Aircraft joint reaming device and using method thereof

Abstract

The invention relates to the technical field of aircraft repair and production, in particular to an aircraft joint reaming device and a using method thereof.The reaming device comprises a positioning shaft, a handle, a joint fixing part and a reaming part; the joint fixing part comprises a conical sleeve, an inclined positioning block, a rotating sleeve, a first sliding disc, a second sliding disc and a cylindrical roller; the joint fixing part is movably mounted at the left end of the positioning shaft and is used for coaxially positioning joint bushings with different hole diameters of an airplane and ensuring the coaxiality of the reaming device and a joint hole; the reaming part comprises a rotary propelling sleeve and a replaceable reaming tool; a reaming tool is fixedly installed at the right end of the rotary propelling sleeve through threads. And the reaming part is rotatably mounted at the right end of the positioning shaft and is used for reaming the aircraft joint bushing. When the reaming device is used, the joint bushing is coaxially positioned through the joint fixing part, then the reaming tool is repeatedly replaced to ream the bushing hole, and the reaming device is high in reaming efficiency and good in precision.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft repair production, in particular to an aircraft joint reaming device and a use method thereof. Background Art

[0002] Joints are common components used for docking and installation on aircraft, such as those connecting wings to the fuselage, or the nose and main landing gear to the fuselage. To protect joints, bushings are installed in the joint holes. However, as flight time increases, these bushings can become severely worn or cracked, compromising flight safety and requiring replacement.

[0003] To ensure proper alignment between the aircraft's wing and fuselage, and the nose and main landing gear, joint components require high positioning accuracy. They must also coordinate with other intersection points and ensure the coaxiality of the joint holes. When replacing a new bushing during aircraft repair, the new bushing will have a certain machining allowance based on the design aperture. After the bushing is installed, the aperture allowance needs to be reamed to meet the design aperture and ensure the coaxiality of the joint holes, thereby ensuring proper wing-body alignment and the installation of the nose and main landing gear.

[0004] However, at present, there is no special tool for reaming the joint bushing. The existing technology mainly uses traditional tooling fixtures to ream the joint holes. The shape of the joint is irregular, and a large number of joint positioners and card plates for controlling the shape are required. The above existing technology has the following shortcomings: First, a large number of joint positioners and card plates for controlling the shape lead to low reaming efficiency, high cost, and difficulty in tooling management; Second, the existing tooling fixtures are difficult to ensure the coaxiality between the joint holes, and the reaming accuracy is low, which makes it difficult to coordinate the installation position with the other matching intersections. Summary of the Invention

[0005] In order to overcome the shortcomings of the existing technology, the present invention provides an aircraft joint reaming device and a method for using the same. By providing a tapered sleeve and an oblique positioning block in the joint fixing portion, the coaxial positioning of the joint bushings of different apertures of the aircraft can be quickly achieved, thereby ensuring the coaxiality of the reaming device and the joint hole, thereby improving the reaming accuracy; by providing a rotating propulsion sleeve in the reaming portion that can be installed with reamers of different specifications, the reaming accuracy can be ensured while improving the reaming efficiency.

[0006] The technical solution of the present invention is:

[0007] An aircraft joint reaming device comprises a positioning shaft, a handle, a joint fixing portion and a reaming portion;

[0008] The front section of the left end of the positioning shaft is a smooth rod, and the rear section of the left end is threaded; the right end of the positioning shaft is a threaded rod; the middle section of the positioning shaft is provided with a handle hole; the handle is inserted into the handle hole to facilitate hand gripping and fixing the positioning shaft;

[0009] The joint fixing portion includes a tapered sleeve, an oblique positioning block, a rotating sleeve, a first sliding plate, a second sliding plate, and a cylindrical roller; the joint fixing portion is movably mounted on the left end of the positioning shaft to achieve coaxial positioning of joint bushings of different apertures on the aircraft, thereby ensuring the coaxiality of the reaming device and the joint hole;

[0010] The reaming part includes a rotary propulsion sleeve and a replaceable reaming tool; the reaming tool is fixedly installed on the right end of the rotary propulsion sleeve through threads; the reaming part is rotatably installed on the right end of the positioning shaft to realize the reaming operation of the aircraft joint bushing.

[0011] Furthermore, the joint fixing portion is movably mounted on the left end of the positioning shaft through the rotating sleeve; the structures and connection relationships of the various components of the joint fixing portion are as follows:

[0012] The inner diameter of the tapered sleeve matches the smooth rod at the front section of the left end of the positioning shaft. The tapered sleeve is arranged at the left end of the positioning shaft and can be flexibly moved left and right along the axis of the positioning shaft. The outer side of the tapered sleeve is a tapered slope, with the tapered end facing left. The outer side of the tapered sleeve is provided with three dovetail grooves distributed along the circumferential direction of 120° along the axis. The bottom of the oblique positioning block is a dovetail seat, and the upper end is a rectangular block structure. The oblique positioning block is clamped in the dovetail groove on the outer side of the tapered sleeve through the dovetail seat, and the oblique positioning block can slide along the dovetail groove on the outer side of the tapered sleeve.

[0013] The rotating sleeve is provided with a threaded hole extending through the axial direction and is movably mounted on the positioning shaft through a thread on the rear section of the left end of the positioning shaft. The rotating sleeve can be moved along the axis of the positioning shaft by rotating the rotating sleeve. A sliding disc connecting portion is provided at the left end of the rotating sleeve, and coaxial annular sliding grooves are provided on the left and right end surfaces of the sliding disc connecting portion. A hexagonal tightening portion is provided at the right end of the rotating sleeve to facilitate rotating the rotating sleeve with a wrench.

[0014] The outer diameters of the first sliding plate and the second sliding plate are the same; coaxial annular sliding grooves are provided inside the first sliding plate and the second sliding plate; the inner diameter of the first sliding plate is the same as the inner diameter of the tapered sleeve; the first sliding plate is buckled on the left side of the sliding plate connecting part of the rotating sleeve from the left end; the inner diameter of the second sliding plate is the same as the outer diameter of the rotating sleeve, and the second sliding plate passes through the rotating sleeve from the right end and is buckled on the right side of the sliding plate connecting part of the rotating sleeve; the coaxial annular sliding grooves inside the first sliding plate and the second sliding plate cooperate with the coaxial annular sliding grooves on the left and right end faces of the sliding plate connecting part of the rotating sleeve to form a cavity; the cylindrical roller is placed radially in the cavity formed by the annular sliding grooves; the first sliding plate, the second sliding plate and the tapered sleeve are fixedly connected together; by rotating the rotating sleeve, the tapered sleeve can be driven to move along the axis of the positioning shaft through the first sliding plate and the second sliding plate.

[0015] Furthermore, the reaming portion is rotatably mounted on the right end of the positioning shaft through the rotating propulsion sleeve; the components of the reaming portion are constructed and connected as follows:

[0016] The interior of the left end of the rotary propulsion sleeve is a threaded hole that matches the threaded rod at the right end of the positioning shaft; the rotary propulsion sleeve is threadedly mounted on the threaded rod at the right end of the positioning shaft; the exterior of the left end of the rotary propulsion sleeve is provided with a hexagonal tightening portion, which is convenient for rotating the rotary propulsion sleeve with a wrench; the right end of the rotary propulsion sleeve is provided with a tool mounting head, and the interior of the tool mounting head is a threaded hole; the reaming tool is fixedly mounted in the threaded hole of the tool mounting head by means of threads; by rotating the rotary propulsion sleeve, the rotary propulsion sleeve can be moved along the axis of the positioning shaft, thereby driving the reaming tool to advance and retract.

[0017] Furthermore, the rotary propulsion sleeve is connected to the right end of the positioning shaft by a left-handed thread; and the reaming tool is connected to the right end of the rotary propulsion sleeve by a right-handed thread.

[0018] Furthermore, the reaming tool is a universal part, and reaming tools of different specifications are selected according to the diameter specifications of the hole to be reamed.

[0019] Furthermore, a method for reaming a joint bushing using the above-mentioned aircraft joint reaming device includes the following steps:

[0020] Step 1: Insert the joint fixing part of the reaming device into the left joint hole. The operator holds the handle and tightens the rotating sleeve with an open-end wrench. The rotating sleeve pushes to the left, driving the tapered sleeve to move. The oblique positioning block on the tapered sleeve slides to the right until the oblique positioning block contacts the surface of the joint hole. Then, tighten the rotating sleeve until the joint fixing part and the positioning shaft are fixed to the left joint to ensure the coaxiality of the positioning shaft and the left joint hole.

[0021] Step 2: Select a suitable reaming tool and install it on the right end of the rotary propulsion sleeve;

[0022] Step 3: The operator holds the handle and uses an open-end wrench to rotate the push sleeve. The rotating push sleeve drives the reaming tool to the right under the action of the thread until the reaming tool passes through the right joint bushing hole, completing the first reaming work;

[0023] Step 4: The operator holds the handle and uses an open-end wrench to reversely rotate the rotary propulsion sleeve until the rotary propulsion sleeve returns to its original position, replaces the reaming tool with a larger aperture, and performs the second reaming operation;

[0024] Step 5: Repeat step 4 until the hole diameter of the joint bushing meets the installation requirements and the reaming is completed.

[0025] Furthermore, when the aircraft joint hole reaming device is used to ream a joint bushing, the thickness of the hole reamed is 0.1 mm each time the reaming tool is replaced.

[0026] Beneficial effects

[0027] The present invention provides an aircraft joint reaming device and a method for using the same. By arranging a tapered sleeve in conjunction with an oblique positioning block in a joint fixing portion, rapid coaxial positioning of joint bushings of different apertures of an aircraft can be achieved, thereby ensuring the coaxiality of the reaming device and the joint hole, thereby improving the reaming accuracy. By arranging a rotating propulsion sleeve in the reaming portion that can be equipped with reamers of different specifications, the reaming accuracy can be ensured while improving the reaming efficiency. This can significantly improve the efficiency when replacing new bushings during aircraft repair. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 Schematic diagram of the overall structure of an embodiment of the present invention;

[0029] Figure 2 for Figure 1 AA cross-section diagram in;

[0030] Figure 3 A schematic diagram of a positioning shaft according to an embodiment of the present invention;

[0031] Figure 4 A schematic diagram of a tapered sleeve according to an embodiment of the present invention;

[0032] Figure 5 This is a schematic diagram of an oblique positioning block according to an embodiment of the present invention;

[0033] Figure 6 This is a schematic diagram of the right side of the rotating sleeve according to an embodiment of the present invention;

[0034] Figure 7 This is a schematic diagram of the left side of the rotating sleeve according to an embodiment of the present invention;

[0035] Figure 8 A schematic diagram of a first sliding disk according to an embodiment of the present invention;

[0036] Figure 9 A schematic diagram of a second sliding disk according to an embodiment of the present invention;

[0037] Figure 10 This is a schematic diagram of the installation of the first sliding plate, the second sliding plate and the rotating sleeve according to an embodiment of the present invention;

[0038] Figure 11 for Figure 10 Schematic diagram of CC cross section in;

[0039] Figure 12 A schematic diagram of a rotary propulsion sleeve according to an embodiment of the present invention;

[0040] Figure 13 A schematic diagram of a reaming tool according to an embodiment of the present invention;

[0041] Figure 14 This is a schematic diagram of the installation of a rotary propulsion sleeve and a reaming tool according to an embodiment of the present invention;

[0042] Figure 15 for Figure 14 BB cross-section diagram in;

[0043] Figure 16 A schematic diagram of a reaming operation according to an embodiment of the present invention;

[0044] Figure 17 This is a schematic diagram of a joint on the side to be reamed according to an embodiment of the present invention;

[0045] In the figure: 1- positioning shaft; 11- smooth rod at the left end of the positioning shaft; 12- threaded section at the left end of the positioning shaft; 13- handle hole; 14- threaded rod at the right end of the positioning shaft; 2- handle; 3- joint fixing portion; 31- tapered sleeve; 311- dovetail groove; 32- oblique positioning block; 321- dovetail seat; 33- rotating sleeve; 331- threaded hole in the rotating sleeve; 332- sliding plate connecting portion; 333- annular groove on the rotating sleeve; 334 -Hexagonal tightening part on the rotating sleeve; 34-first sliding disk; 35-second sliding disk; 36-cylindrical roller; 4-reaming part; 41-rotating propulsion sleeve; 411-internal threaded hole of the rotating propulsion sleeve; 412-hexagonal tightening part on the rotating propulsion sleeve; 413-tool mounting head; 42-reaming tool; 5-left joint; 51-left joint hole; 6-right joint; 61-joint bushing to be reamed; 62-bushing hole. DETAILED DESCRIPTION

[0046] In order to make the technical problems, technical solutions and beneficial effects solved by the present invention more clearly understood and to enable those skilled in the art to better understand the solutions of the present invention, the present invention is further described and fully explained below in conjunction with the accompanying drawings and examples. It should be understood that the specific embodiments described herein are only intended to illustrate the present invention and are not intended to limit the present invention.

[0047] like Figure 1 、 Figure 2 and Figure 3 As shown, an aircraft joint reaming device of this embodiment includes a positioning shaft 1, a handle 2, a joint fixing portion 3 and a reaming portion 4;

[0048] The front section of the left end of the positioning shaft 1 is a smooth rod 11, and the rear section of the left end is formed with a thread 12; the right end of the positioning shaft 1 is a threaded rod 14; the middle section of the positioning shaft 1 is provided with a handle hole 13; the handle 2 is inserted into the handle hole 13, which is convenient for holding and fixing the positioning shaft 1;

[0049] The joint fixing portion 3 includes a tapered sleeve 31, an oblique positioning block 32, a rotating sleeve 33, a first sliding plate 34, a second sliding plate 35, and a cylindrical roller 36; the joint fixing portion 3 is movably mounted on the left end of the positioning shaft 1 to achieve coaxial positioning of joint bushings of different apertures on the aircraft, thereby ensuring the coaxiality of the reaming device and the joint hole;

[0050] The reaming part 4 includes a rotary propulsion sleeve 41 and a reaming tool 42; the reaming tool 42 is fixedly installed on the right end of the rotary propulsion sleeve 41 through threads; the reaming part 4 is rotatably installed on the right end of the positioning shaft 1 to realize the reaming operation of the aircraft joint bushing.

[0051] Furthermore, the joint fixing portion 3 is movably mounted on the left end of the positioning shaft 1 through the rotating sleeve 33; the structure and connection relationship of each component of the joint fixing portion 3 are as follows:

[0052] like Figure 2 、 Figure 4 As shown, the inner diameter of the tapered sleeve 31 matches the smooth rod 11 at the front section of the left end of the positioning shaft 1. The tapered sleeve 31 is sleeved on the left end of the positioning shaft 1 and can flexibly move left and right along the axis of the positioning shaft 1. The outer side of the tapered sleeve 31 is a tapered slope with the tapered end facing left. The outer side of the tapered sleeve 31 is provided with three dovetail grooves 311 distributed along the circumference of 120° along the axis.

[0053] like Figure 5 As shown, the bottom of the oblique positioning block 32 is a dovetail seat 321, and the upper end is a rectangular block structure; the oblique positioning block 32 is clamped in the dovetail groove 311 outside the tapered sleeve 31 through the dovetail seat 321, and the oblique positioning block 32 can slide along the dovetail groove 311 outside the tapered sleeve 31;

[0054] like Figure 6 and Figure 7 As shown, the rotating sleeve 33 has a threaded hole 331 extending through it in the axial direction and is movably mounted on the positioning shaft 1 through the thread 12 at the rear section of the left end of the positioning shaft 1. The rotating sleeve 33 can be moved along the axis of the positioning shaft 1 by rotating the rotating sleeve 33. A sliding disk connecting portion 332 is provided at the left end of the rotating sleeve 33, and coaxial annular sliding grooves 333 are provided on the left and right end surfaces of the sliding disk connecting portion 332. A hexagonal tightening portion 334 is provided at the right end of the rotating sleeve 33 to facilitate rotating the rotating sleeve 33 with a wrench.

[0055] like Figure 8 and Figure 9 As shown, the first sliding plate 34 and the second sliding plate 35 have the same outer diameter; the first sliding plate 34 and the second sliding plate 35 are both provided with a coaxial annular sliding groove; the inner diameter of the first sliding plate 34 is the same as the inner diameter of the tapered sleeve 31; the first sliding plate 34 is buckled on the left side of the sliding plate connecting portion 332 of the rotating sleeve 33 from the left end; the inner diameter of the second sliding plate 35 is the same as the outer diameter of the rotating sleeve 33, and the second sliding plate 35 passes through the rotating sleeve 33 from the right end and is buckled on the right side of the sliding plate connecting portion 332 of the rotating sleeve 33; the coaxial annular sliding grooves inside the first sliding plate 34 and the second sliding plate 35 cooperate with the coaxial annular sliding grooves 333 on the left and right end surfaces of the sliding plate connecting portion 332 of the rotating sleeve 33 to form a cavity; as shown Figure 10 and Figure 11 As shown, the cylindrical roller 36 is placed in the cavity formed by the annular sliding groove along the radial direction; the first sliding plate 34, the second sliding plate 35 and the tapered sleeve 31 are fixed together by three screws distributed 120° along the circumference; by rotating the rotating sleeve 33, the tapered sleeve 31 can be driven to move along the axis of the positioning shaft 1 through the first sliding plate 34 and the second sliding plate 35.

[0056] Furthermore, the reaming portion 4 is rotatably mounted on the right end of the positioning shaft 1 through the rotating propulsion sleeve 41; the components of the reaming portion 4 have the following structure and connection relationship:

[0057] like Figure 2 and Figure 12As shown, the interior of the left end of the rotary propulsion sleeve 41 is a threaded hole 411 that matches the threaded rod 14 at the right end of the positioning shaft 1; the rotary propulsion sleeve 41 is threadedly sleeved on the threaded rod 14 at the right end of the positioning shaft 1; the left end of the rotary propulsion sleeve 41 is provided with a hexagonal tightening portion 412 on the outside, which is convenient for rotating the rotary propulsion sleeve 41 with a wrench; the right end of the rotary propulsion sleeve 41 is provided with a tool mounting head 413, and the interior of the tool mounting head 413 is a threaded hole; the reaming tool 42 is fixedly mounted in the threaded hole of the tool mounting head 413 by means of threads, as shown in FIG. Figure 14 and Figure 15 As shown; by rotating the rotary propulsion sleeve 41, the rotary propulsion sleeve 41 can be moved along the axis of the positioning shaft 1, thereby driving the reaming tool 42 to achieve feed and retract.

[0058] Furthermore, the rotary propulsion sleeve 41 is connected to the right end of the positioning shaft 1 by a left-handed thread; the reaming tool 42 is connected to the right end of the rotary propulsion sleeve 41 by a right-handed thread.

[0059] Furthermore, the reaming tool 42 is a universal part, and reaming tools 42 of different specifications are selected according to the diameter specifications of the hole to be reamed.

[0060] like Figure 16 、 Figure 17 As shown, the method of reaming a joint bushing 61 using an aircraft joint reaming device of this embodiment includes the following steps:

[0061] Step 1: Insert the joint fixing part 3 of the reaming device into the left joint hole 51. The operator holds the handle 2 and tightens the rotating sleeve 33 with an open-end wrench. The rotating sleeve 33 is pushed to the left, driving the tapered sleeve 31 to move. The oblique positioning block 32 on the tapered sleeve 31 slides to the right until the oblique positioning block 32 contacts the surface of the joint hole 51. Then, tighten the rotating sleeve 33 until the joint fixing part 3 and the positioning shaft 1 are fixed to the left joint 5, ensuring the coaxiality of the positioning shaft 1 and the left joint hole 51.

[0062] Step 2: Select a suitable reaming tool 42 and install it on the right end of the rotating propulsion sleeve 41;

[0063] Step 3: The operator holds the handle 2 and uses an open-end wrench to rotate the rotary propulsion sleeve 41. The rotary propulsion sleeve 41 drives the reaming tool 42 to the right under the action of the thread until the reaming tool 42 passes through the bushing hole 62 of the right joint 6, completing the first reaming operation;

[0064] Step 4: The operator holds the handle 2 and uses an open-end wrench to reversely rotate the push sleeve 42 until it returns to its original position, replaces the reaming tool 42 with a larger aperture, and performs a second reaming operation;

[0065] Step 5: Repeat step 4 until the hole diameter of the joint bushing 61 meets the installation requirements, and then finish reaming.

[0066] Furthermore, when the joint bushing 61 is reamed using the above-mentioned aircraft joint hole reaming device, the thickness of the reamed hole is 0.1 mm each time the reaming tool is replaced.

[0067] Although the embodiments of the present invention have been shown and described above, it will be understood that the above embodiments are illustrative and are not to be construed as limitations on the present invention. A person skilled in the art may change, modify, replace and modify the above embodiments within the scope of the present invention without departing from the principles and purpose of the present invention.

Claims

1. An aircraft joint reaming device, characterized by: It includes a positioning shaft, a handle, a joint fixing part and a reaming part; The front section of the left end of the positioning shaft is a smooth rod, and the rear section of the left end is threaded; the right end of the positioning shaft is a threaded rod; the middle section of the positioning shaft is provided with a handle hole; the handle is inserted into the handle hole to facilitate hand gripping and fixing the positioning shaft; The joint fixing portion includes a tapered sleeve, an oblique positioning block, a rotating sleeve, a first sliding plate, a second sliding plate, and a cylindrical roller; the joint fixing portion is movably mounted on the left end of the positioning shaft to achieve coaxial positioning of joint bushings of different apertures on the aircraft, thereby ensuring the coaxiality of the reaming device and the joint hole; The reaming part includes a rotary propulsion sleeve and a replaceable reaming tool; the reaming tool is fixedly installed on the right end of the rotary propulsion sleeve through threads; the reaming part is rotatably installed on the right end of the positioning shaft to realize the reaming operation of the aircraft joint bushing.

2. The aircraft joint reaming device according to claim 1, characterized in that: The joint fixing portion is movably mounted on the left end of the positioning shaft through the rotating sleeve; the structures and connection relationships of the various components of the joint fixing portion are as follows: The inner diameter of the tapered sleeve matches the smooth rod at the front section of the left end of the positioning shaft. The tapered sleeve is arranged at the left end of the positioning shaft and can be flexibly moved left and right along the axis of the positioning shaft. The outer side of the tapered sleeve is a tapered slope, with the tapered end facing left. The outer side of the tapered sleeve is provided with three dovetail grooves distributed along the circumferential direction of 120° along the axis. The bottom of the oblique positioning block is a dovetail seat, and the upper end is a rectangular block structure. The oblique positioning block is clamped in the dovetail groove on the outer side of the tapered sleeve through the dovetail seat, and the oblique positioning block can slide along the dovetail groove on the outer side of the tapered sleeve. The rotating sleeve is provided with a threaded hole extending through the axial direction and is movably mounted on the positioning shaft through a thread on the rear section of the left end of the positioning shaft. The rotating sleeve can be moved along the axis of the positioning shaft by rotating the rotating sleeve. A sliding disc connecting portion is provided at the left end of the rotating sleeve, and coaxial annular sliding grooves are provided on the left and right end surfaces of the sliding disc connecting portion. A hexagonal tightening portion is provided at the right end of the rotating sleeve to facilitate rotating the rotating sleeve with a wrench. The outer diameters of the first sliding plate and the second sliding plate are the same; coaxial annular sliding grooves are provided inside the first sliding plate and the second sliding plate; the inner diameter of the first sliding plate is the same as the inner diameter of the tapered sleeve; the first sliding plate is buckled on the left side of the sliding plate connecting part of the rotating sleeve from the left end; the inner diameter of the second sliding plate is the same as the outer diameter of the rotating sleeve, and the second sliding plate passes through the rotating sleeve from the right end and is buckled on the right side of the sliding plate connecting part of the rotating sleeve; the coaxial annular sliding grooves inside the first sliding plate and the second sliding plate cooperate with the coaxial annular sliding grooves on the left and right end faces of the sliding plate connecting part of the rotating sleeve to form a cavity; the cylindrical roller is placed radially in the cavity formed by the annular sliding grooves; the first sliding plate, the second sliding plate and the tapered sleeve are fixedly connected together; by rotating the rotating sleeve, the tapered sleeve can be driven to move along the axis of the positioning shaft through the first sliding plate and the second sliding plate.

3. The aircraft joint reaming device according to claim 1, characterized in that: The reaming part is rotatably mounted on the right end of the positioning shaft through the rotating propulsion sleeve; the components of the reaming part are constructed and connected as follows: The interior of the left end of the rotary propulsion sleeve is a threaded hole that matches the threaded rod at the right end of the positioning shaft; the rotary propulsion sleeve is threadedly mounted on the threaded rod at the right end of the positioning shaft; the exterior of the left end of the rotary propulsion sleeve is provided with a hexagonal tightening portion, which is convenient for rotating the rotary propulsion sleeve with a wrench; the right end of the rotary propulsion sleeve is provided with a tool mounting head, and the interior of the tool mounting head is a threaded hole; the reaming tool is fixedly mounted in the threaded hole of the tool mounting head by means of threads; by rotating the rotary propulsion sleeve, the rotary propulsion sleeve can be moved along the axis of the positioning shaft, thereby driving the reaming tool to advance and retract.

4. The aircraft joint reaming device according to claim 3, characterized in that: The rotary propulsion sleeve is connected to the right end of the positioning shaft by a left-handed thread; the reaming tool is connected to the right end of the rotary propulsion sleeve by a right-handed thread.

5. The aircraft joint reaming device according to claim 1, characterized in that: The reaming tool is a universal part, and reaming tools of different specifications are selected according to the diameter specifications of the hole to be reamed.

6. A method for reaming an aircraft joint bushing according to any one of claims 1 to 5, characterized in that: The steps include: Step 1: Insert the joint fixing part of the reaming device into the left joint hole. The operator holds the handle and tightens the rotating sleeve with an open-end wrench. The rotating sleeve pushes to the left, driving the tapered sleeve to move. The oblique positioning block on the tapered sleeve slides to the right until the oblique positioning block contacts the surface of the joint hole. Then, tighten the rotating sleeve until the joint fixing part and the positioning shaft are fixed to the left joint to ensure the coaxiality of the positioning shaft and the left joint hole. Step 2: Select a suitable reaming tool and install it on the right end of the rotary propulsion sleeve; Step 3: The operator holds the handle and uses an open-end wrench to rotate the push sleeve. The rotating push sleeve drives the reaming tool to the right under the action of the thread until the reaming tool passes through the right joint bushing hole, completing the first reaming work; Step 4: The operator holds the handle and uses an open-end wrench to reversely rotate the rotary propulsion sleeve until the rotary propulsion sleeve returns to its original position, replaces the reaming tool with a larger aperture, and performs the second reaming operation; Step 5: Repeat step 4 until the hole diameter of the joint bushing meets the installation requirements and the reaming is completed.

7. The reaming method according to claim 6, characterized in that: Each time the reaming tool is replaced, the thickness of the reaming hole is 0.1mm.

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