Machining method for butt joint threads on structural part
By setting marks on the aircraft cabin parts and confirming the deflection angle of the thread starting point, the problems of low efficiency and poor interchangeability of thread and surface feature processing methods in the prior art are solved, and more efficient production and better part interchangeability are achieved.
Patent Information
- Application Number
- CN202510516052.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-23
- Publication Date
- 2025-06-13
AI Technical Summary
In the prior art, there are problems such as many steps, large resource occupancy, low production efficiency, and poor interchangeability of cabin parts.
By setting marks on the parts of the structural part, the surface feature preset position is indicated, and the preset deflection angle of the thread starting point is confirmed on the mating length of the thread structure, ensuring that the thread and the surface feature have a fixed position relationship.
It improves the interchangeability of cabin parts during assembly, reduces production steps and resource occupation, significantly shortens the production cycle and improves production efficiency.
Smart Images
Figure CN120133618A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the field of machining, and particularly to a method for machining butt threads on a structural member. Background Art
[0002] At present, the main structure of some aircraft includes multiple cabin section parts, and adjacent cabin section parts are usually butted and assembled by means of thread fitting.
[0003] Each cabin section part has its own surface features. For example, bosses, grooves, etc. The aircraft has high requirements for the positions of the surface features after the cabin sections are assembled. After assembly, it is necessary to ensure the unity of the shape and the position reference of the surface features on the shape of each cabin section part and the consistency of quality. Therefore, in the existing machining methods, it includes multiple steps such as machining the main shape and butt threads of each cabin section part, after the cabin section parts are thread-connected, marking lines to confirm the installation positions of the surface features, then disassembling the cabin section parts, and machining the surface features of each cabin section part according to the marked lines. The steps, processes, and production resource occupancy of this machining method are relatively high, and the overall production efficiency is low.
[0004] In addition, in the above machining method, although the butt threads of each cabin section part meet the dimensional requirements, since the thread machining step is prior, the initial screwing-in butt starting positions of the butt threads on different cabin section parts are not fixed, so that there is no unified and fixed relative position relationship between the threads and the surface features on the part shape, and effective interchangeability cannot be achieved. When a quality problem occurs in a certain cabin section part, the entire aircraft structural member cannot be assembled, and it is difficult to remedy and replace by re-machining a single cabin section part, resulting in a relatively high cost loss. Summary of the Invention
[0005] In view of this, the present invention provides a method for machining butt threads on a structural member to solve the problems in the prior art that the machining methods for the threads and surface features on the cabin section parts of some aircraft have relatively high steps, processes, production resource occupancy, low overall production efficiency, and poor interchangeability of cabin section parts.
[0006] The present invention provides a method for machining butt joints on a structural member. The structural member includes a first part and a second part. The first part includes a first outer peripheral surface and a first end. A first surface feature preset position is provided on the first outer peripheral surface. The second part includes a second outer peripheral surface and a second end. A second surface feature preset position is provided on the second outer peripheral surface. The method includes: setting a first mark on the first outer peripheral surface, the first mark being adapted to indicate the first surface feature preset position; setting a second mark on the second outer peripheral surface, the second mark being adapted to indicate the second surface feature preset position; machining and setting a first butt joint thread on the first end so that the thread starting point of the first butt joint thread is aligned with the first mark in the circumferential direction, and the pitch of the first butt joint thread is p; machining and setting a second butt joint thread on the second end, the second butt joint thread being in screw fit with the first butt joint thread along the butt joint rotation direction and having the same pitch, and the axial mating length of the two being h. The thread starting point of the second butt joint thread is spaced apart from the second mark by a preset deflection angle in the direction of the butt joint rotation direction in the circumferential direction. The preset deflection angle is A, and A = 360°×(h / p–[h / p]), where [] is the rounding operator.
[0007] Beneficial effects
[0008] By setting the first mark and the second mark to respectively indicate the first surface feature preset position and the second surface feature preset position on the first part and the second part, and on the basis of the first mark and the second mark, combining the mating length of the two thread structures to confirm the preset deflection angle between the thread starting points of different thread structures along the butt joint rotation direction. With such a setting, on the one hand, the respective surface feature structures on the first part and the second part can be used as the positioning basis, and then the thread structures can be aligned and set, so that the thread structures and the surface features have a fixed positional relationship. When subsequent part replacement is required, the machining position required for the thread structure can be confirmed according to the surface features, improving the interchangeability of the cabin section parts during the assembly process, avoiding the influence of the quality defects of a certain cabin section part on the assembly of the overall structural member, and improving the production efficiency. On the other hand, by setting the surface feature preset positions, the installation positions of the surface features can be pre-marked, and the surface features can be machined before, during, and after the machining of the thread structures according to needs, improving the freedom of the machining steps. In addition, such a setting reduces processes such as disassembling the cabin section parts compared with the prior art, significantly shortening the production cycle and improving the production efficiency.
[0009] In an alternative embodiment, the first end portion is provided as a convex shaft end, the first docking thread is provided on the outer peripheral side of the convex shaft end, and the axial distance between the shaft shoulder between the convex shaft end and the first outer peripheral surface and the end of the convex shaft end away from the first outer peripheral surface is the axial mating length h; the second docking thread is provided on the inner side wall of the second end portion, and the second docking thread and the first docking thread are adapted to be mated along the docking rotation direction until the second end portion abuts against the shaft shoulder.
[0010] In an alternative embodiment, when the second docking thread and the first docking thread are screwed together along a preset torque to the limit position, the second end portion abuts against the shaft shoulder.
[0011] In an alternative embodiment, when machining the first docking thread, a milling method or a numerically controlled lathe with a spindle circumferential orientation function is used.
[0012] In an alternative embodiment, when machining the second docking thread, a milling method or a numerically controlled lathe with a spindle circumferential orientation function is used.
[0013] Advantageous Effects
[0014] Using a numerically controlled machine tool to replace the previous lathe for thread machining does not depend on the personal skills of the operator and is more conducive to ensuring the consistency of the reference.
[0015] In an alternative embodiment, the processing method is applicable to aircraft structural parts, and the first part and the second part are cabin parts of the aircraft. Description of the Drawings
[0016] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following will briefly introduce the drawings required for use in the description of the specific embodiments or the prior art. Obviously, the following drawings are some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.
[0017] Figure 1 It is a schematic structural diagram of the first part and the second part of the structural part in the embodiment of the present invention;
[0018] Figure 2 is Figure 1 a schematic structural diagram of the first part shown;
[0019] Figure 3 is Figure 2 a left view structural diagram of the first part in ;
[0020] Figure 4 isFigure 1 Schematic structural diagram of the second part shown with a partial section view;
[0021] Figure 5 For Figure 4 right view structural diagram of the second part in
[0022] Figure 6 Schematic flow diagram of the processing method in the prior art.
[0023] Explanation of reference numerals in the drawings:
[0024] 1. First part; 11. First outer peripheral surface; 12. First end; 13. First preset position of surface features; 14. First docking thread; 15. Shoulder; 2. Second part; 21. Second outer peripheral surface; 22. Second end; 23. Second preset position of surface features; 24. Second docking thread; 3. First mark; 4. Second mark. Detailed implementation manners
[0025] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Apparently, the described embodiments are some, but not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.
[0026] Currently, the main structure of some aircraft includes multiple cabin section parts. Adjacent cabin section parts are usually assembled by means of threaded cooperation. Generally, the internal thread and external thread docking method, or the internal thread, connection ring, and internal thread docking method are used at the connection position during assembly.
[0027] Each cabin section part has its own surface features. For example, bosses, grooves, etc. The aircraft has high requirements for the position of the surface features after the cabin sections are assembled. After assembly, it is necessary to ensure the unity of the shape and the position reference of the surface features on the shape of each cabin section part and the consistency of quality. Therefore, in the existing processing method, it includes: processing the main shape and docking threads of each cabin section part, after the cabin section parts are thread-connected, marking lines to confirm the installation position of the surface features, then disassembling the cabin section parts, and processing the surface features of each cabin section part according to the marked lines. As Figure 6 shown, the steps, processes, and production resource occupation amount of this processing method are relatively high, and the overall production efficiency is low.
[0028] In addition, in the above processing method, although the butt threads of each cabin section part meet the dimensional requirements, since the thread processing step is prior, the initial screwing-in starting positions of the butt threads on different cabin section parts are not fixed. As a result, the surface features on the thread and the part shape lack a unified and fixed relative position relationship, and effective interchangeability cannot be achieved. When a quality problem occurs in a certain cabin section part, the structural parts of the entire aircraft cannot be assembled, and it is difficult to remedy and replace by reprocessing a single cabin section part, resulting in a relatively high cost loss.
[0029] The following combines Figures 1 to 5 to describe the embodiments of the present invention.
[0030] The present invention provides a method for processing butt threads on a structural member, where the structural member includes a first part 1 and a second part 2. The first part 1 includes a first outer peripheral surface 11 and a first end 12, and a first surface feature preset position 13 is provided on the first outer peripheral surface 11. The second part 2 includes a second outer peripheral surface 21 and a second end 22, and a second surface feature preset position 23 is provided on the second outer peripheral surface 21. After the butt threads of the first part 1 and the second part 2 are processed, the first end 12 and the second end 22 thereon can be threadedly connected along the butt screw thread in the axial mating length. Specifically, the specific structures of the first part 1 and the second part 2 are correspondingly set according to the needs of the structural member. Preferably, at least the parts of the first end 12 and the second end 22 corresponding to the first butt thread 14 and the second butt thread 24 are cylindrical parts or cylindrical tube parts.
[0031] The method for processing butt threads on a structural member includes:
[0032] A first mark 3 is set on the first outer peripheral surface 11, and the first mark 3 is adapted to indicate the first surface feature preset position 13. A second mark 4 is set on the second outer peripheral surface 21, and the second mark 4 is adapted to indicate the second surface feature preset position 23. In this embodiment, the first surface feature preset position 13 is the preset position for installing surface features on the first part 1. The surface features include bosses, grooves, etc., and can be set to be single, two or more. The first mark 3 only needs to indicate a selected single one according to needs. The surface features are correspondingly set according to the needs of the first part 1. The surface features on the first surface feature preset position 13 can be selectively set before, during or after the processing of the first butt thread 14. In addition, the way the first mark 3 indicates the first surface feature preset position 13 can be to set it on the first surface feature preset position 13, at a fixed preset distance from the first surface feature preset position 13 along a fixed preset direction, etc., as long as it meets the marking needs and avoids misalignment. Its marking form is set according to needs and can be a scoring line, punctuation, fluorescent marking, etc. The second mark 4 and the second surface feature preset position 23 are the same by analogy.
[0033] The first docking thread 14 is machined on the first end portion 12 so that the starting point of the thread of the first docking thread 14 is aligned with the first mark 3 in the circumferential direction. The pitch of the first docking thread 14 is p. In this embodiment, the pitches of the first docking thread 14 and the second docking thread 24 are equal.
[0034] The second docking thread 24 is machined on the second end portion 22. The second docking thread 24 is in threaded engagement with the first docking thread 14 along the docking thread rotation direction. The axial engagement length of the two is h. The starting point of the thread of the second docking thread 24 is spaced apart from the second mark 4 by a preset deflection angle in the circumferential direction along the docking thread rotation direction. The preset deflection angle is A, and A = 360°×(h / p – [h / p]), where [] is the rounding operator. Specifically, the operation result of [h / p] is the integer part of the quotient obtained by dividing h by p, that is, the largest integer not greater than the quotient.
[0035] By setting the first mark 3 and the second mark 4 to respectively indicate the preset positions 13 of the first surface features and the preset positions 23 of the second surface features on the first part 1 and the second part 2, and on the basis of the first mark 3 and the second mark 4, the preset deflection angle between the starting points of the threads of different thread structures along the docking thread rotation direction is confirmed in combination with the engagement length of the two thread structures. With such a setting, on the one hand, the respective surface feature structures on the first part 1 and the second part 2 can be used as the positioning basis, and then the thread structures are aligned and set, so that the thread structures and the surface features have a fixed positional relationship. When subsequent part replacement is required, the machining position required for the thread structure can be confirmed according to the surface features, improving the interchangeability of the cabin section parts during the assembly process, avoiding the influence of the quality defects of a certain cabin section part on the assembly of the overall structural parts, and improving the production efficiency. On the other hand, by setting the preset positions of the surface features, the installation positions of the surface features can be pre-marked, and the surface features can be machined before, during, and after the machining of the thread structure as required, improving the freedom of the machining steps. In addition, such a setting reduces the processes such as disassembling the cabin section parts compared with the prior art, significantly shortening the production cycle and improving the production efficiency.
[0036] In addition, in this embodiment, the first docking thread 14 is an external thread, and the second docking thread 24 is an internal thread. As a changeable implementation manner, the first docking thread 14 can be an internal thread, and the second docking thread 24 can be an external thread.
[0037] Specifically, in this embodiment, the first end portion 12 includes a convex shaft end. A first docking thread 14 is provided on the outer peripheral side of the convex shaft end. There is a shaft shoulder 15 between the convex shaft end and the first outer peripheral surface 11. The axial distance between the end of the convex shaft end away from the first outer peripheral surface 11 and the other is the axial mating length h. Preferably, both are perpendicular to the axial direction of the first docking thread 14 and the second docking thread 24. As a variant embodiment, the axial distance between the two can also be greater than the axial mating length h. A second docking thread 24 is provided on the inner side wall of the second end portion 22. The second docking thread 24 and the first docking thread 14 are adapted to be screwed together along the docking rotation direction until the second end portion 22 abuts against the shaft shoulder 15.
[0038] With such a setting, when the first part 1 and the second part 2 abut at the end, it can be confirmed that the second docking thread 24 and the first docking thread 14 have reached the axial mating length h, meeting the positioning requirement, which is simple and easy to implement.
[0039] Furthermore, when the second docking thread 24 and the first docking thread 14 are screwed together along a preset torque to the limit position, the second end portion 22 abuts against the shaft shoulder 15. With such a setting, when the second docking thread 24 and the first docking thread 14 are screwed together to the axial mating length h, it is screwed to the limit position along the preset torque. Furthermore, the mating stroke of the second docking thread 24 and the first docking thread 14, that is, the axial mating length h, is accurately positioned through both abutting limit and thread friction limit, avoiding problems such as deviation or dislocation.
[0040] In addition, when selecting a thread processing device, preferably, the thread milling processing method is adopted. This device and milling method can conveniently determine the position of the thread starting point.
[0041] As a variant embodiment, the turning processing method can also be adopted. When the turning processing method is adopted, a numerically controlled lathe with a spindle circumferential orientation function can be used. By adjusting the position of the thread starting point through the encoder of the numerically controlled machine tool, the above method can be realized.
[0042] Specifically, when processing the first docking thread 14, a milling method or a numerically controlled lathe with a spindle circumferential orientation function can be adopted. Similarly, when processing the second docking thread 24, a milling method or a numerically controlled lathe with a spindle circumferential orientation function can also be adopted. The processing methods of the first docking thread 14 and the second docking thread 24 are preferably of the same processing type. As a variant embodiment, different processing types can also be selected.
[0043] Using a numerically controlled machine tool to replace the previous lathe for processing threads does not depend on the personal skills of the operator and is more conducive to ensuring the consistency of the reference.
[0044] In this embodiment, the above processing method is applicable to aircraft structural components, such as missile body structural components that are assembled to form a missile body, etc. The first part 1 and the second part 2 are specifically cabin section parts of the aircraft.
[0045] Although the embodiments of the present invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the present invention, and such modifications and variations fall within the scope defined by the appended claims.
Claims
1. A method for processing a butt-jointed thread on a structural component, the structural component comprising a first part (1) and a second part (2), the first part (1) comprising a first outer peripheral surface (11) and a first end (12), a first surface feature preset position (13) being provided on the first outer peripheral surface (11), the second part (2) comprising a second outer peripheral surface (21) and a second end (22), a second surface feature preset position (23) being provided on the second outer peripheral surface (21), characterized in that: The method comprises: A first mark (3) is arranged on the first peripheral surface (11), the first mark (3) is suitable for indicating the preset position (13) of the first surface feature, and a second mark (4) is arranged on the second peripheral surface (21), the second mark (4) is suitable for indicating the preset position (23) of the second surface feature; A first butt thread (14) is machined on the first end (12) so that a thread starting point of the first butt thread (14) is aligned with the first mark (3) in the circumferential direction, and a pitch of the first butt thread (14) is p; A second butt-joint thread (24) is machined and arranged on the second end portion (22), the second butt-joint thread (24) and the first butt-joint thread (14) are thread-matched along the butt-joint rotation direction and have equal pitches, the axial matching length of the two is h, the thread starting point of the second butt-joint thread (24) and the second mark (4) are spaced apart by a preset deflection angle in the circumferential direction along the butt-joint rotation direction, the preset deflection angle is A, A=360°×(h / p–[h / p]), wherein [] is a rounding operator.
2. The processing method according to claim 1, characterized in that: The first end portion (12) is arranged as a convex shaft end, the outer peripheral side of the convex shaft end is provided with the first docking thread (14), the axial shoulder (15) between the convex shaft end and the first outer peripheral surface (11), and the end of the convex shaft end away from the first outer peripheral surface (11), the axial distance between the two is the axial matching length h; The second butt joint thread (24) is provided on the inner side wall of the second end portion (22), and the second butt joint thread (24) and the first butt joint thread (14) are adapted to be matched along the butt joint rotation direction until the second end portion (22) abuts against the shaft shoulder (15).
3. The processing method according to claim 2, characterized in that: When the second butt-jointed thread (24) and the first butt-jointed thread (14) are screwed to an extreme position along a preset torque, the second end portion (22) abuts against the shaft shoulder (15).
4. The processing method according to any one of claims 1 to 3, characterized in that: When processing the first butting thread (14), a milling method or a CNC lathe with a spindle circumference orientation function is adopted.
5. The processing method according to any one of claims 1 to 3, characterized in that: When processing the second butt thread (24), a milling method or a CNC lathe with a spindle circumference orientation function is adopted.
6. The processing method according to any one of claims 1 to 3, characterized in that: The processing method is applicable to aircraft structural parts, and the first part (1) and the second part (2) are cabin parts of the aircraft.