A drilling and milling fixture for aircraft parts
By designing an adjustable-angle drilling and milling fixture, the problem that existing fixtures cannot simultaneously clamp rectangular and cylindrical parts has been solved, enabling efficient clamping and processing of parts of different shapes and improving processing efficiency.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- SICHUAN AXIAL RES TECH CO LTD
- Filing Date
- 2025-08-06
- Publication Date
- 2026-07-03
AI Technical Summary
Existing aircraft component tooling fixtures have low versatility and cannot simultaneously clamp rectangular and cylindrical components, resulting in low processing efficiency.
An adjustable-angle drilling and milling fixture was designed, including first and second abutment rods. The included angle can be adjusted to 180° or less by a drive component to meet the clamping requirements of rectangular and cylindrical parts. Combined with the clamping assembly, it can achieve stable fixation.
This improved the applicability of the tooling, reduced the frequency of tooling changes, and increased the efficiency of drilling and milling of aircraft parts.
Smart Images
Figure CN224445368U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the technical field of machining tooling for aircraft parts, and in particular to a drilling and milling tooling for aircraft parts. Background Technology
[0002] In the drilling and milling of aircraft parts, the aircraft parts need to be clamped on the worktable of the machine tool using tooling fixtures before drilling and milling are performed.
[0003] However, existing aircraft parts come in various shapes, including rectangular and cylindrical parts. Typically, two different tooling fixtures are needed to hold rectangular and cylindrical parts separately on a machine tool. When machining parts of different shapes, the tooling fixtures need to be changed on the machine tool.
[0004] It is evident that existing tooling fixtures have low versatility and cannot clamp rectangular or cylindrical parts, thus reducing the efficiency of drilling and milling of aircraft parts. Utility Model Content
[0005] In view of the above problems, this utility model provides a drilling and milling fixture for aircraft parts, the purpose of which is to improve the applicability of the fixture.
[0006] To achieve the above objectives, the technical solution adopted by this utility model is as follows:
[0007] A milling fixture for aircraft parts is provided, comprising: a fixture body detachably mounted on a machine tool worktable; a first abutment rod and a second abutment rod symmetrically mounted on the fixture body; a first mounting shaft and a second mounting shaft fixedly mounted on the fixture body; a first sliding groove and a second sliding groove respectively formed on the first abutment rod and the second abutment rod, the first mounting shaft being slidably disposed in the first sliding groove and the second mounting shaft being slidably disposed in the second sliding groove; a moving component slidably mounted on the fixture body and capable of linear reciprocating motion; one end of the first abutment rod being rotatably mounted on the moving component and one end of the second abutment rod being rotatably mounted on the moving component; a first driving component for driving the moving component to move, thereby changing the included angle between the first abutment rod and the second abutment rod; and a clamping assembly disposed on the fixture body for abutting the parts between the first abutment rod and the second abutment rod.
[0008] Furthermore, the tooling also includes: a first guide groove, in which the movable component is slidably mounted; a first hinge shaft and a second hinge shaft, mounted on the movable component; a first abutting rod hingedly mounted on the first hinge shaft, and a second abutting rod hingedly mounted on the second hinge shaft.
[0009] Furthermore, the clamping assembly includes: a second guide groove formed on the tooling body; an abutment block slidably disposed in the second guide groove; a support block fixedly disposed on the tooling body; and a first lead screw, one end of which is rotatably connected to the abutment block, and the other end of which extends through the support block for a fixed length, and the first lead screw and the support block are connected by threads.
[0010] Furthermore, the first driving component is a hydraulic cylinder, the main body of which is fixedly mounted on the tooling body, and the piston rod of the hydraulic cylinder is connected to the moving component.
[0011] Furthermore, the first driving component is a second lead screw, both ends of which are rotatably mounted on the tooling body. The second lead screw and the moving component are connected by a threaded transmission.
[0012] Furthermore, the tooling also includes several through holes formed on the main body of the tooling for bolts to pass through.
[0013] The beneficial effects of this utility model are as follows: By using this utility model, the included angle between the first abutting rod and the second abutting rod can be adjusted. The included angle between the first abutting rod and the second abutting rod can be adjusted to 180°, which can be used to clamp and fix rectangular parts; the included angle between the first abutting rod and the second abutting rod can also be adjusted to less than 180°, which can be used to clamp and fix cylindrical parts; it can meet the clamping requirements of two different shapes of aircraft parts on the machine tool, increase the applicability of this tooling, reduce the tooling change rate, and effectively ensure the drilling and milling efficiency of aircraft parts. Attached Figure Description
[0014] Figure 1 This is a schematic diagram of the overall structure of the tooling body provided in the embodiments of this application.
[0015] Figure 2 A schematic diagram of the overall structure of the first abutment rod and the second abutment rod changing the included angle provided in the embodiments of this application.
[0016] Figure 3 A schematic diagram of the overall structure of a tooling where the first driving component is a hydraulic cylinder, provided for an embodiment of this application.
[0017] The components include: 1. Tooling body; 11. First abutting rod; 12. Second abutting rod; 13. Through hole; 21. First sliding groove; 22. Second sliding groove; 3. Moving component; 31. First hinge shaft; 32. Second hinge shaft; 41. First guide groove; 42. Second guide groove; 51. Abutting block; 52. Support block; 53. First lead screw; 61. Hydraulic cylinder; 62. Second lead screw; 71. First mounting shaft; 72. Second mounting shaft. Detailed Implementation
[0018] To better understand the above technical solutions, the following will provide a detailed explanation of the technical solutions in conjunction with the accompanying drawings and specific implementation methods.
[0019] Reference Figure 1 and Figure 2 As shown in the embodiment of this application, a drilling and milling fixture for aircraft parts is disclosed, comprising: a fixture body 1, detachably mounted on a machine tool worktable; a first abutment rod 11 and a second abutment rod 12, symmetrically mounted on the fixture body 1; a first mounting shaft 71 and a second mounting shaft 72, fixedly mounted on the fixture body 1; a first sliding groove 21 and a second sliding groove 22, respectively formed on the first abutment rod 11 and the second abutment rod 12; the first mounting shaft 71 being slidably disposed within the first sliding groove 21; and the second mounting shaft 72 being slidably disposed within the first sliding groove 21. The first abutment rod 11 is rotatably mounted on the second slide groove 22, and the second abutment rod 12 is rotatably mounted on the second abutment rod 12. The first driving component is used to drive the moving component 3 to move, thereby changing the included angle between the first abutment rod 11 and the second abutment rod 12. The clamping assembly is provided on the tooling body 1 and is used to abut the parts between the first abutment rod 11 and the second abutment rod 12.
[0020] In practical use, when the part to be processed is rectangular, the first driving component drives the moving component 3 to move, pushing the moving component 3 to move until the included angle between the first abutting rod 11 and the second abutting rod 12 is pushed to 180°. Then, the part to be processed is placed on one side of the first abutting rod 11 and the second abutting rod 12. Finally, the clamping assembly clamps the part between the first abutting rod 11, the second abutting rod 12 and the clamping assembly.
[0021] When the part to be processed is cylindrical, the first driving component drives the moving component 3 to move, and pulls the moving component 3 to move until the included angle between the first abutting rod 11 and the second abutting rod 12 is pulled to less than 180°. The specific angle should be adjusted adaptively according to the outer diameter of the part. Then, the part to be processed is placed between the first abutting rod 11 and the second abutting rod 12. Finally, the clamping assembly clamps the part between the first abutting rod 11 and the second abutting rod 12.
[0022] By using this utility model, the included angle between the first abutment rod 11 and the second abutment rod 12 can be adjusted. The included angle between the first abutment rod 11 and the second abutment rod 12 can be adjusted to 180°, which can be used to clamp and fix rectangular parts; the included angle between the first abutment rod 11 and the second abutment rod 12 can also be adjusted to less than 180°, which can be used to clamp and fix cylindrical parts. It can meet the clamping requirements of two different shapes of aircraft parts on the machine tool, increase the applicability of this tooling, reduce the tooling change rate, and effectively ensure the drilling and milling efficiency of aircraft parts.
[0023] Specifically, the tooling also includes: a first guide groove 41, in which the movable component 3 is slidably installed; a first hinge shaft 31 and a second hinge shaft 32, which are installed on the movable component 3; a first abutting rod 11 hingedly installed on the first hinge shaft 31, and a second abutting rod 12 hingedly installed on the second hinge shaft 32.
[0024] In practical use, during the movement of the moving part 3, it can drive the first hinge shaft 31 and the second hinge shaft 32 to push and pull the first abutting rod 11 and the second abutting rod 12 respectively; simultaneously, the first mounting shaft 71 and the second mounting shaft 72 slide in the first slide groove 21 and the second slide groove 22 respectively, guiding and changing the included angle between the first abutting rod 11 and the second abutting rod 12.
[0025] Specifically, the clamping assembly includes: a second guide groove 42, which is formed on the tooling body 1; an abutment block 51, which is slidably disposed in the second guide groove 42; a support block 52, which is fixedly disposed on the tooling body 1; and a first lead screw 53, one end of which is rotatably connected to the abutment block 51, and the other end of which extends through the support block 52 for a fixed length, and the first lead screw and the support block 52 are connected by threads.
[0026] It is worth mentioning that both the first guide groove 41 and the second guide groove 42 can be dovetail grooves.
[0027] In this embodiment, the first driving component is the second lead screw 62, both ends of which are rotatably mounted on the tooling body 1. The second lead screw 62 and the moving component 3 are connected by a threaded transmission.
[0028] It is understandable that through holes 13 are provided in the radial direction on both the first lead screw and the second lead screw 62. The operator can insert one end of the rod into the through hole 13, and the operator can turn the first lead screw or the second lead screw 62 by turning the other end of the rod, thereby driving the abutment block 51 / moving component 3 to move.
[0029] Specifically, the tooling also includes several through holes 13, which are formed on the tooling body 1 for bolts to pass through. By passing the bolts through the through holes 13, the bolt nuts press the tooling body 1 onto the machine tool's worktable, and the other end of the bolts is locked by a nut, thus completing the detachable installation of the tooling body 1 onto the machine tool's worktable.
[0030] Reference Figure 3 As shown, in some embodiments, the first driving component is a hydraulic cylinder 61. The main body of the hydraulic cylinder 61 is fixedly mounted on the tooling body 1, and the piston rod of the hydraulic cylinder 61 is connected to the moving component 3. The moving component 3 can be moved by the extension and retraction movement of the piston rod of the hydraulic cylinder 61.
[0031] Those skilled in the art will understand that although preferred embodiments of the present invention have been described, those skilled in the art, once they learn the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments as well as all changes and modifications falling within the scope of the present invention. Clearly, those skilled in the art can make various alterations and modifications to the present invention without departing from its spirit and scope. Thus, if these modifications and modifications of the present invention fall within the scope of the machine equivalents of the claims of the present invention, the present invention also intends to include these modifications and modifications.
Claims
1. An aircraft component drilling and milling jig, characterized by, include: The main body of the tooling (1) is detachably mounted on the worktable of the machine tool; The first abutting rod (11) and the second abutting rod (12) are symmetrically installed on the tooling body (1); The first mounting shaft (71) and the second mounting shaft (72) are fixedly mounted on the tooling body (1); The first slide groove (21) and the second slide groove (22) are respectively opened on the first abutting rod (11) and the second abutting rod (12). The first mounting shaft (71) is slidably disposed in the first slide groove (21), and the second mounting shaft (72) is slidably disposed in the second slide groove (22). The movable component (3) is slidably mounted on the tooling body (1) and is capable of linear reciprocating motion; one end of the first abutting rod (11) is rotatably mounted on the movable component (3), and one end of the second abutting rod (12) is rotatably mounted on the movable component (3); The first driving component is used to drive the moving component (3) to move, thereby changing the included angle between the first abutting rod (11) and the second abutting rod (12); A clamping assembly is disposed on the tooling body (1) for abutting the parts between the first abutting rod (11) and the second abutting rod (12).
2. The drill-mill tooling for aircraft parts according to claim 1, wherein, Also includes: The first guide groove (41) is in which the movable component (3) is slidably installed; The first hinge shaft (31) and the second hinge shaft (32) are mounted on the moving part (3); the first abutting rod (11) is hingedly mounted on the first hinge shaft (31), and the second abutting rod (12) is hingedly mounted on the second hinge shaft (32).
3. The drilling and milling fixture for aircraft parts according to claim 1, characterized in that, The clamping components include: The second guide groove (42) is provided on the tooling body (1); The abutment block (51) is slidably disposed in the second guide groove (42); The support block (52) is fixedly mounted on the tooling body (1); The first lead screw (53) is rotatably connected to the abutment block (51) at one end and extends a fixed length through the support block (52) at the other end, and the first lead screw and the support block (52) are connected by threads.
4. The drilling and milling fixture for aircraft parts according to claim 1, characterized in that, The first driving component is a hydraulic cylinder (61). The main body of the hydraulic cylinder (61) is fixedly mounted on the tooling body (1), and the piston rod of the hydraulic cylinder (61) is connected to the moving component (3).
5. The drilling and milling fixture for aircraft parts according to claim 1, characterized in that, The first driving component is the second lead screw (62), both ends of which are rotatably mounted on the tooling body (1). The second lead screw (62) and the moving component (3) are connected by a threaded transmission.
6. The drilling and milling fixture for aircraft parts according to claim 1, characterized in that, It also includes several through holes (13) on the tooling body (1) for bolts to pass through.