Aircraft delivery interface skin trimming tool and use method thereof

Abstract

The invention discloses an aircraft delivery interface skin trimming tool and a using method thereof, and belongs to the technical field of aircraft part machining. The trimming tool comprises the following trimming tools for a barrel section wall plate and a ship section wall plate; wherein as for the barrel section wall plates, the barrel section upper wall plate skin trimming tool, the barrel section left wall plate skin trimming tool and the barrel section right wall plate skin trimming tool each comprise two vertical plates which are oppositely arranged, and the two vertical plates are fixedly connected; the ship body left side lower wall plate skin trimming tool, the ship body right side lower wall plate skin trimming tool, the ship bottom left wall plate skin trimming tool and the ship bottom right wall plate skin trimming tool for ship section wall plates are each provided with one side consistent with the corresponding skin in appearance and can be detachably connected to a machine head final assembly fixture. Line drawing trimming is conducted on the skin through the trimming tool, the precision of the trimming basis is improved, and the length error of the skin after trimming is reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft parts processing, and in particular to an aircraft delivery interface skin trimming tool and a use method thereof. Background Art

[0002] The aircraft delivery interface is a special requirement put forward by the customer to facilitate subsequent assembly, which is mainly reflected in the form of retained length of the skin. When the aircraft skin is produced and manufactured, the skin length has a certain margin, and it needs to be trimmed before it can reach the delivery state. The AG600 is a large amphibious aircraft. The upper part adopts a traditional aircraft structure and the lower part is a ship structure. The overall aircraft skin presents an upper semicircular shape and a lower V-shape. The aircraft skin has the characteristics of large area, complex external curves and high precision. The skin that needs to be trimmed at the delivery interface includes the upper wall panel skin of the barrel section, the left wall panel skin of the barrel section, the right wall panel skin of the barrel section, the lower wall panel skin of the left side of the hull, the lower wall panel skin of the right side of the hull, the left wall panel skin of the bottom, and the right wall panel skin of the bottom.

[0003] The existing aircraft delivery interface skin trimming method mainly uses a ruler to measure the skin, and a marking pen to manually mark the parts to be trimmed on the skin. The trimming tools are then used to manually trim the parts. After trimming, the skin size needs to be inspected. The inspection method uses a ruler or vernier caliper to measure the distance from the edge of the skin to the positioning frame and then calculates it to indirectly measure the skin length. The technical problems existing in the existing technology are: due to factors such as different operator operating habits, large trimming size, and the complexity of the skin's external surface, the ruler may shake slightly when drawing the line, resulting in uncertainty in the width and continuity of the skin marking line, inaccurate basis for skin trimming, and large errors in the length of the skin after trimming; the inspection method is not direct and there are large measurement errors. Summary of the Invention

[0004] In order to overcome the problem that the existing aircraft delivery interface skin trimming cannot ensure the skin accuracy, the present invention provides an aircraft delivery interface skin trimming tool and a use method thereof.

[0005] The technical solution adopted by the present invention to solve its technical problem is: The aircraft delivery interface skin trimming tooling includes the barrel section upper wall panel skin trimming tooling, the barrel section left wall panel skin trimming tooling, the barrel section right wall panel skin trimming tooling, the hull left side lower wall panel skin trimming tooling, the hull right side lower wall panel skin trimming tooling, the bottom left wall panel skin trimming tooling and the bottom right wall panel skin trimming tooling; the barrel section upper wall panel skin trimming tooling, the barrel section left wall panel skin trimming tooling and the barrel section right wall panel skin trimming tooling all include two vertical plates arranged opposite to each other, and the two vertical plates are fixedly connected; the hull left side lower wall panel skin trimming tooling, the hull right side lower wall panel skin trimming tooling, the bottom left wall panel skin trimming tooling and the bottom right wall panel skin trimming tooling all have one side that is consistent with the corresponding skin shape, and can be detachably connected to the nose assembly jig.

[0006] In the present application, the skin is trimmed by drawing lines using a trimming tool, thereby improving the accuracy of the trimming basis and reducing the error in the length of the skin after trimming.

[0007] In some embodiments, it also includes a barrel section tooling jig pallet, which is vertically arranged. One of the vertical plates of the barrel section upper wall panel skin trimming tooling, the barrel section left wall panel skin trimming tooling and the barrel section right wall panel skin trimming tooling is fitted with the barrel section tooling jig pallet, and when sliding on the barrel section tooling jig pallet, the other vertical plate can slide along the skin surface.

[0008] In some embodiments, one of the vertical plates of the barrel section upper wall panel skin trimming tool, the barrel section left wall panel skin trimming tool and the barrel section right wall panel skin trimming tool is fitted with the barrel section tooling jig clamp and is rotatably connected to the barrel section tooling jig clamp, and the distribution of the rotation axis is adapted to the center of the skin barrel section, so that when the trimming tool rotates relative to the barrel section tooling jig clamp, the other vertical plate can slide along the skin surface.

[0009] In some embodiments, the barrel section upper wall panel skin trimming tool, the barrel section left wall panel skin trimming tool, and the barrel section right wall panel skin trimming tool are configured as one component.

[0010] In some embodiments, an inspection tool is also included, which is a stop block set on the nose assembly jig. Multiple stops are set on the nose assembly jig corresponding to each skin. When the skin is positioned to the nose assembly jig, the moving block gauge can be used to judge whether the skin size is qualified based on whether the block gauge can pass between the stop block and the edge of the skin.

[0011] In this application, the inspection tooling is used in combination with a block gauge, which can complete the inspection of all inspection points of the skin at one time compared to the previous method of using a ruler or vernier caliper to measure the remaining length of the skin. It can also measure the distance between the edge of the skin and the inspection block more directly, intuitively and quickly.

[0012] In some embodiments, the stopper is detachably fixed to the machine head assembly jig via a latch.

[0013] The present invention also provides a method for using the aircraft delivery interface skin trimming tool as described above, comprising the following contents: S1. When trimming the corresponding skin using the upper, left, or right barrel panel skin trimming tool, place one of the trimming tool's vertical plates against a fixed vertical surface. After securing the skin in the proper position, move the trimming tool while maintaining the contact, allowing the other vertical plate to slide along the skin surface and trim along the sliding path. S2. When using the left side lower hull panel skin trimming tool, the right side lower hull panel skin trimming tool, the left bottom panel skin trimming tool, or the right bottom panel skin trimming tool for trimming, secure the trimming tool to the nose assembly jig, secure the skin in the appropriate position, and then trim along the joint between the trimming tool and the skin.

[0014] In some embodiments, the trimming tool further includes a vertically arranged barrel section tooling jig plate, and one of the vertical plates of the barrel section upper wall panel skin trimming tool, the barrel section left wall panel skin trimming tool, and the barrel section right wall panel skin trimming tool fits the barrel section tooling jig plate and is rotatably connected to the barrel section tooling jig plate. S1 includes the following contents: S1. When trimming the corresponding skin using the barrel section upper panel skin trimming tool, the barrel section left panel skin trimming tool, or the barrel section right panel skin trimming tool, rotate one of the vertical plates of the trimming tool to connect and fit it to the barrel section tooling jig clamp. After fixing the skin in the appropriate position, rotate the trimming tool while maintaining the fit, so that the other vertical plate slides along the skin surface and trims along the sliding path.

[0015] In some embodiments, the aircraft delivery interface skin trimming tool includes an inspection tool, which is a block provided on the nose assembly jig. The method for using the trimming tool further includes the following: S3. Fix at least two stoppers to each skin on the nose assembly jig. After the skin is properly positioned, move the gauge along the edge of the skin to determine if the gauge passes between the skin edge and the stoppers.

[0016] The beneficial effects of the present invention are: The trimming tool is used to mark and trim the skin, which improves the accuracy of the trimming basis and reduces the error in the length of the skin after trimming. Compared with the previous method of using a ruler or vernier caliper to measure the remaining length of the skin, the inspection tool is used in combination with a block gauge to complete all the inspection points of the skin at one time, and the distance between the skin edge and the inspection block can be measured more directly, intuitively and quickly. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 A schematic structural diagram of a trimming tool for the upper wall panel skin of a barrel section in the trimming tool provided by the present invention; Figure 2 This is a schematic structural diagram of a trimming tool for the left wall panel of the barrel section provided by the present invention; Figure 3 This is a schematic structural diagram of the trimming tool for the right wall panel of the barrel section provided by the present invention; Figure 4 A schematic diagram of an application scenario of the trimming tool for trimming the upper wall panel skin of the barrel section provided by the present invention; Figure 5 This is a schematic structural diagram of the trimming tool for the lower wall panels on the left and right sides of the hull provided by the present invention; Figure 6 A schematic diagram of an application scenario of the trimming tool for trimming the skin of the lower left side wall panel of the hull provided by the present invention; Figure 7 This is a schematic structural diagram of the trimming tool for the left and right side panels of the ship's bottom, among the trimming tools provided by the present invention; Figure 8 A schematic diagram of an application scenario of a ship bottom left wall panel skin trimming tool provided by the present invention; Figure 9 A schematic diagram of the inspection tooling structure provided by the present invention; Figure 10 This is a structural schematic diagram of the inspection tool positioning method provided by the present invention.

[0018] The markings in the figure are: 0-nose assembly jig; 1-barrel section upper wall panel skin trimming tool; 10-barrel section upper wall panel skin inspection tool; 2-barrel section left wall panel skin trimming tool; 20-barrel section left wall panel skin inspection tool; 3-barrel section right wall panel skin trimming tool; 30-barrel section right wall panel skin inspection tool; 4-hull left lower wall panel skin trimming tool; 40-hull left lower wall panel skin inspection tool : 5-hull right side lower wall panel skin trimming tool; 50-hull right side lower wall panel skin inspection tool; 6-bottom left wall panel skin trimming tool; 60-bottom left wall panel skin inspection tool; 7-bottom right wall panel skin trimming tool; 70-bottom right wall panel skin inspection tool; 8-skin; 100-stopper; 101-sliding rod; 102-latch; 123-barrel section tooling frame clamp. DETAILED DESCRIPTION

[0019] The present invention will be further described below with reference to the accompanying drawings.

[0020] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0021] like Figures 1-10 As shown, the present invention provides an aircraft delivery interface skin trimming tool and a method of using the same.

[0022] The aircraft delivery interface skin trimming tooling provided by the present invention is mainly divided into two categories, which are respectively applied to barrel section wall panels and ship section wall panels.

[0023] Specifically, the trimming tooling includes a barrel section upper wall panel skin trimming tool 1, a barrel section left wall panel skin trimming tool 2, a barrel section right wall panel skin trimming tool 3, a hull left side lower wall panel skin trimming tool 4, a hull right side lower wall panel skin trimming tool 5, a ship bottom left wall panel skin trimming tool 6, and a ship bottom right wall panel skin trimming tool 7. Among them, the barrel section upper wall panel skin trimming tool 1, the barrel section left wall panel skin trimming tool 2, and the barrel section right wall panel skin trimming tool 3 are used for barrel section wall panels, while the hull left side lower wall panel skin trimming tool 4, the hull right side lower wall panel skin trimming tool 5, the ship bottom left wall panel skin trimming tool 6, and the ship bottom right wall panel skin trimming tool 7 are used for ship section wall panels.

[0024] like Figure 1-Figure 3 As shown, the barrel section upper wall panel skin trimming tool 1, the barrel section left wall panel skin trimming tool 2 and the barrel section right wall panel skin trimming tool 3 all include two vertical plates arranged opposite to each other, and the two vertical plates are fixedly connected. The three are used in the same way. Figure 4 The application scenario example of the barrel section upper wall panel skin trimming tool 1 is used as a demonstration.

[0025] like Figure 5 and Figure 7 As shown, the left side lower wall panel skin trimming tool 4, the right side lower wall panel skin trimming tool 5, the left bottom wall panel skin trimming tool 6 and the right bottom wall panel skin trimming tool 7 all have a side that is consistent with the appearance of the corresponding skin 8, and can be detachably connected to the nose assembly jig 0. Figure 6 and Figure 8 The application scenarios of the left side lower wall panel trimming tool 4 and the bottom left wall panel trimming tool 6 are respectively used as demonstration examples.

[0026] Reference Figure 6 As shown, after the left side lower wall panel skin 8 of the hull is positioned on the nose assembly jig 0, the left side lower wall panel skin trimming tool 4 of the hull is fixed to the nose assembly jig 0. The fitting surface between the trimming tool and the skin 8 is the theoretical length position of the skin 8. A line is drawn along the fitting portion between the tool and the skin 8, and then the excess allowance is trimmed manually.

[0027] Reference Figure 8 As shown, after the left bottom wall panel skin 8 is positioned on the nose assembly jig 0, the left bottom wall panel skin trimming tool 6 is fixed to the nose assembly jig 0. The fitting surface between the trimming tool and the skin 8 is the theoretical length position of the skin 8. A line is drawn along the fitting surface between the tool and the skin 8, and then the excess allowance is trimmed manually.

[0028] In practice, the position of the existing nose assembly jig 0 does not change. Through digital model calculation, the corresponding trimming tool length is designed so that after the trimming tool is fixed on the nose assembly jig 0, the fitting surface between the trimming tool corresponding to the section wall panel and the skin 8 is the theoretical position of the remaining length of the skin 8, so that a line is drawn at this position to assist in trimming the skin 8.

[0029] In the present application, the skin 8 is trimmed by drawing lines using a trimming tool, thereby improving the accuracy of the trimming basis and reducing the error in the length of the skin 8 after trimming.

[0030] In practice, one of the vertical plates of the tooling used for trimming the barrel section wall panel skin 8 should fit into a vertical surface. Taking the wall as an example, since the trimming tooling includes two oppositely arranged vertical plates, the trimming sections of the skin 8 edge can be kept at a fixed distance from the wall.

[0031] In this embodiment, a barrel section jig fixture 123 is further included. The barrel section jig fixture 123 is vertically arranged. One of the vertical plates of the barrel section upper wall panel skin trimming tool 1, the barrel section left wall panel skin trimming tool 2, and the barrel section right wall panel skin trimming tool 3 is attached to the barrel section jig fixture 123. When the other vertical plate slides on the barrel section jig fixture 123, the other vertical plate can slide along the surface of the skin 8. The process of the other vertical plate sliding along the surface of the skin 8 is also the process of marking and drawing lines.

[0032] A vertically mounted barrel section jig plate 123 is added to provide a vertical surface for the barrel section wall panel trimming tooling. In practice, the barrel section jig plate 123 can also be detachably fixed to the existing nose assembly jig 0, thereby further facilitating the implementation by leveraging the existing positioning relationship between the skin 8 and the nose assembly jig 0.

[0033] In some other embodiments, one of the vertical plates of the barrel section upper wall panel skin trimming tool 1, the barrel section left wall panel skin trimming tool 2 and the barrel section right wall panel skin trimming tool 3 fits the barrel section tooling jig clamp 123 and is rotatably connected to the barrel section tooling jig clamp 123, and the distribution of the rotation axis is adapted to the center of the barrel section of the skin 8, so that when the trimming tool rotates relative to the barrel section tooling jig clamp 123, the other vertical plate can slide along the surface of the skin 8.

[0034] When the end face of the barrel section wall panel skin 8 is circular, one of the vertical plates of the cutting tool as described above can be rotated to connect to the barrel section tooling frame clamp 123, which facilitates the fitting and relative rotation of the bevel cutting tool and the barrel section tooling frame clamp 123.

[0035] As an extension, when the end surface of the barrel section wall panel skin 8 is not circular, the above-described embodiment can also be implemented in which one of the vertical plates is rotatably connected to the barrel section jig clamp 123. In order to achieve the alignment and marking of the other vertical plate with the skin 8, the other vertical plate needs to be configured to be vertically movable. For example, the other vertical plate can be configured to have an inward expansion tendency, which can be achieved by using an elastic unit. When the barrel section jig clamp 123 of the trimming jig rotates, the other vertical plate is always aligned with the surface of the skin 8 under the action of the elastic force, thereby achieving the marking and trimming of the barrel section wall panel skin 8 when the end surface is not circular.

[0036] In some embodiments, based on the consistent working principle of the barrel section trimming tooling, the barrel section upper wall panel skin trimming tooling 1, the barrel section left wall panel skin trimming tooling 2 and the barrel section right wall panel skin trimming tooling 3 can be configured as one component.

[0037] Reference Figure 9 As shown, in this embodiment, an inspection tool is also included. The inspection tool is a stop block 100 set on the nose assembly jig 0. Multiple stop blocks 100 are set on the nose assembly jig 0 corresponding to each skin 8. When the skin 8 is positioned to the nose assembly jig 0, the moving block gauge can be used to determine whether the size of the skin 8 is qualified based on whether the block gauge can pass between the stop block 100 and the edge of the skin 8.

[0038] In this embodiment, the inspection tooling corresponding to each skin 8 includes a barrel upper panel skin inspection tool 10, a barrel left panel skin inspection tool 20, a barrel right panel skin inspection tool 30, a hull left lower panel skin inspection tool 40, a hull right lower panel skin inspection tool 50, a bottom left panel skin inspection tool 60, and a bottom right panel skin inspection tool 70. In this embodiment, three stoppers 100 are provided for each inspection tool, that is, three stoppers 100 are provided for each skin 8.

[0039] In this application, by using inspection tooling and a block gauge, compared with the previous method of using a ruler or vernier caliper to measure the remaining length of the skin 8, all inspection points of the skin 8 can be inspected at one time, and the distance between the edge of the skin 8 and the stop block 100 can be measured more directly, intuitively and quickly.

[0040] In this embodiment, the stopper 100 is detachably fixedly connected to the machine head assembly jig 0 via a latch 102 .

[0041] exist Figure 10The figure shows two ways to detachably connect the stopper 100 to the machine head assembly jig 0 via a latch 102: using a sliding rod 101 to push the stopper 100 and insert it into the limit position, or directly placing it in the inspection position and inserting the latch 102 to secure it. The implementation process is simple, fast, and easy to operate. The stopper 100 can be removed when not in use, freeing up operating space.

[0042] In this embodiment, the aforementioned ship section trimming tool is also detachably connected to the nose assembly jig 0 via a latch 102 , so as to facilitate installation and disassembly during implementation and improve work efficiency.

[0043] The present invention also provides a method for using the aircraft delivery interface skin trimming tool as described above, which includes the following contents.

[0044] S1. When trimming the corresponding skin 8 using the upper barrel panel skin trimming tool 1, the left barrel panel skin trimming tool 2, or the right barrel panel skin trimming tool 3, place one of the trimming tool's vertical plates against a fixed vertical surface. After securing skin 8 in the proper position, move the trimming tool while maintaining the contact, allowing the other vertical plate to slide along the surface of skin 8 and trim along the sliding path.

[0045] Obviously, the appropriate position here is based on the target length of the skin 8, so that the skin 8 is at a certain distance from the fixed vertical surface when placed horizontally.

[0046] S2. When trimming using the left side lower hull panel skin trimming tool 4, the right side lower hull panel skin trimming tool 5, the left bottom panel skin trimming tool 6, or the right bottom panel skin trimming tool 7, secure the trimming tool to the nose assembly jig 0, secure skin 8 in the appropriate position, and then trim along the joint between the trimming tool and skin 8.

[0047] Obviously, the appropriate position here is based on the target length of the skin 8, and the skin 8 is placed so that the edge of the surface where it fits with the trimming tool is the trimming position of the marking line.

[0048] It is worth noting that the usage method here has no strict restrictions on the previous and subsequent steps.

[0049] Specifically, in this embodiment, the trimming tooling includes a vertically arranged barrel section tooling jig plate 123, and one of the vertical plates of the barrel section upper wall panel skin trimming tooling 1, the barrel section left wall panel skin trimming tooling 2 and the barrel section right wall panel skin trimming tooling 3 is fitted with the barrel section tooling jig plate 123 and is rotatably connected to the barrel section tooling jig plate 123. S1 includes the following contents.

[0050] S1. When trimming the corresponding skin 8 using the upper barrel panel skin trimming tool 1, the left barrel panel skin trimming tool 2, or the right barrel panel skin trimming tool 3, rotate one of the trimming tool's vertical plates so that it engages with the barrel panel fixture's jig clamp 123. After securing skin 8 in the proper position, rotate the trimming tool while maintaining the engagement, allowing the other vertical plate to slide along the surface of skin 8 and trim along the sliding path.

[0051] Furthermore, the aircraft delivery interface skin trimming tooling includes an inspection tooling, and the inspection tooling is a stopper 100 set on the nose assembly jig 0. The method of using the trimming tooling also includes the following content.

[0052] S3. Attach at least two stoppers 100 to each skin 8 on the nose assembly jig 0. After the skin 8 is properly positioned, move a gauge along the edge of the skin 8 to determine if the gauge passes between the edge of the skin 8 and the stoppers 100.

[0053] Obviously, the proper position here is based on the alignment between skin 8 and nose assembly jig 0, combined with the position of stopper 100. This allows the gauge to measure the distance between the edge of skin 8 and stopper 100 to determine if the skin 8 dimensions are acceptable. The alignment between skin 8 and nose assembly jig 0 is already achieved in the prior art, so only the position of stopper 100 needs to be set accordingly.

[0054] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. Aircraft delivery interface skin trimming tooling, its characteristics are: The trimming tool comprises a barrel section upper wall panel skin trimming tool (1), a barrel section left wall panel skin trimming tool (2), a barrel section right wall panel skin trimming tool (3), a hull left side lower wall panel skin trimming tool (4), a hull right side lower wall panel skin trimming tool (5), a ship bottom left wall panel skin trimming tool (6) and a ship bottom right wall panel skin trimming tool (7); The barrel section upper wall panel skin trimming tool (1), the barrel section left wall panel skin trimming tool (2) and the barrel section right wall panel skin trimming tool (3) all comprise two vertical plates arranged opposite to each other, and the two vertical plates are fixedly connected; The left side lower hull panel skin trimming tool (4), the right side lower hull panel skin trimming tool (5), the left bottom hull panel skin trimming tool (6) and the right bottom hull panel skin trimming tool (7) all have one side that is consistent with the corresponding skin shape and can be detachably connected to the nose assembly jig (0).

2. The aircraft delivery interface skin trimming tool according to claim 1, characterized in that: The utility model further comprises a barrel section tooling jig plate (123), the barrel section tooling jig plate (123) being arranged vertically, one of the vertical plates of the barrel section upper wall panel skin trimming tooling (1), the barrel section left wall panel skin trimming tooling (2) and the barrel section right wall panel skin trimming tooling (3) being fitted with the barrel section tooling jig plate (123), and when sliding on the barrel section tooling jig plate (123), the other vertical plate can slide along the surface of the skin (8).

3. The aircraft delivery interface skin trimming tool as claimed in claim 2, characterized in that: One of the vertical plates of the barrel section upper wall panel skin trimming tool (1), the barrel section left wall panel skin trimming tool (2) and the barrel section right wall panel skin trimming tool (3) fits the barrel section tool frame clamp (123) and is rotatably connected to the barrel section tool frame clamp (123). The rotation axis distribution is adapted to the center of the barrel section of the skin (8), so that when the trimming tool rotates relative to the barrel section tool frame clamp (123), the other vertical plate can slide along the surface of the skin (8).

4. The aircraft delivery interface skin trimming tool according to claim 1, characterized in that: The barrel section upper wall panel skin trimming tool (1), the barrel section left wall panel skin trimming tool (2) and the barrel section right wall panel skin trimming tool (3) are configured as one component.

5. The aircraft delivery interface skin trimming tool according to any one of claims 1 to 4, characterized in that: The invention also includes an inspection tool, which is a stopper (100) arranged on the nose assembly jig (0). A plurality of stoppers (100) are arranged on the nose assembly jig (0) corresponding to each skin (8). When the skin (8) is positioned on the nose assembly jig (0), the movable block gauge can be judged whether the size of the skin (8) is qualified based on whether the block gauge can pass between the stopper (100) and the edge of the skin (8).

6. The aircraft delivery interface skin trimming tool according to claim 5, characterized in that: The stopper (100) is detachably fixedly connected to the machine head assembly jig (0) via a latch (102).

7. The method of using the aircraft delivery interface skin trimming tool is characterized by: The use of the aircraft delivery interface skin trimming tool as claimed in claim 1 includes the following contents: S1. When trimming the corresponding skin (8) using the barrel section upper wall panel skin trimming tool (1), the barrel section left wall panel skin trimming tool (2), or the barrel section right wall panel skin trimming tool (3), one of the vertical plates of the trimming tool is attached to a fixed vertical surface. After the skin (8) is fixed to a suitable position, the trimming tool is moved while maintaining the attached state, so that the other vertical plate slides along the surface of the skin (8) and trims along the sliding track; S2. When using the left side lower hull panel skin trimming tool (4), the right side lower hull panel skin trimming tool (5), the left bottom panel skin trimming tool (6), or the right bottom panel skin trimming tool (7) for trimming, fix the trimming tool to the nose assembly jig (0), fix the skin (8) to a suitable position, and then trim along the joint between the trimming tool and the skin (8).

8. The method for using the aircraft delivery interface skin trimming tool as claimed in claim 7, characterized in that: The trimming tool further comprises a barrel section tool frame clamping plate (123) arranged vertically, one of the vertical plates of the barrel section upper wall panel skin trimming tool (1), the barrel section left wall panel skin trimming tool (2) and the barrel section right wall panel skin trimming tool (3) is fitted with the barrel section tool frame clamping plate (123) and is rotatably connected to the barrel section tool frame clamping plate (123). S1 comprises the following contents: S1. When trimming the corresponding skin (8) using the barrel section upper wall panel skin trimming tool (1), the barrel section left wall panel skin trimming tool (2), or the barrel section right wall panel skin trimming tool (3), one of the vertical plates of the trimming tool is rotated and connected to fit the barrel section tool frame clamp (123). After fixing the skin (8) to a suitable position, the trimming tool is rotated while maintaining the fit state so that the other vertical plate slides along the surface of the skin (8) and trims along the sliding track.

9. The method for using the aircraft delivery interface skin trimming tool as claimed in claim 7 is characterized in that: The interface skin trimming tool includes an inspection tool, which is a stopper (100) provided on the nose assembly jig (0). The method for using the trimming tool also includes the following contents: S3. At least two stoppers (100) are fixed on the nose assembly jig (0) corresponding to each skin (8). After the skin (8) is fixed to a suitable position, a gauge block is moved along the edge of the skin (8). Whether the size of the skin (8) is qualified is determined by whether the gauge block can pass between the edge of the skin (8) and the stoppers (100).

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