A tooling for processing irregularly shaped thin-walled compartment sections made of composite materials and metal laminates

Abstract

This invention relates to a machining fixture for irregularly shaped thin-walled compartments of composite-metal laminates, belonging to the field of parts machining technology. It solves the problems of unstable clamping, large machining vibration, and reduced machining accuracy associated with existing irregularly shaped parts. The fixture includes an adjusting assembly, a retaining ring, a clamping frame, a tie rod, and flanges. One end of the retaining ring is fixed and movably connected to one side of the adjusting assembly, while the other end is detachably or fixedly connected to the other side of the adjusting assembly. The clamping frame is located at one end of the adjusting assembly and is used to clamp the flange at one fixed end. There are at least two flanges, and the lower ends of the flanges can support the upper part of the adjusting assembly. The two ends of the tie rod pass through the axial through holes of the flanges at both ends of the adjusting assembly. This achieves stable clamping of the irregularly shaped thin-walled compartments and improves the machining accuracy of the parts.

Description

Technical Field

[0001] This invention relates to the field of parts processing technology, and in particular to a tooling for processing irregularly shaped thin-walled compartments of composite-metal laminates. Background Technology

[0002] With the rapid development of the aviation industry, the demand for faster and lighter aircraft is increasing. Irregularly shaped thin-walled composite material outer shells with metal inner shells have gained widespread attention in the aviation field due to their lightweight, good thermal insulation, and low drag, and are increasingly being applied to key structural components of aircraft. Compared to traditional aircraft with regular single-metal shells, which only require shape machining after casting, the composite-metal laminated irregularly shaped thin-walled segment manufacturing process is more complex. It involves multiple steps after the metal shell is cast, including full-shape machining (both inside and out), composite material molding, bonding the composite material to the metal shell to form a laminated structure, and machining the composite-metal laminated shell itself.

[0003] For irregularly shaped thin-walled compartment sections made of composite materials and metal laminates: Due to the thin-walled structure, the compartment has poor rigidity and is prone to vibration during machining. The cutting force generated during the cutting process causes deformation of the thin-walled structure, making it impossible to guarantee machining accuracy. The usual method is to use conformal tooling to fit against the surface of the machining area on the opposite side to provide support. However, due to the irregular shape, the conformal tooling used for support cannot be well fixed to the compartment during use, and it is very easy to produce positional deviations from the surface of the machining area. This results in gaps between the conformal tooling, which should fit against the machining area, and fails to provide support. Under the coupled effect of vibration and cutting deformation, the product accuracy cannot meet the requirements.

[0004] The manufacturing process for irregularly shaped thin-walled compartments made of composite materials and metal laminates involves many steps, including internal and external full-shape machining after the metal compartment is cast, composite material molding, bonding of composite materials and metal compartments to form a laminated structure, and machining of the composite material-metal laminated compartment. The irregular shape of the parts means there are no regular shapes available for alignment, and the lack of uniformity in the multiple datums in the manufacturing process leads to machining accuracy errors caused by datum deviations in each process, resulting in the final product failing to meet accuracy requirements.

[0005] Composite-metal laminated structures differ from metal cutting materials in their cutting performance. Different processing schemes for parts such as joints and mounting areas result in large deviations in the precision of the laminated structure after processing, failing to meet usage requirements. Furthermore, the outer layer is made of composite material, which is brittle. Inaccurate clamping forces can damage the composite material, affecting its thermal insulation performance. Summary of the Invention

[0006] Based on the above analysis, the present invention aims to provide a machining fixture for irregularly shaped thin-walled compartments of composite material-metal laminates, in order to solve the problems of unstable clamping, large machining vibration, and reduced machining accuracy of irregularly shaped parts in the prior art.

[0007] On one hand, embodiments of the present invention provide a tooling for processing irregularly shaped thin-walled compartment sections of composite material-metal laminates, including: an adjustment assembly 100, a retaining ring 200, a clamping frame 300, a tie rod 400, and a flange; One end of the retaining ring 200 is fixed and movably connected to one side of the adjustment assembly 100, and the other end is detachably or fixedly connected to the other side of the adjustment assembly 100. The clamping frame 300 is disposed at one end of the adjusting assembly 100 and is used to clamp and fix the flange at one end; There are at least two flanges, and the lower end of each flange can be supported above one end of the adjusting assembly 100; The two ends of the tie rod 400 are respectively inserted into the axial through holes of the flanges at both ends of the adjusting assembly 100.

[0008] It should be noted that the thin-walled compartment is a laminated structure formed by bonding an outer composite material and an inner irregular metal compartment. The machining fixture is used for clamping the metal compartment and the laminated structure after bonding the metal compartment and the composite material on a full-form machine tool. The metal compartment has a process reference block for machining positioning, and the process reference block has pin holes for connection.

[0009] Specifically, the adjustment assembly includes a base 110 and a first roller assembly 120, an adjustment bracket 130, a rotating nut 140, and a limiting assembly 150 mounted on the base. The adjusting bracket 130 is raised and lowered by rotating the nut 140 to adjust the pitch position of the thin-walled compartment. There are at least two first roller assemblies 120, which are installed at both ends of the base 110. The installation position of the thin-walled compartment is adjusted by the first roller assemblies 120 to accommodate thin-walled compartments of different sizes. There are at least two limiting assemblies 150, which are installed at both ends of the base 110 to limit the axial position of the thin-walled compartment.

[0010] Furthermore, the retaining ring 200 is installed on both sides of the base 110 via a pressure plate mounting component, and the retaining ring 200 has a conformal pressure plate 202 with an adjustable distance from the outer surface of the thin-walled compartment on its inner surface facing the thin-walled compartment.

[0011] Furthermore, the clamping frame 300 includes a clamping frame crossbeam, a vertical beam, and inclined beams fixed at both ends near one end of the clamping frame crossbeam and one end of the vertical beam, respectively; a connecting seat is provided at the lower end of the vertical beam; the connecting seat is connected to the lower end of the vertical beam by a shoulder screw, and the height of the clamping frame 300 is adjusted by adjusting the extension length of the screw; a second roller assembly 308 is provided on the side of the inclined beam facing the thin-walled compartment section, and the clamping degree of the clamping frame 300 is adjusted by the second roller assembly 308.

[0012] Specifically, the flange includes an outer flange 500 and an inner flange 600; there are at least two outer flanges 500, and the lower end of the outer flange 500 can be supported above one end of the adjusting assembly 100; there are at least two inner flanges 600, and the lower end of the inner flange 600 can be supported above one end of the adjusting assembly 100; one of the outer flange 500 and the inner flange 600 can be used.

[0013] Furthermore, one end of the outer flange 500 has a frustum for positioning with the center of the machine tool turntable; it has a hole with the same size and position as the pin hole of the metal cabin process reference block; the outer flange 500 also has limiting holes for uniform distribution design, and the pins are sequentially inserted into the pin holes on the limiting assembly 150 and the limiting holes of the outer flange 500.

[0014] Furthermore, the inner flange 600 is provided with a hole whose size and position are consistent with the pin hole of the product process reference block, for fixing the inner flange 600 to the product by inserting a pin shaft; the inner flange 600 also has limiting holes for uniform distribution design, and the pins are sequentially inserted into the pin holes on the limiting component 150 and the limiting holes of the inner flange 600.

[0015] For example, when the metal cabin is machined by a machine tool, the tie rod 400 is inserted into the inner cavity of the metal cabin and connected to the outer flanges 500 at both ends of the cabin, and the outer flanges 500 are pressed against the metal cabin by rotating nuts; the outer flange 500 at one end of the cabin is fixed to the machine tool turntable by a centrally positioned frustum; the outer flange 500 at the other end of the cabin is connected to the clamping frame 300 by a second roller assembly 308; after the connection is completed, the tooling components used for positioning and clamping are disengaged from the metal cabin.

[0016] On the other hand, the present invention also provides a method for processing irregularly shaped thin-walled compartment sections of composite material-metal laminates, wherein the processing fixture is used for clamping during processing, and the method includes the following steps: S1. Irregular metal cabin casting, and four cuboids are cast together with the cabin as process reference blocks during casting. S2. Establish initial machining benchmarks; S3. Rough machining of irregular metal cabins; S4. Measure and adjust the precision machining benchmarks for irregular metal cabins; S5. Perform precision machining on irregular metal cabins; S6. Prepare composite materials and bond the composite material layers to the outside of the irregular metal cabin. S7. Rough machining of composite material layer; S8. Perform precision machining on all parts of the composite material, remove the process reference blocks on the metal housing, and complete the product processing.

[0017] This invention employs an integrated adjustable tooling clamping system, which solves the problems of unstable clamping of irregular shapes and increased vibration during processing, thereby improving the surface quality of the machined parts; and also meets the clamping requirements of parts in multiple states.

[0018] In this invention, the above-described technical solutions can be combined with each other to achieve more preferred combinations. Other features and advantages of this invention will be set forth in the following description, and some advantages may become apparent from the description or be learned by practicing the invention. The objects and other advantages of this invention can be realized and obtained from what is particularly pointed out in the description and drawings. Attached Figure Description

[0019] The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Throughout the drawings, the same reference numerals denote the same parts.

[0020] Figure 1 Fixtures for clamping irregularly shaped thin-walled compartments made of composite-metal laminates; Figure 2 Implementation diagram for clamping irregularly shaped thin-walled compartments of composite-metal laminates; Figure 3 Adjust the components for clamping tooling; Figure 4 For mounting the tooling base; Figure 5 For mounting the tooling roller assembly; Figure 6 Adjust the bracket for clamping tooling; Figure 7 Adjust the bracket for clamping the tooling; Figure 8 For clamping and rotating the nut; Figure 9 For mounting and using tooling limit components; Figure 10 For clamping tooling retainers; Figure 11 For clamping fixtures and clamping frames.

[0021] Figure label: 100-Adjusting assembly; 200-Snap ring; 300-Pressure bracket; 400-Tie rod; 500-External flange; 600-Internal flange; 110-Base; 120-First roller assembly; 130-Adjusting bracket; 140-Swivel nut; 150-Limit assembly; 111-Longitudinal beam; 112-Crossbeam; 113-Column; 114-Reinforcing rib; 115-Snap ring mounting plate; 116-Base plate; 117-Roller assembly mounting plate; 118-Limit assembly mounting plate; 119-Support tube; 121-Upper guide rail; 122-Lower guide rail; 123 - Roller mounting plate; 124 - Roller mounting shaft; 125 - Roller; 126 - Tightening screw; 127 - Bearing; 128 - Screw; 129 - Adjusting bracket; 131 - Bracket; 132 - Pin; 133 - Support screw; 140 - Rotary nut; 201 - Pressure plate mounting part; 202 - Conformal pressure plate; 203 - Screw; 204 - Cover plate; 301 - Pressure frame crossbeam; 302 - Vertical beam; 303 - Inclined beam; 304 - Connecting seat; 305 - Screw cover plate; 306 - Pressure frame screw; 307 - Pressure frame base; 308 - Second roller assembly. Detailed Implementation

[0022] Preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings, which form part of this application and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not intended to limit the scope of the present invention.

[0023] In one specific embodiment of the present invention, a clamping fixture for irregularly shaped thin-walled compartments of composite material-metal laminates is disclosed, which is used for clamping during the processing of the irregularly shaped thin-walled compartments of composite material-metal laminates.

[0024] The clamping fixture for the irregularly shaped thin-walled compartment of the composite material-metal laminate includes: adjustment assembly 100, retaining ring 200, clamping frame 300, tie rod 400, external flange 500, and internal flange 600. One end of the retaining ring 200 is fixed and movably connected to one side of the adjustment assembly 100, and the other end is detachably or fixedly connected to the other side of the adjustment assembly 100. The clamping frame 300 is disposed at one end of the adjusting assembly 100 and is used to clamp and fix the flange at one end; There are at least two external flanges 500, and the lower end of each external flange 500 can be supported above one end of the adjusting assembly 100; there are at least two internal flanges 600, and the lower end of each internal flange 600 can be supported above one end of the adjusting assembly 100; one of the external flanges 500 and the internal flanges 600 may be used. The two ends of the tie rod 400 are respectively inserted into the axial through holes of the outer flange 500 or the inner flange 600 at both ends of the adjusting assembly 100.

[0025] Specifically, the adjustment assembly includes a base 110 and a first roller assembly 120, an adjustment bracket 130, a rotating nut 140, and a limiting assembly 150 mounted on the base; The pitch position of the thin-walled compartment is adjusted by rotating the nut 140 to raise and lower the bracket 130. At least four first roller assemblies 120 are installed at both ends of the base 110. The installation position of the thin-walled compartment is adjusted by the first roller assemblies 120 to accommodate thin-walled compartments of different sizes. At least two limiting assemblies 150 are installed at both ends of the base 110 to limit the axial position of the thin-walled compartment.

[0026] The base 110 is welded into a frame by longitudinal beams 111, cross beams 112, and base plate 116; a column 113 is welded on it and welded to a reinforcing rib 114; a retaining ring mounting plate 115 for mounting retaining ring 200 is welded to the upper end of the column 113, and the mounting plate has threaded holes for tightening screws to fix the retaining ring 200; a roller assembly mounting plate 117 and a limit assembly mounting plate 118 are welded to both ends of the welded frame, and the roller assembly mounting plate 117 and the limit assembly mounting plate 118 have threaded holes; a support tube 119 for adjusting the screw on the bracket 130 is assembled on the middle cross beam in the form of screws.

[0027] The first roller assembly 120 includes: an upper guide rail 121, a lower guide rail 122, a roller mounting plate 123, a roller mounting shaft 124, a roller 125, a tightening screw 126, a bearing 127, a screw 128, and an adjusting bracket 129. The first roller assembly 120 is fixed to the base 110 by screws 128, and the lower guide rail 122, which is welded with the roller mounting plate 123, is slidably connected to the upper guide rail 121. Specifically, the upper guide rail 121 and the lower guide rail 122 are interlocked in an "I" shape. The length of the upper guide rail 121 is greater than the length of the lower guide rail 122, so that the lower guide rail 122 can slide on the upper guide rail 121. A roller mounting plate 123 is welded onto the lower guide rail 122; a roller mounting shaft 124 is mounted on the upper end of the roller mounting plate 123; a roller 125 and a bearing 127 are sequentially installed on the roller mounting shaft 124; an adjusting bracket 129 is mounted on both ends of the upper guide rail 121 by screws; the adjusting bracket 129 has screws 128 and tightening screws 126; the screw holes on the adjusting bracket 129 that connect to the upper guide rail 121 are oblong holes, and the upper guide rail 121 can be adjusted back and forth within the length range of the oblong holes to meet the clamping requirements of different lengths for rough and fine machining of metal cabins and composite materials; a tightening screw 126 is installed in the middle of the adjusting bracket 129, and the position of the roller can be adjusted by sliding the lower guide rail 122 on the upper guide rail 121, and the roller position is tightened by the tightening screw 126 after it is adjusted to the correct position.

[0028] The adjustment bracket 130 includes a bracket 131, a pin 132, and a support screw 133; The bracket 131 is threadedly connected to the support tube 119 equipped with the rotating nut 140 via the support screw 133 and is fixed with the pin 132; Specifically, bracket 131 is a bracket with the same profile as the part, ensuring that it can fit the part profile when adjusting the product; bracket 131 is provided with mounting holes for support screw 133; support screw 133 has a shoulder structure, after the support screw 133 is inserted into the mounting hole on bracket 131, the shoulder structure fits against bracket 131 to play a positioning role; pin 132 is used to sequentially insert into the pin holes on support screw 133 and bracket 131, and fix support screw 133 and bracket 131; The lower end of the outer circle of the rotating nut 140 has a groove that corresponds to the size of the semi-circular annular boss on the support tube 119. When in use, the rotating nut 140 is inserted into the semi-circular annular boss on the support tube 119 to fix the rotating nut 140. The lower end of the support screw 133 has a threaded structure. The rotating nut 140 and the support screw 133 have the same internal thread size. The rotating nut 140 and the support screw 133 are assembled by the thread. Rotating the rotating nut 140 causes the adjusting bracket 130 to rise and fall through the thread action. The adjusting bracket 130 supports the product, and the product can be adjusted in pitch position.

[0029] The limiting component 150 is L-shaped, with one installed at the front and one at the back of the base 110, and fixed to the base 110 by nuts; it has a pin hole for installing a pin.

[0030] Furthermore, the retaining ring 200 includes a pressure plate mounting component 201, a conformal pressure plate 202, a screw 203, and a cover plate 204; The retaining ring 200 is installed on both sides of the base 110 via a pressure plate mounting component. The retaining ring 200 has a conformal pressure plate 202 with an adjustable distance from the outer surface of the thin-walled compartment on its inner surface facing the thin-walled compartment. Specifically, the pressure plate mounting component 201 is fixed to the column 113 on the base 110 using screws on its lower surface. The pressure plate mounting component 201 has threaded holes for mounting the screw 203, which has a ball head at the front. Correspondingly, the conformal pressure plate 202 also has an inner arc spherical surface, ensuring that the conformal pressure plate 202 can rotate 360° around the ball head of the screw 203 to adapt to irregular surfaces of the part at any angle. By adjusting the thread extension length, the conformal pressure plate 202 is ensured to fit snugly against the part's surface. The screw 203 is connected and fixed to the conformal pressure plate 202 using a cover plate 204 and screws.

[0031] Furthermore, the clamping frame 300 includes a clamping frame crossbeam 301, a vertical beam 302, a diagonal beam 303, a connecting seat 304, a screw cover plate 305, a clamping frame screw 306, a clamping frame base 307, and a second roller assembly 308. The clamping frame 300 includes a clamping frame crossbeam 301, a vertical beam 302, and an inclined beam 303 with both ends fixed near one end of the clamping frame crossbeam 301 and the vertical beam 302, respectively. A connecting seat 304 is provided at the lower end of the vertical beam 302. The connecting seat 304 is connected to the lower end of the vertical beam by a shoulder screw. The height of the clamping frame 300 is adjusted by adjusting the extension length of the clamping frame screw 306. A second roller assembly 308 is provided on the side of the inclined beam facing the thin-walled compartment section. The clamping degree of the clamping frame 300 is adjusted by the second roller assembly 308. Specifically, the clamping frame consists of a crossbeam 301, a vertical beam 302, and an inclined beam 303 welded together. A connecting seat 304 is welded to the lower end of the vertical beam 302. A second roller assembly 308 is mounted on the inclined beam 303 via screws. The second roller assembly 308 can be adjusted in position forward and backward, and up and down to meet the clamping requirements of products in different states. The clamping frame screw 306 has a shoulder structure. The clamping frame screw 306 passes through the hole in the connecting seat 304. The shoulder structure fits snugly against the connecting seat 304 for positioning. At the same time, screws and a screw cover plate 305 are used to tightly fix the clamping frame screw 306. The clamping frame base 307 has a threaded hole with the thread size matching that of the screw. By rotating the thread on the clamping frame screw 306, the extension length of the clamping frame screw 306 is adjusted, thereby adjusting the height of the clamping frame 300.

[0032] Furthermore, one end of the outer flange 500 has a frustum for positioning with the center of the machine tool turntable; it is designed with holes of the same size and position as the pin holes of the product process reference block, for fixing the outer flange 500 to the product by inserting a pin shaft; the outer flange 500 also has limiting holes for evenly distributed design, and the pins are inserted sequentially from the pin holes on the limiting component 150 and the limiting holes of the outer flange 500 to play a limiting role.

[0033] Furthermore, the inner flange 600 is designed with holes whose size and position are consistent with the pin holes of the product process reference block, for fixing the inner flange 600 to the product by inserting a pin shaft; the inner flange 600 also has limiting holes for even distribution, and the pins are inserted sequentially from the pin holes on the limiting component 150 and the limiting holes of the inner flange 600 to play a limiting role.

[0034] It should be noted that the adjustment assembly 100, the retaining ring 200, and the clamping frame 300 are used for positioning and clamping before the thin-walled compartment is processed; Place the adjustment assembly 100 on the machine tool worktable, place the metal cabin or laminated structure on the adjustment bracket 130, and ensure that the bracket surface fits the surface of the metal cabin or laminated structure to confirm that the placement position is correct; adjust the pitch state of the cabin by adjusting the height of the two adjustment brackets 130 closest to the outermost part in the length direction; adjust the extension position of the screw 203 on the retaining ring 200 to make the conformal pressure plate 202 fit and press against the surface of the metal cabin or laminated structure; adjust the position of the first roller assembly 120 to the machining position along the length direction according to the length dimension of the metal cabin or laminated structure; When the clamping fixture is used to machine the shape of the metal cabin or the laminated structure, the tie rod 400 is inserted into the inner cavity of the metal cabin and connected to the outer flanges 500 at both ends of the cabin. The outer flanges 500 are then pressed against the metal cabin by rotating nuts. One outer flange 500 at one end of the cabin is fixed to the machine tool turntable by a centrally positioned frustum. The outer flange 500 at the other end of the cabin is connected to the clamping frame 300 by a second roller assembly 308. After the connection is completed, the fixture components used for positioning and clamping are disengaged from the metal cabin. When machining the internal shape of the metal cabin using a machine tool, the tie rod 400 connects to the outer flange 500 of the machine tool turntable from the outside of the metal cabin, and connects to the inner flange 600 at the other end; the inner flange 600 is connected to the clamping frame 300 through the second roller assembly 308; after the connection is completed, the tooling components used for positioning and clamping are disengaged from the metal cabin.

[0035] The clamping fixture of this invention is used to clamp and process irregularly shaped thin-walled compartments of composite material-metal laminates. During the processing, the processing datum is dynamically measured, adjusted and transferred, which greatly reduces the processing accuracy error. With the metal compartment as the datum, the composite material is gradually approximated in the processing method, which further reduces the accuracy deviation after the laminate structure is processed. The integrated adjustable fixture clamping solves the problems of unstable clamping of irregular shapes and increased vibration during processing, improves the surface quality of the processed parts, and meets the clamping requirements of parts in multiple states.

[0036] On the other hand, the present invention also discloses a method for processing an irregularly shaped thin-walled compartment segment of composite material-metal laminate, wherein the irregularly shaped thin-walled compartment segment of composite material-metal laminate is a laminated structure formed by bonding an outer composite material and an inner irregular metal compartment, and the processing method includes the following steps: S1. Casting of irregular metal hulls, and casting four cuboids together with the hull as process reference blocks during casting, and selecting special points A, B, C, and D on each process reference block as reference points. S2. Establish initial machining datum: Establish rough machining datum in the state of irregular metal cabin casting; S3. Rough machining of irregular metal cabin: The irregular metal cabin is clamped with tooling and placed on the machine tool worktable for full-shape machining inside and outside. At the same time, after the rough machining is completed, pin holes are machined on the process reference block according to the set dimensions. S4. Measure and adjust the finishing datum of the irregular metal cabin: Laser scan the rough-machined metal cabin, adjust the clamping posture, and use the pin hole processed in step S3 as the finishing datum. S5. Perform fine machining on the irregular metal cabin. After the fine machining is completed, enlarge the pin hole on the original process reference block. Laser scan the finely machined metal cabin, adjust the clamping posture, and use the enlarged pin hole as the initial processing reference for the stacking. S6. Prepare composite materials and bond the composite material layers to the outside of the irregular metal cabin. S7. Rough machining of composite material layers: According to the initial machining benchmark of the laminate, machining is carried out on each machining part of the composite material with a margin. S8. Measure and adjust each processing part of the composite material one by one; perform fine processing on each processing part of the composite material; remove the process reference block on the metal chamber to complete the product processing.

[0037] Further, the process reference blocks mentioned in step S1 serve as references for subsequent multi-process procedures. The four process reference blocks are regular cuboids, distributed in a dispersed manner, with two on each of the front and rear end faces of the cabin. The two process reference blocks on each end face are symmetrically arranged, and the center lines of the process reference blocks on the front and rear end faces are parallel along the radial direction of the end face. One surface of each process reference block is on the same plane as the front or rear end face of the cabin, and this surface is P1. The surface that intersects P1 perpendicularly and is not connected to the cabin is P2. The surfaces that are adjacent to P1 and P2 are P3 and P4, respectively, where P3 is located on one side of the clockwise direction of the center lines of the two process reference blocks on the same end face. The intersection of the three adjacent surfaces P1, P2, and P3 is selected as the reference point. The two reference points on the front end face of the cabin are A and B, and the two reference points on the rear end face of the cabin are C and D, where the lines connecting A and C and B and D are parallel to the cabin axis.

[0038] Furthermore, the initial machining datum establishment process for the irregular metal cabin casting state described in step S2 is as follows: S201. Perform laser scanning on the metal cabin and scan the process reference block simultaneously. S202. Fit the laser scanning results to obtain the physical cabin scanning model, compare it according to the allowance requirements, and adjust the fitting position to ensure that the allowance of the inner and outer surfaces is roughly uniform, and determine whether the part meets the casting allowance requirements. Specifically, marking points are affixed to the surface of the casting for scanning. After scanning, cloud points are generated in Control X software. The scanned model is then generated through reverse modeling using the numerous cloud points. The scanned model is then fitted and compared with the theoretical model to measure whether the allowance meets the casting allowance requirements. Horizontal center lines, symmetry center lines, and theoretical height lines are drawn in the x, y, and z directions of the theoretical model. The theoretical model has uniform allowances in all directions relative to the cabin design model, and all allowances are design allowances. In one possible design, the casting allowance in all directions is 2 mm; S203. Using analysis software, identify and determine the remaining amount of reference points A, B, C, and D on the four process reference blocks of the metal cabin blank scanning model; The margins in the x, y, and z directions of the reference point are A (A x A y A z ), B (B x B y B z ), C (C x C y C z ), D (D x D y D z ); S204. Select any three points A, B, C, and D with actual allowances and perform bench scribing on the metal cabin blank in three directions: horizontal, symmetrical, and vertical; thus creating a machining datum.

[0039] Furthermore, the horizontal scriber marking steps are as follows: Step 1: Place the thin-walled compartment blank on the marking platform and support it with jacks. The process reference blocks on the front and rear ends are parallel to the radial center line of the end face and are horizontal. Points A, B, C, and D are above the radial center line of the process reference blocks. Step 2: Locate point A on the corresponding process reference block, and use a height gauge to measure and determine the reading HA. x Adjust the jack to adjust the height of the object so that the reading at point A is HA. x At that time, points B and C are respectively HA x -(A x -B x ), HA x -(A x -C x At this point, measuring and verifying point D should yield HA. x -(A x -D x If the error at point D exceeds the allowance requirement, readjust and check the scan allowance. In one possible design, the margin requirement is 0.3 mm.

[0040] Step 3: After adjustment, measure the value A of point A on the process reference block A relative to the horizontal center line of the theoretical model. x0 At this point, adjust the height gauge reading to HA. x -A x0 -A x Then draw horizontal baselines on the front and rear end faces, and extend them to the shape of the compartment. Furthermore, the symmetrical direction fitter marking steps are as follows: Step 1: Rotate the blank of the thin-walled compartment section that has been horizontally scribing on the scribing platform by 90 degrees. At this time, the reference block where point A is located is at the lower edge of the front end face of the compartment. Use a jack to lift the part. Before scribing, use the horizontal reference line of both ends of the right angle ruler to find the alignment. Then use the y-direction allowance of points A and C to scribing. Step 2: Locate point A on the corresponding process reference block, and use a height gauge to measure and determine the reading HA. y Adjust the jack to adjust the height of the object so that the reading at point A is HA. y At that time, point C is HA respectively. y -(A y -Cy ); Step 3: After adjustment, measure the value A of point A on the process reference block A relative to the center line of symmetry of the theoretical model. y0 At this point, adjust the height gauge reading to HA. y +(A y0 -A y Then draw symmetrical baselines on the front and rear end faces, and extend them to the shape of the compartment.

[0041] Furthermore, the height-direction metalworking marking steps are as follows: Step 1: Place the thin-walled compartment blank, with horizontal and symmetrical markings completed on the marking platform, upright on the platform and adjust it using a jack. Use a right-angle ruler to align the horizontal and symmetrical baselines. No further adjustments based on other points are needed. Then, using the allowance in the Z direction at point A, mark the height line and measure the reading HA at point A. z .

[0042] Step 2: After adjustment, measure the value A of point A on the theoretical model's process reference block relative to the cabin's design height. z0 At this point, adjust the height gauge reading to HA. z -A z0 -A z Then, draw the height line at one end of the cabin, and then draw the height line at the other end of the cabin according to the cabin's design height.

[0043] Further, in step S3, the irregular metal cabin is clamped with tooling and placed on the machine tool workbench. According to the fitter's scribing, the front and rear end faces are first machined using machine tool equipment, and the horizontal symmetry reference is transferred so that the plane formed by the symmetry reference lines at both ends of the cabin and the plane formed by the horizontal reference lines at both ends of the cabin are parallel to the vertical plane and horizontal plane of the machine tool coordinate system, respectively. The metal cabin is then rough-machined. After processing, the alignment is performed according to the processing datum created in the state of the casting. The alignment method is to measure the wall thickness, adjust the cabin body according to the wall thickness measurement result to make the allowance in all directions uniform, and then clamp it. Under the synchronous clamping state, the pin hole is machined on the metal cabin body process datum block. The pin hole is located at the center of the process reference block.

[0044] Further, in step S4, the metal cabin after rough machining is scanned with a laser. The machined pin holes are used as the scanning fitting reference for data comparison and fitting. Based on the fitting results, the cabin clamping posture is adjusted to ensure that the allowance is uniform and consistent with the rough machining allowance, and that the reference coincides with the machining reference established in step S2.

[0045] Further, in step S5, the metal cabin after adjustment and clamping is precision machined, and the pin holes on the original process reference block are enlarged after precision machining; the same method as in step S3 is used for alignment; the precision machined metal cabin is laser scanned, and the enlarged pin holes are used as the initial processing reference for stacking for scanning and fitting, the clamping posture is adjusted, and it coincides with the processing reference established in step S2.

[0046] Further, in step S8, the measurement and adjustment are carried out by using a dial indicator to measure according to the characteristics of the metal cabin of the composite material processing part, recording the shape and position dimensions of the composite material after rough processing and the shape and position dimensions of the processed metal cabin, calculating the deviation between the shape and position of the composite material after rough processing and the metal cabin, and adjusting the clamping position of the cabin to meet the allowance value after rough processing of the composite material through tooling.

[0047] Preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings, which form part of this application and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not intended to limit the scope of the present invention.

[0048] Example The following process is used to process irregularly shaped thin-walled sections of composite-metal laminates, which consist of two parts.

[0049] The first part, the metal hull fabrication and tooling implementation process, is as follows: Step 1: The metal hull is cast and formed, and the fitter marks the lines and establishes the initial machining datum for the casting; Step 2: Place the adjustment component 100 on the machine tool worktable, place the metal housing on the adjustment bracket 130, check that the bracket surface fits the metal housing surface, and confirm that the placement position is correct; Step 3: Adjust the position of the tooling with the product on the machine tool so that the plane formed by the symmetrical lines drawn at both ends of the cabin is parallel to the vertical plane of the machine tool coordinate system; Step 4: Adjust the pitch of the cabin by adjusting the height of the two adjustment brackets 130 near the outermost part of the length direction, so that the plane formed by the horizontal lines drawn at both ends of the cabin is parallel to the horizontal plane of the machine tool coordinate system; Step 5: Using the retaining ring 200, adjust the extension position of the screw 203 on the retaining ring 200 so that the conformal pressure plate 202 fits and is pressed tightly against the metal cabin surface; Step 6: Machin the process reference blocks at both ends (including the end face of the cabin) so that the machined surfaces are perpendicular to the plane formed by the symmetry line and the plane formed by the horizontal line; and add pin holes on the process reference blocks according to the set dimensions. Step 7: Adjust the position of the first roller assembly 120 (the roller's axial position on the product) along the length direction according to the length of the metal cabin. After the position is adjusted, use screws 128 to fix the first roller assembly 120 to the base 110. Step 8: The tie rod 400 is inserted into the inner cavity of the metal cabin and connected to the outer flanges 500 at both ends. Threaded nuts are used on the tie rod parts on the outside of the flanges. Rotate the nuts to press the flanges and the metal cabin together. At the same time, pins are inserted into the pin holes of the outer flanges 500 and the process reference blocks on the metal cabin for positioning. Step 9: The lower guide rail 122 of the first roller assembly 120 slides on the upper guide rail 121 to adjust the position of the roller (the roller is in the radial position of the product) so that the roller and the outer circle are in close contact and tangent to the outer circle of the flange. Step 10: Fix the machine tool A-axis rotary table to the truncated cone 500 centered on the outer flange at one end of the cabin, and use a pressure plate to assist in pressing the outer flange. Step 11: Place the clamping frame 300 on the machine tool worktable and adjust the position (axial position) of the clamping frame 300 to be on the same plane as the center of the second roller assembly; adjust the height of the clamping frame 300 by extending the clamping frame screw 306; adjust the position of the rollers of the second roller assembly 308 so that the rollers and the outer circle are in contact and tangent to the outer circle of the flange. Step 12: Remove the retaining ring 200, adjust the adjusting bracket 130 to a certain distance from the cabin body (the distance should be greater than the distance from the center of the outer flange to the maximum outer diameter of the cabin body, ensuring that the cabin body rotation does not interfere with the bracket), and machine the outer shape of the cabin body; the cutting tool feeds along the radial direction of the cabin body. By rotating the machine tool A-axis rotary table, the outer flange 500 is rotated to complete the machining of the cabin body outer shape; Step 12: After the outer shape is processed, adjust the position of the adjusting bracket 130 to fit the cabin body and support the cabin body; at the same time, install the retaining ring and the adjusting assembly 100, and adjust the position of the conformal pressure plate 202 to press the cabin body; adjust the position of the rollers of the second roller assembly on the clamping frame and adjusting assembly (on the side not connected to the machine tool A axis) so that the rollers are away from the outer flange 500. Step 13: Remove the tie rod 400 from the two outer flanges 500 on both sides; Step 14: Replace the external flange 500 that is not connected to the machine tool A-axis rotary table with the internal flange 600; connect the tie rod 400 from the outside of the metal housing to the external flange 500 at the machine tool A-axis end and the replaced internal flange 600, and rotate it; use the nut on the tie rod 400 to press the flange to the metal housing; at the same time, use pins to sequentially insert the replaced internal flange 600 into the pin holes of the process reference block on the metal housing for positioning; Step 15: Readjust the position of the rollers on the second roller assembly 308 on the clamping frame 300 and the adjustment assembly 100 according to steps 9 and 10; Step 16: Rotate the machine tool worktable 90° so that one end of the inner flange 600 is perpendicular to the machine tool cutting tool; Step 17: Machining the inner cavity of the metal cabin. Similarly, by rotating the A-axis turntable of the machine tool, the outer flange 500 is rotated to complete the machining of the inner cavity of the cabin.

[0050] After rough machining of the entire shape of the inner and outer metal compartments, a stress relief process is performed, followed by finish machining. The finish machining method is the same as the rough machining method.

[0051] After the metal cabin is processed, it is bonded to the composite material, and then the composite material-metal cabin are processed to form a laminated structure.

[0052] Part Two, the process of fabricating and tooling for the composite material-metal cabin laminate structure, includes the following steps: Step 1: Place the adjustment component 100 on the machine tool worktable, and place the laminated structure cabin on the adjustment bracket 130 (replace the bracket with a bracket that matches the composite material surface of the laminated structure cabin). Check that the bracket surface fits the cabin surface to confirm that the placement is correct. Step 2: By adjusting the position of the tooling with the product on the machine tool, use a dial indicator to find the center of the line connecting the centers of the pin holes on the two process reference blocks on the end face of the cabin, and the line formed by the center of the line connecting the centers of the pin holes at the front and rear ends. The plane parallel to the vertical plane of the machine tool is the plane of symmetry. Step 3: Adjust the pitch of the cabin by adjusting the height of the two outermost adjustment brackets 130 near the length direction, so that the line connecting the centers of the pin holes on the two process reference blocks on the end face of the cabin is parallel to the horizontal plane of the machine tool and on the same plane, and the plane formed is a horizontal plane. Step 4: Using the retaining ring 200, adjust the extension position of the screw 203 on the retaining ring 200, and press the conformal pressure plate 202 against the composite material surface (replace the conformal pressure plate with a bracket that matches the composite material surface of the laminated structure cabin). Step 5: Roughly machine the composite material end face with a margin; after rough machining, use the metal cabin end face as a reference, adjust the program, and fine machine the composite material end face to ensure that the composite material end face is flush with the metal cabin end face after machining. Rotate the machine tool 180° to machine the other end face. Step 6: Clamp the laminated structure product according to steps 7 to 11 in the metal cabin implementation method, and process the various features of the composite material in the shape after assembly; Step 7: Clamp the product according to steps 3 and 4 of the layer structure tooling implementation process. After clamping, adjust the position of the rollers respectively, remove the outer flange 500 and the clamping frame 300, and remove the end face process chuck with the metal cabin as the reference to complete the product processing.

[0053] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention.

Claims

1. A method for processing irregularly shaped thin-walled compartment sections of composite material-metal laminates, characterized in that, Includes the following steps: S1. The irregular metal cabin body is cast, and four cuboids are cast together with the cabin body as process reference blocks during the casting process. The process reference blocks are distributed, with two on each of the front and rear end faces of the cabin body, and the two process reference blocks on each end face are symmetrically arranged. The process reference blocks on the front and rear end faces are parallel to the center line of the radial direction of the end face. S2. Establish initial machining benchmarks; S3. Rough machining of irregular metal cabins; S4. Measure and adjust the precision machining benchmarks for irregular metal cabins; S5. Perform precision machining on irregular metal cabins; S6. Prepare composite materials and bond the composite material layers to the outside of the irregular metal cabin. S7. Rough machining of composite material layer; S8. Perform precision machining on all parts of the composite material, remove the process reference blocks on the metal housing, and complete the product processing. The establishment of the initial machining datum in the irregular metal cabin casting state described in step S2 includes: S201. Perform laser scanning on the metal cabin and scan the process reference block simultaneously. S202. Fit the laser scanning results to obtain the physical cabin scanning model, compare it according to the allowance requirements, and adjust the fitting position to ensure that the allowance of the inner and outer surfaces is uniform, and determine whether the part meets the casting allowance requirements. S203. Using analysis software, identify and determine the margin of reference points A, B, C, and D on the four process reference blocks of the metal cabin blank scanning model; the margins in the x, y, and z directions of the reference points are A(Ax, Ay, Az), B(Bx, By, Bz), C(Cx, Cy, Cz), and D(Dx, Dy, Dz), respectively. S204. Select any three points A, B, C, and D with actual allowances and perform bench scribing on the metal cabin blank in three directions: horizontal, symmetrical, and height; thus creating a machining datum. The composite material layer is processed using a method that uses the metal cabin as a reference and gradually approximates the composite material. The following tooling is used for machining thin-walled sections: adjustment assembly (100), retaining ring (200), clamping bracket (300), tie rod (400), and flange; One end of the retaining ring (200) is fixed and movably connected to one side of the adjusting assembly (100), and the other end is detachably or fixedly connected to the other side of the adjusting assembly (100). The clamping bracket (300) is disposed at one end of the adjusting assembly (100) and is used to clamp and fix the flange at one end; There are at least two flanges, and the lower end of each flange can be supported above one end of the adjusting assembly (100); The two ends of the tie rod (400) are respectively inserted into the axial through holes of the flanges at both ends of the adjusting assembly (100).

2. The processing method for the irregularly shaped thin-walled compartment section of composite material-metal laminate according to claim 1, characterized in that, The thin-walled compartment is a laminated structure formed by bonding an outer composite material and an inner irregular metal compartment. The machining fixture is used for clamping the metal compartment and the laminated structure after bonding the metal compartment and the composite material on a full-form machine tool. The metal compartment has a process reference block for machining positioning, and the process reference block has pin holes for connection.

3. The processing method for the irregularly shaped thin-walled compartment section of composite material-metal laminate according to claim 2, characterized in that, The adjustment assembly includes a base (110) and a first roller assembly (120), an adjustment bracket (130), a rotating nut (140), and a limiting assembly (150) mounted on the base. The adjusting bracket (130) is raised and lowered by rotating the nut (140) to adjust the pitch position of the thin-walled compartment. There are at least two first roller assemblies (120) installed at both ends of the base (110). The installation position of the thin-walled compartment is adjusted by the first roller assemblies (120) to adapt to thin-walled compartments of different sizes. There are at least two limiting assemblies (150) installed at both ends of the base (110) to limit the axial position of the thin-walled compartment.

4. The processing method for the irregularly shaped thin-walled compartment section of composite material-metal laminate according to claim 3, characterized in that, The retaining ring (200) is installed on both sides of the base (110) via a pressure plate mounting component. The retaining ring (200) has a conformal pressure plate (202) with an adjustable distance from the outer surface of the thin-walled compartment on its inner surface facing the thin-walled compartment.

5. The processing method for the irregularly shaped thin-walled compartment section of composite material-metal laminate according to claim 3, characterized in that, The clamping frame (300) includes a clamping frame crossbeam, a vertical beam, and an inclined beam with both ends fixed near one end of the clamping frame crossbeam and the vertical beam, respectively; a connecting seat is provided at the lower end of the vertical beam; the connecting seat is connected to the lower end of the vertical beam by a shoulder screw, and the height of the clamping frame (300) is adjusted by adjusting the extension length of the screw; a second roller assembly (308) is provided on the side of the inclined beam facing the thin-walled compartment, and the clamping degree of the clamping frame (300) is adjusted by the second roller assembly (308).

6. The processing method for the irregularly shaped thin-walled compartment section of composite material-metal laminate according to claim 2, characterized in that, The flange includes an external flange (500) and an internal flange (600); there are at least two external flanges (500), and the lower end of the external flange (500) can be supported above one end of the adjusting assembly (100); there are at least two internal flanges (600), and the lower end of the internal flange (600) can be supported above one end of the adjusting assembly (100); one of the external flange (500) and the internal flange (600) can be used.

7. The processing method for the irregularly shaped thin-walled compartment section of composite material-metal laminate according to claim 6, characterized in that, The outer flange (500) has a frustum at one end for positioning with the center of the machine tool turntable; it has a hole with the same size and position as the pin hole of the metal cabin process reference block; the outer flange (500) also has a limiting hole for uniform distribution design, and the pin is inserted into the pin hole on the limiting component (150) and the limiting hole of the outer flange (500) in sequence.

8. The processing method for the irregularly shaped thin-walled compartment section of composite material-metal laminate according to claim 7, characterized in that, The inner flange (600) is provided with a hole whose size and position are consistent with the pin hole of the product process reference block, for fixing the inner flange (600) to the product by inserting a pin shaft; the inner flange (600) also has a limiting hole for uniform distribution design, and the pin is inserted into the pin hole on the limiting component (150) and the limiting hole of the inner flange (600) in sequence.

9. The processing method for the irregularly shaped thin-walled compartment section of composite material-metal laminate according to claim 8, characterized in that, When machining the metal cabin body with a machine tool, the tie rod (400) is inserted into the inner cavity of the metal cabin body and connected to the outer flanges (500) at both ends of the cabin body respectively. The outer flanges (500) are pressed against the metal cabin body by rotating nuts. The outer flange (500) at one end of the cabin body is fixed to the machine tool turntable by a centrally positioned frustum. The outer flange (500) at the other end of the cabin body is connected to the clamping frame (300) by the second roller assembly (308). After the connection is completed, the tooling components used for positioning and clamping are disengaged from the metal cabin body.

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