A large length-diameter ratio thin-wall weak rigid carbon fiber cabin body clamping tool and processing method

Abstract

The application discloses a large-length-diameter-ratio thin-wall weak-rigidity carbon fiber cabin clamping tool and a processing method, and belongs to the technical field of cabin turning processing. The clamping tool comprises a mandrel, a first positioning disc, a first moving support, a tensioning disc, a tensioning mechanism, a second positioning disc, a second moving support and a jacking mechanism. The first positioning disc is movably connected to the mandrel through the first moving support, and the moving direction of the first positioning disc is the axial direction of the mandrel. The tensioning disc is connected to the first positioning disc through the tensioning mechanism, and the tensioning disc is provided with a through hole matched with the outer wall of the cabin. The second positioning disc is movably connected to the mandrel through the second moving support, and the moving direction of the second positioning disc is the axial direction of the mandrel. The jacking mechanism is connected to the second positioning disc and abuts against the second end of the cabin and tightens the second positioning disc. The clamping tool and the processing method can realize stable and reliable clamping, and improve the processing quality and the processing efficiency.

Description

Technical Field

[0001] This application belongs to the field of cabin turning technology, and in particular relates to a clamping fixture and processing method for a thin-walled, weakly rigid carbon fiber cabin with a large aspect ratio. Background Technology

[0002] T700 grade carbon fiber is an excellent structural material with characteristics such as lightweight, high specific strength, high temperature resistance, and good overall performance, and is widely used in the aerospace field. Carbon fiber compartments have unique advantages, and their overall performance is significantly better than that of traditional materials such as aluminum alloys.

[0003] The high aspect ratio, thin wall, and weak rigidity of the carbon fiber segment are characterized by a large aspect ratio, thin walls, and no structural end frame at the large end. The segment is weak in rigidity and has large deformation. The large end is elliptical in its natural state, making clamping and alignment difficult and time-consuming. In addition, the processing is difficult and prone to vibration, which can lead to delamination and fiber tearing defects on the processed surface, resulting in unsatisfactory processing quality. Summary of the Invention

[0004] This application provides a clamping fixture and processing method for a large aspect ratio, thin-walled, weakly rigid carbon fiber cabin, aiming to at least partially solve the technical problems of inconvenient clamping and alignment, low processing efficiency, and unsatisfactory processing quality of large aspect ratio, thin-walled, weakly rigid carbon fiber cabin sections. Therefore, This application provides a clamping fixture for a high aspect ratio thin-walled weakly rigid carbon fiber cabin, comprising: a mandrel, a first positioning plate, a first movable bracket, a tensioning plate, a tensioning mechanism, a second positioning plate, a second movable bracket, and a clamping mechanism. The first positioning disk is movably connected to the spindle via the first movable bracket, and the moving direction of the first positioning disk is the axial direction of the spindle, so that the first positioning disk can movably abut against the inner wall of the cabin. The tensioning plate is connected to the first positioning plate through the tensioning mechanism. The tensioning plate has a through hole that matches the outer wall of the cabin. When the tensioning plate is sleeved on the outer wall of the cabin, the tensioning mechanism tightens the tensioning plate and the first positioning plate to achieve the clamping of the first end of the cabin. The second positioning disk is movably connected to the spindle via the second movable bracket, and the moving direction of the second positioning disk is the axial direction of the spindle, so that the second positioning disk can movably abut against the inner wall of the cabin. The tightening mechanism is connected to the second positioning plate so that when the second positioning plate abuts against the inner wall of the cabin, the tightening mechanism abuts against the second end of the cabin and tightens the second positioning plate.

[0005] In some embodiments, the outer peripheral surface of the first positioning disk is configured as a first positioning ramp that adapts to the inner wall surface of the cabin.

[0006] In some embodiments, a plurality of grooves are spaced apart on the first positioning inclined surface along the axial direction of the first positioning inclined surface.

[0007] In some embodiments, the first movable support includes: a first movable base, a fixed plate, and a support rod; The first movable seat is movably disposed on the spindle, and the first movable seat is provided with a locking member to lock the first movable seat on the spindle; The fixed plate is connected to the first movable seat, and there are multiple support rods. The multiple support rods are spaced apart on the fixed plate, and the multiple support rods are connected to the first positioning plate.

[0008] In some embodiments, the tensioning mechanism includes: a pad, a connecting plate, and a first connecting rod; The connecting plate is connected to the first positioning plate via the pad, and the two ends of the first connecting rod are respectively connected to the connecting plate and the tensioning plate.

[0009] In some embodiments, the second movable support includes a second movable seat, which is movably disposed on the spindle, and a locking member is disposed on the second movable seat to lock the second movable seat on the spindle; The clamping mechanism includes a second link and a top plate, the top plate being connected to the second movable seat via the second link.

[0010] In some embodiments, the first positioning plate, the tensioning plate, and the second positioning plate are provided with weight reduction holes.

[0011] In some embodiments, one end of the mandrel is provided with a chuck clamping part, and the other end of the mandrel is provided with a tip adapter part.

[0012] Another aspect of this application embodiment provides a method for processing a thin-walled, weakly rigid carbon fiber cabin with a large aspect ratio, wherein the cabin is a conical cylinder and an annular end frame is provided on the inner side of the small-diameter port of the conical cylinder. The processing method includes: The cabin body is clamped using the aforementioned clamping fixture; Remove the clamping mechanism and measure the thickness of the annular end frame to obtain the initial thickness. The small-diameter end of the cabin is semi-finished. Taking the inner side of the small-diameter end as a reference, and based on the initial thickness, a 2mm allowance is left. A tool path with two-sided entry is used to semi-finish the end face and inner side of the annular end frame using a two-sided tooling method. The cutting parameters include: tool tip radius R0.4, feed rate 8-12mm / min, depth of cut 0.3mm, and the cabin rotation speed 20-30r / min. The thickness of the annular end frame is measured again to obtain the remeasured thickness; The small-diameter end of the cabin is finished. Taking the inner side of the small-diameter end as a reference, based on the remeasured thickness, a tool path with two-sided entry is used to semi-finish the end face and inner side of the annular end frame using a two-sided tooling method. The cutting parameters include: tool tip radius R0.2, feed rate 5-6 mm / min, depth of cut 0.2 mm, and the cabin rotation speed 20-25 r / min. Change the tooling, re-clamp the clamping mechanism to clamp the small diameter end of the cabin, and remove the tensioning plate from the large diameter end side of the cabin; Measure the height margin at the large-diameter end of the cabin to obtain the initial height margin; The large-diameter end face of the cabin is semi-finished. Taking the end face of the small-diameter end as a reference, and based on the initial measured height allowance, a 1mm allowance is left. A tool path with two-sided entry is used to semi-finish the large end face of the cabin skin using a two-sided tooling method. The cutting parameters include: tool tip radius R0.4, feed rate 8-12mm / min, depth of cut 0.3mm, and the cabin rotation speed 20-30r / min. Measure the height margin at the large-diameter end of the cabin to obtain the height margin for remeasurement; The large end skin face of the cabin is finished using the small diameter end face as a reference. Based on the remeasured height allowance, a tool path with two-sided entry is used to finish the large end skin face of the cabin using a two-sided tooling method. The cutting parameters include: tool tip radius R0.2, feed rate 5-6 mm / min, depth of cut 0.2 mm, and the cabin rotation speed 20-25 r / min. The cabin was disassembled and its dimensions were fully inspected according to the design specifications.

[0013] In some embodiments, the processing method further includes: Before clamping the cabin, the end face allowance of the large diameter end of the cabin, the end face allowance of the annular end frame of the small diameter end, and the inner diameter allowance of the annular end frame are measured comprehensively.

[0014] The embodiments of this application have at least the following beneficial effects: The clamping fixture and machining method for a high aspect ratio, thin-walled, weakly rigid carbon fiber housing provided in this application embodiment are based on a mandrel. A first positioning plate and a second positioning plate are respectively matched and abutted against the inner wall of the housing to stably support it. A tensioning plate and a clamping mechanism are connected to the first and second positioning plates respectively, tightening them by relying on the large and small ends of the housing. This reliably clamps the housing onto the fixture, reducing the risk of vibration, delamination, and tearing defects to a certain extent, and improving turning quality. Furthermore, based on the clamping fixture, a reasonable machining process can be arranged, machining allowances adjusted, and appropriate cutting tools and parameters used to avoid defects on the machined surface, ensuring product machining quality. Attached Figure Description

[0015] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 A schematic diagram of the structure of the high aspect ratio thin-walled weak rigidity carbon fiber cabin clamping fixture in an embodiment of this application is shown; Figure 2 It shows Figure 1 A schematic diagram of the structure of the first positioning plate in the clamping fixture; Figure 3 It shows Figure 1 A schematic diagram of the tensioning disc in the clamping fixture; Figure 4 It shows Figure 1 A schematic diagram showing the connection status between the tensioning plate and the first positioning plate in the clamping fixture; Figure 5 A cross-sectional view of a high aspect ratio thin-walled weakly rigid carbon fiber cabin is shown in an embodiment of this application; Figure 6 It shows Figure 5 A half-section diagram of the clamping state of a high aspect ratio thin-walled weakly rigid carbon fiber cabin. Figure 7 It shows Figure 5 Front view of the clamping state of a high aspect ratio thin-walled weakly rigid carbon fiber cabin. Figure 8 It shows Figure 5 A schematic diagram of the end face turning trajectory of the annular end frame of a high aspect ratio thin-walled weakly rigid carbon fiber cabin. Figure 9 It shows Figure 5A schematic diagram of the machining trajectory of the inner side of the annular end frame of a high aspect ratio thin-walled weakly rigid carbon fiber cabin.

[0017] Figure label: 1-Mandrel, 11-Chuck clamping part, 12-Center adapter part, 13-Chuck, 14-Lathe, 15-Center, 16-Turning tool; 2-First positioning plate, 21-First positioning inclined surface, 22-Groove, 23-First weight reduction hole; 3-First movable support, 31-First movable base, 32-Fixed plate, 33-Support rod; 4-Tightening plate, 41-Through hole, 42-Adaptive bevel, 43-Second weight reduction hole; 5-Tensioning mechanism, 51-Padded block, 52-Connecting plate, 53-First connecting rod; 6-Second positioning plate, 61-Second positioning ramp; 7-Second movable support, 71-Second movable base; 8-Tightening mechanism, 81-Second link, 82-Top plate; 9-Carrier body, 91-Annular end frame, 91a-End face, 91b-Inner sidewall, 92-Large diameter end. Detailed Implementation

[0018] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of the embodiments. Based on the embodiments of this application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of this application.

[0019] Furthermore, reference numerals and / or reference letters may be repeated in different examples in this application. Such repetition is for simplification and clarity purposes and does not in itself indicate a relationship between the various embodiments and / or settings discussed. In addition, this application provides examples of various specific processes and materials; however, those skilled in the art will recognize the application of other processes and / or the use of other materials.

[0020] This application is described below with reference to the accompanying drawings and specific embodiments: Based on T700 grade carbon fiber, the high aspect ratio, thin-walled, weakly rigid carbon fiber compartment is shaped like a frustum cone. The compartment has a large aspect ratio, thin walls, and no structural end frame at the large end. The compartment is weak and deformable. The large end is elliptical in its natural state, making clamping and alignment difficult and time-consuming. Moreover, it is difficult to process and is prone to vibration during processing, which can lead to delamination and fiber tearing defects on the processed surface, resulting in unsatisfactory processing quality.

[0021] Therefore, this application provides a clamping fixture and processing method for a high aspect ratio, thin-walled, weakly rigid carbon fiber cabin, which aims to reduce machining defects, improve machining efficiency, and improve machining quality by improving clamping operations and turning processes.

[0022] In this embodiment, the high aspect ratio thin-walled weakly rigid carbon fiber cabin is a frustum-shaped cylinder with its inner diameter changing linearly from large to small. This embodiment uses a cabin of this structure as an example for illustration.

[0023] See Figure 1 , Figure 3 , Figure 4 , Figure 6 and Figure 7 In some embodiments, the high aspect ratio thin-walled weak rigid carbon fiber cabin clamping fixture uses internal support and external locking to clamp and fix the cabin.

[0024] The clamping fixture for the high aspect ratio thin-walled weak rigid carbon fiber cabin may include: a mandrel 1, a first positioning plate 2, a first moving bracket 3, a tensioning plate 4, a tensioning mechanism 5, a second positioning plate 6, a second moving bracket 7, and a top clamping mechanism 8.

[0025] The first positioning disk 2 is movably connected to the spindle 1 via the first movable bracket 3, and the moving direction of the first positioning disk 2 is the axial direction of the spindle 1, so that the first positioning disk 2 can movably abut against and support the inner wall of the cabin 9, press against the cabin 9 from the inside, and be fixed to the spindle 1 based on the first movable bracket 3.

[0026] The tensioning plate 4 is connected to the first positioning plate 2 through the tensioning mechanism 5. The tensioning plate 4 has a through hole 41 that matches the outer wall of the cabin 9. When the tensioning plate 4 is sleeved on the outer wall of the cabin 9, the tensioning mechanism 5 tightens the tensioning plate 4 and the first positioning plate 2, thereby clamping the first end of the cabin 9.

[0027] The second positioning disk 6 is movably connected to the spindle 1 via the second movable bracket 7, and the moving direction of the second positioning disk 6 is the axial direction of the spindle 1, so that the second positioning disk 6 can movably abut against and support the inner wall of the cabin 9.

[0028] The clamping mechanism 8 is connected to the second positioning plate 6 so that when the second positioning plate 6 abuts against the inner wall of the cabin, the clamping mechanism 8 abuts against the second end of the cabin 9 and pulls the second positioning plate 6 tight, thereby achieving the clamping of the second end of the cabin 9.

[0029] Thus, the mandrel 1, in conjunction with the first positioning disk 2 and the second positioning disk 6, respectively contacts and supports the inner wall of the frustum-shaped cylinder of the cabin 9. Then, the externally sleeved tensioning disk 4 and the tensioning mechanism 5 tighten the cabin 9 and the first positioning disk 2, thereby fixing one end of the cabin 9. The second end of the cabin 9 is fixed by tightening the second positioning disk 6 by pressing against the second end of the cabin, thereby fixing the second end of the cabin 9. This achieves stable and reliable clamping and fixing.

[0030] The clamping fixture and machining method for a high aspect ratio, thin-walled, weakly rigid carbon fiber housing provided in this application embodiment are based on a mandrel. A first positioning plate and a second positioning plate are respectively matched and abutted against the inner wall of the housing 9, thereby stably supporting the housing 9. A tensioning plate and a clamping mechanism are respectively connected to the first and second positioning plates, which are tightened by the large and small ends of the housing 9, respectively, thus stably and reliably clamping the housing 9 onto the clamping fixture. This reduces the risk of vibration, delamination, and tearing defects to a certain extent, improving turning quality. Furthermore, based on the clamping fixture, a reasonable machining process can be arranged, machining allowances adjusted, and appropriate cutting tools and cutting parameters used to avoid defects on the machined surface, ensuring product machining quality.

[0031] In some embodiments, the wall of the through hole 41 of the tensioning disc 4 is formed into an adaptable inclined surface 42 so that the inner sidewall of the tensioning disc 4 can fit against the outer wall surface of the cabin 9.

[0032] In some embodiments, the outer peripheral surface of the first positioning disk 2 is configured as a first positioning inclined surface 21 that adapts to the inner wall surface of the cabin 9, so as to adapt to and support the inner wall surface of the cabin 9 in a face-to-face contact manner, disperse the pressure on the inner wall surface of the cabin 9, and reduce the risk of pressure damage.

[0033] See Figure 2 In some embodiments, the first positioning inclined surface 21 is provided with a plurality of grooves 22 spaced apart along the axial direction of the first positioning inclined surface 21, so as to prevent the first positioning inclined surface 21 from being attracted to the inner wall surface of the cabin 9, making it difficult to detach and affecting the disassembly operation.

[0034] In some embodiments, the first movable bracket 3 is movably connected to the spindle 1 and can be flexibly locked and unlocked, thereby flexibly adjusting the position of the first positioning disk 2 and stably locking it.

[0035] The first movable bracket 3 may include: a first movable seat 31, a fixed plate 32, and a support rod 33; the first movable seat 31 is a movable mounting base, movably mounted on the spindle 1, and the first movable seat 31 is equipped with a locking member to lock the first movable seat 31 on the spindle, thereby realizing the lockable and unlockable performance of the first movable seat 31.

[0036] The fixed plate 32 is connected to the first movable seat 31. There are multiple support rods 33, which are spaced apart on the fixed plate 32 and connected to the first positioning plate 2 to support the first positioning plate 2.

[0037] In some embodiments, the first movable seat 31 may be an annular component, sleeved on the mandrel 1, and can be locked onto the mandrel 1 by fastening bolts.

[0038] In some embodiments, the tensioning mechanism 5 is used to connect the first positioning plate 2 and the tensioning plate 4, and needs to adapt to the shape of the cabin 9, extending from the first end of the cabin 9, and tensioning the tensioning plate 4.

[0039] Specifically, the tensioning mechanism 5 may include: a pad 51, a connecting plate 52, and a first connecting rod 53; the connecting plate 52 is connected to the first positioning plate 2 through the pad 51, and the two ends of the first connecting rod 53 are respectively connected to the connecting plate 52 and the tensioning plate 4, thereby fixing the first positioning plate 2 and the tensioning plate 4 based on the first moving seat 31, thereby stably fixing the cabin 9.

[0040] In some embodiments, the second movable support 7 includes a second movable seat 71, which is movably disposed on the spindle 1 and is provided with a locking member to lock the second movable seat 71 onto the spindle 1; the second positioning plate 6 can be directly fixed on the second movable seat 71, thereby allowing the position of the second positioning plate 6 to be flexibly adjusted to adapt to contact support on the inner wall of the cabin 9.

[0041] The clamping mechanism 8 may include a second connecting rod 81 and a top plate 82. The top plate 82 is connected to the second movable seat 71 via the second connecting rod 81, thereby fixing the top plate 82 based on the second movable seat 71 and clamping the end of the cabin 9.

[0042] In some embodiments, the first positioning plate 2, the tensioning plate 4, and the second positioning plate 6 are provided with weight reduction holes, namely the first weight reduction hole 23 and the second weight reduction hole 43, in order to reduce the overall weight of the tooling and facilitate operation.

[0043] See Figure 1 and 6 In some embodiments, one end of the mandrel 1 is provided with a chuck clamping part 11, and the other end of the mandrel 1 is provided with a center adapter part 12, so as to cooperate with the chuck 13 and the center 15 on the lathe 14 respectively to stably fix the mandrel 1.

[0044] See Figure 5 , Figure 6 and Figure 7 This application embodiment also provides a method for processing a thin-walled, weakly rigid carbon fiber cabin with a large aspect ratio. For a frustum-shaped cabin 9, the cabin 9 is a conical cylinder, and an annular end frame 91 is provided on the inner side of the small-diameter port of the conical cylinder, and the large-diameter end 92 is a circular cylinder opening.

[0045] See Figure 8 and Figure 9 The processing method includes: The cabin 9 is clamped using the aforementioned clamping fixture; Remove the clamping mechanism 8 and measure the thickness of the annular end frame 91 to obtain the initial thickness. The end face 91a of the small diameter end of the cabin 9 is semi-finished. Taking the inner side of the small diameter end as a reference, and based on the initial thickness, a 2mm allowance is left. The tool path with two-sided entry is used to semi-finish the end face and inner side of the annular end frame using the two-sided tool connection method. The cutting parameters include: tool tip radius R0.4, feed rate 8-12mm / min, depth of cut 0.3mm, and the cabin rotation speed 20-30r / min. The thickness of the annular end frame is measured again to obtain the remeasured thickness; The small-diameter end of the cabin 9 is finished. Based on the inner side of the small-diameter end as a reference and the remeasured thickness, a tool path with two-sided entry is used to semi-finish the end face and inner side of the annular end frame using a two-sided tooling method. The cutting parameters include: tool tip radius R0.2, feed rate 5-6 mm / min, depth of cut 0.2 mm, and the rotational speed of the cabin 9 is 20-25 r / min. Change the tooling, re-clamp the clamping mechanism 8 to clamp the small diameter end of the cabin 9, and remove the tensioning plate 4 from the large diameter end side of the cabin 9; Measure the height margin at the large-diameter end of the cabin 9 to obtain the initial height margin. The large-diameter end face of the cabin 9 is semi-finished. Taking the end face of the small-diameter end as a reference, and based on the initial height allowance, a 1mm allowance is left. A tool path with two-sided entry is used to semi-finish the large end face of the skin of the cabin 9 using the two-sided tooling method. The cutting parameters include: tool tip radius R0.4, feed rate 8-12mm / min, depth of cut 0.3mm, and the rotational speed of the cabin 9 is 20-30r / min. Measure the height margin at the large-diameter end of the cabin 9 to obtain the height margin for remeasurement; The large end skin face of the cabin 9 is finished using the small diameter end face as a reference and based on the remeasured height allowance. A tool path with two-sided entry is used to finish the large end skin face of the cabin 9 using a two-sided tooling method. The cutting parameters include: tool tip radius R0.2, feed rate 5-6 mm / min, depth of cut 0.2 mm, and the rotational speed of the cabin 9 is 20-25 r / min. The cabin 9 was removed and its dimensions were fully inspected according to the design specifications.

[0046] In some embodiments, the processing method further includes: Before clamping the cabin 9, the end face allowance of the large diameter end 92, the end face allowance of the annular end frame 91 of the small diameter end, and the inner diameter allowance of the annular end frame are measured in a comprehensive manner.

[0047] The following will provide a specific processing procedure to illustrate the above method.

[0048] Step 1, Raw material inspection: The standard dimensions of the T700 grade carbon fiber cabin 9 blank were inspected to determine the allowance distribution.

[0049] Step 2, Fixture installation: The turning fixture is clamped onto the machine tool 14. One end of the chuck 13 of the machine tool 14 clamps the chuck clamping part 11 of the spindle 1. The tailstock center 12 of the machine tool presses against the center adapter part 12. The positioning surface is aligned. The fixture is pressed against from below with a jack and sleepers. The pressing position is 200mm away from the clamping position of the lathe. Step 3: Clamp the product: Loosen the tailstock tip 12, move the tailstock away from the tooling to create operating space, hoist the cabin 9, fit it onto the tooling, and use the top plate 82 to press the annular end frame 91 of the cabin 9 firmly, ensuring that the first positioning plate 2 and the second positioning plate 6 are without gaps to the inner wall of the cabin 9. Remove the jacks and sleepers. Fit the tensioning plate 4 onto the skin of the cabin 9, secure the top plate with bolts, and then secure the tensioning plate with bolts. Remove the jacks and sleepers.

[0050] Step 4: Measure the allowance: Measure the thickness of the annular end frame. The measurement positions are the quadrant line of the end face and 8 points evenly distributed at a 45° offset position. Step 5, Semi-finishing the small end: Using the inner side of the small end as a reference, leave a 2mm allowance for semi-finishing.

[0051] Detailed operation process: (1) Loosen the top plate 82; (2) Determine the reference, adopt the tool path with two-sided entry, and the cutting parameters are: use a turning tool with a tool tip radius of R0.4, the machining parameters are: rotation speed 20-30 r / min, feed rate 8-12 mm / min, depth of cut 0.3 mm, and use the two-sided entry method for machining; (3) Semi-finish machining of the end face 91a of the annular end frame 91; (4) Semi-finished inner circle of small end frame; Step 6: Measure the allowance: Measure the thickness of the annular end frame at 8 evenly distributed points along the quadrant line and at a 45° offset. Step 7: Finish machining of the small end: Using the inner surface of the small end as a reference, it is precision machined to the required dimensions.

[0052] Detailed operation process: (1) Determine the reference and adopt a tool path with two-sided entry. Cutting parameters: use a turning tool with R0.2, machining parameters are: spindle speed 20-25 r / min, feed rate 5-6 mm / min, and depth of cut 0.2 mm. Machining is carried out using the two-sided entry method.

[0053] (2) Finish machining the end face 91a of the annular end frame; (3) Finish machining of the inner circle of the small end frame; Step 8: Change the tooling, use the top plate to press the end of the annular end frame 91, and loosen the tensioning disc 4 of the large diameter end 92; Step 9: Use a machine tool to measure the height allowance: The measurement position can also be the quadrant line and a position at 45° offset, with 8 points evenly distributed; Step 10, Semi-finishing the large end: Using the end face 91a of the annular end frame 91 as a reference, a 1mm allowance is left for semi-finishing.

[0054] Detailed operation process: (1) Determine the reference and adopt a tool path with two-sided entry. Cutting parameters: use a turning tool with a tool tip radius of R0.4, and the machining parameters are: rotation speed 20-30 r / min, feed rate 8-12 mm / min, and depth of cut 0.3 mm. Machining is carried out using the two-sided entry method.

[0055] (2) Semi-finished skin large diameter end 92 end face; Step 11, Measure the height margin: The measurement positions are the quadrant line and 8 points evenly distributed at a 45° offset position; Step 12: Finish machining the end face of the large-diameter end (92mm) of the skin: The end face 91a of the annular end frame 91 is used as a reference for precision machining.

[0056] Detailed operation process: (1) Determine the reference and adopt a tool path with two-sided entry. Cutting parameters: use a turning tool with R0.2, machining parameters are: spindle speed 20-25 r / min, feed rate 5-6 mm / min, and depth of cut 0.2 mm. Machining is carried out using the two-sided entry method.

[0057] (2) Finish the end face of the large-diameter end of the skin at 92°. Step 13, Fitter: Draw quadrant lines on the end face; Step 14: Secure the fixture with the jack and sleepers, loosen the tailstock, lift the product off the fixture, and then lift the fixture off the machine tool.

[0058] Step 15, Final Inspection: Conduct a comprehensive inspection of the dimensions according to the design specifications.

[0059] In the aforementioned steps, a reasonable machining sequence, machining tools, cutting parameters, and tooling are adopted to improve product quality.

[0060] Considering that delamination defects generally occur near the end of processing, when the fibers at the exit position lack support and are prone to delamination, the two-sided cutting method can effectively solve this problem.

[0061] In this application, unless otherwise expressly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature being directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature being directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0062] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", and "counterclockwise" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0063] It should be noted that all directional indications in the embodiments of this application are only used to explain the relative positional relationship and movement of the components in a specific posture. If the specific posture changes, the directional indication will also change accordingly. In this application, unless otherwise explicitly specified and limited, the terms "connection" and "fixed" should be interpreted broadly. For example, "fixed" can be a fixed connection, a detachable connection, or an integral part; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can be the internal connection of two components or the interaction relationship between two components, unless otherwise explicitly limited. For those skilled in the art, the specific meaning of the above terms in this application can be understood according to the specific circumstances. In addition, the descriptions involving "first," "second," etc., in this application are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Thus, features defined with "first" or "second" may explicitly or implicitly include one or more of the aforementioned features. In the description of this application, "multiple" means two or more, unless otherwise explicitly and specifically limited.

[0064] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. In addition, those skilled in the art can combine and integrate the different embodiments or examples described in this specification.

[0065] Furthermore, the technical solutions of the various embodiments can be combined with each other, but only if they are based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such combination of technical solutions does not exist and is not within the scope of protection claimed in this application.

[0066] Although embodiments of this application have been shown and described, those skilled in the art will understand that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of this application, the scope of which is defined by the claims and their equivalents.

Claims

1. A clamping fixture for a high aspect ratio, thin-walled, weakly rigid carbon fiber cabin, characterized in that, include: The components include a spindle, a first positioning plate, a first movable bracket, a tensioning plate, a tensioning mechanism, a second positioning plate, a second movable bracket, and a clamping mechanism. The first positioning disk is movably connected to the spindle via the first movable bracket, and the moving direction of the first positioning disk is the axial direction of the spindle, so that the first positioning disk can movably abut against the inner wall of the cabin. The tensioning plate is connected to the first positioning plate through the tensioning mechanism. The tensioning plate has a through hole that matches the outer wall of the cabin. When the tensioning plate is sleeved on the outer wall of the cabin, the tensioning mechanism tightens the tensioning plate and the first positioning plate to achieve the clamping of the first end of the cabin. The second positioning disk is movably connected to the spindle via the second movable bracket, and the moving direction of the second positioning disk is the axial direction of the spindle, so that the second positioning disk can movably abut against the inner wall of the cabin. The clamping mechanism is connected to the second positioning plate so that when the second positioning plate abuts against the inner wall of the cabin, the clamping mechanism abuts against the second end of the cabin and pulls the second positioning plate tight. The outer peripheral surface of the first positioning disk is configured as a first positioning inclined surface that is adapted to the inner wall surface of the cabin. The first positioning inclined surface is provided with a plurality of grooves spaced apart along the axial direction of the first positioning inclined surface.

2. The clamping fixture for a high aspect ratio, thin-walled, weakly rigid carbon fiber cabin as described in claim 1, characterized in that, The first movable support includes: a first movable base, a fixed plate, and a support rod; The first movable seat is movably disposed on the spindle, and the first movable seat is provided with a locking member to lock the first movable seat on the spindle; The fixed plate is connected to the first movable seat, and there are multiple support rods. The multiple support rods are spaced apart on the fixed plate, and the multiple support rods are connected to the first positioning plate.

3. The clamping fixture for a high aspect ratio, thin-walled, weakly rigid carbon fiber cabin as described in claim 1, characterized in that, The tensioning mechanism includes: a pad, a connecting plate, and a first connecting rod; The connecting plate is connected to the first positioning plate via the pad, and the two ends of the first connecting rod are respectively connected to the connecting plate and the tensioning plate.

4. The clamping fixture for a high aspect ratio, thin-walled, weakly rigid carbon fiber cabin as described in claim 1, characterized in that, The second movable bracket includes a second movable seat, which is movably disposed on the spindle, and a locking member is disposed on the second movable seat to lock the second movable seat on the spindle; The clamping mechanism includes a second link and a top plate, the top plate being connected to the second movable seat via the second link.

5. The clamping fixture for a high aspect ratio, thin-walled, weakly rigid carbon fiber cabin as described in claim 1, characterized in that, The first positioning plate, the tensioning plate, and the second positioning plate are provided with weight reduction holes.

6. The clamping fixture for a high aspect ratio, thin-walled, weakly rigid carbon fiber cabin as described in claim 1, characterized in that, One end of the mandrel is provided with a chuck clamping part, and the other end of the mandrel is provided with a tip adapter part.

7. A method for processing a thin-walled, weakly rigid carbon fiber cabin with a large aspect ratio, characterized in that, The cabin is a conical tube, and an annular end frame is provided on the inner side of the small-diameter port of the conical tube. The processing method includes: The cabin body is clamped using the clamping fixture described in any one of claims 1 to 6; Remove the clamping mechanism and measure the thickness of the annular end frame to obtain the initial thickness. The small-diameter end of the cabin is semi-finished. Taking the inner side of the small-diameter end as a reference, and based on the initial thickness, a 2mm allowance is left. A tool path with two-sided entry is used to semi-finish the end face and inner side of the annular end frame using a two-sided tooling method. The cutting parameters include: tool tip radius R0.4, feed rate 8-12mm / min, depth of cut 0.3mm, and the cabin rotation speed 20-30r / min. The thickness of the annular end frame is measured again to obtain the remeasured thickness; The small-diameter end of the cabin is finished. Taking the inner side of the small-diameter end as a reference, based on the remeasured thickness, a tool path with two-sided entry is used to semi-finish the end face and inner side of the annular end frame using a two-sided tooling method. The cutting parameters include: tool tip radius R0.2, feed rate 5-6 mm / min, depth of cut 0.2 mm, and the cabin rotation speed 20-25 r / min. Change the tooling, re-clamp the clamping mechanism to clamp the small diameter end of the cabin, and remove the tensioning plate from the large diameter end side of the cabin; Measure the height margin at the large-diameter end of the cabin to obtain the initial height margin; The large-diameter end face of the cabin is semi-finished. Taking the end face of the small-diameter end as a reference, and based on the initial measured height allowance, a 1mm allowance is left. A tool path with two-sided entry is used to semi-finish the large end face of the cabin skin using a two-sided tooling method. The cutting parameters include: tool tip radius R0.4, feed rate 8-12mm / min, depth of cut 0.3mm, and the cabin rotation speed 20-30r / min. Measure the height margin at the large-diameter end of the cabin to obtain the height margin for remeasurement; The large end skin face of the cabin is finished using the small diameter end face as a reference. Based on the remeasured height allowance, a tool path with two-sided entry is used to finish the large end skin face of the cabin using a two-sided tooling method. The cutting parameters include: tool tip radius R0.2, feed rate 5-6 mm / min, depth of cut 0.2 mm, and the cabin rotation speed 20-25 r / min. The cabin was disassembled and its dimensions were fully inspected according to the design specifications.

8. The method for processing a high aspect ratio, thin-walled, weakly rigid carbon fiber cabin as described in claim 7, characterized in that, The processing method further includes: Before clamping the cabin, the end face allowance of the large diameter end of the cabin, the end face allowance of the annular end frame of the small diameter end, and the inner diameter allowance of the annular end frame are measured comprehensively.

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