A contouring processing device for aircraft composite honeycomb core materials

Abstract

This invention discloses a contour processing device for aircraft composite honeycomb core materials, belonging to the field of honeycomb core material processing technology. It includes a base plate, a support plate fixed to the top side of the base plate, multiple side plates fixed to the side of the support plate facing the center of the base plate, a clip assembly between two side plates, and a chip removal assembly on the top side of the base plate. The chip removal assembly has an adjustment component. This invention uses the chip removal assembly to blow airflow to the edge of the honeycomb core material, thereby removing the chips generated during cutting and improving the surface quality. Simultaneously, the airflow significantly improves heat dissipation in the processing area, reducing the cutting temperature. The adjustment component allows for adjustment of the airflow size, adapting to the processing needs of honeycomb core materials with different pore sizes and materials. It exhibits excellent process adaptability, improving the overall applicability of the device and enhancing its overall practicality.

Description

Technical Field

[0001] This invention belongs to the field of honeycomb core material processing technology, specifically relating to a contour processing equipment for aircraft composite honeycomb core materials. Background Technology

[0002] Honeycomb core material for aircraft is a lightweight, high-performance sandwich structure material widely used in aerospace. It is primarily composed of a hexagonal honeycomb core made of aramid paper (Nomex), aluminum alloy, or composite materials, which is then bonded to a carbon fiber or glass fiber skin using adhesive or co-curing processes. Thanks to its unique honeycomb topology, this material achieves significant weight reduction while maintaining extremely high specific strength and specific stiffness, reducing weight by 30%-50% compared to traditional metal structures. It has become a core material for secondary load-bearing structures such as wings, control surfaces, and doors in modern aircraft. The key advantages of honeycomb core material lie in its superior mechanical properties: excellent compressive strength in the vertical direction, capable of withstanding aerodynamic loads during flight; and good shear stiffness in the planar direction, effectively transferring structural stress. Simultaneously, the closed-cell honeycomb structure endows the material with natural sound and heat insulation properties, while also possessing corrosion resistance and fatigue resistance. In new-generation aircraft such as the A350 and B787, the proportion of sandwich structures combining honeycomb core material and carbon fiber prepreg exceeds 15%. With the development of aerospace manufacturing technology, honeycomb core materials are evolving towards functional integration, such as embedding sensors for structural health monitoring and using fire-retardant coatings to enhance safety. Their processing technology is also continuously innovating, including precision forming technologies such as CNC contour cutting and laser processing, to meet the increasingly complex surface requirements of aircraft components. The application of this material not only reduces aircraft fuel consumption but also provides important material support for the future of green aviation.

[0003] For example, Chinese Patent Publication No. CN208644880U discloses a contouring processing device for a honeycomb core material of an aircraft composite material, including a slide table: it includes four support blocks that can be located in a plane and are symmetrical in the front, back, left and right directions. The left and right support blocks at the front and back are rotatably supported by left and right ball screws. The left and right support blocks at the front and back are respectively equipped with X-axis servo motors, and the ball screws are equipped with left and right ball sliders that can move left and right. The left and right ball sliders on the front and back ball screws are rotatably supported by the front and back ball screws. The left and right ball sliders at the front or back are equipped with Y-axis servo motors, and the front and back ball screws are equipped with front and back ball sliders. The front and back ball sliders are equipped with vertical slide rails. There is also a contouring processing device, which has a template finger at the bottom of the front foot, a template milling cutter at the bottom of the rear foot, and a ball slider in the middle of the crossbeam that cooperates with the vertical slide rail. The processing device is supported on the vertical slide rail by sliding up and down through the ball slider.

[0004] The processing equipment described in the above application is cumbersome and inconvenient to use when clamping multiple honeycomb core materials, which affects the overall processing efficiency. It is also easy to cause certain damage to the honeycomb core materials and it is difficult to remove the debris generated during the cutting process, which affects the overall processing accuracy.

[0005] Therefore, a contouring processing device for aircraft composite honeycomb core materials is needed to solve the problems mentioned in the background art. Summary of the Invention

[0006] The purpose of this invention is to provide a contour processing device for aircraft composite honeycomb core materials to solve the problems mentioned in the background art.

[0007] To achieve the above objectives, the present invention provides the following technical solution: a contour processing device for aircraft composite honeycomb core material, comprising a base plate, a support plate fixed on the top side of the base plate, a plurality of side plates equally distributed on the side of the support plate facing the center of the base plate, a magazine assembly disposed between two of the side plates, a chip removal assembly disposed on the top side of the base plate, and an adjustment assembly disposed on the chip removal assembly.

[0008] It should be noted in the solution that the magazine assembly includes a rubber plate fixed to the side of the side plate, the rubber plate has a cavity inside, a conveying pipe is provided on one side of the support plate, and a branch pipe communicating with the cavity is connected to the conveying pipe.

[0009] It is worth noting that a liquid cylinder is connected to the conveying pipe, and a nut sleeve is fixed inside the end of the liquid cylinder away from the conveying pipe. A first threaded rod is threadedly connected inside the nut sleeve, and a piston plate is fixed to one end of the first threaded rod, which fits tightly against the inner wall of the liquid cylinder.

[0010] Furthermore, it should be noted that an end plate is fixed to the end of the first threaded rod away from the piston plate, a handle is fixed to the side of the end plate, a rubber sleeve is fitted onto the surface of the handle, and a fixing plate is fixed to the outer wall of the support plate, and the fixing plate is fixed to the liquid cylinder.

[0011] In a preferred embodiment, a rubber pad that mates with the rubber plate is fixed on the side of the side plate.

[0012] In a preferred embodiment, the chip removal assembly includes a blower seat fixed to the top side of the base plate, the blower seat having a ventilation cavity inside, and a blower port communicating with the ventilation cavity having a side opening on the blower seat. The blower port is provided with multiple blowers that are equidistantly distributed, and an air inlet pipe communicating with the ventilation cavity is fixed to the side of the blower seat.

[0013] In a preferred embodiment, the adjustment assembly includes an adjustment plate that fits against the side of the blower base, and the side of the adjustment plate has a plurality of adjustment ports corresponding to the blower openings.

[0014] In a preferred embodiment, a second end plate is fixed to the top of the adjusting plate, a nut sleeve is fixed inside the second end plate, a second threaded rod is threadedly connected inside the nut sleeve, one end of the second threaded rod is rotatably connected to the top surface of the blower seat, and a rotating plate is fixed to the top of the second threaded rod.

[0015] In a preferred embodiment, a plurality of symmetrically distributed support rods are fixed on the bottom side of the base plate, and casters are installed on the bottom of the support rods. A baffle is fixed on the side of the blower base along the length of the blower base. There are two baffles, and the two baffles are symmetrically distributed. The adjustment plate is inserted between the two baffles.

[0016] In a preferred embodiment, two symmetrically distributed diagonal bars are fixed to one end of the base plate, and a handle bar is fixed to the top of the two diagonal bars. The surface of the handle bar is fitted with a rubber sleeve.

[0017] Compared with the prior art, the conformal processing equipment for aircraft composite honeycomb core materials provided by the present invention has at least the following beneficial effects:

[0018] 1. Multiple honeycomb core materials are simultaneously and elastically clamped and fixed by the set spring clip assembly. Multiple core materials can be clamped at the same time, eliminating the need for manual clamping of honeycomb core materials one by one. This greatly reduces manual intervention and is suitable for batch production needs. At the same time, it can provide sufficient clamping force while adaptively adjusting the pressure distribution, effectively avoiding the problems of honeycomb cell wall crushing or deformation caused by traditional rigid clamping. This ensures the integrity of the core material structure, effectively suppresses the micro displacement of the core material during processing, ensures stability under cutting force, improves the surface contour accuracy, and can quickly change the fixture module to meet the flexible production needs of small batches and multiple varieties.

[0019] 2. By blowing airflow through the chip removal component to the edge of the honeycomb core material, the waste chips generated during the cutting of the honeycomb core material are removed. That is, the generated chips are blown away from the honeycomb cells and the processing area in real time during the cutting process, avoiding the secondary cutting of the tool or scratches on the core material surface caused by the accumulation of waste chips, thereby improving the surface quality of the machined material. At the same time, the airflow purging can also significantly improve the heat dissipation conditions of the processing area, reduce the cutting temperature, and reduce the risk of honeycomb core material deformation caused by heat accumulation. It is particularly suitable for precision machining of easily thermally conductive materials such as aluminum alloy honeycomb. It has a simple structure, low energy consumption, and will not cause mechanical contact damage to the honeycomb structure. It maintains the continuity of the processing while ensuring the cleaning effect.

[0020] 3. The size of the airflow blown by the chip removal component can be adjusted by the set adjustment component, which can adapt to the processing needs of honeycomb core materials with different pore sizes and materials, and has excellent process adaptability, as well as the overall applicability and practicality of the device. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the overall structure of the present invention. Figure 1 ;

[0022] Figure 2 This is a schematic diagram of the overall front view of the present invention;

[0023] Figure 3 This is a schematic diagram of the overall structure of the present invention. Figure 2 ;

[0024] Figure 4 This is a schematic diagram of the overall structure of the present invention. Figure 3 ;

[0025] Figure 5 This is a partial structural diagram of the magazine assembly of the present invention;

[0026] Figure 6 This is a cross-sectional view of the magazine assembly of the present invention;

[0027] Figure 7 for Figure 6 Enlarged structural diagram at point A in the middle;

[0028] Figure 8 This is a cross-sectional view of the chip removal component of the present invention;

[0029] Figure 9 This is a partial structural diagram of the adjustment component of the present invention;

[0030] Figure 10 for Figure 9 Enlarged structural diagram at point B.

[0031] In the diagram: 1. Magazine assembly; 101. Rubber plate; 102. Cavity; 103. Conveyor pipe; 104. Fixing plate; 105. Liquid cylinder; 106. Piston plate; 107. First threaded rod; 108. End plate one; 109. Handle rod; 110. Branch pipe; 2. Chip removal assembly; 201. Air blower seat; 202. Ventilation cavity; 203. Air inlet pipe; 204. Air outlet; 3. Adjustment assembly; 301. Adjustment plate; 302. Adjustment port; 303. Baffle; 304. Nut sleeve; 305. Second threaded rod; 306. End plate two; 307. Rotating head plate; 4. Base plate; 5. Support plate; 6. Side plate; 7. Diagonal rod; 8. Handle rod; 9. Rubber pad; 10. Caster wheel; 11. Support leg rod. Detailed Implementation

[0032] The present invention will be further described below with reference to embodiments.

[0033] Please see Figure 1-10 This invention provides a contouring processing device for aircraft composite honeycomb core materials, including a base plate 4, a support plate 5 fixed on the top side of the base plate 4, and multiple equidistant side plates 6 fixed on the side of the support plate 5 facing the center of the base plate 4. A clip assembly 1 is arranged between two side plates 6, and a chip removal assembly 2 is arranged on the top side of the base plate 4. An adjustment assembly 3 is arranged on the chip removal assembly 2. In use, multiple contoured aircraft composite honeycomb core materials to be processed are placed between the multiple side plates 6, and the multiple honeycomb core materials are synchronously and elastically clamped and fixed by the clip assembly 1. The synchronous clamping of multiple core materials can be completed at one time, eliminating the need for manual clamping of honeycomb core materials one by one, greatly reducing manual intervention, and is suitable for batch production needs. At the same time, it can provide sufficient clamping force while adaptively adjusting the pressure distribution, effectively avoiding the problem of honeycomb cell wall crushing or deformation caused by traditional rigid clamping, ensuring the structural integrity of the core material, effectively suppressing the micro-displacement of the core material during processing, ensuring stability under the action of cutting force, improving the surface contour accuracy, and enabling quick replacement of fixture modules. It can meet the flexible production needs of small batches and multiple varieties. After the honeycomb core material is firmly clamped, the edge contour of the honeycomb core material is trimmed. During the processing of the honeycomb core material, the chip removal component 2 blows air to the edge of the honeycomb core material to remove the waste chips generated during the cutting process. That is, the generated chips are blown away from the honeycomb grid and processing area in real time during the cutting process, avoiding the secondary cutting of the tool or scratches on the core material surface caused by the accumulation of waste chips, thereby improving the surface quality of the processed material. At the same time, the airflow can also significantly improve the heat dissipation conditions of the processing area, reduce the cutting temperature, and reduce the risk of honeycomb core material deformation caused by heat accumulation. It is particularly suitable for precision processing of easily thermally conductive materials such as aluminum alloy honeycomb. It has a simple structure, low energy consumption, and will not cause mechanical contact damage to the honeycomb structure. It maintains the continuity of the processing process while ensuring the cleaning effect. The size of the airflow blown by the chip removal component 2 can be adjusted by the adjustment component 3 to adapt to the processing needs of honeycomb core materials with different pore sizes and materials. It has excellent process adaptability and overall practicality.

[0034] Further as Figure 1 , Figure 5 and Figure 7As shown, it is worth noting that the magazine assembly 1 includes a rubber plate 101 fixed to the side of the side plate 6. The rubber plate 101 has a cavity 102 inside. A conveying pipe 103 is provided on one side of the support plate 5. A branch pipe 110 communicating with the cavity 102 is connected to the conveying pipe 103. A liquid cylinder 105 is connected to the conveying pipe 103. A nut sleeve is fixed inside the end of the liquid cylinder 105 away from the conveying pipe 103. A first threaded rod 107 is threaded inside the nut sleeve. A piston plate 106 that fits tightly against the inner wall of the liquid cylinder 105 is fixed to one end of the first threaded rod 107. Multiple conformal aircraft composite honeycomb core materials to be trimmed are placed between multiple side plates 6. By rotating the first threaded rod 107, the first threaded rod 107 drives the piston plate 106 to move inside the liquid cylinder 105. The piston plate 106 forces the liquid in the liquid cylinder 105 through the delivery pipe 103 into the interior of multiple rubber plates 101, causing the rubber plates 101 to expand elastically. This allows the multiple rubber plates 101 to simultaneously and elastically clamp and fix multiple honeycomb core materials, enabling simultaneous clamping of multiple core materials at once. This eliminates the need for manual clamping of each honeycomb core material, significantly reducing manual intervention. It is suitable for mass production needs and can adaptively adjust the pressure distribution while providing sufficient clamping force. This effectively avoids the problems of honeycomb cell wall crushing or deformation caused by traditional rigid clamping, ensuring the structural integrity of the core material. It effectively suppresses the micro-displacement of the core material during processing, ensures stability under cutting force, improves the surface contour accuracy, and allows for quick replacement of fixture modules to meet the flexible production needs of small batches and multiple varieties.

[0035] Further as Figure 7 As shown, it is worth noting that an end plate 108 is fixed to the end of the first threaded rod 107 away from the piston plate 106, and a handle rod 109 is fixed to the side of the end plate 108. A rubber sleeve is fitted onto the surface of the handle rod 109, and a fixing plate 104 is fixed to the outer wall of the support plate 5. The fixing plate 104 is fixed to the liquid cylinder 105. In actual operation, the first threaded rod 107 is rotated by holding and rotating the handle rod 109, which facilitates operation.

[0036] Further as Figure 5 and Figure 6 As shown, it is worth noting that a rubber pad 9 that mates with the rubber plate 101 is fixed on the side of the side plate 6; in actual operation, the rubber pad 9 further improves the stability of the rubber plate 101 in clamping the honeycomb core material.

[0037] Further as Figure 3 , Figure 8 and Figure 9As shown, it is worth noting that the chip removal assembly 2 includes a blower seat 201 fixed to the top side of the base plate 4. The blower seat 201 has a ventilation cavity 202 inside, and a blower port 204 communicating with the ventilation cavity 202 is provided on the side of the blower seat 201. Multiple blower ports 204 are provided and are equidistantly distributed. An air inlet pipe 203 communicating with the ventilation cavity 202 is fixed to the side of the blower seat 201. An air pump is connected to the air inlet pipe 203. During the processing of the honeycomb core material, airflow is delivered to the inside of the blower seat 201 through the air inlet pipe 203, and then blown out through the ventilation cavity 202 and the multiple blower ports 204. Airflow reaches the edges of the honeycomb core material, thereby blowing away the chips generated during cutting. In other words, the chips generated during the cutting process are blown away from the honeycomb cells and the machining area in real time, avoiding the accumulation of chips that could cause secondary cutting by the tool or scratches on the core material surface, thus improving the surface quality of the machined material. At the same time, airflow purging can also significantly improve the heat dissipation conditions of the machining area, reduce the cutting temperature, and reduce the risk of deformation of the honeycomb core material due to heat accumulation. It is particularly suitable for precision machining of easily thermally conductive materials such as aluminum alloy honeycomb. It has a simple structure, low energy consumption, and will not cause mechanical contact damage to the honeycomb structure, maintaining the continuity of the machining process while ensuring the cleaning effect.

[0038] Further as Figure 8 , Figure 9 and Figure 10 As shown, it is worth noting that the adjustment assembly 3 includes an adjustment plate 301 that fits against the side of the blower base 201. Multiple adjustment ports 302 corresponding to the blower nozzles 204 are provided on the side of the adjustment plate 301. An end plate 306 is fixed to the top of the adjustment plate 301, and a nut sleeve 304 is fixed inside the end plate 306. A second threaded rod 305 is threaded into the nut sleeve 304. One end of the second threaded rod 305 is rotatably connected to the top surface of the blower base 201. A rotating head plate 307 is fixed on the top of 5. In actual operation, by rotating the second threaded rod 305, the second threaded rod 305 drives the adjusting plate 301 to move, thereby causing the adjusting port 302 and the air blowing port 204 to be misaligned to different degrees, thereby adjusting the flow diameter of the air blowing port 204, thus adjusting the size of the airflow blown out by the chip removal component 2. It can adapt to the processing needs of honeycomb core materials with different pore sizes and materials, and has excellent process adaptability. It is applicable to the overall device and has good overall practicality.

[0039] This solution includes the following working process: Multiple honeycomb core materials of aircraft-shaped composite materials to be edge-cut are placed between multiple side plates 6. By rotating the first threaded rod 107, the first threaded rod 107 drives the piston plate 106 to move within the liquid cylinder 105. The piston plate 106 then forces the liquid in the liquid cylinder 105 through the delivery pipe 103 into the interior of multiple rubber plates 101, causing the rubber plates 101 to elastically expand. This allows the multiple rubber plates 101 to simultaneously and elastically clamp and fix the multiple honeycomb core materials, completing the simultaneous clamping of multiple core materials in one operation. Airflow is delivered to the blower seat 201 through the air inlet pipe 203, and then blown out through the ventilation cavity 202 and multiple air outlets 204 to the edges of the honeycomb core materials. This process removes the chips generated during the cutting of the honeycomb core material. Specifically, it blows the chips away from the honeycomb cells and the processing area in real time during the cutting process, preventing chip buildup that could cause secondary cutting or scratches on the core material surface, thus improving the surface quality. Simultaneously, the airflow significantly improves heat dissipation in the processing area, reducing cutting temperature and minimizing the risk of honeycomb core material deformation due to heat accumulation. By rotating the second threaded rod 305, the adjusting plate 301 moves, causing the adjusting port 302 and the air outlet 204 to be misaligned to varying degrees. This adjusts the flow diameter of the air outlet 204, thereby regulating the airflow from the chip removal component 2 to adapt to the processing needs of honeycomb core materials with different pore sizes and materials.

[0040] Further as Figure 1 and Figure 9 As shown, it is worth noting that multiple symmetrically distributed support rods 11 are fixed on the bottom side of the base plate 4, and casters 10 are installed on the bottom of the support rods 11. Baffles 303 arranged along the length of the blower base 201 are fixed on the side of the blower base 201. There are two baffles 303, which are symmetrically distributed. The adjustment plate 301 is inserted between the two baffles 303. In actual operation, the casters 10 can be used to easily move the whole device to different occasions. The baffles 303 guide and limit the movement of the adjustment plate 301, thereby improving the stability of the adjustment of the adjustment plate 301.

[0041] Further as Figure 1 , Figure 2 and Figure 3 As shown, it is worth noting that two symmetrically distributed diagonal rods 7 are fixed on one end of the base plate 4, and a handle 8 is fixed to the top of the two diagonal rods 7. The surface of the handle 8 is fitted with a rubber sleeve. In actual operation, the handle 8 can be used to easily push the whole device to move, making it convenient to operate.

[0042] In summary: The spring clip assembly 1 synchronously and elastically clamps and fixes multiple honeycomb core materials, enabling simultaneous clamping of multiple core materials at once. This eliminates the need for manual clamping of each core material individually, significantly reducing manual intervention. Suitable for mass production needs, it provides sufficient clamping force while adaptively adjusting pressure distribution, effectively avoiding the crushing or deformation of the honeycomb grid walls caused by traditional rigid clamping. This ensures the structural integrity of the core material, effectively suppresses micro-displacement of the core material during processing, guarantees stability under cutting forces, and improves the accuracy of the workpiece surface contour. The ability to quickly change fixture modules meets the flexible production needs of small-batch, multi-variety production. After the honeycomb core material is securely clamped, its edge contour is trimmed. During processing, the chip removal assembly 2 blows airflow to the edge of the honeycomb core material, thereby... The chip removal device removes chips generated during the cutting of honeycomb core materials. This means that chips are blown away from the honeycomb cells and processing area in real time during the cutting process, preventing chip buildup that could cause secondary cutting or scratches on the core material surface, thus improving the surface quality. Simultaneously, the airflow significantly improves heat dissipation in the processing area, lowers the cutting temperature, and reduces the risk of honeycomb core material deformation due to heat accumulation. It is particularly suitable for precision machining of thermally conductive materials such as aluminum alloy honeycomb. The device has a simple structure, low energy consumption, and does not cause mechanical contact damage to the honeycomb structure, maintaining the continuity of the processing while ensuring cleaning effectiveness. The adjustable component 3 allows for adjustment of the airflow from the chip removal component 2, adapting to the processing needs of honeycomb core materials with different pore sizes and materials. It exhibits excellent process adaptability and overall practicality.

Claims

1. A contouring processing device for aircraft composite honeycomb core material, comprising a base plate (4), characterized in that, A support plate (5) is fixed on the top side of the base plate (4). Multiple side plates (6) are fixed on the side of the support plate (5) facing the center of the base plate (4). A magazine assembly (1) is provided between two side plates (6). A chip removal assembly (2) is provided on the top side of the base plate (4). An adjustment assembly (3) is provided on the chip removal assembly (2). The magazine assembly (1) includes a rubber plate (101) fixed to the side of the side plate (6), and a cavity (102) is provided inside the rubber plate (101). A delivery pipe (103) is provided on one side of the support plate (5), and a branch pipe (110) communicating with the cavity (102) is connected to the delivery pipe (103). The chip removal assembly (2) includes a blower seat (201) fixed on the top side of the base plate (4). The blower seat (201) has a ventilation cavity (202) inside. The blower seat (201) has an air outlet (204) communicating with the ventilation cavity (202) on its side. There are multiple air outlets (204) and the multiple air outlets (204) are equidistantly distributed. An air inlet pipe (203) communicating with the ventilation cavity (202) is fixed on the side of the blower seat (201). The adjustment component (3) includes an adjustment plate (301) that is fitted to the side of the blower base (201), and the side of the adjustment plate (301) has a plurality of adjustment ports (302) corresponding to the blower port (204). The top end plate (306) is fixed to the top end of the adjustment plate (301), and a nut sleeve (304) is fixed inside the end plate (306). A second threaded rod (305) is threaded inside the nut sleeve (304). One end of the second threaded rod (305) is rotatably connected to the top surface of the blower seat (201), and a rotating head plate (307) is fixed to the top end of the second threaded rod (305).

2. The conformal processing equipment for aircraft composite honeycomb core material according to claim 1, characterized in that, The delivery pipe (103) is connected to a liquid cylinder (105). A nut sleeve is fixed inside the end of the liquid cylinder (105) away from the delivery pipe (103). A first threaded rod (107) is threaded inside the nut sleeve. A piston plate (106) is fixed on one end of the first threaded rod (107) and fits tightly against the inner wall of the liquid cylinder (105).

3. The conformal processing equipment for aircraft composite honeycomb core material according to claim 2, characterized in that, An end plate (108) is fixed to one end of the first threaded rod (107) away from the piston plate (106). A handle rod (109) is fixed to the side of the end plate (108). A rubber sleeve is fitted on the surface of the handle rod (109). A fixing plate (104) is fixed to the outer wall of the support plate (5). The fixing plate (104) is fixed to the liquid cylinder (105).

4. The conformal processing equipment for aircraft composite honeycomb core material according to claim 3, characterized in that, A rubber pad (9) that mates with a rubber plate (101) is fixed on the side of the side plate (6).

5. The conformal processing equipment for aircraft composite honeycomb core material according to claim 4, characterized in that, Multiple symmetrically distributed support rods (11) are fixed on the bottom side of the base plate (4). Universal wheels (10) are installed on the bottom end of the support rods (11). A baffle (303) arranged along the length of the blower seat (201) is fixed on the side of the blower seat (201). There are two baffles (303) and the two baffles (303) are symmetrically distributed. The adjustment plate (301) is inserted between the two baffles (303).

6. The conformal processing equipment for aircraft composite honeycomb core material according to claim 1, characterized in that, Two symmetrically distributed diagonal rods (7) are fixed on one end of the base plate (4), and a handle (8) is fixed on the top of the two diagonal rods (7). A rubber sleeve is fitted on the surface of the handle (8).

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