An automated method and apparatus for manufacturing aircraft panels with a gapped pocket feature

Abstract

The application relates to the technical field of aircraft panel manufacturing, and provides an automatic manufacturing method and equipment for an aircraft panel with a hatch cover sunken feature. The automatic manufacturing method and equipment for the aircraft panel with the hatch cover sunken feature provided by the application adopt a filament laying equipment to lay a composite material skin structure with a hatch cover sunken feature by using an automatic laying technology, so that the problems of low manual laying efficiency, poor quality consistency and avoidance of human quality accidents are solved; and a hot-press forming actuator is further used to automatically hot-press form the filaments in at least the hatch cover area and the slope area, so that automatic hot-press forming of the hatch cover sunken feature is realized, full-automatic forming of the skin with the hatch cover feature is realized, and the method has the advantages of good quality, good quality consistency, high production efficiency, low cost and the like.

Description

Technical Field

[0001] This invention belongs to the field of aircraft panel manufacturing technology, and particularly relates to an automated manufacturing method and equipment for aircraft panels with a recessed cover feature. Background Technology

[0002] Currently, composite aircraft panels with a recessed hatch feature are being developed. These panels consist of a smooth, flush panel and a hatch panel. Existing manufacturing processes primarily involve manual lay-up of carbon fiber epoxy prepreg. The prepreg sheets, cut manually, are laid onto a mold surface. When the prepreg is placed in the hatch area, it is manually compacted to create the recessed hatch area. The mold used for laying the prepreg is a male mold. The manufacturing process includes: tooling preparation (tooling cleaning, applying release agent), prepreg cutting, manual lay-up, autoclave curing, machining, and inspection.

[0003] Because of the sunken structure of the composite wall panel with the cap, current composite material manufacturing processes can only be carried out by manual lay-up molding. This manual lay-up molding process has the following disadvantages:

[0004] 1. Poor product quality consistency. Due to the manual laying method, the laying skills and abilities of different personnel vary greatly, resulting in different laying quality. Human negligence can lead to product quality incidents, which seriously affects the consistency of delivered product quality.

[0005] 2. Manual laying is inefficient and greatly affects the product delivery schedule;

[0006] 3. High manufacturing costs: Due to the large amount of manual labor involved, especially for large skins, the high number of personnel involved greatly increases the manufacturing cost of the product. Summary of the Invention

[0007] The purpose of this invention is to overcome at least one of the shortcomings of the prior art and to provide an automated manufacturing method and equipment for aircraft panels with a recessed cover feature, which has the advantages of good quality, good quality consistency, high production efficiency and low cost.

[0008] The technical solution of this invention is: an automated manufacturing method for aircraft panels with a recessed flap feature, comprising a wire laying step and a flap area forming step, wherein the method includes:

[0009] A filament-laying device is used to lay filaments in a designated filament-laying area, which includes a smooth area, a slope area, and a capping area. The slope area is transitionally connected to the smooth area and the capping area. The filament bundle has a break point in the capping area, and the filament bundle is overlapped or joined at the break point.

[0010] The forming steps for the cap area include:

[0011] The thermoforming actuator is used to automatically thermoform the filament bundles in at least the cap area and the slope area, so that the filament bundles in the corresponding areas are formed.

[0012] Optionally, in the filament-laying area, when laying filaments in the filament-laying area, the breakpoints of adjacent filament bundles in the same layer and direction are staggered.

[0013] And / or, the breakpoints of the filament bundles in adjacent layups are staggered.

[0014] Optionally, the breakpoints of at least five sets of filament bundles in the same direction are staggered sequentially along the length of the filament bundles.

[0015] And / or, the same covered area has at least two sets of filament bundles in different directions, and the at least two sets of filament bundles in different directions have break points.

[0016] Optionally, the misalignment distance between the breakpoints of adjacent filament bundles is 10 to 15 mm;

[0017] And / or, the filament bundles are overlapped at the break points and the overlap length does not exceed 3mm.

[0018] Optionally, when the filament laying equipment is used to lay filaments in a set filament laying area, when the filament bundle enters the cover area from the smooth area through the slope area, the filament laying head of the filament laying equipment enters the cover area from the smooth area through the slope area in an attitude perpendicular to the smooth area.

[0019] Optionally, the forming step of the cap area includes:

[0020] The lower mold of the thermoforming actuator acts on the filament bundle at the edge of the smooth zone and near the slope zone;

[0021] The upper mold of the thermoforming actuator acts on the filament bundle at the edge of the cap area and near the slope area;

[0022] The core mold of the hot pressing actuator acts on the filament bundle in the slope zone between the upper and lower mold bodies.

[0023] Optionally, the pressure of the lower mold body is 10000N-2000N; the pressure of the upper mold body is less than 20N;

[0024] The pressure of the core mold is 20000N - 3000N;

[0025] The heating temperature of the lower mold body acting on the filament bundle is 70-90℃;

[0026] The heating temperature of the upper mold body acting on the filament bundle is 70-90℃;

[0027] The heating temperature of the filament bundle applied by the central core mold is 70-90℃.

[0028] Optionally, the pressure holding time of the central core mold on the filament bundle is 1-2 minutes;

[0029] After the pressure holding time is completed, the lower mold body, upper mold body and middle core mold are cooled down. When the temperature of the lower mold body, upper mold body and middle core mold is lower than 40-50℃, the hot pressing actuator is removed from the mold, and the forming step of the cap area is completed.

[0030] The present invention also provides an automated manufacturing equipment for aircraft panels with a recessed cap feature, employing the aforementioned automated manufacturing method for aircraft panels with a recessed cap feature, comprising a filament laying device and a thermoforming actuator. The filament laying device is used to lay filament bundles in a designated filament laying area; the designated filament laying area includes a smooth area, a slope area, and a cap area, with the slope area transitionally connected to the smooth area and the cap area. The thermoforming actuator is used to automatically thermoform the filament bundles in at least the cap area and the slope area.

[0031] Specifically, the hot pressing actuator includes a lower mold body, an upper mold body, and a central core mold, wherein the central core mold is movably disposed between the lower mold body and the upper mold body;

[0032] The lower mold body is used to act on the filament bundles at the edge of the smooth area and near the slope area;

[0033] The upper mold body is used to act on the filament bundle at the edge of the cap area and near the slope area;

[0034] The central core mold is used to act on the filament bundle in the slope zone;

[0035] The lower mold body, upper mold body, and middle core mold are all connected to lifting drive components; the lower mold body, upper mold body, and middle core mold are all equipped with heating components.

[0036] The present invention provides an automated manufacturing method and equipment for aircraft skin with a recessed flap feature. It uses a wire laying device to automatically lay the composite material skin structure with the recessed flap feature, which solves the problems of low efficiency, poor quality consistency and human error in manual laying. Then, it uses a hot pressing actuator to automatically hot press the wire bundles in at least the flap area and the slope area, which can realize the automated hot pressing of the flap. It realizes the fully automated forming of the skin with the flap feature, which has the advantages of good quality, good quality consistency, high production efficiency and low cost. Attached Figure Description

[0037] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0038] Figure 1 This is a three-dimensional exploded view of an aircraft panel and a hatch with a recessed hatch feature provided in an embodiment of the present invention;

[0039] Figure 2 This is a schematic diagram of the wire laying in the cover area in an automated manufacturing method for an aircraft panel with a recessed cover feature provided in an embodiment of the present invention;

[0040] Figure 3 This is a schematic diagram of the normal vector optimization process in the wire laying step of an automated manufacturing method for an aircraft panel with a recessed flap, as provided in an embodiment of the present invention.

[0041] Figure 4 This is a schematic diagram of the normal vector optimization in the wire laying step of an automated manufacturing method for an aircraft panel with a recessed cover, provided in an embodiment of the present invention.

[0042] Figure 5 This is a three-dimensional schematic diagram of a hot pressing actuator and an aircraft panel in an automated manufacturing equipment for aircraft panels with a recessed cover, provided in an embodiment of the present invention.

[0043] Figure 6 This is a cross-sectional schematic diagram of a thermoforming actuator, an aircraft panel, and a mold in an automated manufacturing equipment for aircraft panels with a recessed cap feature, provided in an embodiment of the present invention. Detailed Implementation

[0044] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention.

[0045] It should be noted that the terms "setup" and "connection" should be interpreted broadly. For example, they can refer to direct setup or connection, or indirect setup or connection through centered components or centered structures.

[0046] Furthermore, in embodiments of this invention, terms such as "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer" are used to indicate orientation or positional relationships based on the orientation or positional relationships shown in the accompanying drawings, or in a conventional placement or usage state. These terms are merely for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the structures, features, devices, or elements referred to must have a specific orientation or positional relationship, nor that they must be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0047] The various specific technical features and embodiments described in the detailed embodiments can be combined in any suitable manner without contradiction. For example, different implementation methods can be formed by combining different specific technical features / embodiments. In order to avoid unnecessary repetition, the various possible combinations of the various specific technical features / embodiments in this invention will not be described separately.

[0048] like Figure 1 , Figure 2 as well as Figures 4 to 6 As shown, this embodiment of the invention provides an automated manufacturing method for an aircraft panel with a recessed cover feature. The aircraft panel 910 has a recessed cover feature 901 for connecting to a cover 920. The above-mentioned automated manufacturing method for the aircraft panel includes a wire laying step and a cover area forming step. The wire laying step includes:

[0049] A fiber-laying device is used to lay fibers in a designated area, placing the fiber bundle 900 (composite material) onto a mold 600 (generally a male mold) to prepare a composite material skin structure (aircraft panel 910). The designated fiber-laying area includes a smooth area 810 (the main body of the aircraft panel), a sloped area 820, and a flap area 830 (corresponding to the flap's recessed feature). The sloped area 820 transitions between the smooth area 810 and the flap area 830. The fiber bundle 900 has a break point 902 in the flap area 830, and the fiber bundle 900 overlaps or butts at the break point 902. The designated fiber-laying area can be a region of the male mold surface, wherein the surface of the flap area 830 is higher than the surface of the smooth area 810, and the two sides of the sloped area 820 connect the flap area 830 and the smooth area 810. The smooth area 810 is generally a flat plane or a smooth area with a certain curvature.

[0050] The forming step of the cap area 830 includes: using a hot pressing actuator to automatically hot press the filament bundles 900 of the cap area 830 and the slope area 820 to form the filament bundles 900 in the corresponding areas, so as to form a composite material preform.

[0051] Driven by the extreme weight reduction and stealth design requirements of aircraft such as fighter jets, the current design of aircraft flaps integrates with the body panels to avoid assembly and unnecessary structural weight. With the widespread adoption of automated layup technology and equipment, the manufacturing of aircraft composite material structures is gradually shifting from manual to automated layup. However, due to the flap protrusion feature in the manufacturing tooling for skin structures with recessed flaps, automated layup is not feasible. Therefore, existing technologies for aircraft composite material structures employ manual layup methods, resulting in low efficiency and uncontrollable layup quality. Automated layup also has its limitations, unable to handle complex structures. The smooth, open structural characteristics of aircraft body panels make them a suitable structure for automated layup processes; however, the edge features of the recessed structure in the flap area can lead to fiber bridging defects, which is a key obstacle to automated body panel manufacturing technology and a critical technical challenge that needs to be addressed. In this application, by laying fibers in a designated area using a fiber-laying device, the fiber bundle 900 has a breakpoint 902 in the cap area 830. The fiber bundle 900 overlaps or butts at the breakpoint 902. The fiber-laying device uses automatic laying technology to lay composite material skin structures with cap depression characteristics, solving the problems of low efficiency, poor quality consistency, and human error in manual laying. Furthermore, by using a hot-pressing actuator to automatically hot-press the fiber bundle 900 in at least the cap area 830 and the slope area 820, the automated hot-pressing of the cap depression can be achieved, realizing fully automated molding of skin with cap features. This has the advantages of good quality, excellent quality consistency, high production efficiency, and low cost.

[0052] In practical applications, before the filament placement step, preparatory steps are performed, which mainly include: cleaning the placement fixture, applying release agent, and measuring the position after the placement fixture is transferred to the placement platform to ensure the accurate relative positional relationship between the filament placement machine and the placement fixture.

[0053] Specifically, during the filament laying process, when laying filaments in the filament laying area, the breakpoints 902 of at least two adjacent filament bundles 900 in the same layer and direction are staggered; that is, each breakpoint 902 is not on the same straight line at the same time, so as to improve the structural reliability.

[0054] Specifically, the breakpoints 902 of the filament bundles 900 in adjacent layers are staggered, which helps to ensure the structural strength of the aircraft panel (skin structure).

[0055] Specifically, the breakpoints 902 of at least five sets of filament bundles 900 in the same direction are staggered along the length of the filament bundles 900 to effectively ensure the structural strength of the aircraft panel (skin structure).

[0056] Specifically, the same cover area 830 has at least two sets of filament bundles 900 in different directions, and the at least two sets of filament bundles 900 in different directions have a break point 902. In specific applications, the cover area 830 has multiple sets of filament bundles 900 in different directions, and the break point 902 of each set of filament bundles 900 in different directions is located at the cover area 830.

[0057] Specifically, such as Figure 2 As shown, the misalignment distance L between the breakpoints 902 of adjacent filament bundles 900 is 10 mm to 15 mm, preferably 12 mm to 13 mm. In this embodiment, the misalignment distance L between the breakpoints 902 of adjacent filament bundles 900 is 13 mm.

[0058] Specifically, the filament bundle 900 is overlapped at the break point 902, and the overlap length does not exceed 3mm to ensure quality.

[0059] Specifically, such as Figure 4 As shown, when the filament placement equipment is used to place filaments in a designated filament placement area, as the filament bundle 900 enters the capping area 830 from the smooth zone 810 via the slope zone 820, the filament placement head (pressure roller 700) of the filament placement equipment enters the capping area 830 from the smooth zone 810 via the slope zone 820 in an attitude perpendicular to the smooth zone 810. The smooth zone 810 is designed and planned according to the specifications for filament placement path planning. During the path planning of the capping area 830, large-scale oscillation of the normal vector of the filament placement machine is avoided. Figure 3 Compared to the unoptimized approach, this method improves layup efficiency and ensures layup speed. In this embodiment, normal vector optimization is performed in the climbing area to smooth the path, preventing the layup head from wobbling and allowing it to continue laying fibers along its original posture, thus improving efficiency. Moreover, to ensure fiber slippage during the thermoforming process in the cap recess area, the path planning must ensure the discontinuity of fibers (filament bundles 900) in the cap area 830. A butt joint or overlap design is implemented at the fiber breakpoint 902, with an overlap length not exceeding 3mm. Furthermore, the breakpoint 902 requires a stepped design (in this embodiment, the step height is 13mm) to avoid breaks on the same straight line. Simultaneously, layups at the same angle are staggered, with at least every 5 layers repeating. In this embodiment, the filament bundle 900 of the aircraft panel (skin) is laid out using an automatic filament laying machine. During the laying process, the step bridging defects in the cap depression area (cap area 830) are ignored in order to complete the skin laying, reduce the risk of bridging in this area, improve the product quality consistency in this area, and improve the manufacturing efficiency of the cap depression area.

[0060] Specifically, the forming steps of the cover area 830 include:

[0061] The lower mold body 521 of the hot press forming actuator acts on the filament bundle 900 at the edge of the smooth zone 810 and near the slope zone 820;

[0062] The upper mold body 523 of the thermoforming actuator acts on the filament bundle 900 at the edge of the cap area 830 and near the slope area 820;

[0063] The core mold 522 of the hot press forming actuator acts on the wire bundle 900 of the slope area 820 between the upper mold body 523 and the lower mold body 521.

[0064] The upper mold body 523 and the lower mold body 521 respectively press the areas on both sides of the slope area 820. The central core mold 522 acts on the filament bundle 900 of the slope area 820 between the upper mold body 523 and the lower mold body 521. The hot pressing actuator hot presses the filament bundle 900 corresponding to the cap area 830, the slope area 820 and the smooth area 810 around the slope area 820.

[0065] Specifically, the pressure exerted by the lower mold 521 is greater than that exerted by the upper mold 523; the pressure exerted by the central core mold 522 is greater than that exerted by the lower mold 521, which is used to prevent the filament bundle 900 from flipping up during the molding process; and through this design, a pressure difference can be established so that the material deformation direction is in the predetermined direction, resulting in a good hot pressing effect.

[0066] In specific applications, the lower mold body 521, upper mold body 523, and central core mold 522 are all equipped with heating components. The system automatically controls the upper mold body 523 and lower mold body 521 to begin heating. The heating temperature is 70-90℃, with a temperature control accuracy of ±5℃. The heating timing of the heating components: the hot pressing actuator can start the heating components upon power-on to improve efficiency. The heating components can be resistance heating devices, etc.

[0067] In this embodiment, the pressure of the lower mold body 521 is 10000N-2000N; the pressure of the upper mold body 523 is less than 20N; the pressure of the central core mold 522 is 20000N-3000N; the heating temperature of the lower mold body 521 acting on the filament bundle 900 is 70-90℃; the heating temperature of the upper mold body 523 acting on the filament bundle 900 is 70-90℃; the heating temperature of the central core mold 522 acting on the filament bundle 900 is 70-90℃.

[0068] Specifically, the holding time of the central core mold 522 on the filament bundle 900 is 1-2 minutes;

[0069] After the aforementioned pressure holding time is completed, the lower mold body 521, upper mold body 523 and middle core mold 522 are cooled down. When the temperature of the lower mold body 521, upper mold body 523 and middle core mold 522 is lower than 40-50℃, the hot pressing forming actuator is removed from the mold, completing the forming step of the cap area 830.

[0070] Specifically, after the forming step 830 in the cap area, a composite material preform forming step is also included:

[0071] The composite material preform is sealed in a vacuum bag and then cured in an autoclave.

[0072] This embodiment also provides an automated manufacturing equipment for aircraft panels with a recessed flap feature. The automated manufacturing method for aircraft panels with a recessed flap feature, as described above, includes a wire laying device and a hot-pressing actuator. The wire laying device is used to lay wire bundles 900 in a designated wire laying area. The designated wire laying area includes a smooth area 810, a slope area 820, and a flap area 830, with the slope area 820 transitionally connected to the smooth area 810 and the flap area 830. The hot-pressing actuator is used to automatically hot-press the wire bundles 900 in at least the flap area 830 and the slope area 820. The hot-pressing actuator includes a lower mold body 521, an upper mold body 523, and a central mold 522, with the central mold 522 movably disposed between the lower mold body 521 and the upper mold body 523. The lower mold body 521 is used to act on the filament bundle 900 at the edge of the smooth area 810 and near the edge of the slope area 820; the upper mold body 523 is used to act on the filament bundle 900 at the edge of the cover area 830 and near the edge of the slope area 820.

[0073] The central core mold 522 is used to act on the filament bundle 900 of the slope zone 820; the lower mold body 521, the upper mold body 523 and the central core mold 522 are all connected to a lifting drive component 520, which can be a cylinder, a hydraulic cylinder or a linear motor (screw drive structure), etc.; the lower mold body 521, the upper mold body 523 and the central core mold 522 are all provided with heating components.

[0074] In this embodiment, the hot press forming actuator has a robotic arm gripping interface 510, which can integrate electrical and pneumatic communication interfaces; the hot press forming actuator can be equipped with pressure and temperature control modules. The hot pressing process of the hot press forming actuator can be referred to as follows:

[0075] a) A robotic arm is used to grasp the thermoforming actuator. After grasping, the electrical system of the thermoforming actuator is automatically connected, performs a self-test, and connects to the host control system.

[0076] b) The system automatically controls the upper mold body 523 and the lower mold body 521 to start heating. The heating temperature is 70-90℃, and the temperature control accuracy is ±5℃ or ±1℃. The heating timing of the heating components can be achieved by starting the hot pressing actuator, which improves efficiency.

[0077] c) Based on the high-precision positioning system of the robotic arm, the thermoforming actuator is positioned directly above (10-20mm) the corresponding area of ​​the cap area 830;

[0078] d) The pneumatic pressing mechanism (cylinder) of the equipment is used to press down the upper and lower mold bodies 521. The pressure of the lower mold body 521 is 1000-2000N, which is used to fix the lower skin. The pressure of the upper mold body 523 is 0-20N, which is used to prevent the filament bundle 900 from flipping up during the molding process, so that the material deformation direction is in the predetermined direction.

[0079] e) Start pressing down the core mold 522. The pressure of the core mold 522 is 2000-3000N. Hold the pressure until it reaches the set point and then stop. The time is 1-2 minutes.

[0080] f) After the pressure holding is completed, the upper mold body 523, lower mold body 521 and middle core mold 522 begin to cool down. When the temperature is below 40-50℃, the hot pressing actuator is grabbed by the robotic arm and removed from the mold to complete the hot pressing of the cap area 830 and obtain the composite material preform.

[0081] After the hot pressing of the 830-inch cap area is completed, the composite material preform is sealed in a vacuum bag and then cured in an autoclave. After curing, machining and testing are carried out to complete the manufacturing of the skin structure with the cap recessed area.

[0082] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions or improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. An automated method of manufacturing an aircraft panel with a grommet sink feature, the method comprising: The method comprises a laying step and a lip region forming step, and the method comprises: The laying step is performed by using a laying device in a set laying region, the set laying region comprises a smoothing region, a slope region and a lip region, the slope region is connected to the smoothing region and the lip region in transition, the tows have breakpoints in the lip region, and the tows are overlapped or butt-jointed at the breakpoints; The lip region forming step comprises: The hot press forming actuator is used to automatically perform hot press forming on the tows in the lip region and the slope region, so that the tows in the corresponding regions are formed; The lip region forming step comprises: The lower die body of the hot press forming actuator acts on the tows in the smoothing region and close to the edge of the slope region; The upper die body of the hot press forming actuator acts on the tows in the lip region and close to the edge of the slope region; The middle core die of the hot press forming actuator acts on the tows in the slope region between the upper die body and the lower die body; The pressure of the lower die body is 10000N-2000N; the pressure of the upper die body is less than 20N; The pressure of the middle core die is 20000N-3000N; The heating temperature of the lower die body acting on the tows is 70-90℃; The heating temperature of the upper die body acting on the tows is 70-90℃; The heating temperature of the middle core die acting on the tows is 70-90℃.

2. An automated method of manufacturing an aircraft panel with a gapped pocket feature as defined in claim 1, wherein, In the laying region, the breakpoints of the adjacent tows in the same layer and in the same direction are arranged in staggered positions; And / or, the breakpoints of the tows in the adjacent layers are arranged in staggered positions.

3. An automated method of manufacturing an aircraft panel with a gapped pocket feature as defined in claim 2, wherein, The breakpoints of at least five groups of tows in the same direction are arranged in staggered positions along the length direction of the tows in sequence; And / or, the same lip region has at least two groups of tows in different directions, and the at least two groups of tows in different directions have breakpoints.

4. An automated method of manufacturing an aircraft panel with a gapped pocket feature as defined in claim 2, wherein, The staggered distance of the breakpoints of the adjacent tows is 10-15mm; And / or, the tows are overlapped at the breakpoints, and the overlapping length is not more than 3mm.

5. An automated method of manufacturing an aircraft panel with a gapped pocket feature as defined in claim 1, wherein, When the tows enter the lip region from the smoothing region through the slope region during the laying step performed by using the laying device in the set laying region, the laying head of the laying device enters the lip region from the smoothing region through the slope region in a posture perpendicular to the smoothing region.

6. An automated method of manufacturing an aircraft panel with a gapped pocket feature as defined in claim 1, wherein, The holding pressure time of the middle core die acting on the tows is 1-2min; After the holding pressure time is completed, the lower die body, the upper die body and the middle core die are cooled, and when the temperature of the lower die body, the upper die body and the middle core die is lower than 40-50℃, the hot press forming actuator is demoulded, and the lip region forming step is completed.

7. An automated aircraft panel manufacturing apparatus with a grommet sink feature, characterized by, An automatic manufacturing method of an aircraft panel with a lip region sinking feature, comprising a laying device and a hot press forming actuator, the laying device is used to lay tows in a set laying region; the set laying region comprises a smoothing region, a slope region and a lip region, the slope region is connected to the smoothing region and the lip region in transition, and the hot press forming actuator is used to automatically perform hot press forming on the tows in the lip region and the slope region.

8. An automated aircraft panel manufacturing apparatus with a grommet sink feature as defined in claim 7, wherein, The hot press forming actuator comprises a lower die body, an upper die body and a middle core die, the middle core die is movably arranged between the lower die body and the upper die body, The lower die body is used to act on the tows in the smoothing region and close to the edge of the slope region; The upper die body is used to act on the tows in the lip region and close to the edge of the slope region; The middle core die is used for acting on the slope area of the wire; The lower die body, the upper die body and the middle core die are connected with lifting driving components; the lower die body, the upper die body and the middle core die are provided with heating components.

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