Helical hole milling method and device for heterogeneous composite multi-laminated component of airplane

Abstract

The invention discloses a spiral hole milling method and device for a heterogeneous composite multi-laminated component of an airplane, and belongs to the technical field of composite multi-laminated component material machining. According to the material type of the heterogeneous composite multi-laminated component, the thickness of the heterogeneous composite multi-laminated component and the heat treatment state of the material, the cutter length, the cutter diameter and the eccentricity are determined; s, according to the determined cutter length, cutter diameter and eccentricity, parameters of revolution speed, rotation speed and feeding speed of cutter cutting are set; after the heterogeneous composite multi-laminated component is clamped and fixed, through holes are milled in a layered machining and differential feeding mode. The large hole drilling capacity of a small cutter is effectively improved, the number of cutters is reduced, and the key technology of large-aperture and large-thickness hole forming of the heterogeneous composite multi-laminated component, which is difficult to achieve through a traditional machining technology, is broken through; the technical problems that in the single-tool drilling process of the heterogeneous composite multi-laminated component of the civil aircraft, the drilling quality is poor, and composite material holes are burnt, layered, split and the like are solved.

Description

Technical Field

[0001] The invention belongs to the technical field of composite multi-layer component material processing, and in particular relates to a method and a device for spiral milling holes of aircraft heterogeneous composite multi-layer components. Background Art

[0002] In order to meet the requirements of lightweight design of civil aircraft, high-strength and lightweight materials such as high-strength aluminum alloy, titanium alloy, A100 new ultra-high-strength steel, and T800-grade composite materials are generally used in aircraft structure selection, and the configuration of aircraft parts is gradually developing towards a laminated structure of different materials. Due to the large diameter and depth of the laminated structure hole, high quality requirements, and high processing difficulty, when the traditional "drilling-expansion-reaming" method is used to make holes, the tool needs to be frequently replaced during the hole making process, the operation is cumbersome, the processing efficiency is low, and the types and quantities of tools used are large, the tool cost is high, and the labor intensity of workers is high. Therefore, high-quality, efficient and low-cost processing technology for large-diameter and large-depth intersection holes has become an urgent need for on-site model development and production, and the spiral milling process technology has significant advantages in reducing the types of tools, reducing tool loss, and improving hole making quality due to its processing principle that is different from the traditional drilling process.

[0003] The spiral milling process is essentially a "milling instead of drilling" process. Its notable feature is that the tool feed trajectory is spiral. The movement of the spiral milling tool consists of three parts, namely the rotation of the tool around its own axis, the revolution of the tool around the center axis of the machined hole, and the axial feed motion of the tool; the combined motion of these three motions enables the tool to cut into and remove workpiece material in a spiral feed manner around the center of the hole; in the spiral milling process, the rotation of the tool is the main motion, and the circumferential (revolution around the center axis of the hole) and axial motions of the tool are feed motions.

[0004] During the spiral milling process, the tool rotates at high speed around its own axis and feeds spirally around the hole axis. The special feeding motion of spiral milling makes the peripheral edge and end edge of the tool participate in cutting at the same time, among which the peripheral edge cuts intermittently, the cutting method is milling, and the end edge cuts continuously, the cutting method is similar to drilling.

[0005] The main differences between spiral milling and traditional drilling are: a) The spiral milling process can use a smaller diameter tool to machine a larger diameter hole. It can process large diameter holes and complex step holes that cannot be machined with a single tool. It can also implement real-time compensation for the hole diameter based on actual conditions. It is especially suitable for making holes in laminated materials.

[0006] b) Spiral milling is intermittent cutting, which is not only easy to remove chips, but also conducive to the heat dissipation of the tool, which can reduce the high-temperature wear of the tool caused by heat accumulation and increase the service life of the tool. More importantly, compared with drilling, spiral milling has a significant improvement in the use of coolant. The entire milling process can be cooled by micro-lubrication or even air cooling, which is a green processing technology.

[0007] c) The processing mechanism of spiral milling is completely different from traditional drilling. The axial force of spiral milling is much smaller than that of traditional drilling, which makes the hole have good outlet quality, especially for carbon fiber composite materials with low interlayer strength. The diameter of the tool used for spiral milling is smaller than the hole to be processed, which makes it easy to remove chips and effectively prevents damage to the processed surface, thus improving the quality of the hole.

[0008] Dong Zhigang and others from the Key Laboratory of Precision and Special Machining of Dalian University of Technology studied the method of suppressing axial force in CFRP spiral milling. They analyzed the relationship between the tool tooth clearance angle and the undeformed chips from the kinematic principle, and proposed a method to prevent the center area of ​​the tool with lower cutting line speed from participating in cutting. They further derived the conditions for preventing the tool center from participating in cutting. By increasing the tool tooth clearance angle and reducing the lead, the center area of ​​the blade can be prevented from participating in cutting in spiral milling, thereby effectively reducing the axial force in CFRP spiral milling. This article only reduces the axial force of single-layer composite hole making to increase the hole making quality.

[0009] Wang Haiyan and others from Northeastern University invented and disclosed an inclined planetary spiral milling method for carbon fiber composite materials. It only describes making the relative movement speed of the center point of the contact surface between the tool and the carbon fiber composite material non-zero, thereby reducing the resistance of milling, increasing processing efficiency and improving the problems of burrs and delamination.

[0010] Bi Yunbo and others from Zhejiang University disclosed a variable parameter controlled hole making method for aircraft laminated structures. The laminated structure only includes a carbon fiber composite material layer and a titanium alloy layer. Holes are made by dynamically adjusting tool parameters. There are only two layers, and other composite metal parts-based and metal composite-based multi-laminate structures are not involved.

[0011] Therefore, there is an urgent need for a method and device for spiral milling holes in aircraft heterogeneous composite multi-layer components. Summary of the invention

[0012] The purpose of the present invention is to provide a method and device for spiral milling of aircraft heterogeneous composite multi-layer components, which can effectively improve the ability of a small knife to drill large holes and save cutting tools, so as to break through the key technology of large-diameter and large-thickness hole making of laminated materials that is difficult to achieve with traditional processing technology, and solve the technical problems of poor hole making quality, composite material hole burning, delamination and splitting in the single-knife hole making process of civil aircraft heterogeneous composite multi-layer components.

[0013] To achieve the above purpose, the technical solution adopted by the present invention is as follows: In one aspect, the present invention provides a method for spiral milling holes in a heterogeneous composite multi-layer component of an aircraft, wherein the heterogeneous composite multi-layer component comprises an outer material layer and one or more inner material layers located below the outer material layer, comprising the following steps: S1, determining the tool length, tool diameter and eccentricity according to the material type of each layer of the heterogeneous composite multi-layer component, the material heat treatment state and the thickness of the layer; S2, according to the tool length, tool diameter and eccentricity determined in S1, set the revolution speed, rotation speed and feed speed parameters of the tool cutting; S3, after the heterogeneous composite multi-layer components are clamped and fixed, through holes are milled out by layered processing and differential feeding.

[0014] Furthermore, S1 is specifically: According to the hole diameter D1 to be processed of the heterogeneous composite multi-layer component material; select the tool diameter d1 (d1> D1); The eccentricity of the tool is adjusted to e1 = (D1-d1) / 2 (1); Among them, e1 is the tool eccentricity, D1 is the hole diameter, and d1 is the tool diameter.

[0015] Furthermore, the method further comprises step 4, performing a countersinking operation on the heterogeneous composite multi-layer component after the spiral milling process in step 3, leaving a margin of 0.1 mm to 0.3 mm in the countersink depth direction, and performing supplementary countersinking to achieve the final accuracy; the calculation formula of the countersink eccentricity is: e2=(D2-d2) / 2(2); Among them, e2 is the countersink eccentricity, D2 is the socket diameter, and d2 is the countersink drill diameter; The formula for calculating the countersink depth is: H=(D2-D1)×tan-1(α / 2)(3); Among them, H is the countersink depth, D2 is the cavity diameter, D1 is the hole diameter, and α is the countersink angle.

[0016] Furthermore, in S1, when the types of laminated materials of the heterogeneous composite multi-layer component are different, the layered processing and differential feed methods should be used for milling, and the position for changing the spiral milling parameters should be selected according to the type of laminated material; when the outer material is a metal material and the inner material is a composite material, the tool cutting revolution speed, rotation speed and feed speed parameters are changed when milling through the metal material; when the outer material is a composite material and the inner material is a metal material, the tool cutting revolution speed, rotation speed and feed speed parameters are changed in the composite material layer.

[0017] Furthermore, when milling holes, when the laminated material is transferred from aluminum alloy, titanium alloy or alloy steel material to composite material, when the tool axial feed to the composite material layer is at least more than the tool tip arc radius, the tool cutting parameters are adjusted to the milling parameters of the composite material; when the laminated material is transferred from the composite material to the aluminum alloy, titanium alloy or alloy steel material layer, when the composite material milling allowance is close to 0.3 mm, the tool cutting parameters are adjusted to the milling parameters of the aluminum alloy, titanium alloy or alloy steel material.

[0018] Furthermore, when milling holes, when the laminated materials are different types of metal materials, the milling parameters are adjusted in the material layer where the tool rotation speed is higher.

[0019] Furthermore, for heterogeneous composite multi-layer components with gaps, when the front end of the tool is still within the gap after the tool mills through the outer material layer, that is, the radius of the tool side edge is all within the gap, the tool cutting parameters (orbital speed, rotation speed, feed speed) are changed to the parameters corresponding to the next milling layer material within the gap; otherwise, the parameters are set according to the above principles.

[0020] On the other hand, the present invention also provides a heterogeneous composite multi-layer spiral milling hole processing device, which includes a tool, a connecting sleeve is provided at one end of the tool, and a round shaft is provided at the front end of the connecting sleeve; the round shaft is used to connect with the mounting hole reserved on the drilling template.

[0021] Furthermore, one end of the connecting sleeve is provided with a round shaft connected to a vacuum cleaner to vacuum chips during the processing.

[0022] Furthermore, the connecting sleeve is provided with a clamping claw, which hooks the stepped shaft screw on the drilling template to complete the docking of the drilling template and the rotary milling hole processing device.

[0023] Compared with the prior art, the present invention has the following beneficial technical effects: The present invention provides a method for spiral milling holes of aircraft heterogeneous composite multi-layer components. According to the material type, thickness and heat treatment state, the tool length, diameter and eccentricity are determined, and the processing parameters such as the revolution speed, rotation speed and feed speed of the spiral milling holes of the heterogeneous composite multi-layer components are formulated; and a method for calculating the countersink depth is established. Thus, the spiral milling hole processing of the one-time composite multi-layer structure is solved, the ability of the small knife to drill large holes is effectively improved and the tool is saved, and the key technology of large-diameter and large-thickness hole making of heterogeneous composite multi-layer components that are difficult to achieve with traditional processing technology is broken through; the technical problems such as poor hole making quality, composite material hole burning, delamination and splitting in the single-knife hole making process of civil aircraft heterogeneous composite multi-layer components are solved. This method can not only reduce the number of tool changes, save production preparation time, and improve processing efficiency, but also reduce the company's tool inventory and reduce production costs.

[0024] The present invention improves hole making efficiency, reduces production costs, and facilitates automation. Unlike the drilling process, this method uses a smaller diameter tool to process a larger diameter hole. It can process large diameter holes and complex step holes that cannot be processed by a single tool, and can implement real-time compensation for the hole diameter according to actual conditions. It is particularly suitable for making holes in heterogeneous laminated materials. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 The present invention is a flowchart of a method for spiral milling holes in a heterogeneous composite multi-layer component of an aircraft according to an embodiment of the present invention.

[0026] Figure 2a It is a schematic diagram of processing heterogeneous laminated materials in a spiral milling method for an aircraft heterogeneous composite multi-laminate component in an embodiment of the present invention.

[0027] Figure 2b It is a schematic diagram of processing heterogeneous laminated materials in a spiral milling method for an aircraft heterogeneous composite multi-laminate component in an embodiment of the present invention.

[0028] Figure 3 The figure is a schematic diagram of the axial feed distance of countersinking in a spiral hole milling method for an aircraft heterogeneous composite multi-layer component according to an embodiment of the present invention.

[0029] Figure 4 Schematic diagram of a heterogeneous composite multi-layer spiral milling hole processing device in an embodiment of the present invention.

[0030] In the figure, 1. tool; 2. connecting sleeve; 3. round shaft; 4. vacuum cleaner. DETAILED DESCRIPTION

[0031] In order to enable those skilled in the art to better understand the scheme of the present invention, the technical scheme in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work should fall within the scope of protection of the present invention.

[0032] It should be noted that the terms "first", "second", etc. in the specification and claims of the present invention and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the data used in this way can be interchanged where appropriate, so that the embodiments of the present invention described herein can be implemented in an order other than those illustrated or described herein. In addition, the terms "including" and "having" and any variations thereof are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device that includes a series of steps or units is not necessarily limited to those steps or units that are clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0033] A spiral milling method for aircraft heterogeneous composite multi-layer components can effectively improve the ability of a small knife to drill large holes and save cutting tools, so as to break through the key technology of traditional processing technology that is difficult to process large-diameter and large-thickness holes in laminated materials, and solve the technical problems of poor hole quality, composite material hole burns, delamination and splitting in the single-knife hole making process of civil aircraft heterogeneous composite multi-layer components.

[0034] Example 1 See also Figure 1 and Figure 4 A spiral milling method for an aircraft heterogeneous composite multi-layer component, wherein the heterogeneous composite multi-layer component comprises an outer material layer and one or more inner material layers located below the outer material layer, specifically comprising the following steps: S1, determining the tool length, tool diameter and eccentricity according to the material type of each layer of the heterogeneous composite multi-layer component, the material heat treatment state and the thickness of the layer; S2, according to the tool length, tool diameter and eccentricity determined in S1, set the revolution speed, rotation speed and feed speed parameters of the tool cutting; S3, after the heterogeneous composite multi-layer component is clamped and fixed by a drilling template, a through hole is milled out by layered processing and differential feeding.

[0035] In S1, the laminates in the heterogeneous composite multi-layer component are different types of materials. Each material and its heat treatment state are confirmed, and the thickness of each material layer and the lamination sequence are obtained.

[0036] Determine the tool length, tool diameter and eccentricity as follows: Calculate the machining hole diameter D1; Select tool length and tool diameter d1 (d1> D1); The eccentricity of the tool is adjusted to e1 = (D1-d1) / 2; Among them, e1 is the tool eccentricity, D1 is the hole diameter, and d1 is the tool diameter.

[0037] Regarding the tool length requirement, ensure that after the tool is installed, there is a safe feed distance between the tool tip and the surface of the part and that it does not interfere with the part.

[0038] In S2, tests were conducted on spiral milling holes of commonly used specifications of product assembly composite materials + aluminum alloy / titanium alloy / structural steel, aluminum alloy / titanium alloy / structural steel + composite materials, aluminum alloy / titanium alloy / structural steel + composite materials + aluminum alloy / titanium alloy / structural steel, and aluminum alloy + titanium alloy + structural steel laminated structures in combination with product requirements. The results were qualified after testing and met the engineering design requirements. The parameters of the machining and cutting revolution speed, rotation speed, and feed speed of spiral milling holes of different materials were optimized and solidified (see Table 1).

[0039] Table 1 Cutting parameters of spiral milling

[0040] In S3, the drill template is a drill template with concentric circles of the holes to be made, which mainly guides and limits the tool. Due to the obvious anisotropy of composite materials, burrs, tears, delamination and other processing damages are prone to occur during the hole making process, which seriously affects the processing quality. When processing composite materials, the upper and lower surfaces of heterogeneous composite multi-layer components should be clamped to prevent the tool from causing delamination of the processed surface at the entry or exit. Titanium alloy materials have a small elastic modulus and the workpiece is easy to deform. The clamping force should not be too large during cutting. Auxiliary supports should be used when necessary. The actual cutting force should be considered when designing the drill template structure to ensure the reliability and rigidity of the clamping, which should be conducive to controlling the deformation of parts during processing.

[0041] In some preferred embodiments of the present invention, S4 is further included, wherein a countersinking operation is performed on the heterogeneous composite multi-layer component after the spiral milling process in S3. The product countersinking can be performed only after the trial countersinking is qualified. During the countersinking, a margin of 0.1 mm to 0.3 mm is generally left in the direction of the depth of the cavity, and supplementary countersinking is performed to achieve the final accuracy. The calculation formula of the countersinking eccentricity is: e2=(D2-d2) / 2; Among them, e2 is the countersink eccentricity, D2 is the socket diameter, and d2 is the countersink drill diameter; The formula for calculating the countersink depth is: H=(D2-D1)×tan-1(α / 2); Among them, H is the countersink depth, D2 is the cavity diameter, D1 is the hole diameter, and α is the countersink angle Example 2 The spiral milling process of heterogeneous composite multi-layer structure described in this patent has a typical laminated structure as follows: Holes are made according to the aforementioned method based on the material types of the two adjacent layers. The spiral milling cutting parameters of different laminated materials are shown in Table 1.

[0042] like Figure 2a , 2b As shown, when milling holes, when the laminated material is transferred from aluminum alloy, titanium alloy or alloy steel material to composite material, when the tool axial feed to the composite material layer is at least more than the tool tip arc radius, the tool cutting parameters are adjusted to the milling parameters of the composite material. When the laminated material is transferred from the composite material to the aluminum alloy, titanium alloy or alloy steel material layer, when the composite material milling allowance is close to 0.3mm, the tool cutting parameters are adjusted to the milling parameters of the aluminum alloy, titanium alloy or alloy steel material. When milling holes, when the laminated materials are different types of metal materials, the milling parameters are adjusted in the material layer with a higher tool rotation speed.

[0043] For heterogeneous composite multi-layer components with gaps, when the front end of the tool is still within the gap after the tool mills through the outer material layer, that is, the radius of the tool side edge is all within the gap, the tool cutting parameters (orbital speed, rotation speed, feed speed) are changed to the parameters corresponding to the next milling layer material within the gap; otherwise, the parameters are set according to the above principles.

[0044] Before processing the product, at least 3 holes are processed on the test plate to verify the set speed and feed parameters. After passing the test, the set and revised parameters are used for formal product hole making. The test plate is made of the same laminate material as the product, and the thickness is as consistent or close to the product laminate as possible. It can be a whole piece or a combination to achieve the required thickness; the test plate laminate form selects the typical laminate of the product, and the material and lamination sequence are the same as those of the product. The thickness of each layer of the test plate is as consistent or close as possible to the thickness of each laminate of the product.

[0045] Example 3 See also Figure 4 The present invention also provides a heterogeneous composite multi-layer spiral milling hole processing device, which includes a tool 1, a connecting sleeve 2 is provided at one end of the tool 1, and a round shaft 3 is provided at the front end of the connecting sleeve 2; one end of the connecting sleeve 2 provided with the round shaft 3 is connected to a vacuum cleaner 4; and a clamping claw is provided on the connecting sleeve.

[0046] Experiment on application parameters of spiral milling (1) Test conditions The processing hole diameters are Φ12mm, Φ14mm, Φ16mm, Φ18mm, and Φ20mm; the processed materials are carbon fiber reinforced composites (CFRP) and titanium alloys (TC4 / TC21). The laminated structure and its spiral milling cutting parameters are shown in Table 2.

[0047] Table 2 Cutting parameters of spiral milling of titanium-composite-titanium laminated structure

[0048] Furthermore, a digital internal micrometer can be used to detect the aperture size; a portable roughness meter can be used to spot check the aperture roughness; the degree of composite material splitting can be visually observed, and the burning of the composite material can be observed using an optical microscope; the height of the exit flash burr can be checked using an ultra-depth of field microscope; and large-scale measuring instruments can be used to detect surface integrity.

[0049] (2) Experimental process For each hole diameter of each material, we first determine a better processing plan by adjusting the processing parameters and tools; then, based on this processing plan, we continuously process 5 to 10 holes to test the stability.

[0050] The heterogeneous composite multi-layer component that needs to be milled is installed on a drilling template, which is used to clamp the heterogeneous composite multi-layer component, and further the drilling template is docked with a rotary milling hole processing device.

[0051] The spiral milling hole processing device includes a tool 1, one end of which is provided with one end of a connecting sleeve 2, the connecting sleeve 2 is positioned by a shaft shoulder and fixed on the tool 1 by four M6 bolts, the other end of the connecting sleeve 2 is provided with a round shaft 3, the two are connected by a flange, and the round shaft 3 is used to dock with the mounting hole reserved on the drilling template; the connecting sleeve 2 is provided with one end of the round shaft 3 connected to a vacuum cleaner 4 for vacuuming chips during the processing process, after the installation of each connecting parts is completed, the heterogeneous composite multi-layer spiral milling hole processing device is held in hand to make the round shaft 3 at the front end of the connecting sleeve 2 extend into the mounting hole on the drilling template, and then the heterogeneous composite multi-layer spiral milling hole processing device is adjusted so that the claw on the connecting sleeve 2 hooks the stepped shaft screw on the drilling template, the drilling template and the spiral milling hole equipment are docked, and the processing test can be started.

[0052] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A method for spiral milling holes in a heterogeneous composite multi-layer component of an aircraft, wherein the heterogeneous composite multi-layer component comprises an outer material layer and one or more inner material layers located below the outer material layer, characterized in that: The following steps are involved: S1, determining the tool length, tool diameter and eccentricity according to the material type of each layer of the heterogeneous composite multi-layer component, the material heat treatment state and the thickness of the layer; S2, according to the tool length, tool diameter and eccentricity determined in S1, set the revolution speed, rotation speed and feed speed parameters of the tool cutting; S3, after the heterogeneous composite multi-layer component is clamped and fixed by a drilling template, a through hole is milled out by layered processing and differential feeding.

2. The method for spiral milling of aircraft heterogeneous composite multi-layer components according to claim 1, characterized in that: S1 is specifically: According to the hole diameter D1 to be processed of the heterogeneous composite multi-layer component material; select the tool diameter d1, d1> D1; The eccentricity of the tool is adjusted to e1 = (D1-d1) / 2; Among them, e1 is the tool eccentricity, D1 is the hole diameter, and d1 is the tool diameter.

3. The method for spiral milling holes of aircraft heterogeneous composite multi-layer components according to claim 2, characterized in that: The countersinking operation is performed on the heterogeneous composite multi-layer components after spiral milling, leaving a margin of 0.1mm to 0.3mm in the countersink depth direction, and supplementary countersinking is adopted to achieve the final accuracy; the calculation formula of the countersink eccentricity is: e2=(D2-d2) / 2; Among them, e2 is the countersink eccentricity, D2 is the socket diameter, and d2 is the countersink drill diameter; The formula for calculating the countersink depth is: H=(D2-D1)×tan-1(α / 2); Among them, H is the countersink depth, D2 is the cavity diameter, D1 is the hole diameter, and α is the countersink angle.

4. The method for spiral milling holes of aircraft heterogeneous composite multi-layer components according to claim 1, characterized in that: In S1, when the types of laminated materials of the heterogeneous composite multi-layer component are different, the milling method should be adopted for layered processing and differential feeding, and the position for changing the spiral milling parameters should be selected according to the type of laminated material; when the outer material is a metal material and the inner material is a composite material, the tool cutting revolution speed, rotation speed and feed speed parameters are changed when milling through the metal material; when the outer material is a composite material and the inner material is a metal material, the tool cutting revolution speed, rotation speed and feed speed parameters are changed in the composite material layer.

5. The method for spiral milling holes of aircraft heterogeneous composite multi-layer components according to claim 4, characterized in that: For heterogeneous composite multi-layer components with gaps, when the front end of the tool is still within the gap after the tool mills through the outer material layer, that is, the tool side edge radius is all within the gap, then the tool cutting parameters are adjusted to the parameters corresponding to the next milling layer material within the gap.

6. The method for spiral milling holes of aircraft heterogeneous composite multi-layer components according to claim 4, characterized in that: When milling holes, when the laminated material is transferred from aluminum alloy, titanium alloy or alloy steel material to composite material, when the tool axial feed to the composite material layer depth is at least more than the tool tip arc radius, the tool cutting parameters are adjusted to the milling parameters of the composite material; when the laminated material is transferred from composite material to aluminum alloy, titanium alloy or alloy steel material layer, when the composite material milling allowance is close to 0.3mm, the tool cutting parameters are adjusted to the milling parameters of aluminum alloy, titanium alloy or alloy steel material.

7. The method for spiral milling holes of aircraft heterogeneous composite multi-layer components according to claim 4, characterized in that: When milling holes, when the stacked materials are different types of metal materials, the milling parameters are adjusted in the material layer where the tool rotation speed is higher.

8. A heterogeneous composite multi-layer spiral milling hole processing device as claimed in any one of claims 1 to 7, characterized in that: The rotary milling hole processing device comprises a tool (1), one end of the tool (1) is provided with one end of a connecting sleeve (2), and the other end of the connecting sleeve (2) is provided with a round shaft (3).

9. The heterogeneous composite multi-layer spiral milling hole processing device according to claim 8, characterized in that: One end of the connecting sleeve (2) provided with a round shaft (3) is connected to a vacuum cleaner (4).

10. The heterogeneous composite multi-layer spiral milling hole processing device according to claim 8, characterized in that: The connecting sleeve is provided with a clamping claw.

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