Aircraft landing gear machining method

Abstract

The present invention relates to a machining method for an aircraft landing gear, and belongs to the field of machining technology. The method comprises the following steps: S1, pre-welding processing: rough machining the bracket, and machining the first through hole; then fine machining the outer surface of the bracket and the first through hole, so that the outer dimensions of the bracket reach the designed dimensions, and the first through hole is reserved for machining allowance; rough machining the outer wall of the shaft body, and rough machining the second through hole that penetrates the shaft body, and the diameter of the second through hole is the same as the diameter of the first through hole; S2, welding the bracket and the shaft body, after welding, the first through hole is connected with the second through hole; S3, clamping the bracket with the first tooling, and fine machining the second through hole and the first through hole to the designed dimensions with the first through hole as the reference; S4, clamping the bracket with the second tooling, and machining the outer wall of the shaft body to the designed dimensions with the second through hole and the first through hole as the reference. The present invention can improve machining efficiency and machining accuracy.

Description

Technical Field

[0001] The invention belongs to the technical field of machining, in particular to a machining method for an aircraft landing gear. Background Art

[0002] An aircraft landing gear Fig.11 As shown, it includes a shaft body 100 and a bracket 200 welded and arranged at one end of the shaft body 100, and the bracket 200 includes two legs 210, which are U-shaped as a whole; the shaft body 100 needs to be machined with a central through hole 110 axially penetrating the shaft body 100 and the bracket 200. During machining, it is usually necessary to firstly rough-machine the bracket 200 and the shaft body 100, and then weld the bracket 200 and the shaft body 100. Since welding will produce certain deformation, the bracket 200 and the shaft body 100 are fine-machined after welding to ensure the position accuracy of the bracket 200 and the shaft body 100. Due to the large size and weight of the bracket 200 and the shaft body 100, the overall size and weight of the landing gear are further increased after welding, the difficulty of machining increases, the efficiency decreases, and the shape of the bracket 200 is irregular, so it is difficult to clamp and position the landing gear during fine machining. In addition, since the bracket 200 and the shaft body 100 are both roughly machined before welding and finely machined after welding, there is no high-precision machining accuracy, and it is difficult to eliminate the shape and position errors caused by welding deformation and ensure the machining accuracy. Summary of the invention

[0003] The technical problem to be solved by the present invention is to provide an aircraft landing gear machining method, which improves the machining efficiency and machining accuracy.

[0004] To solve the above problems, the technical solution adopted by the present invention is: an aircraft landing gear machining method, comprising the following steps:

[0005] S1. Pre-welding processing:

[0006] The bracket is rough-machined and the first through hole is machined; then the outer surface of the bracket and the first through hole are fine-machined so that the outer dimensions of the bracket reach the designed dimensions, and a machining allowance is reserved for the first through hole;

[0007] Rough-machining the outer wall of the shaft body, and rough-machining a second through hole penetrating the shaft body, wherein the diameter of the second through hole is the same as the diameter of the first through hole;

[0008] S2, welding the bracket and the shaft body, and after welding, the first through hole is connected with the second through hole;

[0009] S3, clamping the bracket by using the first tool, and finishing the second through hole and the first through hole to the designed size based on the first through hole;

[0010] S4. Clamp the bracket using the second tooling, and process the outer wall of the shaft body to the designed size based on the second through hole and the first through hole.

[0011] Further, in step S3, the first tooling includes a fixing plate, a supporting plate and a top column which are arranged in sequence, the fixing plate and the supporting plate are arranged vertically and parallel to each other, and the fixing plate is connected to the supporting plate through a plurality of connecting plates; the upper and lower ends of the supporting plate are provided with supporting surfaces, and vertical limiting columns are arranged on both sides of the supporting surface, and locking screws are arranged on the limiting columns; the top column is arranged horizontally, and one end of the top column is fixedly connected to the side wall of the supporting plate, and the other end is provided with a positioning shaft, and the diameter of the positioning shaft is adapted to the diameter of the first through hole; the centers of the positioning shaft, the fixing plate and the supporting plate are on the same horizontal straight line;

[0012] When the bracket is clamped by the first tooling, the positioning shaft is inserted into the first through hole, the end face of the top column is pressed against the inner wall of the bracket, the inner wall of the support leg is supported by the supporting surface, and then the locking screw is rotated to press the side wall of the support leg.

[0013] Furthermore, a sliding hole is provided in the top column, the positioning shaft is located in the sliding hole and slidingly cooperates with the sliding hole, and a driving mechanism for driving the positioning shaft to slide axially is provided in the sliding hole;

[0014] In step S3, after the second through hole is processed to the designed size, the driving mechanism is used to drive the positioning shaft into the sliding hole, and then the first through hole is processed to the designed size.

[0015] Furthermore, the structure of the second tooling is the same as that of the first tooling.

[0016] Furthermore, in step S4, a CNC lathe is used to finish the outer wall of the shaft body to a designed size.

[0017] Furthermore, in step S3, a CNC deep hole boring machine is used to process the second through hole and the first through hole to a designed size.

[0018] Furthermore, a deep hole boring bar is used to fine-process the second through hole and the first through hole, the deep hole boring bar comprises a rod body, a connecting head is provided at the connecting end of the rod body, a tool seat is provided at the cutting end, the tool seat radially penetrates the rod body and slidably cooperates with the rod body, a detachable first boring tool and a second boring tool are provided at both ends of the tool seat respectively, and an oblique through hole with a rectangular cross-section is provided in the tool seat, and the angle between the length direction of the oblique through hole and the axial direction of the rod body is an acute angle or an obtuse angle; the rod body is a hollow rod, a driving rod is provided inside the rod body, a telescopic mechanism is provided in the connecting end of the rod body, one end of the driving rod is fixedly connected to the telescopic mechanism, and the other end of the driving rod is fixedly provided with an oblique rod, the oblique rod penetrates the oblique through hole and slidably cooperates with the oblique through hole, and limit blocks are provided at both ends of the oblique rod, and the limit blocks slidably cooperate with the inner wall of the rod body.

[0019] Furthermore, a coolant inlet is provided at the connecting end of the rod body, and a coolant through hole is provided on the limit block.

[0020] The beneficial effects of the present invention are as follows: 1. The present invention directly processes the shape of the bracket to the designed size before welding, and after welding, there is no need to fine-process the shape of the bracket, and only the shaft body needs to be fine-processed. Since the volume and weight of the bracket before welding are less than the overall volume and weight of the landing gear after welding, the clamping difficulty during bracket processing is lower, the processing is more convenient, and it is conducive to improving the processing efficiency.

[0021] 2. The present invention achieves a higher precision by fine-machining the first through hole on the bracket. During post-welding processing, the second through hole is fine-machined with the first through hole as a reference, thereby ensuring the positional accuracy of the second through hole and the first through hole. Then, the outer circle of the shaft body is fine-machined with the second through hole and the first through hole as a reference, thereby ensuring the positional accuracy of the outer circle of the shaft body, thereby ensuring the processing accuracy of the entire landing gear and eliminating the shape and position errors caused by welding deformation. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a processing flow diagram of the present invention;

[0023] Figure 2 This is a schematic diagram of the bracket after processing before welding;

[0024] Figure 3 This is a schematic diagram of the shaft after processing before welding;

[0025] Figure 4 is a schematic diagram of a front cross-sectional view of a first tool;

[0026] Figure 5 yes Figure 4 Schematic cross-sectional view of AA in the figure;

[0027] Figure 6 is a schematic diagram of a front view and a cross section of the first tool for positioning the bracket;

[0028] Figure 7 yes Figure 6 A schematic cross-sectional view of BB in FIG.

[0029] Figure 8 It is a schematic diagram of the main cross-section of a deep hole boring bar;

[0030] Fig. 9 This is a schematic diagram of the first boring tool during processing;

[0031] Fig.10 This is a schematic diagram of the second boring tool during processing;

[0032] Fig.11It is a schematic cross-sectional view of an aircraft landing gear;

[0033] Figure numerals: 1—fixed plate; 2—support plate; 3—top column; 4—connecting plate; 5—support surface; 6—limiting column; 7—locking screw; 8—positioning shaft; 9—driving mechanism; 10—rod body; 11—connecting head; 12—tool holder; 13—first boring tool; 14—second boring tool; 15—driving rod; 16—telescopic mechanism; 17—oblique rod; 18—limiting block; 19—coolant inlet; 100—shaft body; 110—center through hole; 120—second through hole; 200—bracket; 210—support foot; 220—first through hole. DETAILED DESCRIPTION

[0034] The present invention is further described below in conjunction with the accompanying drawings and embodiments.

[0035] The aircraft landing gear machining method of the present invention is as follows: Figure 1 As shown, the following steps are included:

[0036] S1. Pre-welding processing:

[0037] The bracket 200 is rough-machined and the first through hole 220 is machined; then the outer surface of the bracket 200 and the first through hole 220 are fine-machined so that the outer dimensions of the bracket 200 reach the designed dimensions, and the first through hole 220 is reserved for machining allowance, such as Figure 2 Specifically, the shape of the bracket 200 can be finely processed by using a CNC milling machine, a machining center, or other equipment.

[0038] Compared with the entire aircraft landing gear, the bracket 200 is smaller in weight and volume. Therefore, the outer dimensions of the bracket 200 are directly processed to the designed dimensions before welding, which makes it more convenient to clamp during processing. After welding, the bracket 200 does not need to be processed again, which helps to reduce processing difficulty and improve processing efficiency.

[0039] By fine-machining the first through hole 220 , the dimensional accuracy of the first through hole 220 and the positional accuracy of the first through hole 220 and the bracket 200 are relatively high, and can be used as a reference for fine-machining of the shaft body 100 .

[0040] The outer wall of the shaft body 100 is rough-machined, and the second through hole 120 penetrating the shaft body 100 is rough-machined. Figure 3 As shown, the diameter of the second through hole 120 is the same as the diameter of the first through hole 220. The shaft body 100 may be rough-machined by a lathe, a drilling machine, a boring machine, or other equipment.

[0041] S2. Weld the bracket 200 and the shaft body 100. After welding, the first through hole 220 is connected with the second through hole 120. During welding, the coaxiality of the first through hole 220 and the second through hole 120 should be ensured. After welding, the landing gear can be annealed to eliminate welding stress.

[0042] S3. Clamp the bracket 200 using the first tooling, and use the first through hole 220 as a reference to fine-process the second through hole 120 and the first through hole 220 to the designed size.

[0043] S4. Clamp the bracket 200 using the second tooling, and fine-process the outer wall of the shaft body 100 to the designed size based on the second through hole 120 and the first through hole 220 .

[0044] After processing, the first through hole 220 and the second through hole 120 form the central through hole 110 .

[0045] Since the first through hole 220 is finely machined before welding, the position accuracy and size accuracy of the first through hole 220 are relatively high, so the second through hole 120 is machined with the first through hole 220 as a reference, thereby ensuring the machining accuracy of the second through hole 120. In addition, only one clamping is required to complete the fine machining of the second through hole 120 and the first through hole 220, thereby avoiding the clamping error caused by multiple clamping and ensuring the position accuracy of the second through hole 120 and the first through hole 220. Then, the outer wall of the shaft body 100 is finely machined with the second through hole 120 and the first through hole 220 as a reference, thereby ensuring the position accuracy of the outer circle of the shaft body 100 and the center through hole 110.

[0046] In summary, the present invention first performs fine processing on the bracket 200 and the first through hole 220 before welding. Since the volume and weight of the bracket 200 are smaller than those of the entire landing gear, the processing difficulty is lower, and the dimensional accuracy of the first through hole 220 and the positional accuracy of the first through hole 220 and the bracket 200 can be guaranteed. Then, taking the first through hole 220 as a reference, the positional accuracy of the first through hole 220 and the second through hole 120 is guaranteed. Then, taking the first through hole 220 and the second through hole 120 as a reference, the positional accuracy of the outer circle of the shaft body 100 and the center through hole 110 is guaranteed, thereby ensuring the positional accuracy of the bracket 200 and the shaft body 100, and effectively eliminating the shape and position errors caused by welding deformation.

[0047] In step S3, the first tool is as follows Figure 4 and Figure 5 As shown, it includes a fixed plate 1, a support plate 2 and a top column 3 which are arranged in sequence. The fixed plate 1 and the support plate 2 are arranged vertically and parallel to each other. The fixed plate 1 is connected to the support plate 2 through a plurality of connecting plates 4; support surfaces 5 are arranged at the upper and lower ends of the support plate 2, and vertical limit columns 6 are arranged on both sides of the support surface 5, and locking screws 7 are arranged on the limit columns 6; the top column 3 is arranged horizontally, and one end of it is fixedly connected to the side wall of the support plate 2, and the other end is provided with a positioning shaft 8, and the diameter of the positioning shaft 8 is adapted to the diameter of the first through hole 220; the centers of the positioning shaft 8, the fixed plate 1 and the support plate 2 are on the same horizontal straight line.

[0048] Among them, the fixing plate 1 is used to fix the first tooling as a whole to the main shaft of the machine tool, and can be a circular or rectangular high-strength plate, such as a stainless steel plate. The support plate 2 is used to support the support leg 210 of the bracket 200. According to the shape characteristics of the bracket 200, the support plate 2 is a rectangular plate. The connecting plate 4 can be two rectangular plates, one end of the connecting plate 4 is welded to the side wall of the fixing plate 1, and the other end is welded to the side wall of the support plate 2. In order to stably position the support leg 210, the upper and lower ends of the support plate 2 are both provided with a supporting surface 5, and the supporting surface 5 is used to support the inner side wall of the support leg 210. The limiting column 6 is used to limit the left and right side walls of the support leg 210, and the locking screw 7 is used to tighten the left and right side walls of the support leg 210 to keep the support leg 210 stable. The top column 3 is used to support the inner wall of the bracket 200. In order to reduce the weight, the top column 3 is a hollow column, for example, a metal pipe can be used, or a rectangular hollow rod welded from four steel plates. The positioning shaft 8 is used to cooperate with the first through hole 220 to position the first through hole 220 .

[0049] When the bracket 200 is clamped by the first fixture, the positioning shaft 8 is inserted into the first through hole 220, the end surface of the top column 3 is pressed against the inner wall of the bracket 200, the inner wall of the support leg 210 is supported by the support surface 5, and then the locking screw 7 is rotated to press the side wall of the support leg 210. Figure 6 and Figure 7 shown.

[0050] After clamping, the first tool is mounted on the machine tool. Specifically, in step S3, the second through hole 120 and the first through hole 220 are processed to the designed size using a CNC deep hole boring machine. The four-jaw chuck of the CNC deep hole boring machine is used to clamp the fixed plate 1, thereby connecting the first tool to the spindle of the CNC deep hole boring machine. Since the centers of the positioning shaft 8, the fixed plate 1 and the support plate 2 are on the same horizontal straight line, after the first tool is installed on the CNC deep hole boring machine, the positioning shaft 8 is coaxial with the spindle, thereby ensuring that the first through hole 220 is coaxial with the spindle, thereby ensuring the clamping accuracy of the bracket 200 and the first through hole 220, and then using the first through hole 220 as a reference, a second through hole 120 with higher accuracy can be processed.

[0051] During processing, after the fixing plate 1 is connected to the main shaft of the CNC deep hole boring machine by using a four-jaw chuck, the shaft body 100 can be supported by a center frame so that the entire landing gear remains fixed. Then the deep hole boring bar is installed on the boring bar box, and the main shaft of the CNC deep hole boring machine is used to drive the landing gear to rotate as a whole, and the deep hole boring bar performs fine processing on the second through hole 120.

[0052] In order to complete the fine processing of the second through hole 120 and the first through hole 220 in one clamping, in the present invention, a sliding hole is provided in the top column 3, the positioning shaft 8 is located in the sliding hole and slides with the sliding hole, and a driving mechanism 9 for driving the axial sliding of the positioning shaft 8 is provided in the sliding hole. The driving mechanism 9 can be a linear motor, etc., and a battery can be used to power the linear motor. In order to ensure that the positioning shaft 8 remains stable after extending out of the top column 3, a set of screws can be provided on the top column 3, the screws penetrate the top column 3 and are threadedly matched with the positioning shaft 8. When the positioning shaft 8 needs to be retracted into the inside of the top column 3, the screws can be removed.

[0053] After the second through hole 120 is processed to the designed size, the driving mechanism 9 is used to drive the positioning shaft 8 into the interior of the sliding hole, and then the first through hole 220 is processed to the designed size.

[0054] Specifically, a small amount of machining allowance is reserved when finishing the second through hole 120. Then, the driving mechanism 9 is used to drive the positioning shaft 8 into the sliding hole, so that the positioning shaft 8 is separated from the first through hole 220, and then the deep hole boring bar can enter the first through hole 220 and finish the first through hole 220. During processing, a small amount of machining allowance is also reserved, and then the machining allowances of the first through hole 220 and the second through hole 120 are cut off at one time, and the first through hole 220 and the second through hole 120 are processed to the designed size.

[0055] In the present invention, the position of the positioning shaft 8 can be changed. Therefore, when processing the first through hole 220, there is no need to re-clamp the bracket 200, which can improve the processing efficiency. Only one clamping is required to complete the fine processing of the first through hole 220 and the second through hole 120, eliminating the error caused by clamping, which is beneficial to improving the processing accuracy.

[0056] In the present invention, the structure of the second tooling is the same as that of the first tooling, and the clamping method is also the same. In step S4, the outer wall of the shaft body 100 is finely processed to the designed size using a CNC lathe. Specifically, after step S3 is completed, the first tooling can be directly hoisted to the CNC lathe as a whole without removing the first tooling, and the fixing plate 1 is clamped by the chuck of the CNC lathe, and then the opening of the second through hole 120 is supported to process the outer wall of the shaft body 100.

[0057] In the present invention, a deep hole boring bar is used to finish the second through hole 120 and the first through hole 220. Since the second through hole 120 is deep, the heat dissipation speed of the tool is slow during processing, resulting in a high temperature of the tool, which affects the cutting performance and accelerates tool wear. In order to ensure the performance of the tool and prevent the tool from overheating, the deep hole boring bar of the present invention is as follows: Figure 8As shown, it includes a rod body 10, a connecting head 11 is provided at the connecting end of the rod body 10, and the connecting head 11 is used to install the entire deep hole boring bar to the boring bar box, and a tool holder 12 is provided at the cutting end, and the tool holder 12 is used to install the boring tool. Specifically, the tool holder 12 radially penetrates the rod body 10 and slides with the rod body 10. The two ends of the tool holder 12 are respectively provided with a detachable first boring tool 13 and a second boring tool 14. The first boring tool 13 and the second boring tool 14 can be adopted by the existing technology. The first boring tool 13 and the second boring tool 14 can be fixed to the two ends of the tool holder 12 by screws. An oblique through hole with a rectangular cross section is provided in the tool holder 12, and the angle between the length direction of the oblique through hole and the axial direction of the rod body 10 is an acute angle or an obtuse angle. The rod body 10 is a hollow rod, and a driving rod 15 is provided inside the rod body 10. A telescopic mechanism 16 is provided in the connecting end of the rod body 10, and the telescopic mechanism 16 can be a cylinder, a linear motor and other equipment. One end of the driving rod 15 is fixedly connected to the telescopic mechanism 16, and the other end of the driving rod 15 is fixedly provided with an inclined rod 17, which passes through the inclined through hole and slidably cooperates with the inclined through hole. Limit blocks 18 are provided at both ends of the inclined rod 17, and the limit blocks 18 slide and cooperate with the inner wall of the rod body 10. The outer wall of the limit block 18 fits the inner wall of the rod body 10, which plays a guiding and positioning role. When the telescopic mechanism 16 drives the driving rod 15 to move axially, the limit block 18 and the inclined rod 17 move axially accordingly. When the inclined rod 17 moves axially, it will push the tool holder 12 to move radially, thereby driving the first boring tool 13 and the second boring tool 14 to move radially. When boring a hole, the first boring tool 13 can be used for processing first, such as Fig. 9 As shown, after a period of time, the telescopic mechanism 16 drives the driving rod 15 to move axially, and drives the tool holder 12 to move radially, so that the first boring tool 13 moves toward the direction close to the rod body 10, and the second boring tool 14 moves toward the direction away from the rod body 10, and then the second boring tool 14 can be used for processing, and the first boring tool 13 is in a resting state, as shown in FIG. Fig.10 After a period of time, the driving rod 15 moves in the opposite direction, and can move the first boring tool 13 to the working position, and move the second boring tool 14 to the resting position. Therefore, the present invention can realize the alternating operation of the first boring tool 13 and the second boring tool 14, and avoid the excessive temperature caused by the continuous operation of the boring tool during the deep hole boring process, which affects the cutting performance.

[0058] In the present invention, a coolant inlet 19 is provided at the connecting end of the rod body 10, and a coolant through hole is provided on the stop block 18. The coolant can be introduced into the rod body 10 through the coolant inlet 19, and the coolant flows along the inner hole of the rod body 10 to the cutting end, and then flows to the outside of the rod body 10, and flows out from the gap between the rod body 10 and the hole wall, so as to cool the first boring tool 13 and the second boring tool 14, and discharge the chips at the same time.

[0059] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A method for machining an aircraft landing gear, characterized in that: The following steps are involved: S1. Pre-welding processing: The bracket (200) is roughly machined, and the first through hole (220) is machined; then the outer surface of the bracket (200) and the first through hole (220) are finely machined, so that the outer dimensions of the bracket (200) reach the designed dimensions, and a machining margin is reserved for the first through hole (220); Rough machining is performed on the outer wall of the shaft body (100), and a second through hole (120) penetrating the shaft body (100) is rough machined, wherein the diameter of the second through hole (120) is the same as the diameter of the first through hole (220); S2, welding the bracket (200) and the shaft body (100), wherein after welding, the first through hole (220) is connected to the second through hole (120); S3, using the first tooling to clamp the bracket (200), and using the first through hole (220) as a reference, fine-processing the second through hole (120) and the first through hole (220) to the designed size; The first tooling comprises a fixing plate (1), a supporting plate (2) and a top column (3) which are arranged in sequence, wherein the fixing plate (1) and the supporting plate (2) are arranged vertically and parallel to each other, and the fixing plate (1) is connected to the supporting plate (2) via a plurality of connecting plates (4); the upper end and the lower end of the supporting plate (2) are both provided with a supporting surface (5), and vertical limiting columns (6) are arranged on both sides of the supporting surface (5), and locking screws (7) are arranged on the limiting columns (6); the top column (3) is arranged horizontally, and one end of the top column (3) is fixedly connected to the side wall of the supporting plate (2), and the other end is provided with a positioning shaft (8), and the diameter of the positioning shaft (8) is adapted to the diameter of the first through hole (220); the centers of the positioning shaft (8), the fixing plate (1) and the supporting plate (2) are located on the same horizontal straight line; A sliding hole is provided in the top column (3), the positioning shaft (8) is located in the sliding hole and slidingly cooperates with the sliding hole, and a driving mechanism (9) for driving the positioning shaft (8) to slide axially is provided in the sliding hole; When the bracket (200) is clamped by using the first tool, the positioning shaft (8) is inserted into the first through hole (220), the end surface of the top column (3) is pressed against the inner wall of the bracket (200), the inner wall of the support leg (210) is supported by the support surface (5), and then the locking screw (7) is rotated to press the side wall of the support leg (210) by using the locking screw (7); After the second through hole (120) is machined to the designed size, the driving mechanism (9) is used to drive the positioning shaft (8) into the interior of the sliding hole, and the first through hole (220) is then machined to the designed size; S4. Clamp the bracket (200) using the second tooling, and fine-process the outer wall of the shaft body (100) to the designed size based on the second through hole (120) and the first through hole (220).

2. The aircraft landing gear machining method according to claim 1, characterized in that: The structure of the second tooling is the same as that of the first tooling.

3. The aircraft landing gear machining method according to claim 1, characterized in that: In step S4, a CNC lathe is used to fine-machine the outer wall of the shaft body (100) to a designed size.

4. The aircraft landing gear machining method according to claim 1, characterized in that: In step S3, a CNC deep hole boring machine is used to machine the second through hole (120) and the first through hole (220) to the designed size.

5. The aircraft landing gear machining method according to claim 4, characterized in that: A deep hole boring bar is used to perform fine machining on the second through hole (120) and the first through hole (220), the deep hole boring bar comprising a rod body (10), a connecting head (11) being provided at the connecting end of the rod body (10), a tool holder (12) being provided at the cutting end, the tool holder (12) radially penetrating the rod body (10) and slidingly cooperating with the rod body (10), a detachable first boring tool (13) and a second boring tool (14) being provided at both ends of the tool holder (12), and an oblique through hole with a rectangular cross section being provided in the tool holder (12), the length direction of the oblique through hole being parallel to the axis of the rod body (10). The angle between the two directions is an acute angle or an obtuse angle; the rod body (10) is a hollow rod, a driving rod (15) is arranged inside the rod body (10), a telescopic mechanism (16) is arranged inside the connecting end of the rod body (10), one end of the driving rod (15) is fixedly connected to the telescopic mechanism (16), and the other end of the driving rod (15) is fixedly provided with an inclined rod (17), the inclined rod (17) passes through the inclined through hole and slidably cooperates with the inclined through hole, and limit blocks (18) are arranged at both ends of the inclined rod (17), and the limit blocks (18) slidably cooperate with the inner wall of the rod body (10).

6. The aircraft landing gear machining method according to claim 5, characterized in that: The connecting end of the rod body (10) is provided with a coolant inlet (19), and the limiting block (18) is provided with a coolant through hole.

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