to the eccentric setting of the roller bearing 135, there is a certain gap between the roller bearing 135 and the second arc-shaped track 312 during installation, which facilitates installation. After installation, the height of the roller bearing 135 can be adjusted by rotating the adjusting shaft 134 so that the roller edge fits against the lower surface of the second arc-shaped track 312. Then, the adjusting shaft 134 is locked with bolts to clamp and limit the workpiece mounting plate 13. The structure is simple and reliable.

[0044] Furthermore, in this embodiment, the synchronous guide assembly 23 includes a linear guide rail arranged along the axial direction, a slide plate 24 is provided on the linear guide rail, and a positioning pin 21 and a drill jig sleeve 22 are respectively disposed on the slide plate 24. By sliding the slide plate 24 along the linear guide rail, the positioning pin 21 and the drill jig sleeve 22 disposed on the slide plate 24 can move synchronously along the axial direction, which is simple and reliable.

[0045] Furthermore, in this embodiment, a locating pin mounting plate 25 and a drill jig mounting plate 26 are detachably connected to the slide plate 24. The locating pin 21 is mounted on the locating pin mounting plate 25, and the drill jig 22 is mounted on the drill jig mounting plate 26. Through the modular design of the locating pin 21 and the drill jig 22, the locating pin 21 and the drill jig 22 can be quickly replaced by disassembling and assembling the locating pin mounting plate 25 and the drill jig mounting plate 26, adapting to drilling requirements of different hole diameters.

[0046] Preferably, in this embodiment, a welding base is also included, with an overall machining reference surface (flatness ≤ 0.02 mm), and each component is mounted on the welding base.

[0047] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention in any way. Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make many possible variations and modifications to the technical solutions of the present invention using the methods and techniques disclosed above, or modify them into equivalent embodiments with equivalent changes, without departing from the spirit and technical essence of the present invention. Therefore, any simple modifications, equivalent substitutions, equivalent changes, and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall still fall within the protection scope of the technical solutions of the present invention.

Claims

1. A drilling device for aircraft control sticks, characterized in that: The system includes a circumferential synchronization mechanism (1) and an axial synchronization mechanism (2). The circumferential synchronization mechanism (1) includes a worm gear assembly and two spaced workpiece mounting plates (13). One workpiece mounting plate (13) is provided with a first clamping assembly (41) for clamping the aircraft control lever head (91), and the other workpiece mounting plate (13) is provided with a second clamping assembly (42) for clamping the aircraft control lever body (92). The worm gear assembly is used to drive the two workpiece mounting plates (13) to move synchronously in the circumferential direction. The axial synchronization mechanism (2) includes a positioning pin (21) for positioning the aircraft control lever head (91), a drill jig sleeve (22) for drilling holes in cooperation with the aircraft control lever body (92), and a synchronization mechanism for moving the positioning pin (21) and the drill jig sleeve (22) synchronously in the axial direction. Guide component (23); adjust the circumferential synchronization mechanism (1) and the axial synchronization mechanism (2) so that the positioning pin (21) is inserted into the first hole of the aircraft control lever head (91), and then use a drill bit to drill the first hole of the aircraft control lever body (92) through the drill jig sleeve (22). Then the worm gear assembly drives the aircraft control lever head (91) and the aircraft control lever body (92) to move synchronously in the circumferential direction. The synchronous guide component (23) drives the positioning pin (21) and the drill jig sleeve (22) to move synchronously in the axial direction so that the positioning pin (21) is inserted into the second hole of the aircraft control lever head (91). Then use a drill bit to drill the second hole of the aircraft control lever body (92) through the drill jig sleeve (22). Repeat the above operation to realize the replication of multiple holes of the aircraft control lever head (91) on the aircraft control lever body (92).

2. The drilling device for aircraft control sticks according to claim 1, characterized in that: The worm gear assembly includes two pairs of spaced and meshing worm wheels (11) and worms (12), the two worms (12) are connected by a coupling (14), and the workpiece mounting plate (13) is connected to the worm wheels (11).

3. The drilling device for aircraft control sticks according to claim 2, characterized in that: The worm wheel (11) is a sector-shaped worm wheel. The outer arc surface of the worm wheel (11) meshes with the worm (12), and the inner arc surface is connected to the workpiece mounting plate (13).

4. The drilling device for aircraft control sticks according to claim 3, characterized in that: The bottom of the workpiece mounting plate (13) is provided with an outward protrusion (131), which is connected to the inner arc surface of the worm gear (11).

5. The drilling device for aircraft control sticks according to claim 2, characterized in that: At least one end of the worm (12) is provided with an operating handle (15).

6. The drilling device for aircraft control sticks according to claim 2, characterized in that: The worm (12) is provided with support plates (31) on both sides, and a first arc track (311) is provided on the support plate (31). The bottom of the workpiece mounting plate (13) is provided with a roller (132) that cooperates with the first arc track (311).

7. The drilling device for aircraft control sticks according to claim 6, characterized in that: At least one of the rollers (132) is a V-shaped roller or a U-shaped roller.

8. The drilling device for aircraft control sticks according to claim 6, characterized in that: The support plate (31) is also provided with a second arc-shaped track (312), and the bottom of the workpiece mounting plate (13) is provided with a clamping plate (133). The clamping plate (133) is provided with a rotatable adjustment shaft (134), and the adjustment shaft (134) is provided with a roller bearing (135) that is eccentrically matched with the adjustment shaft (134). The outer ring of the roller bearing (135) is in rolling contact with the lower surface of the second arc-shaped track (312).

9. The drilling device for an aircraft control stick according to any one of claims 1 to 8, characterized in that: The synchronous guide assembly (23) includes a linear guide rail arranged along the axial direction, and a slide plate (24) is provided on the linear guide rail. The positioning pin (21) and the drill jig sleeve (22) are respectively provided on the slide plate (24).

10. The drilling device for an aircraft control stick according to claim 9, characterized in that: The sliding plate (24) is detachably connected to a positioning pin mounting plate (25) and a drill jig mounting plate (26). The positioning pin (21) is mounted on the positioning pin mounting plate (25), and the drill jig (22) is mounted on the drill jig mounting plate (26).

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