Universal milling tool for airplane stringer and using method of universal milling tool
The combination of modular fixture components and pneumatic control systems solves the problems of low efficiency and poor versatility of traditional long stringer clamping methods, achieves efficient and stable long stringer processing, and reduces tooling costs.
Patent Information
- Application Number
- CN202511124043.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-08-12
- Publication Date
- 2025-10-10
AI Technical Summary
The traditional long stringer clamping method has problems such as low operating efficiency, unstable clamping force and poor versatility in milling processing, which makes it difficult to meet the requirements of high-precision and high-efficiency processing.
Modular fixture components and pneumatic control systems are used to achieve fast and precise clamping and loosening of the long stringers through a dovetail clamping mechanism and a pneumatic control system. Combined with the assembly of multiple sets of modular fixture components, it can adapt to the processing of long stringers of different lengths and specifications.
The processing efficiency of the long stringer is improved, the stability and accuracy of the clamping force are ensured, the tooling cost is reduced, and the versatility and efficient processing of long stringers of different specifications are achieved.
Smart Images
Figure CN120755700A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the field of, but is not limited to, mechanical processing technology, and in particular to a universal milling tool for aircraft stringers and a method of using the tool. Background Art
[0002] Stringers are common structural components in aerospace, shipbuilding, and other fields, typically used to reinforce wings and fuselage skins. Stringers have complex structures and vary in length, and their manufacturing and assembly precision are crucial to the integrity and safety of the aircraft.
[0003] During the milling process, the stringer's manufacturing and assembly tolerances must be strictly controlled, requiring the use of advanced CNC machining technology. The stringer must be securely fixed to the workbench during machining to ensure both precision and efficiency. Traditional clamping methods, which often rely on manual or simple mechanical fixtures, suffer from low efficiency, unstable clamping force, and poor versatility. Summary of the Invention
[0004] Purpose of the invention: The embodiment of the present invention provides a universal milling tool for aircraft long stringers and a method of using the same to solve the problems of low operating efficiency, unstable clamping force and poor versatility commonly found in traditional clamping methods of long stringers during milling processing.
[0005] The technical solution of the present invention: An embodiment of the present invention provides a universal milling tool for aircraft long stringers, comprising: modular fixture assemblies of various length specifications, each set of the modular fixture assemblies comprising: a clamp body assembly 1, a vise clamping mechanism 2 and a pneumatic control system 3; Among them, along the length direction of the clamp body assembly 1, multiple groups of vise clamping mechanisms 2 are installed on its upper end surface; the fixed clamping blocks 13 and the movable clamping blocks 14 arranged opposite to each other on the top of each group of the vise clamping mechanisms 2 form a groove, and the long string product 6 is placed in the groove of each group of vise clamping mechanisms 2 along the length direction of the clamp body assembly 1; the top of the fixed clamping block 13 and the movable clamping block 14 of each of the vise clamping mechanisms 2 forms a dovetail positioning surface, which cooperates with the dovetail grooves on both sides of the long string product 6, and the long string product 6 is clamped by the clamping operation of each group of vise clamping mechanisms 2; The pneumatic control system 3 is connected to each group of vise clamping mechanisms 2 through an air circuit, and is used to control the simultaneous clamping and loosening of each group of vise clamping mechanisms 2 through the pneumatic control system 3, or to independently control the clamping and loosening of a single group of vise clamping mechanisms 2; thereby controlling each vise clamping mechanism 2 to implement positioning and clamping of the long stringer product 6 through the pneumatic control system 3.
[0006] Optionally, in the universal milling tool for aircraft longerons described above, the clamp body assembly 1 comprises: a clamp body 7, a positioning pin 9, a butt block 10, a connecting piece 11; The clamp body 7 is a casting structure, comprising a mounting base and a long strip box body fixedly arranged on the mounting base, which is attached to and fixedly connected to the machine tool table through the bottom surface. The mounting base is provided with butt blocks 10 at both ends in the length direction, which are used to ensure the butt joint accuracy when the adjacent two groups of modular clamp assemblies are butt jointed. A plurality of connecting pieces 11 are arranged at the upper end surface of the long strip box body. Cross key grooves are formed in the upper end surface of the connecting pieces 11, which are used to be connected with the cross key grooves in the bottom end surface of the vice clamping mechanism 2.
[0007] Optionally, in the universal milling tool for aircraft longerons described above, The connecting mode of the mounting base of the clamp body 7 and the machine tool is divided into two modes according to the structure of the machine tool: Mode one, the clamp body 7 is provided with a locating edge 8 on one side, which is used to be attached to the positioning pin of the vacuum platform machine tool; Mode two, the long strip box body of the clamp body 7 is provided with positioning pins 9 at both ends, which are used to be fixedly connected with the machine tool with key grooves, so as to ensure the placement position of the clamp body 7.
[0008] Optionally, in the universal milling tool for aircraft longerons described above, the vice clamping mechanism 2 comprises: a jaw body 12, a fixed clamp block 13, a movable clamp block 14, a sliding block 15, a connecting block 16, and a pneumatic motor 17. The lower end surface of the jaw body 12 is provided with cross key grooves, which are connected with the cross key grooves in the upper end surface of the connecting piece 11 in the corresponding clamp body assembly 1. The upper end surface of the jaw body 12 is provided with a key groove and a T-shaped groove. The key groove is located at the end, which is used to be fixedly connected with the fixed clamp block 13 through a screw. The top inner side of the fixed clamp block 13 is formed with a dovetail locating surface, which is used to be attached to the dovetail groove on one side of the longeron product 6, so as to locate the reference position of the longeron product 6. The bottom of the T-shaped groove is provided with a lead screw, and the sliding block 15 is installed through the lead screw. The movable clamp block 14 is fixedly connected to the upper end surface of the sliding block 15, and the movable clamp block 14 is moved along the T-shaped groove through the lead screw. The top inner side of the movable clamp block 14 is formed with a dovetail locating surface, which is used to be attached to the dovetail groove on the other side of the longeron product 6 through the linear motion of the movable clamp block 14 along the T-shaped groove, and the longeron product 6 is clamped by the fixed clamp block 13. The connecting block 16 is fixedly installed on one end surface of the jaw body 12, and the pneumatic motor 17 is installed through the connecting block 16. The pneumatic motor 17 is connected with the lead screw nut on the lead screw through the hole in the center hole of the connecting block 16, which is used to drive the movement of the movable clamp block 14.
[0009] Optionally, in the universal milling tool for aircraft stringers as described above, the pneumatic control system 3 includes: a master control system 18 and a plurality of individual control systems 19; Among them, each single control system 19 is connected to a pneumatic motor 17 of a vise clamping mechanism 2, which is used to drive the corresponding pneumatic motor 17 through the single control system 19, so that the movable clamping block 14 moves toward or away from one end of the fixed clamping block 13, thereby realizing the clamping and loosening of the single vise clamping mechanism 2; the master control system 18 is connected to each single control system 19 through an air circuit, which is used to synchronously control the clamping and loosening of each group of vise clamping mechanisms 2 at the same time.
[0010] Optionally, in the universal milling tool for aircraft stringers as described above, each set of the modular fixture components further includes: a positioning block 4; The positioning block 4 is arranged in the groove formed by the fixed clamping block 13 and the movable clamping block 14 of each group of vise clamping mechanisms 2 along the length direction of the clamping body assembly 1, and the long stringer product 6 is arranged on the positioning block 4, which is used to position the end face of the long stringer product 6 through the positioning block 4.
[0011] Optionally, in the universal milling tooling for aircraft stringers as described above, each set of modular fixture assemblies also includes: multiple auxiliary clamping mechanisms 5; multiple auxiliary clamping mechanisms 5 are installed along the length direction of the stringer product 6, for auxiliary clamping between the stringer product 5 and the positioning block 4.
[0012] Optionally, in the universal milling tool for aircraft long stringers as described above, each set of the auxiliary pressing mechanism 5 includes: a bow clamp 25, a smooth pressing block 26, and a pressing screw 27; Among them, the bow clamp 25 is set to a bow structure, and the bottom end has a clamping end face bent upward, which is used to fit on the bottom end face of the positioning block 4, and a threaded hole is opened at the end of the top straight section. After the clamping screw 27 is screwed through the top threaded hole, the end is connected to the smooth pressing block 26, which fits on the fixed end face of the long string product 5 through the smooth pressing block 26, and auxiliary compression is performed between the long string product 6 and the positioning block 4 through the clamping screw 27.
[0013] Alternatively, in the universal milling tool for aircraft stringers described above, the selection of the pneumatic motor can be calculated based on the clamping force required in CNC machining: The tooling clamping force required for CNC machining is: 4900N~5300N
[0014] T : torque, F a : Clamping force, s :pitch, : Transmission efficiency The selected T-type screw Tr18x4-7h is 61cm long. F a =5000N
[0015]
[0016] =10.62 N·m The required input torque of the air motor is 10.62 N·m According to the input torque of the air motor, the selected air motor parameters Rated air pressure: 0.63Mpa Rated speed: 60rpn / min (rated speed) Rated torque: 19 N·m Gas consumption: 0.5 cubic meters / min Compressed air in the factory: 0.6Mpa In a second aspect, an embodiment of the present invention further provides a method for using the universal milling tool for an aircraft stringer as described in any one of the above items, comprising: Step 1: Select multiple sets of modular fixture components for assembly based on the length of the long stringer product 6, and install the assembled multiple sets of modular fixture components on a CNC machine tool; Step 2: Place the long stringer product 6 into the groove formed by the fixed clamping block 13 and the movable clamping block 14 at the top of each group of vise clamping mechanisms 2 of the universal milling tool, or place it on the positioning block 4 provided in the groove of the group vise clamping mechanism 2; Step 3: Turn on the clamping switch of the pneumatic control system 3 to synchronously clamp the long stringer product 6 through each set of vise clamping mechanisms 2.
[0017] Optionally, in the method for using the universal milling tool for aircraft stringers as described above, the structures of the multiple sets of modular fixture assemblies used for splicing are completely identical, or the lengths of the clamping body assemblies 1 in each set of modular fixture assemblies are different, and the number of vise clamping mechanisms 2 provided is different; the method for using further includes: In step 4, the release switch of the single control system 18 may be turned on for the unused vise clamping mechanisms 2 in each set of modular fixture assemblies.
[0018] The beneficial effects of the present application: the traditional long string tooling adopts the pressing plate pressing mode, which needs two directions of pressing mode, the operation mode is complex, and the processing efficiency is low. In view of the above problems, the embodiment of the present application provides a kind of general milling tooling for aircraft long string and its using method, each group of vise clamping mechanism in each group of modular fixture assembly in general milling tooling adopts dovetail type clamping mode, can simultaneously generate downward and inward clamping force, and adopts pneumatic system control, can automatically complete the clamping and loosening process of long string, simple and fast operation, can greatly improve the processing efficiency of long string. The clamping force of traditional pressing mode cannot be calculated, it is easy to cause that the clamping force is too small, cannot meet the processing requirement, or the clamping force is too large to cause the deformation of long string product. The tooling of the present application can be accurately regulated and controlled through pneumatic control system, and set to the required clamping force of long string numerical control system. Traditional tooling needs to design different milling tooling one by one corresponding to different long strings, the number is large, and it is easy to cause that the tooling cost is too much. The present application adopts modular assembly form, can meet the milling processing of long string of different length specifications, through the assembly of different module assemblies, reuse, to achieve the purpose of reducing tooling cost. BRIEF DESCRIPTION OF DRAWINGS
[0019] The drawings are used to provide further understanding of the technical scheme of the present application, and constitute a part of the specification, and together with the embodiments of the present application, are used to explain the technical scheme of the present application, and do not constitute limitation to the technical scheme of the present application.
[0020] Fig. 1 is a structural schematic view of the modular fixture assembly in the general milling tooling for aircraft long string provided by the embodiment of the present application; Fig. 1a is a front view, and Fig. 1b is a back view; Figure 2 Fig. 2 is a structural schematic view of the clamp body assembly in the modular fixture assembly shown in Fig. 1; Figure 3 Fig. 3 is a structural schematic view of the vise clamping mechanism in the modular fixture assembly shown in Fig. 1; Figure 4 Fig. 4 is an installation structural schematic view of the vise clamping mechanism, positioning block and long string product shown in Fig. 1; Figure 5 Fig. 5 is a sectional view of the vise clamping mechanism shown in Fig. 1; Figure 3 Figure 5 Fig. 5a is a radial sectional view, and Fig. 5b is an axial sectional view; Figure 6 Fig. 6 is a structural schematic view of the pneumatic control system in the modular fixture assembly provided by the embodiment of the present application; Figure 7 Fig. 7 is an auxiliary pressing mechanism schematic view in the modular fixture assembly provided by the embodiment of the present application.
[0021] Marked in the drawing: 1, clamp body assembly, 2 vice clamping mechanism, 3 pneumatic control system, 4 positioning block, 5 auxiliary pressing mechanism, 6 longeron product, 7 clamp body, 8 alignment edge, 9 positioning bolt, 10 butt joint block, 11 connecting piece, 12 clamp body, 13 fixed clamp block, 14 movable clamp block, 15 sliding block, 16 connecting block, 17 pneumatic motor, 18 general control system, 19 single control system, 25 arc-shaped clamp, 26 smooth surface pressing block, 27 pressing screw. DETAILED DESCRIPTION
[0022] To make the objects, technical solutions, and advantages of the present application clearer, the following will describe the embodiments of the present application in detail with reference to the drawings. It should be noted that the embodiments herein and the features in the embodiments can be combined with each other as long as there is no conflict.
[0023] As described in the above background, the main application and important role of the longeron, and the important influence of the manufacturing and assembly precision of the longeron on the aircraft have been explained. In the milling process, the traditional clamping method of the longeron has problems such as low operation efficiency, unstable clamping force, and poor universality, etc. Specifically as follows: 1) Low operation efficiency: manual clamping and loosening takes a long time, affecting production efficiency; 2) Unstable clamping force: the traditional clamp is difficult to accurately control the clamping force, which may cause workpiece deformation or reduce the machining precision; 3) Poor universality: different clamps need to be replaced for different specifications of the longeron, increasing equipment investment and maintenance cost.
[0024] In view of the above problems, it is urgent to design a longeron milling clamp that can realize fast, accurate and stable clamping, and has high universality. In view of this demand, the embodiments of the present application provide a universal milling tool for an aircraft longeron and a using method thereof. The universal milling tool provided by the embodiments of the present application is an automatic clamping tool based on pneumatic control, which can realize fast clamping and loosening of longerons of different specifications, and ensure the stability and accuracy of the clamping force through a closed-loop control system.
[0025] The following specific embodiments provided by the present application can be combined with each other, and the same or similar concepts or processes may not be described again in some embodiments.
[0026] The universal milling tool for an aircraft longeron provided by the embodiments of the present application comprises a plurality of length specifications of modular clamp assembly. As shown in FIG. 1, it is a structural schematic diagram of the modular clamp assembly in the universal milling tool for an aircraft longeron provided by the embodiments of the present application. FIG. 1a is a front view, and FIG. 1b is a back view. The main components of each modular clamp assembly in the universal milling tool provided by the embodiments of the present application include: clamp body assembly 1, vice clamping mechanism 2, and pneumatic control system 3.
[0027] As shown in Figure 1, the upper end surface of each clamping body assembly 1 can be mounted with multiple sets of vise clamping mechanisms 2 along its length. The fixed clamping blocks 13 and movable clamping blocks 14, positioned opposite each other at the top of each set of vise clamping mechanisms 2, form a groove. The stringer product 6 is positioned within the groove of each set of vise clamping mechanisms 2 along the length of the clamping body assembly 1. Furthermore, dovetail positioning surfaces are formed on the tops of the fixed clamping blocks 13 and movable clamping blocks 14 of each set of vise clamping mechanisms 2. These dovetail positioning surfaces mate with dovetail grooves on the bottom sides of the stringer product 6, allowing the stringer product 6 to be clamped securely through the clamping operation of each set of vise clamping mechanisms 2.
[0028] The pneumatic control system 3 in the embodiment of the present invention is connected to each group of vise clamping mechanisms 2 through an air circuit, and is used to control the simultaneous clamping and loosening of each group of vise clamping mechanisms 2 through the pneumatic control system 3, or to independently control the clamping and loosening of a single group of vise clamping mechanisms 2; thereby controlling each vise clamping mechanism 2 to implement positioning and clamping of the long stringer product 6 through the pneumatic control system 3.
[0029] like Figure 3 Figure 1 shows a schematic diagram of the vise clamping mechanism within the modular fixture assembly of the embodiment shown in Figure 1. The fixed clamping block 13 and the movable clamping block 14 at the top of the vise clamping mechanism 2 in this embodiment of the present invention form dovetail positioning surfaces that mate with dovetail grooves on either side of the stringer product 6 to clamp the stringer. The stringer product 6 is placed within the grooves formed by the fixed clamping block 13 and the movable clamping block 14. The pneumatic control system 3 controls the tightening and loosening of the vise clamping mechanism 2 to achieve positioning and clamping of the stringer product 6.
[0030] It should be noted that, as shown in Figure 1, six sets of vise clamping mechanisms 2 are installed in one modular fixture assembly. The present invention does not limit the length of the clamping body assembly 1 in each modular fixture assembly, nor the number of vise clamping mechanisms 2 installed in each modular fixture assembly. Furthermore, based on the length of the stringer product 6, the modular fixture assembly provided in the present invention can be used to assemble and fix stringer products 6 of varying lengths for milling processing by assembling multiple sets of modular fixture assemblies.
[0031] In one implementation of the embodiment of the present invention, Figure 2The figure shows a schematic structural diagram of the clamp body assembly in the modular fixture assembly provided by the embodiment shown in FIG1 . The clamp body assembly 1 in this implementation includes: a clamp body 7, a positioning pin 9, a docking block 10, and a connector 11. In this implementation, the clamp body 7 is a casting structure, including a mounting base and a long strip box body fixedly mounted on the mounting base, which is affixed and fixedly connected to the machine tool table through its bottom surface. The mounting base is provided with docking blocks 10 at both ends in the longitudinal direction, which are used to ensure docking accuracy when two adjacent sets of modular fixture assemblies are docked. A plurality of connectors 11 are installed at intervals on the upper end surface of the long strip box body, and a cross keyway is provided on the upper end surface of the connector 11 for mating with the cross keyway on the bottom end surface of the vise clamping mechanism 2.
[0032] In the optional scheme, the connection method between the clamping body 7 and the machine tool is divided into two types according to the different structures of the machine tool: first, a leveling edge 8 is set on one side of the clamping body 7, which can be fitted with the positioning pin of the vacuum platform machine tool; second, positioning pins 9 are installed at both ends of the clamping body 7, which can cooperate with the machine tool with a keyway to ensure the placement of the clamping body 7.
[0033] In one implementation of the embodiment of the present invention, Figures 3 to 5 As shown, the vise clamping mechanism 2 includes: a clamp body 12 , a fixed clamping block 13 , a movable clamping block 14 , a slider 15 , a connecting block 16 , and a pneumatic motor 17 .
[0034] In this implementation, a cross keyway is provided on the lower end surface of the clamp body 12 , which is connected to the cross keyway on the upper end surface of the connecting member 11 in the corresponding clamp body assembly 1 through a positioning key.
[0035] In this implementation, the upper end surface of the clamp body 12 is provided with a keyway and a T-slot; the keyway is located at the end and is used to fix the fixed clamp block 13 to the end of the clamp body 12 via screws. The fixed clamp block 13 has a dovetail positioning surface formed on the inner side of the top, which is used to mate with the dovetail slot on one side of the long string product 6 to determine the reference position of the long string product 6. A lead screw is provided at the bottom of the T-slot, and a slider 15 is mounted via the lead screw. The movable clamp block 14 is fixedly connected to the upper end surface of the slider 15, and the lead screw drives the slider 15 and the movable clamp block 14 to move along the T-slot; the movable clamp block 14 has a dovetail positioning surface formed on the inner side of the top, which is used to mate with the dovetail slot on the other side of the long string product 6 when the movable clamp block 14 moves linearly along the T-slot, thereby clamping the long string product 6 with the fixed clamp block 13.
[0036] In this implementation, the caliper body 12 is fixedly mounted with a connecting block 16 on one end face of the dynamic clamping block 14, and an air motor 17 is installed through the connecting block 16. The air motor 17 passes through the hole on the end face of the center hole of the connecting block 16 and is connected to the screw nut on the screw to drive the movement of the dynamic clamping block 14.
[0037] In one implementation of the embodiment of the present invention, Figure 6 As shown, the pneumatic control system 3 includes: a master control system 18 and multiple groups of individual control systems 19. In this implementation, on the one hand, each individual control system 19 is connected to a corresponding pneumatic motor 17 of a vise clamping mechanism 2, and is used to drive the corresponding pneumatic motor 17 through the individual control system 19, causing the dynamic clamping block 14 to move toward or away from one end of the fixed clamping block 13, thereby achieving the clamping and loosening of the individual vise clamping mechanism 2. On the other hand, the master control system 18 is connected to each individual control system 19 via an air circuit, and is used to synchronously control the simultaneous clamping and loosening of each group of vise clamping mechanisms 2, thereby ensuring the synchronization and smoothness of the movement of multiple groups of dynamic clamping blocks 14 in each modular fixture assembly.
[0038] In one implementation of the embodiment of the present invention, as shown in FIG1 and FIG1 Figure 4 As shown, each modular clamp assembly may further include a positioning block 4. In this implementation, the positioning block 4 is disposed along the length of the clamp body assembly 1 within a groove formed by the fixed clamping block 13 and the movable clamping block 14 of each set of vise clamping mechanisms 2. The stringer product 6 is disposed on the positioning block 4, thereby positioning the stringer product 6 end face.
[0039] In one implementation of the embodiment of the present invention, as shown in FIG1 and FIG1 Figure 7 As shown, each set of modular clamp components may further include: a plurality of auxiliary pressing mechanisms 5 ; a plurality of auxiliary pressing mechanisms 5 are installed along the length direction of the long stringer product 6 for auxiliary pressing between the long stringer product 5 and the positioning block 4 .
[0040] In a specific embodiment of this implementation, each set of the auxiliary pressing mechanism 5 includes: a bow clamp 25, a smooth pressing block 26, and a pressing screw 27. The bow clamp 25 is configured as a bow-shaped structure, with an upwardly bent pressing end surface at the bottom end for contact with the bottom end surface of the positioning block 4, and a threaded hole is formed at the end of the straight top section. After the pressing screw 27 is screwed through the top threaded hole, the end is connected to the smooth pressing block 26, which contacts the fixed end surface of the long string product 5 through the smooth pressing block 26, and the pressing screw 27 is used to provide auxiliary pressure between the long string product 6 and the positioning block 4.
[0041] It should be noted that the selection of the pneumatic motor 17 in the embodiment of the present invention can be calculated based on the clamping force required in CNC machining: The tooling clamping force required for CNC machining is: 4900N~5300N; ; T : torque, F a : Clamping force, s : pitch, : Transmission efficiency; The selected T-type screw Tr18x4-7h is 61cm long. F a =5000N; ;
[0042] =10.62 N·m.
[0043] The required input torque of the pneumatic motor 17 is 10.62 N·m; According to the input torque of the pneumatic motor, the selected pneumatic motor parameters are: Rated air pressure: 0.63Mpa; Rated speed: 60rpn / min (rated speed); Rated torque: 19 N·m; Gas consumption: 0.5 cubic meters / min; Compressed air in the factory: 0.6Mpa.
[0044] Based on the universal milling tool for aircraft long stringers provided in the above embodiments of the present invention, the embodiments of the present invention also provide a method for using the universal milling tool for aircraft long stringers provided in any of the above embodiments, the method comprising the following steps: Step 1: Select multiple sets of modular fixture components for assembly according to the length of the long stringer product 6, and install the assembled multiple sets of modular fixture components on a CNC machine tool.
[0045] Step 2: Place the long stringer product 6 into the groove formed by the fixed clamping block 13 and the movable clamping block 14 at the top of each group of vise clamping mechanisms 2 of the universal milling tool, or place it on the positioning block 4 provided in the groove of the group vise clamping mechanism 2; Step 3: Turn on the clamping switch of the pneumatic control system 3 to synchronously clamp the long stringer product 6 through each set of vise clamping mechanisms 2.
[0046] It should be noted that the structures of the multiple sets of modular clamp assemblies selected in step 1 above can be exactly the same. In an optional solution, the lengths of the clamp body assemblies 1 in each set of modular clamp assemblies are different, and the number of vise clamping mechanisms 2 provided is different. After the multiple sets of modular clamp assemblies are assembled, there may be a situation where the length of the long string product 6 is less than the length of the multiple clamp body assemblies 1 after assembly. In this case, some vise clamping mechanisms 2 may not be used. In this case, the method of use provided by the present invention further includes the following steps: In step 4, the release switch of the single control system 18 may be turned on for the unused vise clamping mechanisms 2 in each set of modular fixture assemblies.
[0047] The traditional long-string tooling adopts a pressure plate clamping method, which requires clamping in two directions, is complex to operate, and has low processing efficiency. In response to the above problems, an embodiment of the present invention provides a universal milling tooling for aircraft long-strings and a method of use thereof. Each set of vise clamping mechanisms in each set of modular fixture assemblies in the universal milling tooling adopts a dovetail clamping method, which can simultaneously generate downward and inward clamping forces, and is controlled by a pneumatic system, which can automatically complete the clamping and loosening processes of the long stringer. The operation is simple and fast, which can greatly improve the processing efficiency of the long stringer. The clamping force of the traditional clamping method cannot be calculated, which can easily result in the clamping force being too small to meet the processing requirements, or the clamping force being too large to cause deformation of the long stringer product. The tooling of the present invention can be precisely controlled by a pneumatic control system and set to the clamping force required by the long-string CNC system. Traditional tooling requires the design of different milling tooling for different long strings, which corresponds to a large number of them and easily leads to excessive tooling costs. The present invention adopts modular components to meet the milling and cutting of long trusses of different lengths. By assembling and reusing different modular components, the cost of tooling can be reduced. Although the embodiments disclosed herein are as described above, the contents are merely provided to facilitate understanding of the present invention and are not intended to limit the present invention. Any person skilled in the art may make any modifications and variations in the form and details of the embodiments without departing from the spirit and scope of the present invention. However, the scope of patent protection of the present invention shall remain subject to the scope defined by the appended claims.
Claims
1. A universal milling tool for aircraft stringers, characterized in that: include: Modular fixture assemblies of various lengths, each set of modular fixture assemblies comprising: a fixture body assembly (1), a vise clamping mechanism (2) and a pneumatic control system (3); Wherein, a plurality of sets of vise clamping mechanisms (2) are installed on the upper end surface of the clamping body component (1) along the length direction thereof; the fixed clamping blocks (13) and the movable clamping blocks (14) arranged opposite to each other on the top of each set of the vise clamping mechanisms (2) form a groove, and the long string product (6) is placed in the groove of each set of the vise clamping mechanisms (2) along the length direction of the clamping body component (1); the fixed clamping blocks (13) and the movable clamping blocks (14) of each set of the vise clamping mechanisms (2) form a dovetail positioning surface on the top, which cooperates with the dovetail grooves on both sides of the long string product (6), and the long string product (6) is clamped by the clamping operation of each set of the vise clamping mechanisms (2); The pneumatic control system (3) is connected to each group of vise clamping mechanisms (2) through an air circuit, and is used to control the simultaneous clamping and loosening of each group of vise clamping mechanisms (2) through the pneumatic control system (3), or to independently control the clamping and loosening of a single group of vise clamping mechanisms (2); thereby controlling each vise clamping mechanism (2) to implement positioning and clamping of the long stringer product (6) through the pneumatic control system (3).
2. The universal milling tool for aircraft stringers according to claim 1, characterized in that: The clamp body assembly (1) comprises: a clamp body (7), a positioning pin (9), a docking block (10), and a connecting piece (11); The clamp body (7) is a casting structure, comprising a mounting base and a long strip box body fixedly arranged on the mounting base, and is attached to and fixedly connected to the machine tool table through its bottom surface. The mounting base is provided with docking blocks (10) at both ends in the length direction, and is used to ensure docking accuracy when two adjacent sets of modular fixture components are docked through the docking blocks (10); a plurality of groups of connecting members (11) are installed at intervals on the upper end surface of the long strip box body, and a cross keyway is provided on the upper end surface of the connecting member (11) for mating with the cross keyway on the bottom end surface of the vise clamping mechanism (2).
3. The universal milling tool for aircraft stringers according to claim 2, characterized in that: The connection method between the mounting base of the clamp body (7) and the machine tool is divided into two types according to the structure of the machine tool: Method 1: a aligning edge (8) is provided on one side of the clamp body (7) for fitting with a positioning pin of a vacuum platform machine tool; Method 2: Positioning pins (9) are respectively installed at both ends of the long strip box body of the clamp body (7) for fixing with a machine tool with a keyway to ensure the placement position of the clamp body (7).
4. The universal milling tool for aircraft stringers according to claim 1, characterized in that: The vise clamping mechanism (2) comprises: a clamp body (12), a fixed clamping block (13), a movable clamping block (14), a slider (15), a connecting block (16), and a pneumatic motor (17); The lower end surface of the clamp body (12) is provided with a cross keyway, which is connected to the cross keyway on the upper end surface of the connecting member (11) in the corresponding clamp body assembly (1) via a positioning key; The upper end surface of the clamp body (12) is provided with a keyway and a T-shaped slot, the keyway being located at the end and being used to fix the fixed clamp block (13) to the end of the clamp body (12) by means of screws, and a dovetail positioning surface is formed on the inner side of the top of the fixed clamp block (13) and is used to fit with the dovetail slot on one side of the long string product (6) to locate the reference position of the long string product (6); A lead screw is provided at the bottom of the T-slot, and a slider (15) is installed through the lead screw, and a movable clamping block (14) is fixedly connected to the upper end surface of the slider (15), and the lead screw drives the slider (15) and the movable clamping block (14) to move along the T-slot; a dovetail positioning surface is formed on the inner side of the top of the movable clamping block (14), which is used to fit the dovetail groove on the other side of the long string product (6) when the movable clamping block (14) moves linearly along the T-slot, and clamp the long string product (6) with the fixed clamping block (13); The clamp body (12) is fixedly mounted with a connecting block (16) on one end surface of the movable clamp block (14), and an air motor (17) is mounted through the connecting block (16). The air motor (17) passes through an opening on the end surface of the center hole of the connecting block (16) and is connected to a lead screw nut on the lead screw to drive the movement of the movable clamp block (14).
5. The universal milling tool for aircraft stringers according to claim 4, characterized in that: The pneumatic control system (3) includes: a master control system (18) and multiple groups of individual control systems (19); Each individual control system (19) is connected to a corresponding pneumatic motor (17) of a vise clamping mechanism (2), and is used to drive the corresponding pneumatic motor (17) through the individual control system (19), so that the movable clamping block (14) moves toward or away from one end of the fixed clamping block (13), thereby achieving the clamping and loosening of the individual vise clamping mechanism (2); the master control system (18) is connected to each individual control system (19) through an air circuit, and is used to synchronously control the clamping and loosening of each group of vise clamping mechanisms (2) at the same time.
6. The universal milling tool for aircraft stringers according to any one of claims 1 to 5, characterized in that: Each set of modular fixture components further includes: a positioning block (4); The positioning block (4) is arranged in a groove formed by the fixed clamping block (13) and the movable clamping block (14) of each group of vise clamping mechanisms (2) along the length direction of the clamp body assembly (1), and the long string product (6) is arranged on the positioning block (4) for positioning the end face of the long string product (6) through the positioning block (4).
7. The universal milling tool for aircraft stringers according to claim 6, characterized in that: Each set of modular clamp components further includes: a plurality of auxiliary pressing mechanisms (5); a plurality of auxiliary pressing mechanisms (5) are installed along the length direction of the long stringer product (6) for auxiliary pressing between the long stringer product 5 and the positioning block (4).
8. The universal milling tool for aircraft stringers according to claim 7, characterized in that: Each group of the auxiliary pressing mechanism (5) comprises: a bow-shaped clamp (25), a smooth pressing block (26), and a pressing screw (27); The bow clamp (25) is configured as a bow structure, with a bottom end having an upwardly bent pressing end face for fitting on the bottom end face of the positioning block (4), and a threaded hole being provided at the end of the top straight section. After the pressing screw (27) is screwed through the top threaded hole, the end is connected to the smooth pressing block (26), which fits on the fixed end face of the long truss product 5 through the smooth pressing block (26), and auxiliary pressing is performed between the long truss product (6) and the positioning block (4) through the pressing screw (27).
9. The method for using the universal milling tool for aircraft stringers according to any one of claims 1 to 8, characterized in that: include: Step 1, selecting multiple sets of modular fixture components for assembly according to the length of the long stringer product (6), and installing the assembled multiple sets of modular fixture components on a CNC machine tool; Step 2, placing the long stringer product (6) into the groove formed by the fixed clamping block (13) and the movable clamping block (14) at the top of each group of vise clamping mechanisms (2) of the universal milling tool, or placing it on the positioning block (4) provided in the groove of the group vise clamping mechanism (2); Step 3, turning on the clamping switch of the pneumatic control system (3), and synchronously clamping the long stringer product (6) through each set of vise clamping mechanisms (2).
10. The method for using the universal milling tool for aircraft stringers according to claim 9, wherein: The structures of the plurality of modular clamp assemblies for splicing are completely identical, or the lengths of the clamp body assemblies (1) in each modular clamp assembly are different, and the number of vise clamping mechanisms (2) provided is different; the method of use further includes: In step 4, for the unused vise clamping mechanisms (2) in each set of modular fixture assemblies, a release switch of a single control system (18) may be turned on.