A parallel hole reaming operation method

Abstract

A parallel hole reaming operation method is used to realize the processing of the inner hole of the shaft sleeve on the landing gear strut during the aircraft repair process. It uses a parallel hole reaming operation auxiliary tool to guide the reamer feeding trajectory, and completes the processing of the inner hole of the shaft sleeve on the landing gear strut of the aircraft through the reamer, including the measurement process of the axis distance L between the inner holes of the left and right shaft sleeves of the original machine, the process of replacing the new shaft sleeve, the process of processing the inner hole of the reference shaft sleeve, the process of installing the right positioning rod, the process of installing the left positioning rod, the process of adjusting the position of the left positioning rod and the reaming process. The present invention not only ensures the size and matching accuracy of the reaming hole, but also reduces the cost of aircraft repair, and achieves the purpose of making the performance of the landing gear strut consistent with that of the original machine when it leaves the factory after the aircraft overhaul operation.

Description

Technical Field

[0001] The invention relates to a reaming operation method, in particular to a reaming operation method which can realize a hole parallel to the axis of a reference hole. Background Art

[0002] As attached Figure 1 As shown, a landing gear strut 1 on an aircraft is in a tripod structure, and through holes for assembly with other hinged components are provided at its three apex corners, and sleeves are installed in the through holes. According to the requirements of the design drawing of the landing gear strut 1, two groups of right sleeves 1-2 located on the right side of the tripod are arranged up and down, and the inner hole axes of the two groups of right sleeves 1-2 coincide, and the inner hole axis of the left sleeve 1-1 located on the left side of the tripod is parallel to the inner hole axis of the right sleeve 1-2. The distance between the inner hole axes of the left and right sleeves is L, and the upper deviation of L is +0.2, the lower deviation is 0, and the tolerance is 0.2mm. After the aircraft undergoes high-frequency take-off and landing operations, the left sleeve 1-1 and the right sleeve 1-2 on the landing gear strut 1 will be worn. Since the landing gear strut 1 is one of the key components of the aircraft landing gear assembly, it is of great significance to the safe flight of the aircraft. Therefore, during the overhaul of the aircraft, the left sleeve 1-1 and the right sleeve 1-2 on the landing gear strut 1 need to be replaced.

[0003] In order to ensure that the performance of the landing gear strut 1 is consistent with the original machine (in this manual, the aircraft before overhaul is referred to as the original machine) when it leaves the factory after the aircraft overhaul is completed, the inner hole axis of the left sleeve 1-1 is parallel to the inner hole axis of the right sleeve 1-2, and the distance L between the inner holes of the left and right sleeves is the same as the original machine parameters. However, during the aircraft repair process, the processing of the inner holes of the left and right sleeves is not only restricted by the matching parts, but also due to the influence of individual differences, it is difficult to use the same processing method as the original machine parts. Therefore, it is necessary to innovatively design a method for reaming parallel holes to solve the problem of processing the inner holes of the sleeves on the landing gear struts during the aircraft repair process. Summary of the invention

[0004] The present invention provides a parallel hole reaming operation method, which is used to realize the processing of the inner hole of the shaft sleeve on the landing gear strut during the aircraft repair process. The method ensures that the axes of the inner holes of the left and right shaft sleeves are parallel and the distance between the axes of the inner holes of the left and right shaft sleeves is completely consistent with that of the original machine by guiding the reamer feed trajectory, so as to achieve the purpose of ensuring that the performance of the landing gear strut after the aircraft overhaul operation is the same as that of the original machine when it leaves the factory.

[0005] To achieve the above object, the present invention adopts the following technical solution:

[0006] A parallel hole reaming operation method, which uses a parallel hole reaming operation auxiliary tool to guide the reamer feed trajectory, and completes the processing of the inner hole of the shaft sleeve on the aircraft landing gear strut through the reamer. It includes a measurement process of the axis distance L between the inner holes of the left and right shaft sleeves of the original machine, a replacement process of a new shaft sleeve, a reference shaft sleeve inner hole processing process, a right positioning rod installation process, a left positioning rod installation process, a left positioning rod position adjustment process and a reaming process; the parallel hole reaming operation auxiliary tool includes a base, a left positioning sleeve, a right positioning sleeve, a left positioning rod, a right positioning sleeve, a left positioning rod, a right positioning rod, and a reaming process. Rod and locking mechanism, a workpiece accommodating groove is provided in the middle part of the base, a right positioning sleeve is installed on the right side of the base, and a left positioning sleeve is installed on the left side of the base, the left positioning sleeve is provided with an eccentric sleeve, the offset of the central axis of its inner hole and the central axis of the outer cylindrical surface is δ, and δ is equal to half of the tolerance of the inner hole axis spacing L of the left and right shaft sleeves on the aircraft landing gear strut, the workpiece locking assembly is arranged on the periphery of the base and the side of the workpiece accommodating groove; the left positioning rod passes through the left positioning sleeve; the right positioning rod passes through the right positioning sleeve.

[0007] In the above-mentioned parallel hole reaming operation method, in the parallel hole reaming operation auxiliary tool adopted therein, the left positioning sleeve is composed of two parts located at the upper and lower parts, and a locking groove is provided on the outer circumferential surface of the eccentric sleeve of each part, and the locking groove is a conical groove evenly distributed on the outer circumferential surface of the eccentric sleeve.

[0008] In the above-mentioned parallel hole reaming operation method, in the parallel hole reaming operation auxiliary tool adopted therein, the locking mechanism is provided with a left positioning sleeve locking assembly; the left positioning sleeve locking assembly includes two groups of locking nails arranged upper and lower, which respectively cooperate with the locking grooves on the outer circumferential surfaces of the eccentric sleeves of the upper and lower parts of the left positioning sleeve to lock and fix the upper and lower parts of the left positioning sleeve.

[0009] In the parallel hole reaming operation method, in the parallel hole reaming operation auxiliary tool adopted therein, the locking mechanism is further provided with a landing gear strut locking assembly, and the landing gear strut locking assembly comprises a pressure plate, a pressure block, a spinning rod, a positioning pin, a screw and a pressure nail; the pressure plate comprises two parts arranged in an upper and lower manner, and a pressure block is arranged between the upper and lower parts of the pressure plate; the inner side surface of the pressure block is attached to the edge of the landing gear strut, and a blind hole cooperating with the spinning rod is arranged on the pressure block; the spinning rod and the base workpiece container The threaded hole on the side wall of the groove cooperates, and the tail of the spinning rod is inserted into the blind hole of the clamping block. An annular positioning groove is also provided at the tail of the spinning rod. The annular positioning groove cooperates with the positioning pin passing through the pressure plate and the clamping block to lock the spinning rod in position; the screw is arranged on the right side and upper edge of the base, and its tail can pass through the side wall of the base workpiece accommodating groove and collide with the landing gear strut; the clamping nail is arranged between the landing gear strut and the side wall of the base workpiece accommodating groove, and the vertical positioning of the landing gear strut is achieved by the clamping nail.

[0010] The specific operation steps of each process of the above parallel hole reaming operation method are as follows:

[0011] a. Measurement of the axis distance L between the inner holes of the left and right shaft sleeves of the original machine: Use a projector or parallel reaming operation auxiliary tool and a measuring tool to measure the axis distance L between the inner holes of the left and right sleeves of the original machine;

[0012] b. Replacement of new sleeves: Remove the left and right sleeves of the original machine, process three sets of new sleeves with the same structure and material as the original sleeves, and make the inner hole size of the three sets of new sleeves smaller than the inner hole size of the corresponding original sleeves, and then respectively embed them in the three through holes of the landing gear strut tripod of the aircraft;

[0013] c. Machining the inner hole of the reference sleeve: Ream the two new sleeves installed on the right side of the aircraft landing gear struts to make the inner hole sizes of the two new sleeves on the right side completely consistent with the inner hole sizes of the two right sleeves on the original aircraft;

[0014] d. Installation of the right positioning rod: Install the aircraft landing gear strut as a workpiece on the base of the parallel reaming operation auxiliary tool, and insert the right positioning rod of the parallel reaming operation auxiliary tool into the inner holes of the right positioning sleeve of the base and the two sets of new sleeves on the right side of the workpiece, so that the inner walls of the two sets of new sleeves on the right side of the workpiece are tightly fitted with the right positioning rod;

[0015] e. Installation of the left positioning rod: insert the left positioning rod of the parallel reaming auxiliary tool into the left positioning sleeve arranged on the left side of the base and the inner hole of the new shaft sleeve on the left side of the workpiece, so that the left positioning rod fits tightly against the inner wall of the left positioning sleeve;

[0016] f. Adjustment of the position of the left positioning rod: Use a measuring tool to measure the distance between the left positioning rod and the right positioning rod, and then convert the distance between the center axes of the left and right positioning rods, that is, the distance between the axes of the inner holes of the left and right sleeves of the workpiece at this time is L1. Compare L1 with the distance between the axes of the inner holes of the left and right sleeves of the original machine, and calculate the difference ΔL between the two, ΔL=L1-L. Then rotate the left positioning sleeve according to the value of ΔL, and drive the left positioning rod to move left and right through the eccentric sleeve structure of the left positioning sleeve, so that the distance between the center axes of the left and right positioning rods is completely consistent with the distance between the axes of the inner holes of the left and right sleeves of the original machine L;

[0017] g. Reaming: Lock and fix the left positioning sleeve, right positioning sleeve and workpiece respectively through the workpiece locking assembly, then take out the left positioning rod, and then insert the reamer into the left positioning sleeve, and complete the reaming operation under the guidance of the left positioning sleeve.

[0018] In the above-mentioned parallel hole reaming operation method, in operation step a, when measuring the value of the axis distance L between the inner holes of the left and right bushings of the original machine by cooperating with the parallel hole reaming operation auxiliary tool and the measuring tool, the left locating rod and the right locating rod are respectively inserted into the inner holes of the two groups of right bushings and one group of left bushings of the landing gear struts of the original machine, and then the distance between the left locating rod and the right locating rod is measured by the measuring tool, and then the distance between the center axes of the left locating rod and the right locating rod is converted, that is, the axis distance L of the inner holes of the left and right bushings of the original machine.

[0019] In the above-mentioned parallel hole reaming operation method, in the parallel hole reaming operation auxiliary tool, the left positioning sleeve is also provided with a rotating handle, and the rotating handle is provided with a scale value, and the scale value corresponds to the distance that the left positioning sleeve rotates to drive the left positioning rod to move left and right.

[0020] In the above parallel hole reaming operation method, in operation step e, before the left positioning rod is inserted into the left positioning sleeve arranged on the left side of the base and the inner hole of the left shaft sleeve of the workpiece, the scale value 0 line on the left positioning sleeve rotating handle is rotated to the center axis position.

[0021] In the above parallel hole reaming operation method, in operation step f, when ΔL>0, rotate the rotating handle of the left positioning sleeve to decrease its scale value; when ΔL=0, directly perform step g operation; when ΔL<0, rotate the rotating handle of the left positioning sleeve to increase its scale value.

[0022] The parallel hole reaming operation method adopts a reamer whose front end is a conical end face, and the circular runout of the hole to be processed is controlled by the centering effect of the conical end face.

[0023] The present invention provides a parallel hole reaming operation method, which is suitable for processing the inner holes of left and right shaft sleeves on a landing gear strut tripod of an aircraft during an aircraft overhaul process. The parallel hole reaming operation auxiliary tool is used to guide the reamer feed trajectory, and the reamer is used to realize the processing of the parallel inner holes of the left and right shaft sleeves on the aircraft landing gear strut. Compared with the traditional boring machine processing parallel hole method, the method has the advantages of flexible operation and strong environmental adaptability, and is more in line with the characteristics of individualized processing of parts in the repair industry. It not only ensures the size and matching accuracy of the reamed hole, but also reduces the aircraft repair cost, and achieves the purpose of ensuring that the performance of the landing gear strut after the aircraft overhaul operation is the same as that of the original aircraft when it leaves the factory. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a schematic diagram of the landing gear strut structure on an aircraft;

[0025] Figure 2 yes Figure 1 A top view of

[0026] Figure 3It is a schematic diagram of assembling a parallel hole reaming operation auxiliary tool with a landing gear strut on an aircraft;

[0027] Figure 4 1 is a schematic diagram of the left positioning sleeve structure;

[0028] Figure 5 yes Figure 4 Schematic diagram of the AA section structure;

[0029] Figure 6 It is a schematic diagram of reaming parallel holes using a reamer.

[0030] Explanation of the symbols in the figure:

[0031] 1 is the landing gear strut, 1-1 is the left shaft sleeve, 1-2 is the right shaft sleeve; 2 is the base; 3 is the clamping pin; 4 is the left positioning sleeve, 4-1 is the rotating handle, 4-2 is the eccentric sleeve, 4-3 is the locking groove; 5 is the locking pin; 6 is the left positioning rod; 7 is the pressure plate; 8 is the spinning rod; 9 is the positioning pin; 10 is the clamping block; 11 is the right positioning sleeve; 12 is the right positioning rod; 13 is the screw; 14 is the reamer. DETAILED DESCRIPTION

[0032] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

[0033] See Figure 1. Figure 2 A landing gear strut 1 on an aircraft is in a tripod structure. Through holes for assembly with other hinged parts are provided at its three vertex positions, and bushings are installed in the through holes. According to the requirements of the design drawing of the landing gear strut 1, two groups of right bushings 1-2 located on the right side of the tripod are arranged up and down, and the inner hole axes of the two groups of right bushings 1-2 coincide. The inner hole axis of the left bushing 1-1 located on the left side of the tripod is parallel to the inner hole axis of the right bushing 1-2. The distance between the inner hole axes of the left and right bushings is L, the upper deviation of L is +0.2, the lower deviation is 0, and the tolerance is 0.2mm.

[0034] See also Figure 3 , Figure 4 , Figure 5The present invention provides a parallel hole reaming operation method, which is used to realize the processing of the inner hole of the shaft sleeve on the landing gear strut during the aircraft repair process. The parallel hole reaming operation auxiliary tool is used to guide the reamer feeding trajectory, and the processing of the inner hole of the shaft sleeve on the landing gear strut 1 of the aircraft is completed by the reamer, which specifically includes the measurement process of the axis distance L between the inner holes of the left and right shaft sleeves of the original machine, the process of replacing the new shaft sleeve, the process of processing the inner hole of the reference shaft sleeve, the process of installing the right positioning rod, the process of installing the left positioning rod, the process of adjusting the position of the left positioning rod and the process of reaming; the parallel hole reaming operation auxiliary tool used by it includes a base 2, a left positioning sleeve 4, a right positioning sleeve 11, a left positioning rod 6, a right positioning rod 12 and a locking mechanism, the middle part of the base 2 is provided with a workpiece accommodating groove, the right positioning sleeve 11 is equipped on the right side of the base 2, and the left positioning sleeve 4 is equipped on the left side of the base 2; the workpiece locking assembly is arranged on the periphery of the base 2 and the side of the workpiece accommodating groove; the left positioning rod 6 passes through the left positioning sleeve 4; the right positioning rod 12 passes through the right positioning sleeve 11.

[0035] See also Figure 4 , Figure 5 In the parallel hole reaming operation method of the present invention, the left positioning sleeve 4 is composed of two parts located at the upper and lower parts, and an eccentric sleeve 4-2 and a rotating handle 4-1 are provided in each part. The offset between the central axis of the inner hole of the eccentric sleeve 4-2 and the central axis of the outer cylindrical surface is δ, and δ is equal to half of the tolerance of the distance L between the inner hole axes of the left and right sleeves on the landing gear strut of the aircraft, that is, δ=0.1mm; the rotating handle 4-1 is located on the outer side of the eccentric sleeve 4-2, and the eccentric sleeve 4-2 can be driven to rotate by the rotating handle 4-1, and then the left positioning rod 6 tightly fitted with the inner wall of the eccentric sleeve 4-2 is driven to move left and right by the eccentric sleeve 4-2. A locking groove 4-3 is provided on the outer cylindrical surface of the eccentric sleeve 4-2 of each part of the left positioning sleeve 4, and the locking groove 4-3 is a conical groove evenly distributed on the outer circumferential surface of the eccentric sleeve 4-2.

[0036] See also Figure 3The parallel hole reaming operation method of the present invention, in the parallel hole reaming operation auxiliary tool adopted by the parallel hole reaming operation auxiliary tool, the locking mechanism is provided with a left positioning sleeve locking assembly and a landing gear strut locking assembly; the left positioning sleeve locking assembly includes two groups of locking nails 5 arranged upper and lower, which respectively cooperate with the locking grooves 4-3 on the outer circumferential surfaces of the eccentric sleeve 4-2 of the upper and lower parts of the left positioning sleeve 4 to lock and fix the upper and lower parts of the left positioning sleeve 4; the landing gear strut locking assembly includes a pressing plate 7, a pressing block 10, a spinning rod 8, a positioning pin 9, a screw 13 and a pressing nail 3, the pressing plate 7 includes two parts arranged upper and lower, and the pressing block 10 is assembled between the upper and lower parts of the pressing plate 7, and the pressing block 10 is inside The side is attached to the edge of the landing gear strut 1, and a blind hole cooperating with the spinning rod 8 is provided on the clamping block 10. The spinning rod 8 cooperates with the threaded hole on the side wall of the base workpiece receiving groove, and the tail of the spinning rod 8 is inserted into the blind hole of the clamping block 10. An annular positioning groove is also provided at the tail of the spinning rod 8. The annular positioning groove cooperates with the positioning pin 9 passing through the pressure plate 7 and the clamping block 10 to lock the spinning rod 8 in place; the screw 13 is arranged on the right side and upper edge of the base 2, and its tail can pass through the side wall of the base workpiece receiving groove and collide with the landing gear strut 1; the clamping nail 3 is arranged between the landing gear strut 1 and the side wall of the base workpiece receiving groove, and the vertical positioning of the landing gear strut 1 is achieved by the clamping nail 3.

[0037] See also Figures 1 to 6 The specific operation steps of each process of the parallel hole reaming operation method of the present invention are as follows:

[0038] a. Measurement of the axis spacing L between the inner holes of the left and right sleeves of the original aircraft: Measure the axis spacing L between the inner holes of the left and right sleeves of the original aircraft by using a projector or a parallel reaming operation auxiliary tool in combination with a measuring tool. When the axis spacing L between the inner holes of the left and right sleeves of the original aircraft is measured by using a parallel reaming operation auxiliary tool in combination with a measuring tool, insert the left positioning rod 6 and the right positioning rod 12 into the inner holes of two groups of right sleeves and one group of left sleeves of the landing gear struts of the original aircraft respectively, and then use the measuring tool to measure the distance between the left positioning rod and the right positioning rod, and then convert the distance between the center axes of the left positioning rod 6 and the right positioning rod 12, that is, the axis spacing L between the inner holes of the left and right sleeves of the original aircraft;

[0039] b. Replacement of new sleeves: Remove the left and right sleeves of the original machine, process three sets of new sleeves with the same structure and material as the original sleeves, and make the inner hole size of the three sets of new sleeves smaller than the inner hole size of the corresponding original sleeves, and then respectively embed them in the three through holes of the tripod of the aircraft landing gear strut 1;

[0040] c. Machining the inner hole of the reference sleeve: Ream the two new sleeves installed on the right side of the aircraft landing gear struts to make the inner hole sizes of the two new sleeves on the right side completely consistent with the inner hole sizes of the two right sleeves on the original aircraft;

[0041] d. Installation of the right positioning rod: The aircraft landing gear strut 1 is installed as a workpiece on the base 2 of the parallel reaming operation auxiliary tool, and the right positioning rod 12 of the parallel reaming operation auxiliary tool is inserted into the right positioning sleeve 11 provided on the base 2 and the inner holes of the two sets of new sleeves on the right side of the workpiece, so that the inner walls of the two sets of new sleeves on the right side of the workpiece are tightly fitted with the right positioning rod 12;

[0042] e. Installation of the left positioning rod: First, rotate the scale value 0 line on the rotating handle 4-1 of the left positioning sleeve 4 to the central axis position, and then insert the left positioning rod 6 of the parallel reaming auxiliary tool into the left positioning sleeve 4 set on the left side of the base 2 and the inner hole of the new shaft sleeve on the left side of the workpiece, so that the left positioning rod 6 is tightly fitted with the inner wall of the left positioning sleeve 4;

[0043] f. Adjustment of the position of the left positioning rod: Use a measuring tool to measure the distance between the left positioning rod 6 and the right positioning rod 12, and then convert the distance between the center axes of the left positioning rod 6 and the right positioning rod 12, that is, the distance L1 between the inner holes of the left and right shaft sleeves of the workpiece at this time, and compare L1 with the distance L between the inner holes of the left and right shaft sleeves of the original machine, and calculate the difference ΔL between the two, ΔL=L1-L, and then rotate the left positioning sleeve 4 according to the value of ΔL, and drive the left positioning rod 6 to move left and right through the eccentric sleeve 4-2 structure of the left positioning sleeve 4. When ΔL>0, rotate the rotating handle 4-1 of the left positioning sleeve 4 to decrease its scale value. When ΔL=0, directly proceed to step g. When ΔL<0, rotate the rotating handle 4-1 of the left positioning sleeve 4 to increase its scale value until the distance between the center axes of the left positioning rod 6 and the right positioning rod 12 is completely consistent with the distance L between the inner holes of the left and right shaft sleeves of the original machine;

[0044] g. Reaming: The left positioning sleeve 4, the right positioning sleeve 11 and the workpiece are locked and fixed respectively by the workpiece locking assembly, and then the left positioning rod 6 is taken out, and then the reamer 14 is inserted into the left positioning sleeve 4, and the reaming operation is completed under the guidance of the left positioning sleeve 4. In this process, the front end of the reamer 14 used is a conical end face, and the circular runout of the hole to be processed is controlled by the centering effect of the conical end face.

Claims

1. A parallel hole reaming method, Features: The parallel hole reaming operation auxiliary tool is used to guide the feeding trajectory of a reamer (14), and the reamer (14) is used to complete the processing of the inner hole of the shaft sleeve of the landing gear strut (1) of the aircraft, including the measurement process of the axis distance L between the inner holes of the left and right shaft sleeves of the original aircraft, the replacement process of the new shaft sleeve, the reference shaft sleeve inner hole processing process, the right positioning rod installation process, the left positioning rod installation process, the left positioning rod position adjustment process and the reaming process; the parallel hole reaming operation auxiliary tool comprises a base (2), a left positioning sleeve (4), a right positioning sleeve (11), a left positioning rod (6), a right positioning rod (12) and a locking mechanism, and the base (2 ) is provided with a workpiece receiving groove in the middle part, a right positioning sleeve (11) is mounted on the right side of the base (2), and a left positioning sleeve (4) is mounted on the left side of the base (2), the left positioning sleeve (4) is provided with an eccentric sleeve (4-2), the offset between the central axis of the inner hole and the central axis of the outer cylindrical surface is δ, and δ is equal to half of the tolerance of the distance L between the inner holes of the left and right shaft sleeves on the aircraft landing gear strut (1), and the workpiece locking assembly is arranged on the periphery of the base (2) and the side of the workpiece receiving groove; the left positioning rod (6) passes through the left positioning sleeve (4); the right positioning rod (12) passes through the right positioning sleeve (11); In the parallel hole reaming auxiliary tool used therein, the left positioning sleeve (4) is composed of two parts located at an upper part and a lower part, and a locking groove (4-3) is provided on the outer circumferential surface of the eccentric sleeve (4-2) of each part thereof, and the locking groove (4-3) is a conical groove evenly distributed on the outer circumferential surface of the eccentric sleeve (4-2); In the parallel hole reaming auxiliary tool used therein, the locking mechanism is provided with a left positioning sleeve locking assembly; the left positioning sleeve locking assembly comprises two sets of locking pins (5) arranged at the top and the bottom, which respectively cooperate with locking grooves (4-3) on the outer circumferential surfaces of the eccentric sleeves (4-2) of the upper and lower parts of the left positioning sleeve (4) to lock and fix the upper and lower parts of the left positioning sleeve (4).

2. The parallel hole reaming method according to claim 1, Features: In the parallel hole reaming auxiliary tool adopted by the invention, the locking mechanism is further provided with a landing gear strut locking assembly, the landing gear strut locking assembly comprising a pressure plate (7), a pressure block (10), a spinning rod (8), a positioning pin (9), a screw (13) and a pressure nail (3); the pressure plate (7) comprises two parts arranged in an upper and lower manner, and the pressure block (10) is assembled between the upper and lower parts of the pressure plate (7); the inner side surface of the pressure block (10) is attached to the edge of the landing gear strut (1), and a blind hole cooperating with the spinning rod (8) is provided on the pressure block (10); the spinning rod (8) is connected to the side wall of the workpiece receiving groove of the base The tail of the spinning rod (8) is inserted into the blind hole of the pressing block (10), and an annular positioning groove is also provided at the tail of the spinning rod (8). The annular positioning groove cooperates with the positioning pin (9) passing through the pressing plate (7) and the pressing block (10) to lock the spinning rod (8) in place; the screw (13) is arranged on the right side and upper side edge of the base (2), and its tail can pass through the side wall of the base workpiece receiving groove and contact the landing gear strut (1); the pressing nail (3) is arranged between the landing gear strut (1) and the side wall of the base workpiece receiving groove, and the vertical positioning of the landing gear strut (1) is achieved by the pressing nail (3).

3. The parallel hole reaming method according to any one of claims 1 to 2, Features: The specific steps of each process are as follows: a. Measurement of the axis distance L between the inner holes of the left and right shaft sleeves of the original machine: Use a projector or parallel reaming operation auxiliary tool and a measuring tool to measure the axis distance L between the inner holes of the left and right sleeves of the original machine; b. Replacement of new bushings: Remove the left and right bushings of the original machine, and process three sets of new bushings with the same structure and material as the original bushings, and make the inner hole size of the three sets of new bushings smaller than the inner hole size of the corresponding original bushings, and then respectively install them in the three through holes of the tripod of the aircraft landing gear strut (1); c. Machining the inner hole of the reference sleeve: Ream the two new sleeves installed on the right side of the aircraft landing gear struts to make the inner hole sizes of the two new sleeves on the right side completely consistent with the inner hole sizes of the two right sleeves on the original aircraft; d. Installation of the right positioning rod: The aircraft landing gear strut (1) is installed as a workpiece on the base (2) of the parallel reaming operation auxiliary tool, and the right positioning rod (12) of the parallel reaming operation auxiliary tool is inserted into the right positioning sleeve (11) provided on the base (2) and the inner holes of the two sets of new shaft sleeves on the right side of the workpiece, so that the inner walls of the two sets of new shaft sleeves on the right side of the workpiece are tightly fitted with the right positioning rod (12); e. Installation of the left positioning rod: insert the left positioning rod (6) of the parallel reaming auxiliary tool into the left positioning sleeve (4) arranged on the left side of the base (2) and the inner hole of the new shaft sleeve on the left side of the workpiece, so that the left positioning rod (6) is tightly fitted with the inner wall of the left positioning sleeve (4); f. Adjustment of the position of the left positioning rod: Use a measuring tool to measure the distance between the left positioning rod (6) and the right positioning rod (12), and then convert the distance between the center axes of the left positioning rod (6) and the right positioning rod (12), that is, the distance L1 between the inner holes of the left and right shaft sleeves of the workpiece at this time. Compare L1 with the distance L between the inner holes of the left and right shaft sleeves of the original machine, and calculate the difference ΔL between the two, ΔL=L1-L. Then, according to the value of ΔL, rotate the left positioning sleeve (4), and drive the left positioning rod (6) to move left and right through the eccentric sleeve (4-2) structure of the left positioning sleeve (4), so that the distance between the center axes of the left positioning rod (6) and the right positioning rod (12) is completely consistent with the distance L between the inner holes of the left and right shaft sleeves of the original machine; g. Reaming: The left positioning sleeve (4), the right positioning sleeve (11) and the workpiece are locked and fixed respectively by means of the workpiece locking assembly, and then the left positioning rod (6) is removed. Then, the reamer (14) is inserted into the left positioning sleeve (4), and the reaming operation is completed under the guidance of the left positioning sleeve (4).

4. The parallel hole reaming method according to claim 3, Features: In operation step a, when the value of the axis distance L between the inner holes of the left and right shaft sleeves of the original aircraft is measured by using the parallel reaming operation auxiliary tool and the measuring tool, the left positioning rod (6) and the right positioning rod (12) are respectively inserted into the inner holes of the two groups of right shaft sleeves and one group of left shaft sleeves of the landing gear struts of the original aircraft, and then the distance between the left positioning rod and the right positioning rod is measured by using the measuring tool, and then the distance between the center axes of the left positioning rod (6) and the right positioning rod (12) is converted to be the axis distance L between the inner holes of the left and right shaft sleeves of the original aircraft.

5. The parallel hole reaming method according to claim 3, Features: In the parallel hole reaming auxiliary tool, the left positioning sleeve (4) is also provided with a rotating handle (4-1), and the rotating handle (4-1) is provided with a scale value, and the scale value corresponds to the distance that the left positioning rod (6) moves left and right when the left positioning sleeve (4) rotates.

6. The parallel hole reaming method according to claim 5, Features: In operation step e, before the left positioning rod (6) is inserted into the left positioning sleeve (4) arranged on the left side of the base (2) and the inner hole of the left shaft sleeve (1-1) of the workpiece, the scale value 0 line on the rotating handle (4-1) of the left positioning sleeve (4) is rotated to the central axis position.

7. The parallel hole reaming method according to claim 6, Features: In operation step f, when ΔL>0, the rotating handle (4-1) of the left positioning sleeve (4) is rotated to decrease the scale value; when ΔL=0, the operation of step g is directly performed; when ΔL<0, the rotating handle (4-1) of the left positioning sleeve (4) is rotated to increase the scale value.

8. The parallel hole reaming method according to claim 3, Features: The front end of the reamer (14) used in the invention is a conical end face, and the circular runout of the hole to be processed is controlled by the centering effect of the conical end face.

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