Aircraft air inlet skin replacing device and replacing method

Abstract

The aircraft air inlet duct skin replacing device is configured to be connected with an aircraft air inlet duct, the aircraft air inlet duct comprises a plurality of partition frames arranged at intervals, an outer skin and an inner skin, the outer skin is arranged on the outer side walls of the partition frames and connected with the partition frames, and the inner skin is arranged on the inner side walls of the partition frames and connected with the partition frames. The aircraft air inlet skin replacing device comprises two abutting parts and an adjusting assembly, the two abutting parts are arranged in a spaced mode, arranged between the two abutting parts and connected with the two abutting parts, and the adjusting assembly can adjust the distance between the two abutting parts and adjust the distance between the two abutting parts. And the pushing part is used for pushing the two abutting parts to abut against two opposite inner walls of one bulkhead or two adjacent bulkheads respectively. The method can effectively solve the problems that the position of the bulkhead possibly changes after the old skin is removed, so that the new skin is not attached to the outer side framework during assembly, and the skin cracks and rivets are broken.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft maintenance, and particularly relates to an aircraft intake duct skin replacement device and a replacement method. Background Art

[0002] Generally, an aircraft intake duct is formed into an integral sealed structure by arranging frames and skins. For example, in the Chinese utility model patent with the publication number: CN221699016U, titled: An intake duct lip structure with multiple functions, wherein the skin and the baffle are butt-jointed and combined to form a closed air flow channel at the front end of the intake duct lip, and an absorbing core material is arranged in the air flow channel; an air intake pipe and an exhaust pipe are also arranged on the baffle to enable the hot air to flow in the designed direction; the air intake and exhaust pipe lines are integrated into one body, having an efficient anti-icing and de-icing function while also taking into account good absorbing performance.

[0003] During flight, the inner skin in the front section of the intake duct is prone to cracking due to problems such as being impacted by high-speed air flow, repeatedly adjusted by the regulating plate, insufficient structural strength of the intake duct during the manufacturing process, and assembly stress caused by the non-fitting of the inner skin and the frame. When repairing the aircraft, it is necessary to replace the inner skin of the intake duct with a thicker one. However, when replacing, the skin in the front section of the intake duct is a multi-curved skin, and the position of the frame may change after the old skin is removed, making it easy to generate assembly stress due to non-fitting with the outer skeleton during assembly. Moreover, the aerodynamic load in the front section of the intake duct is complex, which will further aggravate the influence of the assembly stress, resulting in problems such as skin cracks and rivet fractures.

[0004] Therefore, there is an urgent need for an aircraft intake duct skin replacement device and a replacement method to solve the problem in the prior art that the position of the frame may change after the old skin is removed, resulting in non-fitting of the new skin and the outer skeleton during assembly, thereby causing skin cracks and rivet fractures. Summary of the Invention

[0005] The purpose of the present invention is to overcome the above technical deficiencies and propose an aircraft intake duct skin replacement device and a replacement method to solve the technical problem in the prior art that the position of the frame may change after the old skin is removed, resulting in non-fitting of the new skin and the outer skeleton during assembly, thereby causing skin cracks and rivet fractures.

[0006] To achieve the above technical purpose, the present invention adopts the following technical solutions: In a first aspect, the present invention provides an aircraft intake duct skin replacement device configured to be connected to an aircraft intake duct. The aircraft intake duct includes: a plurality of frames arranged at intervals, an outer skin, and an inner skin. The outer skin is arranged on the outer side wall of the frames and is connected to all the frames, and the inner skin is arranged on the inner side wall of the frames and is connected to all the frames. The device includes: Two abutting parts, the two abutting parts are arranged at intervals; and An adjusting assembly, arranged between the two abutting parts and connected to both of the two abutting parts, the adjusting assembly can adjust the distance between the two abutting parts, and is used to push the two abutting parts to respectively abut against two opposite inner walls of a septum or two adjacent septums.

[0007] In some embodiments, the abutting part is an elastic structure.

[0008] In some embodiments, the outer diameters of the two abutting parts gradually increase in the direction away from each other.

[0009] In some embodiments, the adjusting assembly includes at least one linear driving part, the linear driving part has a fixed end and a telescopic end, and the fixed end of the linear driving part is connected to one abutting part, and the telescopic end is connected to the other abutting part, and is used to drive the two abutting parts to approach or move away from each other.

[0010] In some embodiments, the number of the linear driving parts in the adjusting assembly is two, the adjusting assembly further includes a connecting body, the connecting body is arranged between the two abutting parts, the two linear driving parts are respectively arranged at both ends of the connecting body, and the fixed ends of the two linear driving parts are both connected to the connecting body, and the telescopic ends are respectively connected to the two abutting parts, and are used to drive the two abutting parts to slide relative to the connecting body respectively.

[0011] In some embodiments, the connecting body is cylindrical and has a through hole along its axis, the adjusting assembly further includes two sliding rods, one end of the sliding rod is connected to the abutting part, and the other end is slidably inserted into the through hole.

[0012] In some embodiments, the through hole has a first segment and a second segment with equal depths, the circumferential inner wall of the first segment is provided with a positive internal thread, the circumferential inner wall of the second segment is provided with a reverse internal thread, the circumferential outer walls of the two sliding rods are respectively provided with a positive external thread and a reverse external thread that can cooperate with the positive internal thread and the reverse internal thread, and the rotation of the connecting body around its own axis can drive the two sliding rods to approach or move away from each other along the axial direction of the connecting body.

[0013] In some embodiments, the adjusting assembly further includes two locking parts, the locking parts are slidably connected to the sliding rods and can abut against the connecting body, and are used to limit the sliding of the sliding rods relative to the connecting body.

[0014] In some embodiments, the two locking parts are respectively slidably sleeved on the two sliding rods and are respectively threadedly connected to the two sliding rods.

[0015] In a second aspect, the present invention further provides a method for replacing the skin of an aircraft inlet duct. By using the aircraft inlet duct skin replacement device as described above, the specific steps are as follows: Disassemble the outer skin, remove the old outer skin, and inspect the holes of the outer skin and the frames; Fix the frames, and use the aircraft inlet duct skin replacement device to fix the distance between two adjacent frames; Disassemble the inner skin, remove the old inner skin, and inspect the holes of the inner skin and the frames; Fix the frames, and use the aircraft inlet duct skin replacement device to fix the distance between two opposite inner walls of the same frame; Position and drill the new inner skin. Use the holes on the frames to position the new inner skin, and use the first drilling die to ream the holes of the new inner skin; Install the new inner skin and rivet the new inner skin; Position and drill the new outer skin. Use the holes on the frames to position the new outer skin, and use the second drilling die to ream the holes of the new outer skin; Install the new outer skin and rivet the new outer skin.

[0016] Compared with the prior art, the beneficial effects of the aircraft inlet duct skin replacement device and the replacement method provided by the present invention include: the two abutting parts are arranged at intervals, the adjusting component is arranged between the two abutting parts and is connected to both of the two abutting parts, and the adjusting component can drive the two abutting parts to slide close to or away from each other, so that the two abutting parts respectively abut against two opposite inner walls of the frame or two adjacent frames. Compared with the prior art, by arranging the adjusting component and the two abutting parts on the frames of the aircraft inlet duct, and using the adjusting component to drive the two abutting parts to respectively abut against two opposite inner walls of the frame or two adjacent frames to fix the two adjacent frames, it can prevent the positions of the frames from changing after the old skin is removed, and can solve the technical problem that the new skin may not fit the outer skeleton during assembly due to the possible change in the position of the frame after the old skin is removed, resulting in skin cracks and rivet fractures. Description of the Drawings

[0017] Figure 1 is a three-dimensional view of an aircraft inlet duct provided by an embodiment of the present invention; Figure 2 is a three-dimensional view of another perspective of an aircraft inlet duct provided by an embodiment of the present invention; Figure 3 is a three-dimensional view of an aircraft inlet duct skin replacement device provided by an embodiment of the present invention; Figure 4 is a schematic diagram of an aircraft inlet duct skin replacement device provided by an embodiment of the present invention connected to two adjacent frames; Figure 5 It is a schematic diagram of a skin replacement device for an aircraft inlet connected to opposite side walls of the same frame; Figure 6 It is a schematic diagram of another perspective of a skin replacement device for an aircraft inlet connected to opposite side walls of the same frame; Figure 7 It is a cross-sectional view of a first drilling die provided in an embodiment of the present invention connected to a frame; Figure 8 It is a cross-sectional view of a second drilling die provided in an embodiment of the present invention connected to a frame.

[0018] Explanation of reference numerals: Aircraft inlet 100; Frame 110; Outer skin 120; Inner skin 130; Contact portion 200; Adjusting assembly 300, Linear driving portion 310; Connecting body 320; Sliding rod 330; Locking member 340; First drilling die 400; Second drilling die 500. Detailed implementation manners

[0019] In order to make the objectives, technical solutions and advantages of the present invention clearer, 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 used to limit the present invention.

[0020] In order to solve the technical problem that the position of the frame 110 may change after the old skin is removed, resulting in the new skin not fitting the outer skeleton during assembly, thereby causing skin cracks and rivet fractures, the present invention provides a skin replacement device and a replacement method for an aircraft inlet 100, which can realize setting an adjusting assembly 300 and two contact portions 200 on the frame 110 of the aircraft inlet 100, and using the adjusting assembly 300 to drive the two contact portions 200 to respectively contact the two opposite inner walls of the frame 110 or two adjacent frames 110, so as to fix the two adjacent frames 110 and prevent the position of the frame 110 from changing after the old skin is removed.

[0021] Please refer to Figures 1 to 6 , Figures 1 to 3Schematic structural diagram of a skin replacement device and a replacement method for an aircraft inlet 100 in an embodiment of the present invention. The aircraft inlet 100 skin replacement device is configured to be connected to the aircraft inlet 100. The aircraft inlet 100 includes: a plurality of spaced-apart frames 110, an outer skin 120, and an inner skin 130. The outer skin 120 is disposed on the outer sidewall of the frames 110 and is connected to all the plurality of frames 110. The inner skin 130 is disposed on the inner sidewall of the frames 110 and is connected to all the plurality of frames 110. The aircraft inlet 100 skin replacement device includes: two abutting portions 200 and an adjustment assembly 300. The two abutting portions 200 are spaced apart from each other. The adjustment assembly 300 adjusts the distance between the two abutting portions 200 and is connected to both the two abutting portions 200. The adjustment assembly 300 can drive the two abutting portions 200 to slide closer to or away from each other, and is used to push the two abutting portions 200 to respectively abut against two opposite inner walls of a frame 110 or two adjacent frames 110.

[0022] In this device, compared with the prior art, by providing an adjustment assembly 300 and two abutting portions 200 on the frame 110 of the aircraft inlet 100, the adjustment assembly 300 is used to drive the two abutting portions 200 to respectively abut against two opposite inner walls of the frame 110 or two adjacent frames 110, so as to fix two adjacent frames 110 and prevent the position of the frame 110 from changing due to the removal of the old skin, and it can solve the technical problem that the new skin may not fit the outer skeleton during assembly due to the possible change in the position of the frame 110 after the old skin is removed, resulting in skin cracks and rivet fractures.

[0023] Further, the aircraft inlet 100 is composed of a plurality of spaced-apart frames 110, an outer skin 120, and an inner skin 130, and the frames 110 are elliptical. In order to prevent the position of the frames 110 from changing, the aircraft inlet 100 skin replacement device is provided between two adjacent frames 110, and the aircraft inlet 100 skin replacement device is provided between two opposite inner walls of the same frame 110, which can effectively fix the position of the frame 110 and prevent it from deforming or displacing.

[0024] In one embodiment, as Figures 4 to 6 shown, the abutting portion 200 is an elastic structure.

[0025] The abutting portion 200 is a structure with elasticity, which can fit the surface of the frame 110, and at the same time can avoid damaging the surface of the frame 110 caused by the abutting portion 200, and can improve reliability and safety.

[0026] Further, here the abutting portion 200 is rubber or plastic that is common in the market and easy to purchase, which is a conventional setting well-known to those skilled in the art, and will not be elaborated here too much.

[0027] In one embodiment, the cross-sectional area of the abutting portion 200 gradually increases in a direction away from the adjusting assembly 300.

[0028] By providing a structure with a gradually changing cross-sectional area, the stability of the device can be improved, and a stable supporting force can be provided for the frame 110.

[0029] In one embodiment, please refer to Figure 3 , the adjusting assembly 300 includes at least one linear driving portion 310. The linear driving portion 310 has a fixed end and a telescopic end, and the fixed end of the linear driving portion 310 is connected to one abutting portion 200, and the telescopic end is connected to another abutting portion 200, for driving the two abutting portions 200 to approach or move away from each other.

[0030] Through the movement of the telescopic end of the linear driving portion 310 relative to its fixed end, relative sliding between the two abutting portions 200 can be achieved.

[0031] In one embodiment, please refer to Figure 3 , the number of linear driving portions 310 in the adjusting assembly 300 is two. The adjusting assembly 300 further includes a connecting body 320. The connecting body 320 is disposed between the two abutting portions 200. The two linear driving portions 310 are respectively disposed at both ends of the connecting body 320, and the fixed ends of the two linear driving portions 310 are both connected to the connecting body 320, and the telescopic ends are respectively connected to the two abutting portions 200, for respectively driving the two abutting portions 200 to slide relative to the connecting body 320.

[0032] The connecting body 320 is disposed in the middle of the two abutting portions 200. By respectively connecting the two linear driving portions 310 to the two abutting portions 200, the stability and adjustability of the device operation can be improved, and it is convenient for the user to reasonably select the construction according to the on-site construction conditions.

[0033] Further, the linear driving portion 310 here is a push rod motor, a hydraulic cylinder and a cylinder that are common and easy to purchase in the market, which are conventional settings well known to those skilled in the art, and will not be elaborated here too much.

[0034] In one embodiment, please refer to Figure 3 , the connecting body 320 is cylindrical and has a through hole along its axis. The adjusting assembly 300 further includes two sliding rods 330. One end of the sliding rod 330 is connected to the abutting portion 200, and the other end is slidably inserted into the through hole.

[0035] The cooperation between the through hole and the sliding rod 330 is used to realize the sliding connection between the abutting portion 200 and the connecting body 320, and the overall stability of the device can be improved.

[0036] In one embodiment, please refer toFigure 3 The through-hole has a first segment and a second segment with equal depths. The circumferential inner wall of the first segment is provided with a positive internal thread, and the circumferential inner wall of the second segment is provided with a reverse internal thread. The circumferential outer walls of the two sliding rods 330 are respectively provided with a positive external thread and a reverse external thread that can cooperate with the positive internal thread and the reverse internal thread, and the rotation of the connecting body 320 around its own axis can drive the two sliding rods 330 to approach or move away from each other along the axis of the connecting body 320.

[0037] Specifically, by respectively arranging two-way threads with the same depth at both ends of the through-hole, and using the rotation of the screw rod relative to the two-way threads, the two sliding rods 330 can slide relative to the connecting body 320 in opposite directions respectively.

[0038] Furthermore, here the connecting body 320 is a two-way thread sleeve that is common and easy to purchase in the market. The two sliding rods 330 are respectively a positive screw rod and a reverse screw rod that cooperate with the two-way thread sleeve. Here, the two-way thread sleeve, the positive screw rod, and the reverse screw rod are all conventional settings well-known to those skilled in the art, and will not be elaborated here too much.

[0039] In one embodiment, please refer to Figure 3 The adjusting assembly 300 further includes two locking members 340. The locking members 340 are slidably connected to the sliding rods 330 and can abut against the connecting body 320 to limit the sliding of the sliding rods 330 relative to the connecting body 320.

[0040] The locking members 340 are connected to the sliding rods 330 and can be detachably connected to the connecting body 320, so that the sliding members cannot continue to slide relative to the connecting body 320, which can improve the structural stability, thereby effectively keeping the distance between the frames 110 from deforming or displacing.

[0041] In one embodiment, please refer to Figure 3 The two locking members 340 are respectively slidably sleeved on the two sliding rods 330 and are respectively threadedly connected to the two sliding rods 330.

[0042] Making the detachable connection between the locking members 340 and the sliding rods by means of threaded connection is not only simple in structure but also convenient in operation.

[0043] In addition, in some embodiments, an elastic sheet or a gasket is further provided at the abutting portion between the locking member 340 and the connecting body 320, which can increase the locking effect and will not be elaborated here too much.

[0044] The present invention also provides a method for replacing the skin of the aircraft inlet duct 100. By using the above-mentioned device for replacing the skin of the aircraft inlet duct 100, the specific steps are as follows: Disassemble the outer skin 120, remove the outer skin 120 from multiple frames 110, and perform non-destructive testing on the holes of the outer skin 120 and the frames 110; Fix the frames 110, install the skin replacement device for the aircraft inlet duct 100 between two adjacent frames 110 to fix the distance between two adjacent frames 110; Disassemble the inner skin 130, remove the inner skin 130 from multiple frames 110, and perform non-destructive testing on the holes of the inner skin 130 and the frames 110; Fix the frames 110, install the skin replacement device for the aircraft inlet duct 100 between two opposite inner walls of each frame 110 to fix the distance between two opposite inner walls of the frame 110; Locate the new inner skin 130, and locate the new inner skin 130 by using the holes on the frames 110; Drill holes in the new inner skin 130, and ream the holes of the new inner skin 130 by using the first drilling die 400; Install the new inner skin 130, and rivet the inner skin 130 of the inlet duct; Locate the new inner skin 130, and locate the new outer skin 120 by using the holes on the frames 110; Drill holes in the new inner skin 130, and ream the holes of the new inner skin 130 by using the second drilling die 500; Install the new outer skin 120, and rivet the inner skin 130 of the inlet duct.

[0045] Specifically, as Figure 7 、 Figure 8 shown, when the user disassembles the old skin, first disassemble the old outer skin 120 from multiple frames 110, and conduct a magnifying glass inspection on the hole edges of the outer skin 120 and the frame structure, and perform non-destructive testing on the suspected crack locations; then set and install the skin replacement device for the aircraft inlet duct 100 between each adjacent pair of frames 110, so that the two abutting parts 200 respectively abut against two adjacent frames 110 to fix the distance between two adjacent frames 110; then disassemble the old inner skin 130 from multiple frames 110, and conduct a magnifying glass inspection on the hole edges of the inner skin 130 and the frame structure, and perform non-destructive testing on the suspected crack locations; finally, set and install the skin replacement device for the aircraft inlet duct 100 between two opposite side walls of each frame 110, so that the two abutting parts 200 respectively abut against two opposite side walls of the same frame 110 to fix the distance between two opposite side walls of the same frame 110.

[0046] Further, when installing the new inner skin 130, it is first necessary to position and drill holes in the new inner skin 130. The user uses the first drilling die 400 to position the holes on the new inner skin 130. The first drilling die 400 is a stepped cylindrical structure with a small-diameter section and a large-diameter section, and the first drilling die 400 is also provided with a through hole. The user first connects the small-diameter section of the first drilling die 400 to the frame 110, then lays the new inner skin 130 on the outer walls of each frame 110, and uses the skin replacement device of the aircraft inlet duct 100 to press the new inner skin 130 tightly against the inner wall of the frame 110. Since the holes on the frame 110 penetrate the frame 110, the user can use a drill bit to pass through the through hole of the first drilling die 400 from the outer wall of the frame 110 to position the holes on the new inner skin 130; then the user drills the new inner skin 130 by reaming and drilling respectively. Specifically, the first drilling die 400 is composed of multiple drilling dies with gradually increasing hole diameters. For example, if the target hole diameter is 8 mm, first use a drill bit with a diameter of 2 mm to ream and drill the positioning holes, and then use drill bits with diameters of 4 mm, 6 mm, and 8 mm respectively to ream and drill the positioning protrusions. Finally, rivet the new inner skin 130 to multiple frames 110.

[0047] Further, generally, the outer skin 120 does not need to be replaced. If the outer skin 120 needs to be replaced after inspection with a magnifying glass, when the user installs the new outer skin 120, it is first necessary to position and drill holes in the new inner skin 130. The user first uses a positioning tool to position the holes on the new inner skin 130. The positioning tool has a threaded section and a tapered section. The user threads the threaded section of the positioning tool onto the frame 110. When covering the new outer skin 120 on the inner wall of the frame 110, the tapered section of the positioning tool can form a positioning protrusion on the new outer skin 120. Then the user uses the second drilling die 500 to ream and drill the positioning protrusion in a step-by-step reaming manner. The second drilling die 500 is composed of multiple drilling dies with gradually increasing hole diameters. For example, if the target hole diameter is 8 mm, first use a drill bit with a diameter of 2 mm to ream and drill the positioning protrusion, and then use drill bits with diameters of 4 mm, 6 mm, and 8 mm respectively to ream and drill the positioning protrusion. Finally, rivet the new outer skin 120 to multiple frames 110.

[0048] To better understand the present invention, the following Figures 1 to 8 will describe the technical solution of the present invention in detail: The two abutting parts 200 are arranged at intervals from each other. The adjusting component 300 is arranged between the two abutting parts 200 and is connected to both of the two abutting parts 200. Moreover, the adjusting component 300 can drive the two abutting parts 200 to slide closer to or away from each other so that the two abutting parts 200 respectively abut against two opposite inner walls of the frame 110 or two adjacent frames 110. Compared with the prior art, by arranging the adjusting component 300 and the two abutting parts 200 on the frame 110 of the aircraft inlet duct 100, the adjusting component 300 is utilized to drive the two abutting parts 200 to respectively abut against two opposite inner walls of the frame 110 or two adjacent frames 110 to fix the two adjacent frames 110 and prevent the position of the frame 110 from changing after the old skin is removed.

[0049] For the specific working process of the present invention, when a user disassembles the old skin, first, the old outer skin 120 is detached from a plurality of frames 110, and the hole edges of the outer skin 120 and the skeleton structure are inspected with a magnifying glass. Non-destructive testing is carried out at the suspected crack positions. Then, a skin replacement device for the aircraft inlet duct 100 is arranged and installed between each adjacent pair of frames 110 so that the two abutting parts 200 respectively abut tightly against the two adjacent frames 110 to fix the distance between the two frames 110. Then, the old inner skin 130 is detached from a plurality of frames 110, and the hole edges of the inner skin 130 and the skeleton structure are inspected with a magnifying glass. Non-destructive testing is carried out at the suspected crack positions. Finally, a skin replacement device for the aircraft inlet duct 100 is arranged and installed between the two opposite side walls of each frame 110 so that the two abutting parts 200 respectively abut tightly against the two opposite side walls of the same frame 110 to fix the distance between the two opposite side walls of the same frame 110.

[0050] Further, when installing the new inner skin 130, it is first necessary to position and drill holes in the new inner skin 130. The user uses the first drilling die 400 to position the holes in the new inner skin 130. The first drilling die 400 is a stepped cylindrical structure with a small-diameter section and a large-diameter section, and the first drilling die 400 is also provided with a through hole. The user first connects the small-diameter section of the first drilling die 400 to the frame 110, then lays the new inner skin 130 on the outer walls of each frame 110, and uses the skin replacement device of the aircraft intake duct 100 to press the new inner skin 130 tightly against the inner wall of the frame 110. Since the holes in the frame 110 penetrate the frame 110, the user can use a drill bit to pass through the through hole of the first drilling die 400 from the outer wall of the frame 110 to position the holes in the new inner skin 130. Then the user drills the holes in the new inner skin 130 by using the methods of reaming and drilling respectively. Specifically, the first drilling die 400 is composed of multiple drilling dies with gradually increasing hole diameters. For example, if the target hole diameter is 8 mm, first use a drill bit with a diameter of 2 mm to ream and drill the positioning holes, and then use drill bits with diameters of 4 mm, 6 mm, and 8 mm respectively to ream and drill the positioning protrusions in sequence. Finally, rivet the new inner skin 130 to multiple frames 110.

[0051] Further, when the user installs the new outer skin 120, it is first necessary to position and drill holes in the new inner skin 130. The user first uses a positioning tool to position the holes in the new inner skin 130. The positioning tool has a threaded section and a tapered section. The user threads the threaded section of the positioning tool onto the frame 110. When covering the new outer skin 120 on the inner wall of the frame 110, the tapered section of the positioning tool can form a positioning protrusion on the new outer skin 120. Then the user uses the second drilling die 500 to ream and drill the positioning protrusion in a step-by-step reaming manner. The second drilling die 500 is composed of multiple drilling dies with gradually increasing hole diameters. For example, if the target hole diameter is 8 mm, first use a drill bit with a diameter of 2 mm to ream and drill the positioning protrusion, and then use drill bits with diameters of 4 mm, 6 mm, and 8 mm respectively to ream and drill the positioning protrusion in sequence. Finally, rivet the new outer skin 120 to multiple frames 110.

[0052] Through the above structure and method, the present invention can solve the technical problem that the position of the frame 110 may change after the old skin is removed, resulting in non-fitting of the new skin and the outer skeleton during assembly, thereby causing skin cracks and rivet fractures.

[0053] The specific embodiments of the present invention described above do not constitute a limitation on the protection scope of the present invention. Any other corresponding changes and deformations made according to the technical concept of the present invention should be included in the protection scope of the claims of the present invention.

Claims

1. An aircraft inlet skin replacement device configured to be connected to an aircraft inlet, the aircraft inlet comprising: A plurality of spaced-apart spacer frames, an outer skin, and an inner skin, the outer skin being disposed on the outer sidewalls of the spacer frames and connected to all of the plurality of spacer frames, the inner skin being disposed on the inner sidewalls of the spacer frames and connected to all of the plurality of spacer frames, characterized by comprising: Two abutting portions, the two abutting portions being spaced apart from each other; and An adjustment assembly, disposed between the two abutting portions and connected to both of the two abutting portions, the adjustment assembly being capable of adjusting the distance between the two abutting portions for pushing the two abutting portions to respectively abut against two opposite inner walls of a spacer frame or two adjacent spacer frames.

2. The aircraft inlet skin replacement device according to claim 1, wherein, The abutting portion is an elastic structure.

3. The aircraft inlet skin replacement device according to claim 1, wherein The outer diameters of the two abutting portions gradually increase in the direction away from each other.

4. The aircraft inlet skin replacement device according to claim 1, wherein The adjustment assembly includes at least one linear drive portion, the linear drive portion having a fixed end and a telescopic end, and the fixed end of the linear drive portion being connected to one abutting portion and the telescopic end being connected to the other abutting portion for driving the two abutting portions to approach or separate from each other.

5. The aircraft inlet skin replacement device according to claim 4, wherein, The number of the linear drive portions in the adjustment assembly is two, the adjustment assembly further includes a connecting body, the connecting body being disposed between the two abutting portions, the two linear drive portions being respectively disposed at both ends of the connecting body, and the fixed ends of the two linear drive portions being both connected to the connecting body and the telescopic ends being respectively connected to the two abutting portions for respectively driving the two abutting portions to slide relative to the connecting body.

6. The aircraft inlet skin replacement device according to claim 5, wherein, The connecting body is cylindrical and has a through hole along its axis, the adjustment assembly further includes two sliding rods, one end of each sliding rod being connected to the abutting portion and the other end being slidably inserted into the through hole.

7. The aircraft inlet skin replacement device according to claim 6, wherein, The through hole has a first segment and a second segment with equal depths, the circumferential inner wall of the first segment is provided with a positive internal thread, the circumferential inner wall of the second segment is provided with a reverse internal thread, the circumferential outer walls of the two sliding rods are respectively provided with a positive external thread and a reverse external thread that can cooperate with the positive internal thread and the reverse internal thread, and the rotation of the connecting body around its own axis can drive the two sliding rods to approach or separate from each other along the axial direction of the connecting body.

8. The aircraft inlet skin replacement device according to claim 7, characterized in that, The adjustment assembly further includes two locking members, the locking members being slidably connected to the sliding rods and capable of abutting against the connecting body for restricting the sliding of the sliding rods relative to the connecting body.

9. The aircraft inlet skin replacement device according to claim 8, wherein, The two locking members are respectively slidably sleeved on the two sliding rods and are respectively threadedly connected to the two sliding rods.

10. A method for replacing the skin of an aircraft inlet, characterized in that, When using the aircraft inlet skin replacement device according to any one of claims 1-9, the specific steps are as follows: Disassemble the outer skin, remove the old outer skin, and inspect the holes of the outer skin and the spacer frames; Fix the spacer frames, and use the aircraft inlet skin replacement device to fix the distance between two adjacent spacer frames; Disassemble the inner skin, remove the old inner skin, and inspect the holes of the inner skin and the spacer frames; Fix the spacer frames, and use the aircraft inlet skin replacement device to fix the distance between two opposite inner walls of the same spacer frame; Position and drill the new inner skin, use the holes on the spacer frames to position the new inner skin, and use the first drilling die to ream the new inner skin; Install the new inner skin and rivet the new inner skin; Locate and drill holes for the new inner skin, use the holes on the bulkhead to locate the new outer skin, and use the second drilling die to ream the holes for the new inner skin; Install the new outer skin and rivet the new outer skin.

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