Airplane delivery interface skin trimming tooling and method of use

Abstract

This invention discloses a cutting fixture for aircraft delivery interface skin and its usage method in the field of aircraft component processing technology. The cutting fixture includes the following cutting fixtures for barrel section panels and ship section panels; wherein, for barrel section panels: the upper barrel section panel skin cutting fixture, the left barrel section panel skin cutting fixture, and the right barrel section panel skin cutting fixture all include two vertically arranged opposite each other, and the two vertically arranged plates are fixedly connected; wherein, for ship section panels: the lower left hull panel skin cutting fixture, the lower right hull panel skin cutting fixture, the left bottom panel skin cutting fixture, and the right bottom panel skin cutting fixture all have one side consistent with the shape of the corresponding skin and can be detachably connected to the nose assembly frame. By using the cutting fixture to perform line marking and cutting on the skin, the accuracy of the cutting basis is improved, and the error in the length of the skin after cutting is reduced.

Description

Technical Field

[0001] This invention relates to the field of aircraft parts processing technology, specifically to an aircraft delivery interface skin trimming tool and its usage method. Background Technology

[0002] The aircraft delivery interface is a special requirement put forward by the customer to facilitate subsequent assembly, mainly reflected in the form of the skin length. During aircraft skin manufacturing, the skin length has a certain margin, which needs to be trimmed to reach the delivery state. The AG600 is a large amphibious aircraft, with a traditional aircraft structure on the upper part and a boat structure on the lower part. The overall aircraft skin has a semi-circular upper part and a V-shaped lower part, characterized by its large area, complex curved surface, and high precision. The skin requiring trimming 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 left wall panel skin of the hull, the lower right wall panel skin of the hull, the left wall panel skin of the bottom, and the right wall panel skin of the bottom.

[0003] Current methods for trimming aircraft delivery interface skins primarily involve using a ruler to guide the trimming area onto the skin, manually marking the areas to be trimmed with a marker, and then manually trimming using trimming tools. After trimming, the skin dimensions need to be inspected. This is done by measuring the distance from the skin edge to the positioning frame using a ruler or calipers, and then calculating the distance to indirectly measure the skin length. The existing technology has several technical problems: variations in operator habits, large trimming dimensions, and the complexity of the skin's curved surface can all affect the process. Slight wobbling of the ruler during marking can lead to inaccuracies in the width and continuity of the marked lines, resulting in imprecise trimming and significant errors in the trimmed skin length. Furthermore, the inspection method is indirect and subject to substantial measurement errors. Summary of the Invention

[0004] To overcome the problem that existing aircraft delivery interface skin trimming methods cannot guarantee skin accuracy, this invention provides an aircraft delivery interface skin trimming tool and its usage method.

[0005] The technical solution adopted by this invention to solve its technical problem is:

[0006] The aircraft delivery interface skin trimming fixture includes trimming fixtures for the upper bulkhead of the barrel section, the left bulkhead of the barrel section, the right bulkhead of the barrel section, the lower bulkhead of the left side of the hull, the lower bulkhead of the right side of the hull, the left bulkhead of the bottom of the hull, and the right bulkhead of the bottom of the hull. Each of the trimming fixtures for the upper bulkhead of the barrel section, the left bulkhead of the barrel section, and the right bulkhead of the barrel section includes two vertical plates that are fixedly connected. Each of the trimming fixtures for the lower bulkhead of the left side of the hull, the lower bulkhead of the right side of the hull, the left bulkhead of the bottom of the hull, and the right bulkhead of the bottom of the hull has one side that matches the shape of the corresponding skin and can be detachably connected to the nose assembly frame.

[0007] In this application, a trimming fixture is used to trim the skin by marking lines, thereby improving the accuracy of the trimming basis and reducing the error in the length of the trimmed skin.

[0008] In some embodiments, the tooling frame plate is further included. The tooling frame plate is vertically arranged. One of the vertical plates of the upper wall panel skin trimming tool, the left wall panel skin trimming tool, and the right wall panel skin trimming tool of the barrel segment is attached to the tooling frame plate. When sliding on the tooling frame plate, the other vertical plate can slide along the skin surface.

[0009] In some embodiments, one of the vertical plates of the barrel segment upper wall panel skin trimming fixture, the barrel segment left wall panel skin trimming fixture, and the barrel segment right wall panel skin trimming fixture is attached to the barrel segment fixture frame plate and is rotatably connected to the barrel segment fixture frame plate. The rotation axis is distributed and adapted to the center of the skin barrel segment, so that when the trimming fixture rotates relative to the barrel segment fixture frame plate, the other vertical plate can slide along the skin surface.

[0010] In some embodiments, the upper wall panel skin trimming fixture, the left wall panel skin trimming fixture, and the right wall panel skin trimming fixture of the barrel segment are configured as a single component.

[0011] In some embodiments, an inspection fixture is also included, which is a stop block set on the head assembly frame. Multiple stops are set on the head assembly frame corresponding to each skin. When the skin is positioned on the head assembly frame, the moving gauge can determine whether the skin size is qualified based on whether the gauge can pass between the stop block and the edge of the skin.

[0012] In this application, the inspection fixture, combined with gauge blocks, allows for the inspection of all inspection points of the skin at once, compared to the previous method of measuring the remaining length of the skin using rulers or vernier calipers. It also enables a more direct, intuitive, and rapid measurement of the distance between the skin edge and the inspection block.

[0013] In some embodiments, the stop is detachably fixed to the head assembly frame via a pin.

[0014] This invention also provides a method for using the aircraft delivery interface skin trimming fixture as described above, comprising the following:

[0015] S1. When using the barrel section upper wall panel skin trimming fixture, barrel section left wall panel skin trimming fixture, or barrel section right wall panel skin trimming fixture to trim the corresponding skin, one of the vertical plates of the trimming fixture is attached to a fixed vertical surface. After fixing the skin to the appropriate position, the trimming fixture is moved while maintaining the attachment state, so that the other vertical plate slides along the skin surface and trims along the sliding trajectory.

[0016] S2. When using the hull lower left side panel skin trimming fixture, hull lower right side panel skin trimming fixture, bottom left panel skin trimming fixture, or bottom right panel skin trimming fixture for trimming, fix the trimming fixture to the machine head assembly frame, fix the skin in the appropriate position, and then trim along the joint between the trimming fixture and the skin.

[0017] In some embodiments, the trimming fixture further includes a vertically arranged barrel segment fixture frame plate. One of the vertical plates of the barrel segment upper wall panel skin trimming fixture, the barrel segment left wall panel skin trimming fixture, and the barrel segment right wall panel skin trimming fixture is attached to the barrel segment fixture frame plate and rotatably connected to it. S1 includes the following:

[0018] S1. When using the barrel section upper wall panel skin trimming fixture, barrel section left wall panel skin trimming fixture, or barrel section right wall panel skin trimming fixture to trim the corresponding skin, rotate one of the vertical plates of the trimming fixture to connect and fit against the barrel section fixture frame clamping plate. After fixing the skin in the appropriate position, rotate the trimming fixture while maintaining the fit, so that the other vertical plate slides along the skin surface and trims along the sliding trajectory.

[0019] In some embodiments, the aircraft delivery interface skin trimming fixture includes an inspection fixture, which is a stop block mounted on the nose assembly jig. The method of using the trimming fixture also includes the following:

[0020] S3. Fix at least two stops to each skin on the machine head assembly frame. After the skin is fixed in the appropriate position, move the gauge block along the edge of the skin and judge whether the skin size is qualified based on whether the gauge block can be moved between the skin edge and the stop block.

[0021] The beneficial effects of this invention are:

[0022] By using a trimming fixture to mark and trim the skin, the accuracy of the trimming basis is improved and the error in the length of the skin after trimming is reduced. By using an inspection fixture, combined with a gauge block, compared with the previous method of measuring the remaining length of the skin using a ruler or vernier caliper, all inspection points of the skin can be inspected at one time, and the distance between the skin edge and the inspection block can be measured more directly, intuitively and quickly. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the structure of the trimming fixture for the upper wall panel of the barrel section provided by the present invention.

[0024] Figure 2 This is a schematic diagram of the structure of the trimming fixture for the left wall panel of the barrel section provided by the present invention.

[0025] Figure 3 This is a schematic diagram of the structure of the right wall panel skin trimming fixture for the barrel section provided by the present invention.

[0026] Figure 4 A schematic diagram illustrating the application scenario of the trimming fixture for the upper wall panel of the barrel section provided by the present invention.

[0027] Figure 5 A schematic diagram of the structure of the trimming tooling for the lower wall panels on both sides of the hull provided by the present invention.

[0028] Figure 6 A schematic diagram illustrating the application scenario of the trimming tool for the lower left side wall panel skin of a ship hull provided by the present invention.

[0029] Figure 7 This is a schematic diagram of the structure of the trimming fixture for the left and right sidewall panels of the ship's bottom, provided by the present invention.

[0030] Figure 8 This is a schematic diagram illustrating the application scenario of the ship bottom left wall panel skin trimming fixture provided by the present invention.

[0031] Figure 9 A schematic diagram of the inspection tooling structure provided by the present invention;

[0032] Figure 10 This is a structural schematic diagram of the inspection tooling positioning method provided by the present invention.

[0033] The diagram is labeled as follows: 0 - Assembly jig for the engine head; 1 - Fixture for trimming the upper wall panel skin of the barrel section; 10 - Fixture for inspecting the upper wall panel skin of the barrel section; 2 - Fixture for trimming the left wall panel skin of the barrel section; 20 - Fixture for inspecting the left wall panel skin of the barrel section; 3 - Fixture for trimming the right wall panel skin of the barrel section; 30 - Fixture for inspecting the right wall panel skin of the barrel section; 4 - Fixture for trimming the lower wall panel skin of the port side of the hull; 40 - Fixture for inspecting the lower wall panel skin of the port side of the hull. 5-Host starboard lower bulkhead skin trimming fixture; 50-Host starboard lower bulkhead skin inspection fixture; 6-Board left bulkhead skin trimming fixture; 60-Board left bulkhead skin inspection fixture; 7-Board right bulkhead skin trimming fixture; 70-Board right bulkhead skin inspection fixture; 8-Skin; 100-Stop block; 101-Sliding rod; 102-Pin; 123-Barrel section tooling frame clamping plate. Detailed Implementation

[0034] The invention will be further described below with reference to the accompanying drawings.

[0035] To make the objectives, technical solutions, and advantages of this invention clearer, the 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 merely illustrative and not intended to limit the invention.

[0036] like Figures 1-10 As shown, the present invention provides a tooling for trimming the skin of an aircraft delivery interface and its usage method.

[0037] Aircraft delivery interface skin trimming fixture. The trimming fixture provided by this invention is mainly divided into two categories, which are applied to barrel section wall panels and ship section wall panels respectively.

[0038] Specifically, the trimming fixtures include trimming fixture 1 for the upper wall panel of the barrel section, trimming fixture 2 for the left wall panel of the barrel section, trimming fixture 3 for the right wall panel of the barrel section, trimming fixture 4 for the lower wall panel of the left side of the hull, trimming fixture 5 for the lower wall panel of the right side of the hull, trimming fixture 6 for the left wall panel of the bottom of the hull, and trimming fixture 7 for the right wall panel of the bottom of the hull. Among them, trimming fixtures 1, 2, and 3 for the upper wall panel of the barrel section are used for the barrel section wall panels, while trimming fixtures 4, 5, 6, and 7 for the lower wall panel of the left side of the hull, 6, and 7 for the right wall panel of the bottom of the hull are used for the hull section wall panels.

[0039] like Figures 1-3 As shown, the barrel section upper wall panel skin trimming fixture 1, the barrel section left wall panel skin trimming fixture 2, and the barrel section right wall panel skin trimming fixture 3 all include two vertical plates arranged opposite each other, and the two vertical plates are fixedly connected. The three fixtures are used in the same way. Figure 4 The application scenario of the barrel section upper wall panel skin trimming tool 1 is used as an example for demonstration.

[0040] like Figure 5 and Figure 7 As shown, the lower left side panel skin trimming fixture 4, the lower right side panel skin trimming fixture 5, the left bottom panel skin trimming fixture 6, and the right bottom panel skin trimming fixture 7 all have one side that is consistent with the shape of the corresponding skin 8, and can be detachably connected to the engine head assembly frame 0. Figure 6 and Figure 8 The application scenarios of tool 4 for trimming the lower left side panel of the hull and tool 6 for trimming the left side panel of the bottom of the hull are used as examples to demonstrate the application scenarios.

[0041] Reference Figure 6 As shown, after the lower left side panel skin 8 of the hull is positioned on the engine head assembly frame 0, the lower left side panel skin trimming fixture 4 of the hull is fixed on the engine head assembly frame 0. The location where the trimming fixture and the skin 8 are in contact is the theoretical position of the skin 8 length. A line is drawn along the contact area between the fixture and the skin 8, and then the excess material is trimmed manually.

[0042] Reference Figure 8 As shown, after the bottom left wall panel skin 8 is positioned on the engine head assembly frame 0, the bottom left wall panel skin trimming fixture 6 is fixed on the engine head assembly frame 0. The location where the trimming fixture and the skin 8 are in contact is the theoretical position of the skin 8 length. A line is drawn along the contact area between the fixture and the skin 8, and then the excess material is trimmed manually.

[0043] In practice, the position of the existing engine head assembly frame 0 remains unchanged. Through digital model calculation, the corresponding trimming fixture length is designed so that after the trimming fixture is fixed on the engine head assembly frame 0, the contact surface between the trimming fixture corresponding to the ship section wall panel and the skin 8 is the theoretical position of the remaining length of the skin 8. Lines are then drawn at this position to assist in the trimming of the skin 8.

[0044] In this application, the skin 8 is trimmed by drawing lines using a trimming fixture, which improves the accuracy of the trimming basis and reduces the error in the length of the skin 8 after trimming.

[0045] In practice, one of the vertical plates of the tooling used for trimming the wall panel skin 8 of the barrel section should be attached to a vertical surface. Taking the wall as an example, since the trimming tooling contains two vertical plates that are set opposite to each other, the cutting surface of the edge of the skin 8 can be trimmed at a fixed distance from the wall.

[0046] In this embodiment, the tooling frame 123 is also included. The tooling frame 123 is vertically arranged. One of the vertical plates of the barrel segment upper wall panel skin trimming tool 1, the barrel segment left wall panel skin trimming tool 2, and the barrel segment right wall panel skin trimming tool 3 is attached to the tooling frame 123. When the tooling frame 123 slides, 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.

[0047] A vertically oriented barrel segment tooling bracket 123 is added to provide the vertical surface to be fitted in the barrel segment wall panel trimming tooling practice. In practice, the barrel segment tooling bracket 123 can also be detachably fixed on the original machine head assembly bracket 0, so as to further facilitate the implementation by utilizing the positioning relationship between the original skin 8 and the machine head assembly bracket 0.

[0048] In some other embodiments, one of the vertical plates of the barrel segment upper wall panel skin trimming fixture 1, the barrel segment left wall panel skin trimming fixture 2, and the barrel segment right wall panel skin trimming fixture 3 is attached to the barrel segment fixture frame clamping plate 123 and is rotatably connected to the barrel segment fixture frame clamping plate 123. The rotation axis is distributed and adapted to the center of the barrel segment skin 8, so that when the trimming fixture rotates relative to the barrel segment fixture frame clamping plate 123, the other vertical plate can slide along the surface of the skin 8.

[0049] When the end face of the barrel section wall panel skin 8 is circular, one of the vertical plates of the trimming fixture described above can be rotated to connect the barrel section fixture frame clamping plate 123. This facilitates the fitting and relative rotation of the oblique cutting fixture and the barrel section fixture frame clamping plate 123.

[0050] As an extension, when the end face of the barrel section wall panel skin 8 is not circular, this can also be implemented as described above, with one of the vertical plates rotating and connected to the barrel section tooling frame clamping plate 123. In order to achieve the adhering and marking of the other vertical plate to 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 through an elastic unit. When the trimming tooling adhering to the barrel section tooling frame clamping plate 123 rotates, the other vertical plate always adheres to the surface of the skin 8 under the action of elastic force, thereby achieving the marking and trimming when the end face of the barrel section wall panel skin 8 is not circular.

[0051] In some embodiments, based on the consistent working principle of the barrel segment trimming fixtures, the barrel segment upper wall panel skin trimming fixture 1, the barrel segment left wall panel skin trimming fixture 2, and the barrel segment right wall panel skin trimming fixture 3 can be configured as a single component.

[0052] Reference Figure 9 As shown, this embodiment also includes an inspection fixture, which is a stop block 100 set on the machine head assembly frame 0. Each skin 8 is provided with multiple stop blocks 100 on the machine head assembly frame 0. When the skin 8 is positioned on the machine head assembly frame 0, the moving gauge can determine whether the size of the skin 8 is qualified based on whether the gauge can pass between the stop block 100 and the edge of the skin 8.

[0053] In this embodiment, for each skin panel 8, the inspection fixtures include: upper wall panel skin inspection fixture 10, left wall panel skin inspection fixture 20, right wall panel skin inspection fixture 30, lower left side wall panel skin inspection fixture 40, lower right side wall panel skin inspection fixture 50, left bottom wall panel skin inspection fixture 60, and right bottom wall panel skin inspection fixture 70. In this embodiment, each inspection fixture is equipped with three stops 100, meaning each skin panel 8 is equipped with three stops 100.

[0054] In this application, by using inspection fixtures and gauge blocks, compared with the previous method of measuring the remaining length of the skin 8 using rulers or vernier calipers, all inspection points of the skin 8 can be inspected at once, and the distance between the edge of the skin 8 and the stop block 100 can be measured more directly, intuitively and quickly.

[0055] In this embodiment, the stop block 100 is detachably and fixedly connected to the machine head assembly frame 0 by means of a pin 102.

[0056] exist Figure 10 The diagram demonstrates two methods in which the stop block 100 can be detachably connected to the machine head assembly frame 0 via a pin 102: either by pushing the stop block 100 with the sliding rod 101 and inserting it for limiting, or by directly placing it in the inspection position and inserting the pin 102 for connection and fixation. The implementation process is simple, quick, and easy to operate. When not in use, the stop block 100 can be removed, thereby freeing up operating space.

[0057] In this embodiment, the aforementioned ship section trimming fixture is also detachably connected to the engine head assembly frame 0 via pin 102 to facilitate installation and disassembly during implementation and improve work efficiency.

[0058] The present invention also provides a method for using the aircraft delivery interface skin trimming tool as described above, including the following:

[0059] S1. When using the barrel section upper wall panel skin trimming fixture 1, barrel section left wall panel skin trimming fixture 2, or barrel section right wall panel skin trimming fixture 3 to trim the corresponding skin 8, one of the vertical plates of the trimming fixture is attached to a fixed vertical surface. After fixing the skin 8 to a suitable position, the trimming fixture is moved while maintaining the attachment state, so that the other vertical plate slides along the surface of the skin 8 and trims along the sliding trajectory.

[0060] Obviously, the appropriate position here is based on the target length of the skin 8, so that when the skin 8 is placed horizontally, it is a certain distance away from the fixed vertical surface.

[0061] S2. When using the following tools for trimming: the lower left side hull panel skin trimming tool 4, the lower right side hull panel skin trimming tool 5, the left bottom hull panel skin trimming tool 6, or the right bottom hull panel skin trimming tool 7, fix the trimming tool to the machine head assembly frame 0, fix the skin 8 in the appropriate position, and then trim along the joint between the trimming tool and the skin 8.

[0062] Obviously, the appropriate position here is based on the target length of the skin 8, and the skin 8 is placed so that its edge and the edge of the trimming fixture are the line trimming position.

[0063] It is worth noting that there are no strict restrictions on the steps involved in using this method.

[0064] Specifically, in this embodiment, the trimming fixture includes a vertically arranged barrel segment fixture frame plate 123. One of the vertical plates of the barrel segment upper wall panel skin trimming fixture 1, the barrel segment left wall panel skin trimming fixture 2, and the barrel segment right wall panel skin trimming fixture 3 are attached to the barrel segment fixture frame plate 123 and are rotatably connected to the barrel segment fixture frame plate 123. S1 includes the following content.

[0065] S1. When using the barrel section upper wall panel skin trimming fixture 1, barrel section left wall panel skin trimming fixture 2, or barrel section right wall panel skin trimming fixture 3 to trim the corresponding skin 8, one of the vertical plates of the trimming fixture is rotated and connected to fit the barrel section fixture frame clamping plate 123. After fixing the skin 8 in a suitable position, the trimming fixture is rotated while maintaining the fit, so that the other vertical plate slides along the surface of the skin 8 and trims along the sliding trajectory.

[0066] Furthermore, the aircraft delivery interface skin trimming fixture includes an inspection fixture, which is a stop block 100 set on the nose assembly frame 0. The method of using the trimming fixture also includes the following.

[0067] S3. On the machine head assembly frame 0, at least two stops 100 are fixed for each skin 8. After the skin 8 is fixed in the appropriate position, the gauge block is moved along the edge of the skin 8. The size of the skin 8 is judged based on whether the gauge block can be moved between the edge of the skin 8 and the stop block 100.

[0068] Obviously, the appropriate position here is based on the positioning between the skin 8 and the head assembly frame 0. Combined with the position of the stop block 100, the distance between the edge of the skin 8 and the stop block 100 can be measured by the gauge block to determine whether the dimensions of the skin 8 are qualified. The positioning between the skin 8 and the head assembly frame 0 has been achieved by existing technology, so it is only necessary to set the position of the stop block 100 accordingly.

[0069] The above description is merely 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 within the protection scope of the present invention.

Claims

1. An aircraft delivery interface skin trim tooling characterized by: The trimming fixtures include the upper wall panel trimming fixture (1), the left wall panel trimming fixture (2), the right wall panel trimming fixture (3), the lower left wall panel trimming fixture (4), the lower right wall panel trimming fixture (5), the left bottom wall panel trimming fixture (6), and the right bottom wall panel trimming fixture (7). The barrel section upper wall panel skin trimming fixture (1), the barrel section left wall panel skin trimming fixture (2) and the barrel section right wall panel skin trimming fixture (3) all contain two vertical plates arranged opposite to each other, and the two vertical plates are fixedly connected. The lower left side panel skin trimming fixture (4), the lower right side panel skin trimming fixture (5), the left bottom panel skin trimming fixture (6), and the right bottom panel skin trimming fixture (7) all have one side that is consistent with the shape of the corresponding skin and can be detachably connected to the engine head assembly frame (0). It also includes a barrel segment tooling frame plate (123). The barrel segment tooling frame plate (123) is set vertically. One of the vertical plates of the barrel segment upper wall panel skin trimming tool (1), the barrel segment left wall panel skin trimming tool (2), and the barrel segment right wall panel skin trimming tool (3) is attached to the barrel segment tooling frame plate (123) and is rotatably connected to the barrel segment tooling frame plate (123). The rotation axis distribution is adapted to the center of the skin (8) barrel segment, so that when the trimming tool rotates relative to the barrel segment tooling frame plate (123), the other vertical plate can slide along the surface of the skin (8).

2. The aircraft delivery interface skin trim kit of Claim 1, further characterized by: The upper wall panel trimming fixture (1), the left wall panel trimming fixture (2), and the right wall panel trimming fixture (3) of the barrel section are configured as one component.

3. An aircraft delivery interface skin trim tooling as in any of claims 1-2, further characterized by: It also includes inspection fixtures, which are blocks (100) set on the head assembly frame (0). Each skin (8) has multiple blocks (100) set on the head assembly frame (0). When the skin (8) is positioned on the head assembly frame (0), the moving gauge can determine whether the size of the skin (8) is qualified based on whether the gauge can pass between the block (100) and the edge of the skin (8).

4. The aircraft delivery interface skin trim kit of Claim 3, wherein: The stop block (100) is detachably and fixedly connected to the head assembly frame (0) by a pin (102).

5. Method of using an aircraft delivery interface skin trimming tooling, characterized in that: The aircraft delivery interface skin trimming fixture as described in claim 1 includes the following: S1. When using the barrel section upper wall panel skin trimming tool (1), barrel section left wall panel skin trimming tool (2) or barrel section right wall panel skin trimming tool (3) to trim the corresponding skin (8), one of the vertical plates of the trimming tool is attached to a fixed vertical surface. After fixing the skin (8) to a suitable position, the trimming tool is moved while maintaining the attachment state, so that the other vertical plate slides along the surface of the skin (8) and trims along the sliding trajectory. S2. When using the lower left side panel skin trimming tool (4), the lower right side 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 machine head assembly frame (0), fix the skin (8) in the appropriate position, and then trim along the joint between the trimming tool and the skin (8).

6. The method of using an aircraft delivery interface skin trim kit of claim 5, wherein: The trimming fixture also includes a vertically arranged barrel segment fixture frame plate (123). One of the vertical plates of the barrel segment upper wall panel skin trimming fixture (1), the barrel segment left wall panel skin trimming fixture (2), and the barrel segment right wall panel skin trimming fixture (3) is attached to the barrel segment fixture frame plate (123) and is rotatably connected to the barrel segment fixture frame plate (123). S1 includes the following: S1. When using the barrel section upper wall panel skin trimming tool (1), barrel section left wall panel skin trimming tool (2) or barrel section right wall panel skin trimming tool (3) to trim the corresponding skin (8), one of the vertical plates of the trimming tool is rotated and connected to fit the barrel section tool frame clamping plate (123). After fixing the skin (8) to a suitable position, the trimming tool is rotated while maintaining the fit, so that the other vertical plate slides along the surface of the skin (8) and trims along the sliding trajectory.

7. The method of using the aircraft delivery interface skin trimming fixture as described in claim 5, characterized in that: aircraft delivery... The interface skin trimming fixture includes an inspection fixture, which is a stop (100) set on the machine head assembly frame (0). The usage method of the trimming fixture also includes the following: S3. Fix at least two stops (100) on the machine head assembly frame (0) for each skin (8). After the skin (8) is fixed in the appropriate position, move the gauge along the edge of the skin (8) and judge whether the size of the skin (8) is qualified based on whether the gauge can be moved between the edge of the skin (8) and the stop (100).

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