Aviation part seat reverse hooking tool and machining method

Abstract

The invention relates to the technical field of aviation part machining, in particular to an aviation part seat reverse hooking tool and a machining method. The cutter bar is connected to the lower portion of the cutter handle, and the reamer is connected to the lower portion of the cutter bar. Wherein a cooling water channel is formed in the cutter handle and the cutter bar, the reamer is provided with a notch part, a liquid outlet communicated with the cooling water channel is formed in the notch part, and a valve control structure is further arranged in the cooling water channel. In this way, the machining precision can be effectively guaranteed, compared with an electric spark machining mode or other machining modes, the machining time is saved, the machining quality is improved, the reliability of the production process is improved, the machining limitation of a common T-shaped tool can be effectively overcome, and the product quality is improved; and the reamer can be cooled.

Description

Technical Field

[0001] The invention relates to the technical field of aviation component processing, and in particular to an aviation component seat reverse hook tool and a processing method. Background Art

[0002] In the field of aviation parts processing, especially in the processing of structural parts such as seats, it is often involved in the manufacture of complex hole structures, such as closed countersunk holes. While these hole structures provide the necessary connection and assembly functions, they also place high demands on the processing technology. Traditional processing methods, such as using a machining center (CNC) for rotary cutting, have obvious limitations.

[0003] Existing machining centers usually operate according to NC programs. The machine tool spindle rotates and moves to the specified XY coordinate position, and then cuts along the Z axis for processing. This method requires that the tool must pass through a feature larger than its rotational outer diameter during the rotation process. For structural features such as closed countersink holes, traditional processing methods are not only inefficient, but also easily cause tool damage, increasing processing costs.

[0004] In addition, although EDM can process complex shapes, its efficiency is relatively low and it is not suitable for large-scale production. The overall structure of the product is large and not suitable for lathe processing, which further limits the application scope of existing processing methods.

[0005] Therefore, in order to solve the above problems, we propose an aviation component seat back-hook tool and processing method. Summary of the invention

[0006] The purpose of the present invention is to solve the above-mentioned shortcomings in the prior art and to propose an aviation component seat reverse hook tool and processing method.

[0007] In order to achieve the above object, the present invention adopts the following technical solutions:

[0008] Design a reverse hook tool for seats of aviation parts, including:

[0009] A knife handle, a knife rod connected below the knife handle, and a reamer connected below the knife rod;

[0010] Wherein, cooling water channels are arranged inside the tool handle and the tool rod, the reamer has a notch portion, a liquid outlet connected to the cooling water channel is opened at the notch portion, and a valve control structure is also arranged in the cooling water channel.

[0011] Furthermore, the tool handle and the tool rod are both cylindrical structures, and the reamer is a circular structure.

[0012] Furthermore, the shank includes an upper connecting section and a lower connecting section, the upper connecting section and the lower connecting section are connected via a fastener, wherein the valve control structure is installed inside the lower connecting section.

[0013] Furthermore, the valve control structure includes a valve plug sliding in the cooling water channel, the bottom of the valve plug is fixedly connected to a connecting column, the lower end of the connecting column is rotatably connected to a rotating ring, and a spring is provided between the rotating ring and the cooling water channel.

[0014] Furthermore, the cooling water channel is in a step structure, and two ends of the spring respectively abut against the step of the step structure and the lower side of the rotating ring.

[0015] Furthermore, an adjusting rod is rotatably connected in the cooling water channel, a baffle portion is formed at the bottom of the adjusting rod, and the baffle portion blocks the liquid outlet, wherein a driving assembly is arranged between the adjusting rod and the rotating ring.

[0016] Furthermore, the driving assembly includes a sleeve connected to the lower connecting section, and two spiral grooves are opened on the outer side of the sleeve, wherein the two sides of the rotating ring are fixedly connected with guide shafts sliding in the spiral grooves, and the bottom of the rotating ring is also fixedly connected with a connecting shaft, and the connecting shaft is plugged into the adjusting rod.

[0017] Furthermore, the bottom of the connecting shaft has a rectangular hole, the top of the adjusting rod has a rectangular section, and the rectangular section is plugged into the rectangular hole.

[0018] Furthermore, the top of the lower connecting section has a step opening, and the sleeve is placed in the step opening, wherein a positioning notch is opened at the upper end of the sleeve, and a protrusion that is snapped into the positioning notch is formed at the bottom of the upper connecting section.

[0019] In addition, the present invention also proposes a method for processing an aviation component seat, using the above-mentioned tool, the method comprising:

[0020] Orient the spindle on the CNC machine to ensure that the reamer direction of the tool is consistent with the preset direction;

[0021] Move the reamer over the tail structure of an aircraft seat-type component;

[0022] Control the machine tool spindle to move in the Z direction, so that the reamer passes through the through hole and cuts to the root position of the processed hole;

[0023] The machine tool spindle is rotated to drive the reverse hook cutter to rotate, move from bottom to top in the processing hole, and cut along the inner diameter of the processing hole to complete the reverse hook processing of the tail structure of aircraft seat parts;

[0024] After completing the cutting of the processing hole, stop the spindle rotation, move the reamer to the position of the through hole, move the machine tool spindle up in the Z direction, lift the tool and return to zero, and complete the processing process.

[0025] The invention proposes an aviation component seat reverse hook tool and processing method, which has the beneficial effect that after the tool in the invention moves to the Z direction of the specified XY position, the machine tool spindle rotates again, which can effectively ensure the processing accuracy. Compared with electric spark or other processing methods, this tool and method save processing time, improve processing quality and improve the reliability of the production process, can effectively overcome the limitations of commonly used T-shaped tool processing and improve product quality. Secondly, a cooling water channel is built into the tool, and the reamer can be cooled during the processing to ensure the continuous working stability of the entire tool. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 A perspective view of the present invention;

[0027] Figure 2 is a cross-sectional view of the present invention;

[0028] Figure 3 for Figure 2 A schematic diagram of the enlarged structure of area A;

[0029] Figure 4 It is a structural schematic diagram of the valve control structure of the present invention;

[0030] Figure 5 It is a schematic diagram of the structure of the adjusting rod of the present invention;

[0031] Figure 6 A schematic cross-sectional view of a product to be processed;

[0032] Figure 7 It is the front view of the present invention.

[0033] In the figure: 1. tool handle; 11. upper connecting section; 12. lower connecting section; 2. tool rod; 3. reamer; 31. notch; 32. liquid outlet; 4. cooling water channel; 5. valve control structure; 51. valve plug; 52. connecting column; 53. rotating ring; 54. spring; 6. adjusting rod; 61. baffle; 7. driving assembly; 71. sleeve; 72. spiral groove; 73. guide shaft; 74. connecting shaft; 75. positioning notch; 76. protrusion. DETAILED DESCRIPTION

[0034] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0035] Reference Figure 1-7 An embodiment of the present invention discloses an aviation component seat reverse hook tool, specifically the reverse hook tool comprises a tool handle 1, a tool rod 2 connected below the tool handle 1, and a reamer 3 connected below the tool rod 2;

[0036] A cooling water channel 4 is arranged inside the tool handle 1 and the tool rod 2 , the reamer 3 has a notch 31 , a liquid outlet 32 ​​connected to the cooling water channel 4 is opened at the notch 31 , and a valve control structure 5 is also arranged in the cooling water channel 4 .

[0037] In some embodiments, the tool handle 1 and the tool rod 2 of the present invention are both cylindrical structures, and the reamer 3 is a 3 / 4 circumferential structure. Specifically, the diameter of the tool rod 2 of the present invention is smaller than the diameter of the tool handle 1 to form a first-step structure as a whole.

[0038] Furthermore, the shank 1 in the present invention comprises an upper connecting section 11 and a lower connecting section 12, wherein the upper connecting section 11 and the lower connecting section 12 are connected via fasteners, wherein the valve control structure 5 is installed inside the lower connecting section 12. Preferably, the fasteners described in this embodiment are configured as bolts, and in this embodiment, the upper connecting section 11 and the lower connecting section 12 are connected and fixed by bolts, so that during assembly, the internal valve control structure 5 can be conveniently installed and the convenience of subsequent disassembly and maintenance can be ensured. Furthermore, in this embodiment, there are four bolts distributed around the circumference, and the bolts are hexagon socket bolts.

[0039] On the basis of the above embodiments, the valve control structure 5 in the present invention includes a valve plug 51 sliding in the cooling water channel 4, the valve plug 51 abuts against the bottom opening of the upper connecting section 11 to close the cooling water channel 4, the bottom of the valve plug 51 is fixedly connected with a connecting column 52, the lower end of the connecting column 52 is rotatably connected with a rotating ring 53, a spring 54 is arranged between the rotating ring 53 and the cooling water channel 4, and a liquid hole is opened on the end face of the rotating ring 53 in this embodiment to ensure the flow of coolant.

[0040] Specifically, in this embodiment, the diameter of the valve plug 51 is smaller than the diameter of the opening in the lower connecting section 12. Of course, the diameter of the valve plug 51 should be larger than the opening diameter of the upper connecting section 11. In this way, when the valve plug 51 moves, the opening between the upper connecting section 11 and the lower connecting section 12 is connected to achieve the conduction of the cooling water channel 4. When the valve plug 51 is reset, the bottom opening of the upper connecting section 11 can also be closed.

[0041] Preferably, the cooling water channel 4 in this embodiment is a step structure, and the two ends of the spring 54 respectively abut against the step of the step structure and the lower side of the rotating ring 53. That is to say, in the initial state, the spring 54 is arranged to abut against the rotating ring 53 to control the valve plug 51 to remain at the bottom opening of the upper connecting section 11, thereby closing the entire cooling water channel 4. During operation, the opening of the upper connecting section 11 can be connected to the coolant. When the coolant is supplied into the cooling water channel 4 via a liquid pump, the valve plug 51 is driven downward by the pressure of the coolant, so that the entire cooling water channel 4 can be opened. When the coolant is discharged through the cooling water channel 4 and the liquid outlet 32, the tool can be cooled.

[0042] In some embodiments, in the present invention, an adjusting rod 6 is also rotatably connected in the cooling water channel 4, and a baffle portion 61 is formed at the bottom of the adjusting rod 6, and the baffle portion 61 blocks the liquid outlet 32. Specifically, the baffle portion 61 described in this embodiment is eccentrically arranged with the adjusting rod 6, and the baffle portion 61 is designed to block the liquid outlet 32 ​​to form different sizes of liquid outlet 32 ​​widths to further adjust the liquid output, wherein a driving component 7 is arranged between the adjusting rod 6 and the rotating ring 53.

[0043] On the basis of the above-mentioned embodiments, the driving assembly 7 in this embodiment includes a sleeve 71 connected to the lower connecting section 12, and two spiral grooves 72 are provided on the outer side of the sleeve 71, wherein the two sides of the rotating ring 53 are fixedly connected with guide shafts 73 sliding in the spiral grooves 72, and the bottom of the rotating ring 53 is also fixedly connected with a connecting shaft 74, and the connecting shaft 74 is plugged into the adjusting rod 6.

[0044] In addition, in order to ensure the circumferential locking between the connecting shaft 74 and the adjusting rod 6, the bottom of the connecting shaft 74 in the present invention has a rectangular hole, and the top of the adjusting rod 6 has a rectangular section, and the rectangular section is plugged into the rectangular hole. Of course, the depth of the rectangular hole described in this embodiment is greater than the length of the rectangular section.

[0045] That is to say, in specific operation, when the external pressurized coolant enters the cooling water channel 4, the coolant will resist the movement of the valve plug 51, thereby realizing the conduction of the cooling water channel 4, and the coolant can be sprayed outward along the cooling water channel 4 and the liquid outlet 32 ​​to cool the reamer 3;

[0046] At the same time, when the valve plug 51 moves, the valve plug 51 will drive the rotating ring 53 to move downward. Since guide shafts 73 are provided on both sides of the rotating ring 53, driven by the spiral groove 72 of the sleeve 71, the rotating ring 53 will synchronously generate a rotational motion when it moves downward. When the rotating ring 53 rotates, it will drive the adjusting rod 6 to rotate through the connecting shaft 74. Since the baffle portion 61 is fixedly installed at the bottom of the adjusting rod 6, the baffle portion 61 will open the liquid outlet 32 ​​when it rotates, thereby forming a complete water path to ensure that the coolant can be sprayed out along the inside of the tool.

[0047] It should be noted that, since the rotation angle of the adjusting rod 6 described in the present invention is limited by the descending height of the valve plug 51, that is, when the coolant pressure is relatively high, the rotation angle of the adjusting rod 6 increases, and the baffle portion 61 blocks the liquid outlet 32 ​​to a minimum, thereby ensuring that the high-pressure coolant can be sprayed out quickly. On the contrary, when the coolant pressure is relatively low, the rotation angle of the adjusting rod 6 is relatively small, and the baffle portion 61 blocks the liquid outlet 32 ​​over a large area, thereby forming a small-sized flow outlet. When the coolant is discharged through the pinion flow outlet, it is obvious that when the flow area is reduced, the water flow velocity will increase. At this time, the coolant can also be guaranteed to form a high-pressure jet to ensure the spraying and cooling of the reamer 3.

[0048] Of course, in the initial state, the valve plug 51 closes the bottom opening of the upper connecting section 11, and the baffle portion 61 stops and closes the liquid outlet 32 ​​to ensure that the entire cooling water channel 4 is closed and protected when not in operation to prevent debris from entering the interior of the cooling water channel 4, thereby protecting the cooling water channel 4.

[0049] In a further embodiment, the top of the lower connecting section 12 in the present invention has a step opening, and the sleeve 71 is placed in the step opening, wherein the upper end of the sleeve 71 is provided with a positioning notch 75, and the bottom of the upper connecting section 11 is formed with a protrusion 76 that is snap-fitted into the positioning notch 75. That is, in the present invention, by providing a positioning notch 75 at the top of the sleeve 71, when the upper connecting section 11 is connected and fixed, the protrusion 76 at the bottom of the upper connecting section 11 is snap-fitted into the positioning notch 75 to complete the circumferential locking and fixation of the sleeve 71, thereby ensuring the stability of the operation.

[0050] See also Figure 6 , Figure 7 , Figure 6 This is a cross-sectional view of the product. Figure 7 The main view of the tool, where B is the through hole and C is the processed countersunk hole. The diameter D of the cutting position of the tool is smaller than the tail structural hole B of the aircraft seat component. In addition, to ensure normal cutting, B>D, (CB) / 2<E.

[0051] In addition, the present invention also proposes a method for processing an aviation component seat, which uses the above-mentioned tool, and the method comprises:

[0052] Orient the spindle on the CNC machine tool to ensure that the reamer 3 direction of the tool is consistent with the preset direction;

[0053] Move reamer 3 to the upper part of the tail structure of the aircraft seat component;

[0054] Control the machine tool spindle to move in the Z direction, so that the reamer 3 passes through the through hole and cuts to the root position of the processed hole;

[0055] The machine tool spindle is rotated to drive the reverse hook cutter to rotate, move from bottom to top in the processing hole, and cut along the inner diameter of the processing hole to complete the reverse hook processing of the tail structure of aircraft seat parts;

[0056] After the cutting of the processing hole is completed, the main shaft rotation is stopped, the reamer 3 is moved to the position of the through hole, the machine tool spindle is moved up in the Z direction, the tool is lifted and returned to zero, and the processing process is completed.

[0057] In summary, after the tool in the present invention moves to the Z direction of the specified XY position, the machine tool spindle rotates again, which can effectively ensure the processing accuracy. Compared with electric spark or other processing methods, this tool and method save processing time, improve processing quality and improve the reliability of the production process, and can effectively overcome the limitations of commonly used T-shaped tool processing and improve product quality. Secondly, a cooling water channel 4 is built into the tool. During the processing, the reamer 3 can be cooled to ensure the continuous working stability of the entire tool.

[0058] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical scheme and inventive concept of the present invention within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

Claims

1. An aviation component seat reverse hook tool, characterized in that: include; A knife handle (1), a knife rod (2) connected below the knife handle (1), and a reamer (3) connected below the knife rod (2); A cooling water channel (4) is provided inside the tool handle (1) and the tool rod (2); the reamer (3) has a notch (31); a liquid outlet (32) connected to the cooling water channel (4) is provided at the notch (31); and a valve control structure (5) is also provided in the cooling water channel (4).

2. The reverse hook tool for aviation parts seats according to claim 1, characterized in that: The tool handle (1) and the tool rod (2) are both cylindrical structures, and the reamer (3) is a 3 / 4 circumference structure.

3. The reverse hook tool for aviation parts seats according to claim 1, characterized in that: The shank (1) comprises an upper connecting section (11) and a lower connecting section (12), the upper connecting section (11) and the lower connecting section (12) being connected via a fastener, wherein the valve control structure (5) is installed inside the lower connecting section (12).

4. The reverse hook tool for aviation parts seats according to claim 3, characterized in that: The valve control structure (5) comprises a valve plug (51) sliding in the cooling water channel (4), the bottom of the valve plug (51) being fixedly connected to a connecting column (52), the lower end of the connecting column (52) being rotatably connected to a rotating ring (53), and a spring (54) being provided between the rotating ring (53) and the cooling water channel (4).

5. The reverse hook tool for aviation parts seats according to claim 4, characterized in that: The cooling water channel (4) is in a step structure, and two ends of the spring (54) respectively abut against the step of the step structure and the lower side of the rotating ring (53).

6. The reverse hook tool for aviation parts seats according to claim 4, characterized in that: An adjusting rod (6) is also rotatably connected in the cooling water channel (4), a baffle portion (61) is formed at the bottom of the adjusting rod (6), and the baffle portion (61) blocks the liquid outlet (32), wherein a driving assembly (7) is provided between the adjusting rod (6) and the rotating ring (53).

7. The reverse hook tool for aviation parts seats according to claim 6, characterized in that: The driving assembly (7) comprises a sleeve (71) connected to the lower connecting section (12), and two spiral grooves (72) are provided on the outer side of the sleeve (71), wherein guide shafts (73) sliding in the spiral grooves (72) are fixedly connected to both sides of the rotating ring (53), and a connecting shaft (74) is also fixedly connected to the bottom of the rotating ring (53), and the connecting shaft (74) is plugged into the adjusting rod (6).

8. The reverse hook tool for seats of aviation parts according to claim 7, characterized in that: The bottom of the connecting shaft (74) has a rectangular hole, and the top of the adjusting rod (6) has a rectangular section, and the rectangular section is plugged into the rectangular hole.

9. The reverse hook tool for aviation parts and seats according to claim 7, characterized in that: The top of the lower connecting section (12) has a step opening, and the sleeve (71) is placed in the step opening, wherein the upper end of the sleeve (71) is provided with a positioning notch (75), and the bottom of the upper connecting section (11) is formed with a protrusion (76) that is snap-fitted into the positioning notch (75).

10. A method for processing an aviation component seat, characterized in that: Using a cutting tool as claimed in any one of claims 1 to 9, the method comprising: Orient the spindle on the CNC machine tool to ensure that the direction of the reamer (3) of the tool is consistent with the preset direction; Move the reamer (3) to the upper part of the tail structure of the aircraft seat component; Controlling the machine tool spindle to move in the Z direction so that the reamer (3) passes through the through hole and cuts to the root position of the processed hole; The machine tool spindle is rotated to drive the reverse hook cutter to rotate, move from bottom to top in the processing hole, and cut along the inner diameter of the processing hole to complete the reverse hook processing of the tail structure of aircraft seat parts; After the cutting of the processing hole is completed, the spindle rotation is stopped, the reamer (3) is moved to the position of the through hole, the machine tool spindle is moved up in the Z direction, the tool is lifted and returned to zero, and the processing process is completed.

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