A processing mechanism for an aircraft vertical tail rib

Abstract

The utility model discloses a processing mechanism for aircraft vertical tail rib, including upper mould and lower mould, upper mould and lower mould are used for supporting mechanism element, be equipped with high -efficient integrated moulding assembly on upper mould and lower mould, the case relates to aircraft manufacturing technical field, and it has the beneficial effect that: the case can guarantee not leaving the hole mark on the workpiece under the condition of guaranteeing the trepanning of vacuum, thereby greatly improving the quality of workpiece, and can save a lot of later -stage processing cost.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft manufacturing technology, specifically relating to a processing mechanism for aircraft vertical tail ribs. Background Technology

[0002] In aircraft manufacturing, casting is a process that directly shapes workpieces. To ensure the quality of cast parts, a vacuum is required in the mold during the pressing process. However, vacuuming requires drilling holes in the mold wall, which can leave hole marks on the produced parts, affecting the quality of the finished product. Utility Model Content

[0003] In order to solve the above-mentioned problems in the existing technology, the present invention aims to provide a processing mechanism for aircraft vertical tail ribs, including an upper mold and a lower mold, wherein the upper mold and the lower mold are used to support the mechanism components, and the upper mold and the lower mold are provided with a high-efficiency integrated molding component; The high-efficiency integrated molding component includes: a shaping groove, a barrier, a vacuum tube head, a feeding tube head, a guide hole, a guide frame, a lifting hole, a pressing frame, and a sealing frame. The shaping groove is formed on the lower mold, the enclosure is installed around the shaping groove, the vacuum tube head is distributed and installed on both sides of the enclosure, the feed tube head is installed on the front side of the enclosure, the guide hole and the lifting hole are formed on the upper mold, the guide frame passes through the guide hole and is connected to the sealing frame, and the pressing frame passes through the lifting hole and is connected to the sealing frame.

[0004] Preferably, the dimensions of the sealing frame are consistent with the dimensions of the inner side of the enclosure.

[0005] Preferably, the guide frame is provided with a limiting block.

[0006] Beneficial effects This machining mechanism for aircraft vertical tail ribs has the following advantages: This project utilizes a highly efficient one-piece molding component, which ensures that no hole marks are left on the workpiece while guaranteeing the opening for vacuuming, thereby greatly improving the quality of the workpiece and saving a lot of post-processing costs. Attached Figure Description

[0007] The present invention will now be described in further detail with reference to the accompanying drawings and specific implementation methods.

[0008] Figure 1-4 This is a three-dimensional structural schematic diagram of a machining mechanism for an aircraft vertical tail rib according to the present invention. Figure 5 This is a side view of the processing mechanism for the vertical tail rib of an aircraft according to the present invention. In the diagram: 1. Upper mold; 2. Lower mold; 3. Shaping groove; 4. Enclosure; 5. Vacuum tube head; 6. Feed tube head; 7. Guide hole; 8. Guide frame; 9. Lifting hole; 10. Pressing frame; 11. Sealing frame; Detailed Implementation

[0009] To make the objectives, technical solutions, and advantages of this utility model clearer, the present utility model 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 only for explaining the present utility model and are not intended to limit the present utility model; that is, the described embodiments are only some embodiments of the present utility model, and not all embodiments. The components of the embodiments of the present utility model described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0010] 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 claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0011] The following is combined with Figure 1-5 This invention describes a specific embodiment of a processing mechanism for an aircraft vertical tail rib, comprising an upper mold 1 and a lower mold 2. The upper mold 1 and the lower mold 2 are used to support the mechanism components, and the upper mold 1 and the lower mold 2 are provided with a high-efficiency integrated molding assembly. The high-efficiency integrated molding component includes: a shaping groove 3, a barrier 4, a vacuum tube head 5, a feeding tube head 6, a guide hole 7, a guide frame 8, a lifting hole 9, a pressing frame 10, and a sealing frame 11. The shaping groove 3 is formed on the lower mold 2, the enclosure 4 is installed around the shaping groove 3, the vacuum tube head 5 is distributed and installed on both sides of the enclosure 4, the feed tube head 6 is installed on the front side of the enclosure 4, the guide hole 7 and the lifting hole 9 are formed on the upper mold 1, the guide frame 8 passes through the guide hole 7 and is connected to the sealing frame 11, and the pressing frame 10 passes through the lifting hole 9 and is connected to the sealing frame 11.

[0012] It should be noted that during the casting process, the upper mold 1 is fastened onto the lower mold 2, and the sealing frame 11 is embedded into the inner side of the enclosure 4 to a certain depth to ensure that the inside of the shaping groove 3 is sealed. Then, the feed pipe head 6 is closed, and the inside is evacuated to a vacuum state through the vacuum pipe heads 5 at various positions. Then, the sealing frame 11 is lowered through the guide frame 8 into the guide hole 7 by the push-down pressing frame 10, thereby sealing the opening corresponding to the vacuum pipe head 5. Then, the liquid metal for casting can be introduced through the feed pipe head 6 and shaped.

[0013] Preferably, the dimensions of the blocking frame 11 are consistent with the inner dimensions of the enclosure 4.

[0014] It should be noted that the sealing frame 11, which has the same dimensions as the inner side of the enclosure 4, can ensure the sealing of the inside of the shaping groove 3.

[0015] Preferably, the guide frame 8 is provided with a limiting block.

[0016] It should be noted that the limiting block is used to limit the descent range of the sealing frame 11, so that its final descent position is just enough to seal the opening corresponding to the vacuum tube head 5, preventing it from affecting the part forming.

[0017] The above description is merely an example and illustration of the structure of this utility model. Those skilled in the art can make various modifications or additions to the specific embodiments described or use similar methods to replace them, as long as they do not deviate from the structure of the utility model or exceed the scope defined in the claims, they should all fall within the protection scope of this utility model.

Claims

1. A machining mechanism for an aircraft vertical tail rib, comprising an upper mold and a lower mold, wherein the upper mold and the lower mold are used to support mechanism components, characterized in that, The upper and lower molds are equipped with high-efficiency integrated molding components; The high-efficiency integrated molding component includes: a shaping groove, a barrier, a vacuum tube head, a feeding tube head, a guide hole, a guide frame, a lifting hole, a pressing frame, and a sealing frame. The shaping groove is formed on the lower mold, the enclosure is installed around the shaping groove, the vacuum tube head is distributed and installed on both sides of the enclosure, the feed tube head is installed on the front side of the enclosure, the guide hole and the lifting hole are formed on the upper mold, the guide frame passes through the guide hole and is connected to the sealing frame, and the pressing frame passes through the lifting hole and is connected to the sealing frame.

2. The machining mechanism for an aircraft vertical tail rib according to claim 1, characterized in that, The dimensions of the sealing frame are consistent with the dimensions of the inner side of the enclosure.

3. The machining mechanism for an aircraft vertical tail rib according to claim 1, characterized in that, The guide frame is equipped with a limit block.

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