Flexible device for multi-station aircraft complex structural part and multi-point equal-symmetry machining method

Abstract

The embodiment of the invention discloses a flexible device for a multi-station aircraft complex structural member and a multi-point equal symmetry machining method, in the flexible device, one or two flexible supports are installed on T-shaped grooves located in the same straight line to form a reference symmetry axis, and the other flexible supports are symmetrically installed on the T-shaped grooves in the two sides of the reference symmetry axis; one process lap is assembled at the end part of each group of process lugs of the joint part; wherein one or two process laps are installed on the corresponding flexible supports used for forming the reference symmetry axis and used for constructing the symmetry axis of the joint part, and the other process laps are installed on the flexible supports at the corresponding positions of the two sides of the reference symmetry axis. And after the joint parts and the process laps respectively mounted on the process lugs form a multi-point equal-symmetry mounting structure, the joint parts are mounted on the flexible supports at the corresponding positions through the process laps, and are positioned, mounted and locked. According to the technical scheme provided by the embodiment of the invention, the problems of time and labor waste, high machining difficulty, low machining efficiency and the like caused by the fact that part machining is realized through repeated clamping in an existing machining mode for aircraft parts with complex structures are solved.

Description

Technical Field

[0001] The present invention relates to the field of mechanical manufacturing equipment technology, but is not limited thereto, and in particular to a flexible device and a multi-point isosymmetrical processing method for multi-station aircraft complex structural parts. Background Art

[0002] At present, there are many types of aircraft parts known in the art, especially joint parts, and the joint parts are special-shaped parts with complex structures and no regularity.

[0003] The processing technology for the above-mentioned complex structural special-shaped parts in aircraft parts, especially the joint parts, is very complicated; the processing technology usually adopts a reserved rough material process frame and realizes the part processing through repeated clamping. This processing technology is time-consuming, labor-intensive, difficult to process, and has low processing efficiency. Summary of the invention

[0004] Purpose of the present invention: In order to solve the above-mentioned technical problems, the embodiments of the present invention provide a flexible device for multi-station aircraft complex structural parts and a multi-point symmetrical processing method to solve the existing processing methods for complex structural aircraft parts. Since the parts need to be processed through repeated clamping, it is time-consuming and labor-intensive, the processing is difficult, and the processing efficiency is low.

[0005] Technical solution of the present invention: In the first aspect, the embodiment of the present invention provides a flexible device for multi-station aircraft complex structural parts, including: the flexible device is used to form a multi-point symmetrical installation structure for joint parts 10, and the symmetrical flexible device includes: a flexible bottom plate 1, a plurality of flexible supports 2 and a plurality of process headers 3;

[0006] The flexible base plate 1 is configured as a regular polygonal base or a circular base, and a plurality of T-shaped slots 9 are formed on the upper end surface of the flexible base plate 1 in an equiangular form and are emitted along the center point;

[0007] One or two of the flexible supports 2 are installed on the T-slots 9 located in the same straight line to form a reference symmetry axis of the flexible device, and the remaining flexible supports 2 are symmetrically installed on the T-slots 9 on both sides of the reference symmetry axis; a threaded hole 8 is opened at the bottom of each flexible support 2, so that after constructing an equisymmetrical installation structure of the joint-like parts 10, each flexible support 2 is fixedly installed on the flexible bottom plate 1 by screws;

[0008] Each set of process lugs of the joint parts 10 is respectively equipped with a process lap 3 at the end thereof; one or two process laps 3 are installed on the corresponding flexible support 2 for forming the reference symmetry axis, and are used to construct the symmetry axis of the joint parts 10, and the remaining process laps 3 are installed on the flexible support 2 at corresponding positions on both sides of the reference symmetry axis; the process laps 3 are symmetrically provided with positioning pin holes 4 and process countersunk holes 5 along the symmetry axis;

[0009] After the joint parts 10 and the process lap joints 3 respectively installed on each process ear piece form a multi-point symmetrical installation structure, they are installed on the flexible support 2 at the corresponding position through each process lap joint 3, and are positioned through the positioning pin hole 4 and locked through the process countersunk hole 5.

[0010] Optionally, in the flexible device for multi-station aircraft complex structural parts as described above,

[0011] The multi-point symmetrical installation structure formed by the joint-type parts 10 and each process lap 3 is installed on the flexible support 2 at the corresponding position in the form of the upper and lower end surfaces of the process lap 3 being aligned with the upper end surface of the flexible support 2, forming two installation forms; and in the two installation forms, all the process laps 3 and the positioning pin holes 4 and the process countersunk holes 5 are arranged symmetrically with the same symmetry axis.

[0012] Optionally, in the flexible device for multi-station aircraft complex structural parts as described above,

[0013] The process lap joints 3 respectively assembled at the ends of each set of process lugs in the joint parts 10 are designed and formed according to the structure of the corresponding process lugs in the joint parts 10;

[0014] Each of the process laps 3 comprises: a support mounting portion and an ear piece connecting portion; the support mounting portion of each process lap 3 matches the shape of the upper end surface of the flexible support 2, the support mounting portion of each process lap 3 has the same thickness, and the support mounting portions of the two symmetrically arranged process laps 3 are mirror-image structures;

[0015] The ear connecting portion of each process lap 3 is arranged on the inner end surface of the support mounting portion, and the angle of the ear connecting portion is the same as the angle of the corresponding installed process ear, and is used to connect with the corresponding process ear of the joint-type parts 10, so that the joint-type parts 10 can be installed in the multi-point symmetrical installation structure constructed by the flexible support 2 and the process lap 3 in both forward and reverse forms through multiple process laps 3.

[0016] Optionally, in the flexible device for multi-station aircraft complex structural parts as described above,

[0017] A plurality of pairs of process lap joints 3 symmetrically arranged on both sides of the symmetry axis are provided with positioning pin holes 4 and process countersunk holes 5 along the symmetry axis, and each process lap joint 3 used for constructing the symmetry axis is provided with a process countersunk hole 5 located on the symmetry axis;

[0018] After completing the multi-point symmetrical positioning of the joint parts 10 through the flexible support 2 and the process lap 3, the process lap 3 is positioned and connected to the flexible support 2 using a positioning pin 7 at the positioning pin hole 4, and the process lap 3 is locked and installed on the flexible support 2 using a hexagon socket screw 6 at the process countersunk hole 5.

[0019] Optionally, in the flexible device for multi-station aircraft complex structural parts as described above, the joint part 10 is a three-joint part with three process ears; the flexible base plate 1 is set as a regular hexagonal base or a regular triangle base or a circular base, and a 30° angle T-slot 9 or a 60° angle T-slot 9 is set on the flexible base plate 1;

[0020] The flexible device specifically comprises: 3 flexible supports 2 and 3 process headers 3; one flexible support 2 is arranged on the reference symmetry axis, and the other two flexible supports 2 are symmetrically arranged on both sides of the reference symmetry axis;

[0021] Among them, one process lap joint 3 is installed on the top of the flexible support 2 located on the reference symmetry axis, and is used to form the symmetry axis of the joint-type part 10 through one point; the other two process lap joints 3 are installed on both sides of the symmetry axis; through the coordinated installation of three process lap joints 3 and three process ears in the three-joint part, an equisymmetrical installation structure of an isosceles triangle located in the same plane formed by three points is constructed.

[0022] Optionally, in the flexible device for multi-station aircraft complex structural parts as described above, the joint part 10 is a four-joint part with four process ears; the flexible base plate 1 is set as a square base, a rectangular base or a circular base, and the flexible base plate 1 is provided with a 30° angle T-slot 9, a 45° angle T-slot 9, or a 90° angle T-slot 9;

[0023] The flexible device specifically comprises: 4 flexible supports 2 and 4 process headers 3; wherein 2 flexible supports 2 are arranged on the reference symmetry axis, and the other two flexible supports 2 are symmetrically arranged on both sides of the reference symmetry axis;

[0024] Among them, two process laps 3 are installed on the top of the flexible support 2 located on the reference symmetry axis, and are used to form the symmetry axis of the joint-type parts 10 through two points; the other two process laps 3 are installed on both sides of the symmetry axis; through the coordinated installation of four process laps 3 and four process ears in the four-joint parts, a square or rectangular symmetrical installation structure formed by four points and located in the same plane is constructed.

[0025] Optionally, in the flexible device for multi-station aircraft complex structural parts as described above,

[0026] A T-shaped connecting block 11 is provided at the bottom of each flexible support 2, which is used for precise connection with the T-shaped slot 9 on the upper end surface of the flexible base plate 1. After the symmetrical installation structure of the joint-type parts 10 is constructed on the flexible base plate 1 through the process lap 3, the flexible support 2 is locked and pressed onto the flexible base plate 1 using the hexagon socket screw 6 and the threaded hole 8 on the base of the flexible support 2.

[0027] In a second aspect, an embodiment of the present invention further provides a multi-point equal symmetry multi-point equal symmetry processing method for aircraft complex structural parts, using any of the above-mentioned flexible devices for multi-station aircraft complex structural parts to perform multi-point equal symmetry multi-point equal symmetry processing methods on joint parts 10, and the multi-point equal symmetry multi-point equal symmetry processing method includes:

[0028] Step 1, selecting multiple points of the joint part 10, the selected multiple points are located in the same plane, and the multiple points form a polygon of an axisymmetric structure; selecting at least one group of symmetrical points located on both sides of the symmetry axis as positioning points when the part 10 is clamped;

[0029] Step 2: One or two points of the joint part 10 on the symmetry axis are used as locking points, a process countersunk hole 5 located at the locking point is opened on the corresponding process lap joint 3, and a hexagon socket screw 6 is used for locking and installation;

[0030] Step 3, the symmetrical points of the joint parts 10 on both sides of the symmetry axis are used as each group of positioning points, and positioning pin holes 4 located at the positioning points are opened on the corresponding process joints 3, and positioning pins 7 are used for positioning installation; wherein, after each group of positioning points is flipped, the positions of two of the points are swapped;

[0031] Step 4, the joint-type parts 10 are located on the symmetrically installed process joints 3 on both sides of the symmetry axis, and symmetrically arranged process countersunk holes 5 are set on the outside or inside of the symmetrically arranged positioning pin holes 4 along the symmetry axis, and the hexagon socket screws 6 are used to cooperate with the locking installation to complete the symmetrical installation of multiple points of the joint-type parts 10 at one workstation.

[0032] Optionally, the multi-point isosymmetric multi-point isosymmetric processing method for aircraft complex structural parts as described above further includes:

[0033] Step 5, after removing the joint parts 10 by disassembling each process joint 3, use the symmetry axis as the flipping axis, flip the part 10 and the process joint 3 at the same time, and repeat steps 2 to 4. The position of the locking point on the symmetry axis remains in the original position after flipping, and the positions of two of the symmetrical points of the symmetrically set positioning points and the symmetrically set locking points are mirror-swapped after flipping; use the locating pin 7 for positioning installation, and use the hexagon socket screw 6 for locking installation, so as to complete the symmetrical installation of multiple points at another workstation of the joint part 10.

[0034] Optionally, in the above-mentioned multi-point isosymmetric multi-point isosymmetric processing method for aircraft complex structural parts, the joint part 10 is a three-joint part with three process ears, and the multi-point isosymmetric processing method includes:

[0035] Step 1, select three points of the joint part 10, and use the three points to form an isosceles triangle located in the same plane; select symmetrical points at two base angles of the isosceles triangle as positioning points when clamping the joint part 10;

[0036] Step 2, the joint parts 10 are respectively provided with process ears at the three sharp corners of the isosceles triangle, and the points of the joint parts 10 at the vertex of the isosceles triangle are used as locking points, and the locking points are located on the symmetry axis and are specifically provided at the process lap joints 3 at the corresponding positions;

[0037] Step 3, the joint parts 10 are respectively provided with positioning pin holes 4 at the intersection positions of the process ears on both sides of the isosceles triangle at the corresponding side bottom angles, that is, positioning pin holes 4 symmetrically arranged along the symmetry axis are formed on the symmetrically arranged process overlaps 3, and positioning pins 7 are used for positioning and installation; wherein, after each group of positioning points is flipped, the positions of two of the points are swapped;

[0038] Step 4: Place the joint part 10 on the connecting line of the two bottom angles of the isosceles triangle, set symmetrically arranged process countersunk holes 5 on the process overlap 3 along the symmetry axis, and use hexagon socket screws 6 to lock and install, so as to complete the multi-point symmetrical installation of the joint part 10 at one station;

[0039] Step 5, after removing the joint part 10 by disassembling the three process joints 3, use the symmetry axis of the isosceles triangle as the flipping axis, flip the part 10 and the process joint 3 at the same time, and repeat steps 2 to 4. After flipping, the locking points at the top angles of the isosceles triangle remain in the original position, and the positions of the positioning points and locking points at the two bottom angles of the isosceles triangle are mirror-swapped; use the locating pin 7 for positioning installation, and use the hexagon socket screw 6 for locking installation, so as to complete the multi-point symmetrical installation of the joint part 10 at another workstation.

[0040] Beneficial effects of the present invention: For the joint parts 10 in aircraft special-shaped parts with complex structures, the traditional method requires multiple stations, such as more than 6 stations, to complete the clamping of parts. The embodiment of the present invention provides a flexible device and process method for multi-station aircraft complex structural parts, with a flexible base plate 1 with a symmetrical structure as the mounting substrate of the entire device, symmetrical mounting points are constructed on the upper end surface of the flexible base plate 1, and multiple process headers 3 are arranged based on the structure of the joint parts 10 themselves according to actual use requirements to construct a multi-point symmetrical mounting surface of the part. Multiple process headers 3 are installed on each flexible support 2 according to the principle of axial symmetry, and the position arrangement of the locating pin holes 4 for installing the locating pins and the process countersunk holes 5 for installing the hexagon socket screws on the process headers 3 also follows the principle of axial symmetry. The technical solution provided by the embodiment of the present invention has the following beneficial effects:

[0041] (1) The flexible device in the embodiment of the present invention adopts the principle of axisymmetry to construct a multi-point symmetrical installation structure, which can ensure that the parts can be flipped along the symmetrical axis no matter how they are clamped. The positioning pin hole 4 is used to locate the parts, and then the process countersunk hole 5 is used to locate the parts in cooperation with the hexagon socket screw 6, thereby ensuring accurate positioning and reliable locking of the parts, thereby achieving reliable symmetrical processing.

[0042] (2) The flexible device provided in the embodiment of the present invention is used to simplify the part clamping method that requires multiple stations (for example, more than 6 stations) in the traditional process to be completed into two-station clamping of positive and negative stations. The clamping method of constructing a multi-point symmetrical installation structure innovatively proposed in the embodiment of the present invention greatly reduces the processing stations of the parts, simplifies the processing process setting, and improves the production efficiency; in addition, the flexible device of the embodiment of the present invention is used to construct a multi-point symmetrical installation structure for the joint part 10, which can reduce the error caused by clamping as much as possible, thereby greatly improving the processing quality of the parts;

[0043] (3) By using the flexible device provided in the embodiment of the present invention, it is no longer necessary to manufacture a set of special milling tools for each complex process structural part of the same family of parts, which greatly saves tooling costs; moreover, the joint parts 10 are mostly family parts, and the production form is typical multi-variety and small batch; the product line is frequently changed during the production process. If traditional special tooling is used to clamp the parts, due to the lack of flexibility in the use of the tooling, one set of vacuum milling tools for each part will have the disadvantages of high manufacturing cost, long production cycle, and occupied space. The flexible device provided in the embodiment of the present invention solves these problems;

[0044] (4) The multi-point symmetrical processing method performed by the flexible device provided in the embodiment of the present invention changes the reserved rough material process frame in the traditional processing technology, and realizes the process mode of part processing by repeated clamping. The advantages of the process method provided by the present invention are: it greatly simplifies the part processing technology, effectively prevents vibration during processing, and improves the surface quality of parts; and effectively controls the deformation of parts; in addition, for each complex process part of the same family of parts, it is no longer necessary to manufacture a set of special milling tools, which greatly saves tooling costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] The accompanying drawings are used to provide a further understanding of the technical solution of the present invention and constitute a part of the specification. Together with the embodiments of the present application, they are used to explain the technical solution of the present invention and do not constitute a limitation on the technical solution of the present invention.

[0046] Figure 1 A schematic diagram of the structure of a complex structure aircraft part in an embodiment of the present invention;

[0047] Figure 2 A top view of a flexible device for clamping joint parts of a multi-station aircraft complex structural part provided by an embodiment of the present invention;

[0048] Figure 3 A schematic structural diagram of a clamping method for clamping joint parts by a flexible device for a multi-station aircraft complex structural part provided by an embodiment of the present invention;

[0049] Figure 4 A schematic structural diagram of another clamping form of a flexible device for clamping joint-type parts of a multi-station aircraft complex structure provided by an embodiment of the present invention;

[0050] Figure 5 A schematic diagram of the installation structure of process overlaps and joint parts in a flexible device for multi-station aircraft complex structural parts provided by an embodiment of the present invention;

[0051] Figure 6 A schematic structural diagram of a flexible bottom plate in a flexible device for a multi-station aircraft complex structural part provided by an embodiment of the present invention;

[0052] Figure 7 A schematic structural diagram of a symmetrically arranged flexible support for complex structural parts of an aircraft provided in an embodiment of the present invention.

[0053] Description of reference numerals:

[0054] 1. Flexible base plate; 2. Flexible support; 3. Process overlap; 4. Locating pin hole; 5. Process countersunk hole; 6. Hexagon socket screw; 7. Locating pin; 8. Threaded hole; 9. T-slot; 10. Connector parts; 11. T-connecting block. DETAILED DESCRIPTION

[0055] In order to make the purpose, technical solution and advantages of the present invention more clear, the embodiments of the present invention will be described in detail with reference to the accompanying drawings. It should be noted that the embodiments and features in the embodiments of the present application can be combined with each other arbitrarily without conflict.

[0056] The above background technology has explained that the difficulty in processing complex structural special-shaped parts in aircraft parts is to use a reserved rough material process frame and realize the process of part processing through repeated clamping. This processing method is time-consuming and labor-intensive, has high processing difficulty and low processing efficiency.

[0057] In response to the problems existing in the processing methods of complex structure aircraft parts, the embodiments of the present invention provide a flexible device for multi-station complex aircraft structural parts and a multi-point equal symmetry and multi-point equal symmetry processing method, providing a novel idea and easy use. According to the multi-point structure of the complex structural part, a virtual symmetry axis on the part can be constructed through process overlaps and locating pin holes thereon, and a flexible and adjustable flexible device can be used to cleverly realize the posture adjustment of the part.

[0058] The present invention provides the following specific embodiments which can be combined with each other. The same or similar concepts or processes may not be described in detail in some embodiments.

[0059] Figure 1 is a schematic diagram of the structure of a complex structure aircraft part in an embodiment of the present invention, Figure 2 A top view of a flexible device for clamping joint parts of a multi-station aircraft complex structure provided by an embodiment of the present invention, Figure 3 A schematic structural diagram of a clamping form for clamping joint parts of a flexible device for multi-station aircraft complex structural parts provided by an embodiment of the present invention.

[0060] like Figure 1 As shown, the clamping object of the flexible device in the embodiment of the present invention is, for example, a joint part 10 of a special-shaped structure. The structure of the joint part 10 generally includes a joint base and process ears extending from multiple end surfaces of the base, and there is no special structural rule between these process ears, which may be as follows Figure 1 The flexible device provided in the embodiment of the present invention is designed based on the structural characteristics of the joint part 10, that is, the characteristics of multiple process ears, and multiple process laps are set as required. The process laps 3 are provided with positioning pin holes 4 and process countersunk holes, so that the process laps 3 and the joint part 10 are installed in coordination to construct a multi-point symmetrical installation structure.

[0061] like Figure 2 and Figure 3 As shown, the structure of the flexible device for multi-station aircraft complex structural parts provided by the embodiment of the present invention includes: a flexible bottom plate 1, a plurality of flexible supports 2 and a plurality of process headers 3. It should be noted that in the embodiment of the present invention, the number of the flexible supports 2 and the process headers 3 is the same, which is a one-to-one corresponding installation form.

[0062] like Figure 2 and Figure 3 The flexible device shown in the embodiment of the present invention is configured as a regular polygonal base or a circular base with a certain thickness, for example, it can be a regular hexagonal base, or it can be a base of various other symmetrical shapes, and the upper end surface of the flexible base 1 is provided with a plurality of T-slots 9 emitted along the center point at equal angles.

[0063] In the embodiment of the present invention, the size of the flexible base plate 1 can be set according to the processing requirements of the parts to meet the standard of part installation; the T-slots 9 on the flexible base plate 1 are provided to achieve symmetrical clamping of the parts, for example Figure 2 and Figure 3 The parts in the embodiment of the present invention adopt a symmetrical clamping structure of an isosceles triangle. It should be noted that the "equi-symmetry" in the embodiment of the present invention refers to the construction of an equi-symmetric structure for the joint parts 10, that is, the joint parts 10 are constructed with multiple process joints 3 used in combination to construct multiple vertex angles located in the same plane, and a symmetrical shape is formed with the plane where these vertex angles are located, which is the equi-symmetric installation structure in the embodiment of the present invention.

[0064] One or two flexible supports 2 in the embodiment of the present invention are installed on the T-slots 9 located in the same straight line to form the reference symmetry axis of the flexible device, and the remaining flexible supports 2 are symmetrically installed on the T-slots 9 on both sides of the reference symmetry axis; a threaded hole 8 is provided at the bottom of each flexible support 2. After the symmetrical installation structure of the joint parts 10 is constructed by the process lap 3 and the flexible supports 2 are fixedly installed at the corresponding positions, each flexible support 2 is fixedly installed on the flexible bottom plate 1 by screws.

[0065] The end of each group of process lugs of the joint-type parts 10 in the embodiment of the present invention is respectively equipped with a process lap 3, that is, the process laps 3 installed at each process lug are used to construct the symmetrical installation structure of the part. The specific construction structure is: one or two process laps 3 are installed on the corresponding flexible support 2 used to form the reference symmetry axis, which is used to construct the symmetry axis of the joint-type parts 10, and the remaining process laps 3 are installed on the flexible supports 2 at corresponding positions on both sides of the reference symmetry axis. In addition, the process laps 3 are symmetrically provided with positioning pin holes 4 and process countersunk holes 5 along the symmetry axis.

[0066] In the embodiment of the present invention, the flexible device of the above structure is adopted. After the joint parts 10 and the process lap joints 3 respectively installed on the process ears form a multi-point symmetrical installation structure, they are installed on the flexible support 2 at the corresponding position through each process lap joint 3, and positioned through the positioning pin hole 4, and locked and installed through the process countersunk hole 5, thus completing the multi-point symmetrical positioning installation of the joint parts 10. In the specific implementation, the virtual symmetry axis of the part is formed by the process lap joint 3 and the positioning pin hole structure thereon, and the posture adjustment of the part is cleverly achieved by using a flexible and adjustable flexible device, thereby greatly simplifying the processing technology of such special-shaped and complex parts; therefore, the processing technology realized by the flexible device has the characteristics of rapid positioning, flexible adjustment, efficient clamping, and simplicity.

[0067] Further, Figure 4 A schematic diagram of another clamping method for a flexible device for clamping complex parts of a multi-station aircraft complex structure provided by an embodiment of the present invention, Figure 4 The flexible device provided by the embodiment of the present invention, the joint parts 10 and the multi-point symmetrical installation structure formed by each process lap joint 3 can be installed on the flexible support 2 at the corresponding position by aligning the upper and lower end surfaces of the process lap joint 3 with the upper end surface of the flexible support 2, that is, forming two clamping forms (that is, forming two installation structures), such as Figure 3 and Figure 4 In the clamping form shown, the joint parts 10 and each process lap joint 3 are flipped and installed as a whole; all the process lap joints 3 and the positioning pin holes 4 and process countersunk holes 5 in the above two installation structures are arranged symmetrically with the same symmetry axis.

[0068] It should be noted that the structure and geometric dimensions of the flexible support 2 in the embodiment of the present invention can be configured according to actual use requirements. The use of the flexible support 2 is to align the position of the flexible support 2 on the flexible base plate 1 according to the position designed in advance with an axially symmetrical structure, and then lock and install it. At this time, it is required to ensure that the positioning pin holes 4 and the process countersunk holes 5 on the process lap 3 in the equisymmetrical installation structure of the joint-type parts 10 are symmetrically distributed along the virtual symmetry axis. After installation in the above manner, the part is flipped along the symmetry axis when it is turned over for clamping, and the adjustment of the clamping posture of the positive and negative stations can be easily realized when the part is clamped, thereby greatly simplifying the processing technology, and it has the characteristics of fast clamping speed and high flexibility in use.

[0069] The flexible device provided in the embodiment of the present invention adopts the principle of axial symmetry to construct a multi-point symmetrical installation structure, which can ensure that the parts can be flipped along the symmetry axis no matter how the clamping is arranged. The parts are positioned by the locating pin hole 4 in cooperation with the locating pin, and then locked by the process countersunk hole 5 in cooperation with the hexagon socket screw 6, thereby ensuring the precise positioning and reliable locking of the parts, and then realizing reliable symmetrical processing; in addition, the above-mentioned symmetrical installation structure greatly reduces the processing stations of the parts and simplifies the processing process setting.

[0070] In one implementation of the present invention, the structure of the process lap joint 3 respectively assembled at the end of each set of process tabs in the joint parts 10 is designed and formed according to the structure of the corresponding process tabs in the joint parts 10. Figure 5 As shown, it is a schematic diagram of the installation structure of process overlaps and joint parts in the flexible device provided in an embodiment of the present invention.

[0071] In this implementation, Figure 5 As shown, the structure of each process lap 3 includes: a support mounting portion and an ear piece connecting portion; the support mounting portion of each process lap 3 matches the shape of the upper end surface of the flexible support 2, and the thickness of the support mounting portion of each process lap 3 is the same; in particular, the support mounting portions of two process laps 3 symmetrically arranged with respect to the axis of symmetry are mirror structures, so that when the part is flipped, the structures of the two process laps 3 symmetrically arranged before and after the flipping are exactly the same.

[0072] In this implementation, Figure 5As shown, the ear connection part of each process lap 3 is arranged on the inner end face of the support mounting part, and the angle of the ear connection part is the same as the angle of the corresponding installed process ear, which is arranged based on the structural form of the corresponding process ear, and is used to connect with the corresponding process ear of the joint part 10, and after the connection, an equisymmetrical installation structure can be constructed through the process lap 3. Based on the above-mentioned structural features of each process lap 3, the joint part 10 can be installed in the multi-point equisymmetrical installation structure constructed by the flexible support 2 and the process lap 3 in both forward and reverse forms through multiple process laps 3. It should be noted that, referring to Figure 3 The forward installation structure shown in the figure, the reverse installation form of the joint parts 10 is: the forward installation structure is turned over by taking the symmetry axis as the turning axis, the joint parts 10 and the process lap joint 3 are turned over 180° together, and then the process lap joint is installed on the flexible support 2 at the corresponding position, so as to form Figure 4 Reverse mounting structure shown.

[0073] In one implementation of the embodiment of the present invention, multiple pairs of process lap joints 3 symmetrically arranged on both sides of the symmetry axis are provided with positioning pin holes 4 and process countersunk holes 5 along the symmetry axis, and each process lap joint 3 for constructing the symmetry axis is provided with a process countersunk hole 5 located on the symmetry axis.

[0074] Based on the opening setting on each process lap 3, after completing the multi-point symmetrical positioning of the joint parts 10 through the flexible support 2 and the process lap 3, the positioning pin 7 is used at the positioning pin hole 4 to position the process lap 3 and connect it to the flexible support 2, and the hexagon socket screw 6 is used at the process countersunk hole 5 to lock the process lap 3 and install it on the flexible support 2; then, each flexible support 2 is fixedly installed on the flexible base plate 1 with screws, thereby completing a form of installation of the joint parts 10.

[0075] It should be noted that the embodiment of the present invention does not limit the number of flexible supports 2 used to construct the reference symmetry axis to 1 or 2, and also does not limit the number of process laps 3 used to construct the part symmetry axis to 1 or 2; specifically, whether it is 1 or 2 is determined according to the actual structure of the joint part 10. For example, for constructing an isosceles triangle structure or a regular pentagon structure, 1 flexible support 2 and 1 process lap 3 are used to construct the symmetry axis; for another example, for constructing a square or rectangular structure, two points and one line formed by two flexible supports 2 and two process laps 3 are used as the symmetry axis. Two implementation examples are used as follows for illustration.

[0076] Implementation Example 1

[0077] by Figures 2 to 6 The flexible device provided in the embodiment shown is shown as an example, and the joint part 10 is as follows Figure 1The three-joint part with three process tabs is shown in FIG. Figure 6 As shown, it is a schematic diagram of the structure of a flexible bottom plate in a flexible device for a multi-station aircraft complex structural part provided by an embodiment of the present invention. The flexible bottom plate 1 in the embodiment 1 is set as a regular hexagonal base, and a 30° angle T-slot 9 is set on the flexible bottom plate 1; the flexible bottom plate 1 of the structural design takes into account the need for setting the odd-numbered parts. Figures 2 to 6 The parts in the machine adopt a symmetrical clamping structure of isosceles triangle.

[0078] In this implementation example 1, the flexible device specifically includes: 3 flexible supports 2 and 3 process headers 3; one flexible support 2 is arranged on the reference symmetry axis, and the other two flexible supports 2 are symmetrically arranged on both sides of the reference symmetry axis; Figures 2 to 4 As shown. Figure 7 As shown, it is a schematic diagram of the structure of a symmetrically arranged flexible support for complex structural parts of an aircraft provided in an embodiment of the present invention. The structure of the flexible support in the embodiment of the present invention is designed according to actual needs. A T-shaped connecting block 11 is provided at the bottom of the flexible support 2, which is used to accurately connect with the T-shaped slot 9 on the upper end surface of the flexible bottom plate 1. After positioning at a suitable position on the flexible bottom plate 1, the flexible support 2 is locked by using a hexagon socket screw 6 through a threaded hole 8.

[0079] In this implementation example 1, one process lap joint 3 is installed on the top of the flexible support 2 located on the reference symmetry axis, and is used to form the symmetry axis of the joint part 10 through one point; the other two process lap joints 3 are installed on both sides of the symmetry axis; through the coordinated installation of the three process lap joints 3 and the three process ears in the three-joint part, an equisymmetrical installation structure of an isosceles triangle located in the same plane formed by the three points is constructed, such as Figures 2 to 4 shown.

[0080] In this implementation example 1, among the three process laps 3, one is the construction point of the symmetry axis, and the remaining two process laps 3 form an axisymmetric arrangement structure along the symmetry axis extended from the construction point. The positioning pin holes 4 and process countersunk holes 5 on the symmetrical process laps 3 must also ensure that they form an axisymmetric arrangement structure along the symmetry axis. The positioning structure of the positioning pin 7 and the positioning pin hole 4 is used for part positioning, and the screw locking method of the hexagon socket screw 6 and the process countersunk hole 5 is used for part locking. The flexible support 2 is fixed in a manner that the flexible support 2 is locked and installed on the flexible base plate 1 after determining its own installation position on the flexible base plate 1 according to the positioning pin holes 4 and the process countersunk holes 5 on the process lap 3. In addition, since the position of the flexible support 2 in the T-slot 9 is flexibly adjustable, the flexible device provided in each embodiment of the present invention can adapt to the clamping of parts with different symmetrical structures.

[0081] It should be noted that if Figure 6As shown, the flexible base plate 1 in the embodiment 1 is, for example, a regular hexagonal base plate with a certain thickness, and the size of the base plate can be set according to the processing requirements of the parts. The specific structure of the flexible base plate 1 used for three-joint parts is not limited in the embodiment of the present invention. For example, the flexible base plate 1 can also be a regular triangle base or a circular base or other symmetrical figures; in addition, T-slots 9 are arranged on the flexible base plate 1 according to the principle of equal angles, and 60° angle T-slots 9 or 120° angle T-slots 9 can also be arranged on the flexible base plate 1. In the embodiment of the present invention, the structural form and layout form of the flexible base plate 1, the flexible support 2 and the process header 3 are based on the standard of being able to construct a multi-point symmetrical installation structure of the joint-type parts 10.

[0082] Implementation Example 2

[0083] In the flexible device provided in this embodiment 2, the joint part 10 is, for example, a four-joint part with four process ears. For the four-joint part, the flexible bottom plate 1 in this embodiment 2 is, for example, set as a square base, and the flexible bottom plate 1 is, for example, provided with a 45° angle T-slot 9.

[0084] In this implementation example 2, the flexible device specifically includes: 4 flexible supports 2 and 4 process headers 3; wherein 2 flexible supports 2 are arranged on the reference symmetry axis, and the other two flexible supports 2 are symmetrically arranged on both sides of the reference symmetry axis.

[0085] In this implementation example 1, two process laps 3 are installed on the top of the flexible support 2 located on the reference symmetry axis, and are used to form the symmetry axis of the joint-type part 10 through two points; another two process laps 3 are installed on both sides of the symmetry axis; through the coordinated installation of four process laps 3 and four process ears in the four-joint part, a square or rectangular symmetrical installation structure formed by four points and located in the same plane is constructed.

[0086] It should be noted that the specific structure of the flexible base plate 1 for four-joint parts is not limited in the embodiment of the present invention. For example, the flexible base plate 1 in the embodiment may also be a rectangular base or a circular base, and a 90° angle T-slot 9 or a 30° angle T-slot 9 may be provided on the flexible base plate 1. In the embodiment of the present invention, the structural form and layout form of the flexible base plate 1, the flexible support 2 and the process header 3 are based on the standard of being able to construct a multi-point symmetrical installation structure of the joint parts 10.

[0087] Based on the flexible device for multi-station aircraft complex structural parts provided by the above embodiments of the present invention, the embodiments of the present invention further provide a multi-point equal symmetry multi-point equal symmetry processing method for aircraft complex structural parts. The flexible device for multi-station aircraft complex structural parts provided by any of the above embodiments can be used to perform the multi-point equal symmetry multi-point equal symmetry processing method on the joint parts 10. The multi-point equal symmetry multi-point equal symmetry processing method includes the following steps:

[0088] Step 1: Select multiple points of the joint part 10, where the selected multiple points are located in the same plane and form a polygon with an axisymmetric structure.

[0089] In step 1, at least one group of symmetrical points located on both sides of the symmetry axis are selected as positioning points when the part 10 is clamped, so that when the part 10 is turned over around the symmetry axis, the two positioning points in each group are interchanged with each other in a symmetrical manner.

[0090] Step 2, use one or two points of the joint part 10 on the axis of symmetry as locking points, open a process countersunk hole 5 at the locking point on the corresponding process lap joint 3, and use a hexagon socket screw 6 to lock and install it.

[0091] In this step, the locking point on the process overlap 3 for constructing the axis of symmetry is not used for positioning but only for locking, because it will cause over-positioning of the parts.

[0092] Step 3, use the symmetrical points of the joint parts 10 on both sides of the symmetry axis as each group of positioning points, open positioning pin holes 4 at the positioning points on the corresponding process joints 3, and use positioning pins 7 to cooperate with positioning installation; wherein, after each group of positioning points is flipped, the positions of two of the points are swapped.

[0093] Step 4, the joint parts 10 are located on the symmetrically installed process joints 3 on both sides of the symmetry axis, and symmetrically arranged process countersunk holes 5 are set on the outside or inside of the symmetrically arranged positioning pin holes 4 along the symmetry axis, and are locked and installed with hexagon socket screws 6.

[0094] Through the above steps 1 to 4, the symmetrical installation of multiple points of a workstation of the joint-type parts 10 is completed, for example, Figure 3 The installation structure in.

[0095] Furthermore, based on the flexible device and the above-mentioned installation method provided in the embodiment of the present invention, the process method provided in the embodiment of the present invention further includes the following steps:

[0096] Step 5, after removing the joint parts 10 by disassembling each process lap joint 3, use the symmetry axis as the flipping axis, flip the part 10 and the process lap joint 3 at the same time, repeat steps 2 to 4, and keep the position of each locking point after flipping. After each group of positioning points is flipped, the positions of two of the points are swapped; use the locating pin 7 for positioning installation, and use the hexagon socket screw 6 for locking installation; at this time, complete the symmetrical installation of multiple points at another workstation of the joint part 10.

[0097] It should be noted that the reference Figure 3 and Figure 4 As shown, by using the device provided in the embodiment of the present invention in conjunction with the corresponding process method, the joint parts 10 are flipped along the axis of symmetry to form a reverse clamping form. Since the process lap 3 cooperates with the joint parts 10 to construct an equisymmetrical structure, the installation positioning and locking method can repeat the installation steps of the front clamping form. Therefore, this processing technology has the advantages of being simple, reliable and easy to operate.

[0098] Taking the three-joint part 10 with three process ears in the embodiment of the present invention as an example, the multi-point equal symmetry multi-point equal symmetry processing method is described. Specifically, the following steps are included:

[0099] Step 1, select three points of the joint part 10, and use the three points to form an isosceles triangle located in the same plane;

[0100] In this embodiment, symmetrical points at the two bottom angles of the isosceles triangle are selected as positioning points when the joint part 10 is clamped; when the part 10 is turned over around the axis of symmetry, the two positioning points can be interchanged with each other in a symmetrical form.

[0101] Step 2, the joint parts 10 are respectively provided with process ears at the three sharp corners of the isosceles triangle, and the points of the joint parts 10 at the vertex of the isosceles triangle are used as locking points, and the locking points are located on the symmetry axis and are specifically provided at the process lap joints 3 at the corresponding positions;

[0102] In this step, the selected locking points are not used for positioning, as this will cause over-positioning of the part.

[0103] Step 3, respectively set positioning pin holes 4 at the intersection positions of the corresponding side bottom angles of the process ears on both sides of the isosceles triangle of the joint parts 10, that is, form positioning pin holes 4 symmetrically arranged along the axis of symmetry on the symmetrically arranged process joints 3, and use positioning pins 7 to cooperate in positioning and installation; wherein, after each group of positioning points is flipped, the positions of two of the points are swapped.

[0104] Step 4: Place the joint part 10 on the connecting line of the two bottom angles of the isosceles triangle, set symmetrically arranged process countersunk holes 5 on the process overlap 3 along the symmetry axis, and use hexagon socket screws 6 to lock and install, so as to complete the multi-point symmetrical installation of the joint part 10 at one station;

[0105] It should be noted that different mechanical locking structures can be set at the locking points as needed; when the joint parts 10 are flipped around the symmetry axis of the isosceles triangle, the positioning points and locking points at the bottom corners can be installed interchangeably.

[0106] Step 5, after removing the joint part 10 by disassembling the three process joints 3, use the symmetry axis of the isosceles triangle as the flipping axis, flip the part 10 and the process joint 3 at the same time, and repeat steps 2 to 4. After flipping, the locking points at the top angles of the isosceles triangle remain in the original position, and the positions of the positioning points and locking points at the two bottom angles of the isosceles triangle are mirror-swapped; use the locating pin 7 for positioning installation, and use the hexagon socket screw 6 for locking installation, so as to complete the multi-point symmetrical installation of the joint part 10 at another workstation.

[0107] In view of the complex structure of the joint parts 10 in the aircraft special-shaped parts, the traditional method requires multiple stations (for example, more than 6 stations) to complete the clamping of the parts. The flexible device and process method for multi-station aircraft complex structural parts provided by the embodiment of the present invention use a flexible base plate 1 with a symmetrical structure as the mounting substrate of the entire device, and construct symmetrical mounting points on the upper end surface of the flexible base plate 1. In addition, based on the structure of the joint parts 10 themselves, multiple process headers 3 are arranged according to actual use requirements to construct a multi-point symmetrical mounting surface of the part. Multiple process headers 3 are installed on each flexible support 2 according to the principle of axial symmetry, and the position arrangement of the locating pin holes 4 for installing the locating pins and the process countersunk holes 5 for installing the hexagon socket screws provided on the process headers 3 also follows the principle of axial symmetry. The technical solution provided by the embodiment of the present invention has the following beneficial effects:

[0108] (1) The flexible device in the embodiment of the present invention adopts the principle of axisymmetry to construct a multi-point symmetrical installation structure, which can ensure that the parts can be flipped along the symmetrical axis no matter how they are clamped. The positioning pin hole 4 is used to locate the parts, and then the process countersunk hole 5 is used to locate the parts in cooperation with the hexagon socket screw 6, thereby ensuring accurate positioning and reliable locking of the parts, thereby achieving reliable symmetrical processing.

[0109] (2) The flexible device provided in the embodiment of the present invention is used to simplify the part clamping method that requires multiple stations (for example, more than 6 stations) in the traditional process to be completed into two-station clamping of positive and negative stations. The clamping method of constructing a multi-point symmetrical installation structure innovatively proposed in the embodiment of the present invention greatly reduces the processing stations of the parts, simplifies the processing process setting, and improves the production efficiency; in addition, the flexible device of the embodiment of the present invention is used to construct a multi-point symmetrical installation structure for the joint part 10, which can reduce the error caused by clamping as much as possible, thereby greatly improving the processing quality of the parts;

[0110] (3) By using the flexible device provided in the embodiment of the present invention, it is no longer necessary to manufacture a set of special milling tools for each complex process structural part of the same family of parts, which greatly saves tooling costs; moreover, the joint parts 10 are mostly family parts, and the production form is typical multi-variety and small batch; the product line is frequently changed during the production process. If traditional special tooling is used to clamp the parts, due to the lack of flexibility in the use of the tooling, one set of vacuum milling tools for each part will have the disadvantages of high manufacturing cost, long production cycle, and occupied space. The flexible device provided in the embodiment of the present invention solves these problems;

[0111] (4) The multi-point symmetrical processing method performed by the flexible device provided in the embodiment of the present invention changes the reserved rough material process frame in the traditional processing technology, and realizes the process mode of part processing by repeated clamping. The advantages of the process method provided by the present invention are: it greatly simplifies the part processing technology, effectively prevents vibration during processing, and improves the surface quality of parts; and effectively controls the deformation of parts; in addition, for each complex process part of the same family of parts, it is no longer necessary to manufacture a set of special milling tools, which greatly saves tooling costs.

[0112] Although the embodiments disclosed in the present invention are as above, the contents are only embodiments adopted to facilitate understanding of the present invention and are not intended to limit the present invention. Any technician in the field to which the present invention belongs can make any modifications and changes in the form and details of implementation without departing from the spirit and scope disclosed in the present invention, but the patent protection scope of the present invention shall still be subject to the scope defined in the attached claims.

Claims

1. A flexible device for complex multi-station aircraft structural parts, characterized in that: The flexible device is used to form a multi-point symmetrical installation structure for joint parts (10), and the symmetrical flexible device comprises: a flexible base plate (1), a plurality of flexible supports (2) and a plurality of process joints (3); The flexible base plate (1) is configured as a regular polygonal base or a circular base, and a plurality of T-shaped slots (9) extending along a center point are formed on the upper end surface of the flexible base plate (1) in an equiangular form; One or two of the flexible supports (2) are mounted on T-slots (9) located in the same straight line to form a reference symmetry axis of the flexible device, and the remaining flexible supports (2) are symmetrically mounted on the T-slots (9) on both sides of the reference symmetry axis; a threaded hole (8) is provided at the bottom of each flexible support (2), so that after constructing an isosymmetrical mounting structure of a joint-type part (10), each flexible support (2) can be fixedly mounted on the flexible bottom plate (1) using screws; The end of each group of process lugs of the joint part (10) is respectively equipped with a process lap (3); one or two process laps (3) are installed on the corresponding flexible support (2) used to form the reference symmetry axis, and are used to construct the symmetry axis of the joint part (10), and the remaining process laps (3) are installed on the flexible supports (2) at corresponding positions on both sides of the reference symmetry axis; the process laps (3) are symmetrically provided with positioning pin holes (4) and process countersunk holes (5) along the symmetry axis; After the joint parts (10) and the process lap joints (3) respectively installed on each process ear piece form a multi-point symmetrical installation structure, they are installed on the flexible support (2) at the corresponding position through each process lap joint (3), and are positioned through the positioning pin hole (4), and locked and installed through the process countersunk hole (5).

2. The flexible device for multi-station aircraft complex structural parts according to claim 1 is characterized in that: The multi-point symmetrical installation structure formed by the joint parts (10) and each process lap joint (3) is installed on the flexible support (2) at the corresponding position in the form of the upper and lower end surfaces of the process lap joint (3) being aligned with the upper end surface of the flexible support (2), forming two installation forms; and in the two installation forms, all the process lap joints (3) and the positioning pin holes (4) and the process countersunk holes (5) are arranged symmetrically along the same symmetry axis.

3. The flexible device for multi-station aircraft complex structural parts according to claim 2 is characterized in that: The process lap joints (3) respectively assembled at the ends of each group of process lugs in the joint parts (10) are designed and formed according to the structure of the corresponding process lugs in the joint parts (10); Each of the process laps (3) comprises: a support mounting portion and an ear piece connecting portion; the support mounting portion of each process lap (3) matches the shape of the upper end surface of the flexible support (2), the support mounting portion of each process lap (3) has the same thickness, and the support mounting portions of two symmetrically arranged process laps (3) are mirror-image structures; The ear piece connection part of each process lap (3) is arranged on the inner end surface of the support mounting part, and the angle of the ear piece connection part is the same as the angle of the corresponding installed process ear piece, and is used to connect with the corresponding process ear piece of the joint-type part (10), so that the joint-type part (10) can be installed in a multi-point symmetrical installation structure constructed by the flexible support (2) and the process lap (3) in both forward and reverse forms through multiple process laps (3).

4. The flexible device for multi-station aircraft complex structural parts according to claim 3 is characterized in that: A plurality of pairs of process lap joints (3) symmetrically arranged on both sides of the symmetry axis are provided with positioning pin holes (4) and process countersunk holes (5) along the symmetry axis, and each process lap joint (3) used to construct the symmetry axis is provided with a process countersunk hole (5) located on the symmetry axis; After the multi-point symmetrical positioning of the joint part (10) is completed by the flexible support (2) and the process lap (3), the process lap (3) is positioned and connected to the flexible support (2) by using a positioning pin (7) at the positioning pin hole (4), and the process lap (3) is locked and installed on the flexible support (2) by using a hexagon socket screw (6) at the process countersunk hole (5).

5. The flexible device for multi-station aircraft complex structural parts according to any one of claims 1 to 4, characterized in that: The joint part (10) is a three-joint part with three process ears; the flexible base plate (1) is configured as a regular hexagonal base, a regular triangle base or a circular base, and a 30° angle T-slot (9) or a 60° angle T-slot (9) is provided on the flexible base plate (1); The flexible device specifically comprises: three flexible supports (2) and three process headers (3); one flexible support (2) is arranged on the reference symmetry axis, and the other two flexible supports (2) are symmetrically arranged on both sides of the reference symmetry axis; Among them, one process lap joint (3) is installed on the top of the flexible support (2) located on the reference symmetry axis, and is used to form the symmetry axis of the joint-type parts (10) through one point; the other two process lap joints (3) are installed on both sides of the symmetry axis; through the coordinated installation of the three process lap joints (3) and the three process ears in the three-joint parts, an equisymmetrical installation structure of an isosceles triangle located in the same plane formed by the three points is constructed.

6. The flexible device for multi-station aircraft complex structural parts according to any one of claims 1 to 4, characterized in that: The joint part (10) is a four-joint part with four process ears; the flexible base plate (1) is configured as a square base, a rectangular base or a circular base, and the flexible base plate (1) is provided with a 30° angle T-slot (9), a 45° angle T-slot (9), or a 90° angle T-slot (9); The flexible device specifically comprises: 4 flexible supports (2) and 4 process headers (3); wherein 2 flexible supports (2) are arranged on the reference symmetry axis, and the other two flexible supports (2) are symmetrically arranged on both sides of the reference symmetry axis; Among them, two process laps (3) are installed on the top of the flexible support (2) located on the reference symmetry axis, and are used to form the symmetry axis of the joint-type parts (10) through two points; another two process laps (3) are installed on both sides of the symmetry axis; through the coordinated installation of the four process laps (3) and the four process ears in the four-joint parts, a square or rectangular symmetrical installation structure formed by the four points and located in the same plane is constructed.

7. The flexible device for multi-station aircraft complex structural parts according to any one of claims 1 to 4, characterized in that: A T-shaped connection block (11) is provided at the bottom of each of the flexible supports (2) for precise connection with the T-shaped slot (9) on the upper end surface of the flexible base plate (1). After an isosymmetrical installation structure of a joint-type part (10) is constructed on the flexible base plate (1) by means of a process overlap (3), the flexible support (2) is locked and pressed onto the flexible base plate (1) by means of a hexagon socket screw (6) and a threaded hole (8) on the base of the flexible support (2).

8. A multi-point isosymmetric multi-point isosymmetric processing method for aircraft complex structural parts, characterized in that: A multi-point isosymmetric multi-point isosymmetric processing method is performed on joint parts (10) using a flexible device for multi-station aircraft complex structural parts according to any one of claims 1 to 7, wherein the multi-point isosymmetric multi-point isosymmetric processing method comprises: Step 1, selecting multiple points of a joint part (10), wherein the selected multiple points are located in the same plane and the multiple points form a polygon of an axisymmetric structure; selecting at least one group of symmetrical points located on both sides of the axis of symmetry as positioning points when the part (10) is clamped; Step 2, one or two points of the joint part (10) on the axis of symmetry are used as locking points, a process countersunk hole (5) located at the locking point is opened on the corresponding process overlap (3), and a hexagon socket screw (6) is used for locking installation; Step 3, using the symmetrical points of the joint parts (10) on both sides of the symmetry axis as each group of positioning points, opening positioning pin holes (4) at the positioning points on the corresponding process overlap (3), and using positioning pins (7) for positioning installation; wherein, after each group of positioning points is flipped, the positions of two of the points are swapped; Step 4, the joint-type parts (10) are located on the symmetrically installed process joints (3) on both sides of the symmetry axis, and symmetrically arranged process countersunk holes (5) are set on the outside or inside of the symmetrically arranged positioning pin holes (4) along the symmetry axis, and hexagon socket screws (6) are used to cooperate with the locking installation to complete the symmetrical installation of multiple points of a workstation of the joint-type parts (10).

9. The multi-point isosymmetric multi-point isosymmetric processing method for aircraft complex structural parts according to claim 8, characterized in that: Also includes: Step 5, after removing the joint parts (10) by disassembling each process joint (3), flip the parts (10) and the process joint (3) at the same time with the axis of symmetry as the flipping axis, and repeat steps 2 to 4. The position of the locking point on the axis of symmetry remains at the original position after flipping, and the positions of two symmetrical points of the symmetrically set positioning points and the symmetrically set locking points are mirror-swapped after flipping; the positioning pins (7) are used for positioning installation, and the hexagon socket screws (6) are used for locking installation, so as to complete the symmetrical installation of multiple points of the joint parts (10) at another station.

10. The multi-point isosymmetric multi-point isosymmetric processing method for aircraft complex structural parts according to claim 8, characterized in that: The joint part (10) is a three-joint part with three process ears, and the multi-point equal symmetry processing method comprises: Step 1, selecting three points of the joint part (10), and forming an isosceles triangle located in the same plane with the three points; selecting symmetrical points at two base angles of the isosceles triangle as positioning points when clamping the joint part (10); Step 2, the joint parts (10) are respectively provided with process ears at the three sharp corners of the isosceles triangle, and the points of the joint parts (10) at the vertex of the isosceles triangle are used as locking points, and the locking points are located on the symmetry axis and are specifically provided at the process overlaps (3) at corresponding positions; Step 3, positioning pin holes (4) are respectively arranged at the intersection positions of the process ears on both sides of the isosceles triangle of the joint parts (10) at the corresponding side bottom angles, that is, positioning pin holes (4) symmetrically arranged along the symmetry axis are formed on the symmetrically arranged process overlaps (3), and positioning pins (7) are used for positioning installation; wherein, after each group of positioning points is flipped, the positions of two of the points are swapped; Step 4, the joint part (10) is placed on the connecting line of the two bottom angles of the isosceles triangle, and symmetrically arranged process countersunk holes (5) are set on the process overlap (3) along the symmetry axis, and hexagon socket screws (6) are used to lock and install, so as to complete the multi-point symmetrical installation of the joint part (10) at one station; Step 5, after removing the joint part (10) by disassembling the three process joints (3), use the symmetry axis of the isosceles triangle as the flipping axis, flip the part (10) and the process joint (3) at the same time, and repeat steps 2 to 4. After flipping, the locking point at the top angle of the isosceles triangle remains in the original position, and the positions of the positioning points and locking points at the two bottom angles of the isosceles triangle are mirror-swapped; use the positioning pin (7) to cooperate with the positioning installation, and use the hexagon socket screw (6) to cooperate with the locking installation, so as to complete the multi-point symmetrical installation of the joint part (10) at another workstation.

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