A machining method for aircraft aerial nacelle cover

Abstract

The present invention discloses a machining method for an aircraft nacelle cover, which includes bench marking, selecting and machining a first reference surface, rough milling an inner cavity, rough milling an outer shape, aging treatment, selecting and machining a second reference surface, fine milling an outer shape, and fine milling an inner cavity. In this machining method, a VMC‑1400 machining center and a DMU80 five-axis machining center are used. Four first reference surfaces and two planes are used as positioning references for rough milling, and a second reference surface for the fine milling step is opened on the basis of the first reference surface. At the same time, using this machining step, during fine milling, the processing can be completed in one go, effectively shortening the processing time and improving the quality and efficiency of part processing. While ensuring processing efficiency, the method prevents parts from being easily deformed during processing and vibration marks from being easily generated on the processed surface, ensuring that the accuracy of the parts is affected. In addition, the method can solve the defect of filling the inner cavity of the nacelle cover with fixed materials such as gypsum in traditional processing. The method is easy to use and reusable.

Description

Technical Field

[0001] The invention relates to the technical field of mechanical processing, in particular to a method for machining an aircraft aerial nacelle cover. Background Art

[0002] Aircraft pod covers are hollow, thin-walled components used to cover the aircraft's pod. Weight-reducing grooves are located on the sidewalls and top of the cover. Made from precision-cast magnesium alloy (ZM5), magnesium alloy boasts light weight, high specific strength and stiffness, and strong electromagnetic interference shielding. While maintaining strength and excellent shielding properties, the cover also reduces the pod's weight, playing a key role in the overall structure.

[0003] During the milling process of the nacelle cover, the part is relatively large in size, but the overall wall thickness of the part is only 6mm, especially the wall thickness of the weight-reducing groove on the part is only 3mm, which makes it easy to deform during the processing; at the same time, since the wall thickness of the part is relatively thin and the inner cavity of the part itself has no supporting structure, chatter marks are easily generated on the processing surface of the nacelle cover during the processing, which not only affects the part accuracy, but also makes it difficult to guarantee the surface roughness.

[0004] In the past, during processing, shaping materials such as gypsum were used to fill the inner cavity of the pod cover to achieve the effect of supporting the pod cover. This can reduce the occurrence of defects such as deformation and chatter marks during milling. However, during the filling process, these filling materials have a phase change process. After this process, the filling material cannot effectively adhere to the inner cavity wall of the pod cover, and the supporting and shaping effects are limited, which cannot avoid the occurrence of defects such as deformation and chatter marks. Moreover, this method of strengthening the strength of parts in the processing of pod covers is cumbersome to use and cannot be reused. Summary of the Invention

[0005] The object of the present invention is to provide a machining method for an aircraft nacelle cover, so as to solve the problem that the parts are easily deformed and chatter marks are easily generated on the machined surface during the milling process of the nacelle cover.

[0006] In order to solve the above technical problems, the present invention adopts the following technical solutions:

[0007] A method for machining an aircraft pod cover is disclosed. The pod cover is a thin-walled hollow shell casting made of ZM5 magnesium alloy precision casting. Multiple weight-reducing grooves are machined on the outer surface of the pod cover. The pod cover wall thickness is required to be 6±0.03mm, and the weight-reducing groove wall thickness is required to be 3±0.03mm. The machining method includes bench marking, selecting and machining a first reference surface, rough milling the inner cavity, rough milling the outer shape, aging treatment, selecting and machining a second reference surface, and fine milling the outer shape and inner cavity. The machining method uses a VMC-1400 machining center and a DMU80 five-axis machining center.

[0008] S1. Fitter marking: Fitter measures or scans the nacelle cover casting with a scanner to determine the machining allowance and mark it out;

[0009] S2. Select and machine the first reference surface: Using a VMC-1400 machining center, mill four first reference surfaces on the vertical surface 2 on both sides of the nacelle cover's outer shape along its length, with the inner cavity of the nacelle cover facing downward. Mill the two flat surfaces at the top of the nacelle cover until they are visible.

[0010] S3. Rough milling of the inner cavity: With the inner cavity of the nacelle cover facing upward, clamp the first reference surface on the workbench of the VMC-1400 machining center, and rough mill the inner cavity and bottom of the nacelle cover with a 1.5mm margin. Leave a 2mm margin on the edge of the nacelle cover.

[0011] S4. Rough milling: With the inner cavity of the nacelle cover facing downward, clamp the first reference surface on the work table of the DMU80 five-axis machining center, and rough mill the outer shape with a 1mm allowance.

[0012] S5. Aging treatment: Keep the temperature in the aging furnace at 170-175℃ for 3-5h, then air cool;

[0013] S6. Select and process the second reference surface: With the inner cavity of the nacelle cover facing upward, use the DMU80 five-axis machining center to clamp the first reference surface, and mill the edge of the nacelle cover until it is visible, which serves as the second reference surface.

[0014] S7. Finish milling: Install the first fixture into the inner cavity of the nacelle cover. The first fixture abuts the inner bottom, inner inclined surface, and inner side surface of the inner cavity, with the abutment points corresponding to the machining locations of the weight reduction grooves. With the inner cavity of the nacelle cover facing downward, clamp the second reference surface on the worktable of the DMU80 five-axis machining center. Finish mill the outer shape of the nacelle cover and the weight reduction grooves to the process dimensions. Finish mill one side of the edge, leaving a 0.5mm margin.

[0015] S8. Finish milling of the inner cavity: Place the nacelle cover with the inner cavity facing upward on the second fixture. The second fixture supports the two flat surfaces, the outer inclined surface, the four first reference surfaces, and the edge of the nacelle cover. The nacelle cover is mounted on the worktable of the DMU80 five-axis machining center using the second fixture. The inner cavity, the other side of the edge, the mounting holes, the mating surface, and the peripheral reference surface are finish milled to the process dimensions to obtain the finished nacelle cover 1 part.

[0016] A further technical solution is: in the steps S7 and S8, the fine milling is performed in at least two steps, and a margin of at least 0.1 mm is left after the first processing, and the nacelle cover is removed, the processing surface is fully cooled, and the internal stress of the nacelle cover is released, and then it is re-clamped and processed to the process size.

[0017] A further technical solution is: the internal stress release time of the nacelle cover is 4-5 hours.

[0018] A further technical solution is: the S2 adopts a Φ63 disc cutter, the tool speed is 1500-2000r / min, and the moving speed is 1200-1500mm / min.

[0019] A further technical solution is: the S3 and S4 adopt Φ16 side milling, the tool speed is 6000-6500r / min, and the moving speed is 1200-1500mm / min.

[0020] A further technical solution is: the milling cutter rotation speed of S6, S7 and S8 is 7500-8000r / min, and the moving speed is 1200-1300mm / min.

[0021] A further technical solution is that the second tooling is provided with a support plate with an adjustable distance for pressing against the outer shape of the nacelle cover.

[0022] A further technical solution is: the second tooling is provided with a positioning rod with an adjustable distance for pressing against the outer shape of the nacelle cover, and the positioning rod corresponds to the weight-reducing groove on the first reference surface.

[0023] Compared with the prior art, the present invention can achieve at least one of the following beneficial effects:

[0024] The present invention proposes a machining method for an aircraft nacelle cover, which utilizes four first reference planes and two planes as positioning references for rough milling, and opens a second reference plane for a fine milling step on the basis of the first reference planes. At the same time, by using this machining step, the fine milling can be completed in one go, effectively shortening the machining time and improving the parts machining quality and machining efficiency.

[0025] Based on the second reference surface, the first and second fixtures are used to reinforce the outer shape and inner cavity of the thin-walled shell-shaped nacelle cover, respectively. While ensuring processing efficiency, the fixtures provide support for the part's outer shape and inner cavity, enhancing its strength and preventing deformation during processing and chatter marks on the processed surface that could affect part accuracy. Furthermore, this fixture overcomes the drawback of traditional processing involving the use of fixed materials such as gypsum to fill the nacelle cover's inner cavity. It is easy to use and reusable.

[0026] When fine-milling the outer shape and inner cavity of the nacelle cover, without pursuing processing speed, the two processing steps of fine milling the outer shape and fine milling the inner cavity can be carried out twice respectively. The nacelle cover is removed and the processing surface is fully cooled to release the internal stress of the nacelle cover. After re-clamping, it is processed to the process size in order to maximize the accuracy of the parts and ensure the safety and quality of aircraft accessories. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is a structural schematic diagram of the nacelle cover in the present invention.

[0028] Figure 2 For the present invention Figure 1 Schematic diagram of the structure from another perspective.

[0029] Figure 3 This is a structural schematic diagram of the first tooling installed in the inner cavity of the nacelle cover in the present invention.

[0030] Figure 4 For the present invention Figure 3 Schematic diagram of the structure from another perspective.

[0031] Figure 5 For the present invention Figure 3 Schematic diagram of the structure of the first tooling.

[0032] Figure 6 For the present invention Figure 5 Schematic diagram of the structure from another perspective.

[0033] Figure 7 This is a structural schematic diagram of the nacelle cover of the present invention being installed on the second tooling.

[0034] Figure 8 For the present invention Figure 7 Schematic diagram of the structure from another perspective.

[0035] Figure 9 For the present invention Figure 7 Schematic diagram of the structure of the second tooling.

[0036] Figure numerals: 1. Nacelle cover; 2. Weight reduction groove; 3. Plane; 4. First tooling; 5. Second tooling; 6. Support plate; 7. Positioning rod. DETAILED DESCRIPTION

[0037] To make the objectives, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions of the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings herein can be arranged and designed in various different configurations.

[0038] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention as claimed, but rather merely represents selected embodiments of the present invention. All other embodiments derived by persons of ordinary skill in the art based on the embodiments of the present invention without creative effort are also within the scope of protection of the present invention.

[0039] It should be noted that, in the absence of conflict, the embodiments and features of the embodiments of the present invention can be combined with each other.

[0040] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, it does not need to be further defined or explained in subsequent drawings.

[0041] In the description of the present invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," "outer," etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, or are the orientations or positional relationships in which the inventive product is typically placed when in use, or are the orientations or positional relationships commonly understood by those skilled in the art. These terms are intended only to facilitate the description of the present invention and to simplify the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limiting the present invention. Furthermore, the terms "first," "second," etc., are used only to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0042] In the description of the present invention, it should also be noted that, unless otherwise expressly specified or limited, the terms "disposed," "installed," "connected," and "connected" should be understood in a broad sense. For example, they may refer to fixed connections, detachable connections, or integral connections; they may refer to mechanical connections or electrical connections; they may refer to direct connections or indirect connections through an intermediate medium; and they may refer to internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on the specific circumstances.

[0043] Example 1:

[0044] This embodiment Figures 1-9As shown, a machining method for an aircraft pod cover is described. The pod cover 1 is a thin-walled hollow shell casting made of ZM5 magnesium alloy precision casting. Multiple weight-reducing grooves 2 are machined on the outer surface of the pod cover 1. The wall thickness of the pod cover 1 is required to be 6±0.03mm, and the wall thickness of the weight-reducing grooves 2 is required to be 3±0.03mm. The machining method includes bench marking, selecting and machining a first reference surface, rough milling of the inner cavity, rough milling of the outer shape, aging treatment, selecting and machining a second reference surface, and fine milling of the outer shape and the inner cavity. The machining method uses a VMC-1400 machining center and a DMU80 five-axis machining center.

[0045] S1. Marking by fitter: A fitter measures or scans the casting of the nacelle cover 1 with a scanner to determine the machining allowance and mark it;

[0046] S2. Select and machine the first reference surface: Using a VMC-1400 machining center, mill four first reference surfaces on the vertical surface 2 on both sides of the nacelle cover 1 along its length, with the inner cavity of the nacelle cover 1 facing downward. Mill the two flat surfaces 3 at the top of the nacelle cover until they are visible.

[0047] S3. Rough milling of the inner cavity: With the inner cavity of the nacelle cover plate 1 facing upward, clamp the first reference surface on the work table of the VMC-1400 machining center, and rough mill the inner cavity and bottom of the nacelle cover plate 1 with a 1.5mm margin. A 2mm margin is left for the edges of the nacelle cover plate 1.

[0048] S4. Rough milling: With the inner cavity of the nacelle cover 1 facing downward, clamp the first reference surface on the work table of the DMU80 five-axis machining center, and rough mill the outer shape with a 1mm allowance.

[0049] S5. Aging treatment: Keep the temperature in the aging furnace at 170-175℃ for 3-5h, then air cool;

[0050] S6. Select and process the second reference surface: With the inner cavity of the nacelle cover 1 facing upward, use the DMU80 five-axis machining center to clamp the first reference surface, and mill the edge of the nacelle cover 1 until it is visible, which serves as the second reference surface.

[0051] S7. Finish milling: Install the first tooling 4 into the inner cavity of the nacelle cover 1. The first tooling 4 abuts the inner bottom, inner inclined surface, and inner side surface of the inner cavity, with the abutment points corresponding to the machining positions of the weight-reducing groove 2. With the inner cavity of the nacelle cover 1 facing downward, clamp the second reference surface on the worktable of the DMU80 five-axis machining center. Finish mill the outer shape of the nacelle cover 1 and the weight-reducing groove 2 to the process dimensions. Finish mill one side of the edge, leaving a 0.5mm margin.

[0052] S8. Finish milling of the inner cavity: Place the nacelle cover 1 with its inner cavity facing upward on the second fixture 5. The second fixture 5 is positioned against the two flat surfaces 3, the outer inclined surface, the four first reference surfaces, and the edge of the nacelle cover 1. Mount the nacelle cover 1 on the worktable of the DMU80 five-axis machining center using the second fixture 5. Finish mill the inner cavity, the other side of the edge, the mounting holes, the mating surface, and the peripheral reference surface to the process dimensions to obtain the finished nacelle cover 1.

[0053] The working process of the present invention is as follows: first, the precision casting parts of the nacelle cover (hereinafter referred to as parts) are bench-marked to determine the machining allowance; then, along the length direction of the part (based on the longest side), the inner cavity of the part is placed downward on the VMC-1400 machining center, four symmetrical first reference surfaces are roughly milled on the two long sides of the part shape, and the two planes 3 at the top of the part shape are milled to a light finish (filed and flattened) to use the planes 3 as secondary references; the inner cavity of the nacelle cover is placed upward on the VMC-1400 machining center, and the four The first reference surface is used for rough milling of the inner cavity and bottom of the nacelle cover 1 with a 1.5mm allowance, and the edge of the nacelle cover 1 is left with a 2mm allowance; the inner cavity of the nacelle cover 1 is set downward on the workbench of the DMU80 five-axis machining center, and the four first reference surfaces are clamped, and the outer shape is rough milled with a 1mm allowance; after the rough milling is completed, the part needs to be removed from the VMC-1400 machining center, kept at 170-175℃ in an aging furnace for 3-5h, and then air-cooled for aging treatment to ensure the internal stress balance and part strength. Affected by the high temperature generated during milling, the DMU80 five-axis machining center clamps the four first reference surfaces of the part, with the inner cavity of the nacelle cover 1 facing upwards. The edge of the nacelle cover 1 is milled to a shine (filed and flattened) as the second reference surface; the first tooling 4 is installed into the inner cavity of the nacelle cover 1. The first tooling 4 respectively presses against the inner bottom surface, inner inclined surface and inner side surface of the part's inner cavity, and the positions of each pressing point correspond to the processing positions of the weight reduction groove 2. The inner cavity of the nacelle cover 1 is set downwards on the worktable of the DMU80 five-axis machining center, clamping the second reference surface. The outer surface of the nacelle cover plate 1 and the weight-reducing groove 2 are fine-milled to the process size, and one side of the edge is fine-milled with a 0.5mm margin. The inner cavity of the nacelle cover plate 1 is placed upward and installed on the second tooling 5. The second tooling 5 is respectively against the two planes 3, the outer inclined surface, the four first reference surfaces and the edge of the outer shape of the nacelle cover plate 1. The nacelle cover plate 1 is installed on the worktable of the DMU80 five-axis machining center through the second tooling 5. The inner cavity, the other side of the edge, the mounting hole, the mating surface and the peripheral reference surface are fine-milled to the process size to obtain the finished parts of the nacelle cover plate 1.

[0054] Note that the VMC-1400 machining center in step S2 uses a Φ63 disc cutter with a tool speed of 1500-2000 r / min and a moving speed of 1200-1500 mm / min.

[0055] S3 and S4 use Φ16 side milling, tool speed 6000-6500r / min, moving speed 1200-1500mm / min;

[0056] The milling cutter speed of S6, S7 and S8 is 7500-8000r / min, and the moving speed is 1200-1300mm / min.

[0057] The internal stress release time of the nacelle cover 1 is 4-5 hours.

[0058] The present invention utilizes four first reference planes and two planes as positioning references for rough milling, and opens a second reference plane for the fine milling step on the basis of the first reference plane. At the same time, by using this processing step, the fine milling can be completed in one go, effectively shortening the processing time and improving the part processing quality and processing efficiency.

[0059] Based on the second reference surface, the first and second fixtures are used to reinforce the outer shape and inner cavity of the thin-walled shell-shaped nacelle cover, respectively. While ensuring processing efficiency, the fixtures provide support for the part's outer shape and inner cavity, enhancing its strength and preventing deformation during processing and chatter marks on the processed surface that could affect part accuracy. Furthermore, this fixture overcomes the drawback of traditional processing involving the use of fixed materials such as gypsum to fill the nacelle cover's inner cavity. It is easy to use and reusable.

[0060] Example 2:

[0061] Based on the above embodiment, this embodiment shows that in steps S7 and S8, the fine milling is divided into at least two processes, and at least 0.1 mm of margin is left after the first process, and the nacelle cover plate 1 is removed, the processing surface is fully cooled, and the internal stress of the nacelle cover plate 1 is released, and then it is re-clamped and processed to the process size.

[0062] The outer shape and inner cavity of the nacelle cover 1 can be fine-milled. Without pursuing processing speed, the two processing steps of fine milling of the outer shape and fine milling of the inner cavity can be carried out twice respectively. The nacelle cover 1 is removed and the processing surface is fully cooled to release the internal stress of the nacelle cover. After re-clamping, it is processed to the process size in order to improve the accuracy of the parts as much as possible and ensure the safety and quality of aircraft accessories.

[0063] Based on the above embodiment, it is preferred that:

[0064] The second tooling 5 is provided with a support plate 6 which can be adjusted in distance and is used to press against the outer shape of the nacelle cover 1 .

[0065] The support plate 6 can be used to press against necessary parts of the part's shape to increase the thickness and strength, thereby preventing deformation and chatter marks during part processing.

[0066] The second tooling 5 is provided with a positioning rod 7 with an adjustable distance for pressing against the outer shape of the nacelle cover 1 . The positioning rod 7 corresponds to the weight-reducing groove 2 on the first reference surface.

[0067] The positioning rods 7 can be used to position the parts using the four first reference surfaces, enabling quick assembly. This is particularly true for the second embodiment, where the two disassembly processes save time and ensure accurate part assembly. Furthermore, by resting against the lightening grooves 2 on the first reference surface, they provide support and prevent deformation of the thin grooves 2 during milling of the inner cavity.

[0068] Although the present invention has been described in detail with reference to the aforementioned embodiments, it is still possible for those skilled in the art to modify the technical solutions described in the aforementioned embodiments, or to make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A machining method for an aircraft aerial pod cover, wherein the pod cover (1) is a thin-walled hollow shell casting made of ZM5 magnesium alloy precision casting, and a plurality of weight-reducing grooves (2) are machined on the outer shell surface of the pod cover (1), the wall thickness of the pod cover (1) is 6±0.03 mm, and the wall thickness of the weight-reducing grooves (2) is 3±0.03 mm; the machining method comprises bench marking, selecting and machining a first reference surface, rough milling an inner cavity, rough milling an outer shape, aging treatment, selecting and machining a second reference surface, fine milling an outer shape, and fine milling an inner cavity, and the machining method uses a VMC-1400 machining center and a DMU80 five-axis machining center, and is characterized in that: S1. Fitter marking: The fitter measures or scans the casting of the nacelle cover (1) with a scanner to determine the machining allowance and mark it; S2. Select and process the first reference surface: on both sides of the outer shape of the nacelle cover plate (1) in the longitudinal direction, with the inner cavity of the nacelle cover plate (1) facing downward, use the VMC-1400 machining center to mill out four first reference surfaces on the vertical surfaces on both sides of the outer shape of the nacelle cover plate (1), and mill the two planes (3) on the top of the outer shape of the nacelle cover plate until they are visible; S3, rough milling of the inner cavity: with the inner cavity of the nacelle cover plate (1) facing upwards, clamp the first reference surface on the work table of the VMC-1400 machining center, and rough mill the inner cavity around and bottom of the nacelle cover plate (1) with a 1.5mm margin, and leave a 2mm margin on the edge of the nacelle cover plate (1); S4, rough milling shape: with the inner cavity of the nacelle cover (1) facing downward, clamp the first reference surface on the work table of the DMU80 five-axis machining center, and rough mill the shape with a full 1mm allowance; S5. Aging treatment: Keep the temperature in the aging furnace at 170-175℃ for 3-5h, then air cool; S6. Select and process the second reference surface: With the inner cavity of the nacelle cover plate (1) facing upward, use the DMU80 five-axis machining center to clamp the first reference surface, and mill the edge of the nacelle cover plate (1) until it is visible, which serves as the second reference surface; S7, fine milling of the outer shape: the first tool (4) is installed into the inner cavity of the nacelle cover plate (1), the first tool (4) respectively abuts against the inner bottom surface, the inner inclined surface and the inner side surface of the inner cavity, and the positions of the abutting points respectively correspond to the processing positions of the weight reduction groove (2), the inner cavity of the nacelle cover plate (1) is downward, and the second reference surface is clamped on the working table of the DMU80 five-axis machining center, and the outer shape of the nacelle cover plate (1) and the weight reduction groove (2) are fine milled to the process size, and one side of the edge is fine milled with a 0.5mm margin. S8, precision milling of the inner cavity: the inner cavity of the nacelle cover (1) is placed upward and mounted on the second fixture (5), wherein the second fixture (5) respectively abuts against the two planes (3), the outer inclined surface, the four first reference surfaces and the edge of the outer shape of the nacelle cover (1). The nacelle cover (1) is mounted on the work table of the DMU80 five-axis machining center through the second fixture (5), and the inner cavity, the other side of the edge, the mounting hole, the mating surface and the circumferential reference surface are precision milled to the process size to obtain the precision-machined parts of the nacelle cover (1).

2. The method for machining an aircraft nacelle cover according to claim 1, characterized in that: In the steps S7 and S8, the fine milling is performed in at least two steps. After the first step, a margin of at least 0.1 mm is left. The nacelle cover plate (1) is removed to fully cool the processing surface and release the internal stress of the nacelle cover plate (1). The nacelle cover plate (1) is then re-clamped and processed to the process size.

3. The machining method of an aircraft nacelle cover according to claim 2, characterized in that: The internal stress release time of the nacelle cover plate (1) is 4-5 hours.

4. The method for machining an aircraft nacelle cover according to claim 1, wherein: The S2 adopts a Φ63 disc cutter with a tool speed of 1500-2000r / min and a moving speed of 1200-1500mm / min.

5. The method for machining an aircraft nacelle cover according to claim 1, characterized in that: The S3 and S4 adopt Φ16 side milling, the tool speed is 6000-6500r / min, and the moving speed is 1200-1500mm / min.

6. The method for machining an aircraft nacelle cover according to claim 1, characterized in that: The milling cutter rotation speed of S6, S7 and S8 is 7500-8000 r / min, and the moving speed is 1200-1300 mm / min.

7. The method for machining an aircraft nacelle cover according to claim 1, characterized in that: The second tooling (5) is provided with a support plate (6) with an adjustable distance and which presses against the outer shape of the nacelle cover plate (1).

8. The method for machining an aircraft nacelle cover according to claim 1, characterized in that: The second tooling (5) is provided with a positioning rod (7) with an adjustable distance and pressed against the outer shape of the nacelle cover (1); the positioning rod (7) corresponds to the weight-reducing groove (2) on the first reference surface.

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