CN210188619U - Acute angle machining tool for aircraft structural part - Google Patents
Acute angle machining tool for aircraft structural part Download PDFInfo
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- CN210188619U CN210188619U CN201920970960.9U CN201920970960U CN210188619U CN 210188619 U CN210188619 U CN 210188619U CN 201920970960 U CN201920970960 U CN 201920970960U CN 210188619 U CN210188619 U CN 210188619U
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Abstract
The utility model provides an aircraft structure acute angle processing cutter, the technical problem that the aircraft structure machining efficiency of purpose solution acute angle structure is low. The adopted technical scheme is as follows: an acute angle machining tool for an aircraft structural part comprises a shaft lever and an installation table, wherein a connecting lug is arranged at the bottom end of the shaft lever; the mounting table is fixed on the shaft rod, and the bottom of the mounting table is provided with a groove for accommodating the connecting lug and a threaded hole matched with the connecting lug; the mounting table is formed by coaxially and fixedly connecting annular pieces, the annular pieces are provided with a plurality of types with different outer diameters, and the outer diameters are linearly increased from top to bottom; the circumferential surface of the annular piece is uniformly provided with a plurality of mounting grooves communicated with the upper surface and the lower surface of the annular piece; and a milling element is fixed in the mounting groove, and a milling edge of the milling element extends out of the mounting groove and extends obliquely upwards along the side surface of the mounting table. The utility model discloses can process the aircraft structure of acute angle structure fast effectively.
Description
Technical Field
The utility model relates to a machining cutter of aviation spare part, concretely relates to aircraft structure acute angle processing cutter.
Background
Aircraft structural members are important components of aircraft, and in the aircraft manufacturing industry, machining of aircraft structural members is frequently involved. In aircraft structural members, acute angle structures consisting of double edges, one edge and one plate, or double plates are often present. The processing of the airplane structural member with the acute angle structure is very inconvenient; the traditional method is to process the edges or plates of the aircraft structural member by adopting a cylindrical flat-bottom milling cutter or a cylindrical ball-end milling cutter, and then continuously reduce the diameter of the cutter to reduce the processing residues of the included angles at the joints of the edges or plates. The method is very complicated, needs a plurality of cutters to feed repeatedly, and has large workload and low processing efficiency. In view of this, the utility model provides an aircraft structure acute angle processing cutter can process the aircraft structure of acute angle structure fast effectively.
Disclosure of Invention
An object of the utility model is to provide an aircraft structure acute angle processing cutter realizes effectively processing fast of the aircraft structure of acute angle structure.
In order to achieve the above object, the utility model adopts the following technical scheme:
the acute angle processing cutter for the aircraft structural part comprises a shaft rod, wherein a connecting lug is arranged at the bottom end of the shaft rod;
the mounting table is fixed on the shaft rod, and the bottom of the mounting table is provided with a groove for accommodating the connecting lug and a threaded hole matched with the connecting lug;
the annular piece is provided with a plurality of types with different outer diameters, the annular piece is coaxially and fixedly connected to form a mounting table, and the outer diameters of the annular piece increase progressively in a linear mode from top to bottom;
the mounting grooves are uniformly distributed on the peripheral side of the annular piece and communicated with the upper surface and the lower surface of the annular piece;
the milling element is fixed in the mounting groove, a milling edge of the milling element extends out of the mounting groove, and the milling edge of the milling element extends obliquely upwards along the side surface of the mounting table.
Preferably, the milling element is strip-shaped or sheet-shaped, and two long sides of the milling element respectively form a milling edge of the milling element to realize twice use of the milling element; the milling element is provided with a first strip-shaped hole extending along the length direction of the milling element, the mounting groove is provided with a threaded hole matched with the first strip-shaped hole, and the milling element is fixed in the mounting groove through a bolt.
Preferably, the mounting groove is in an open shape with a narrow inner part and a wide outer part, the milling element is fixed on one surface of the mounting groove facing to the rotating direction, and the rest space in the mounting groove where the milling element is not arranged constitutes a waste material channel.
Preferably, the bottom of the milling element is provided with an angle milling piece, and a milling edge of the angle milling piece is flush with a milling edge of the milling element; the angle milling piece is provided with a second strip-shaped hole and is fixedly connected with the milling element and the mounting groove through bolts.
Preferably, the angle milling piece is of an acute-angle isosceles triangle structure, and two waist edges of the angle milling piece respectively form a milling edge of the angle milling piece to realize twice use of the angle milling piece.
Preferably, the top of the ring-shaped member is provided with a plurality of embedded through holes and threaded holes, and the embedded through holes of the ring-shaped member are correspondingly matched with the threaded holes at the top of the adjacent ring-shaped member below the ring-shaped member.
Preferably, the shaft rod is provided with a limiting edge extending along the length direction of the shaft rod, and the inner annular wall of the annular member is provided with a limiting groove matched with the limiting edge.
The beneficial effects of the utility model are concentrated, the utility model is provided with the mounting platform consisting of a plurality of ring-shaped pieces, the outer diameters of the ring-shaped pieces are linearly increased from top to bottom, thereby the mounting groove communicated with the ring-shaped pieces is extended upwards in an inclined way, and the milling edges of the milling elements fixed in the mounting groove are also extended upwards in an inclined way; when the spindle rod drives the mounting table to rotate, the milling edges of the milling elements form a circular truncated cone-shaped milling track, and the included angle between the side surface and the bottom surface of the circular truncated cone is the same as the included angle of the aircraft structural member, so that the side edges or the side plates of the aircraft structural member are milled; in the machining process, a cutter does not need to be replaced, repeated feed is also not needed, milling machining of the lateral edge or the side plate of the aircraft structural part can be completed through one-time feed, and machining efficiency is greatly improved. In addition, the diameter difference of the annular parts can be changed by selecting the annular parts with different outer diameters, so that the inclination angle of the milling element is changed, the milling track formed by milling edges of the milling element is changed, and the angle between the side surface and the bottom surface of the circular truncated cone-shaped milling track is changed; therefore, the utility model discloses just can be applicable to the aircraft structure of different angles, application scope is wider, and the commonality is stronger.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings needed to be used in the embodiments or technical descriptions will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present application, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a front view of the present invention;
FIG. 2 is a schematic view of the construction of the shaft;
FIG. 3 is a schematic view of the structure of the annular member;
FIG. 4 is a bottom view of the ring;
FIG. 5 is a schematic view of a milling element;
FIG. 6 is a schematic structural view of a corner milling member;
reference numerals: 1. a shaft lever; 2. connecting lugs; 3. an installation table; 4. a groove; 5 an annular member; 6. mounting grooves; 7. a milling element; 8. a first bar-shaped hole; 9. milling an angle part; 10. a second bar-shaped hole; 11. an embedded via; 12. a limiting edge; 13. a limiting groove.
Detailed Description
In the following, only certain exemplary embodiments are briefly described. As those skilled in the art will recognize, the described embodiments may be modified in various different ways, all without departing from the spirit or scope of the present invention. Accordingly, the drawings and description are to be regarded as illustrative in nature, and not as restrictive.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", and the like, indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically limited otherwise.
Embodiments of the present invention will be described in detail below with reference to fig. 1 to 6.
The embodiment of the utility model provides an aircraft structure acute angle processing cutter, this processing cutter includes: axostylus axostyle 1, the bottom of axostylus axostyle 1 sets up engaging lug 2. It should be understood that the mounting table 3 is fixed to the shaft rod 1, and then the top end of the shaft rod 1 is coaxially fixed to the driving shaft.
The mounting table 3 is fixed on the shaft rod 1, a groove 4 for accommodating the connecting lug 2 is formed in the bottom of the mounting table 3, and a threaded hole matched with the connecting lug 2 is formed in the bottom of the mounting table 3; it should be understood that the mounting table 3 is fixed to the shaft rod 1 by placing the mounting table 3 into the top end of the shaft rod 1 and screwing the bolts into the engaging lugs 2 of the shaft rod 1 to fix the engaging lugs 2 in the grooves 4 at the bottom of the mounting table 3, and the heads of the bolts are located in the grooves 4 and do not extend out of the bottom surface of the mounting table 3.
The annular part 5 is provided with a plurality of types with different outer diameters, the annular part 5 is coaxially and fixedly connected to form the mounting table 3, and the outer diameters of the annular part 5 increase linearly from top to bottom.
And the mounting grooves 6 are uniformly distributed on the peripheral side of the annular piece 5 and communicated with the upper surface and the lower surface of the annular piece 5.
And the milling element 7 is fixed in the mounting groove 6, and a milling edge of the milling element 7 extends out of the mounting groove 6, and the milling edge of the milling element 7 extends obliquely upwards along the side surface of the mounting table 3. It will be appreciated that when the spindle 1 is rotated, the milling edges of the milling elements 7 will form a frustoconical milling path.
The embodiment of the utility model is explained below, the utility model is provided with the mounting table 3 composed of a plurality of ring-shaped pieces 5, the outer diameters of the ring-shaped pieces 5 are increased linearly from top to bottom, thereby the mounting groove 6 communicated with the plurality of ring-shaped pieces 5 is extended obliquely upwards, and the milling edges of the milling elements 7 fixed in the mounting groove 6 are also extended obliquely upwards; when the shaft lever 1 drives the mounting table 3 to rotate, the milling edges of the milling elements 7 form a circular truncated cone-shaped milling track, and the included angle between the side surface and the bottom surface of the circular truncated cone is the same as the included angle of the aircraft structural part, so that the side edges or the side plates of the aircraft structural part are milled; in the machining process, a cutter does not need to be replaced, repeated feed is also not needed, milling machining of the lateral edge or the side plate of the aircraft structural part can be completed through one-time feed, and machining efficiency is greatly improved. In addition, the diameter difference of the annular parts 5 can be changed by selecting the annular parts 5 with different outer diameters, so that the inclination angle of the milling element 7 is changed, the milling track formed by milling edges of the milling element 7 is changed, and the angle between the side surface and the bottom surface of the circular truncated cone-shaped milling track is changed; therefore, the utility model discloses just can be applicable to the aircraft structure of different angles, application scope is wider, and the commonality is stronger.
As a further optimization of the present invention, the milling element 7 is strip-shaped or sheet-shaped, and two long sides of the milling element 7 respectively form a milling edge thereof, thereby realizing twice use of the milling element 7; it should be understood that both the long sides of the milling element 7 can be used as milling edges, which can improve the utilization of the milling element 7 and reduce the equipment cost. Milling component 7 sets up the first bar hole 8 that extends along its length direction, mounting groove 6 sets up the screw hole with first bar hole 8 adaptation, milling component 7 passes through the bolt fastening in mounting groove 6. It will be appreciated that the milling element 7 is mounted in such a way that the upper edge of the first bar-shaped hole 8 abuts against the uppermost bolt flank, while the lower edge of the first bar-shaped hole 8, depending on the angle of inclination of the milling element 7, may be spaced from the lowermost bolt flank, which results in a more secure mounting of the milling element 7. This is because, during the milling process, the side surface of the aircraft structural member will generate an oblique downward force on the milling element 7, so that the milling element 7 tends to move downward, and the upper edge of the first strip-shaped hole 8 abuts against the side surface of the uppermost bolt, so that the milling element 7 can be effectively prevented from sliding downward.
Furthermore, the mounting groove 6 is open with a narrow inside and a wide outside, the milling element 7 is fixed on one surface of the mounting groove 6 facing the rotation direction, and the rest space in the mounting groove 6 where the milling element 7 is not arranged constitutes a waste material channel. It will be appreciated that when the spindle 1 rotates the ring 5, the waste channel is located in front of the milling element 7, so as to facilitate the discharge of the waste chips generated by milling, and to prevent the waste chips from accumulating between the milling element 7 and the milled surface of the aircraft structure, thereby protecting the milled surface of the aircraft structure and the milling element 7.
Furthermore, a corner milling piece 9 is arranged at the bottom of the milling element 7, and the milling edge of the corner milling piece 9 is flush with the milling edge of the milling element 7; the angle milling piece 9 is provided with a second strip-shaped hole 10 and is fixedly connected with the milling element 7 and the mounting groove 6 through bolts. It will be appreciated that when milling aircraft structural members of different included angles, it is necessary to vary the angle of inclination of the milling element 7, which results in a variation in the height of the bottom end of the milling element 7; if the height of the bottom end of the milling element 7 is too high, a large amount of milling residues will be generated at the bottom of the side wall of the aircraft structure, and if the height is too low, excessive milling will be caused. To avoid this, the length of the milling element 7 can be set conservatively, so that the bottom end of the milling element 7 does not extend sufficiently to the bottom of the mounting table 3; at the same time, a corner milling piece 9 is additionally arranged at the bottom of the milling element 7. When the inclination angle of the milling element 7 is changed, the corner milling piece 9 is rotated to enable the milling edge of the corner milling piece 9 to be flush with the milling edge of the milling element 7, the corner milling piece 9 is moved along the length direction of the milling element 7 to enable the height of the bottom end of the corner milling piece 9 to be constant, and finally the corner milling piece 9 is fixed in the mounting groove 6. Therefore, when milling the aircraft structural parts with different included angles, the milling angle part 9 can be flexibly adjusted, and the bottom of the side wall of the aircraft structural part can be fully and properly milled.
Further, the angle milling piece 9 is in an acute angle isosceles triangle structure, and two waist edges of the angle milling piece 9 respectively form a milling edge thereof to realize twice use of the angle milling piece 9. It should be understood that the angle of the top angle of the milling corner piece 9 is preferably 30 to 60 degrees, and both waist edges of the milling corner piece 9 can be used as milling edges, so that the utilization rate of the milling corner piece 9 can be improved, and the equipment cost can be reduced.
Furthermore, the top of the ring-shaped member 5 is provided with a plurality of embedded through holes 11 and threaded holes, and the embedded through holes 11 of the ring-shaped member 5 are correspondingly matched with the threaded holes at the top of the adjacent ring-shaped member 5 below the ring-shaped member. It should be understood that the two adjacent ring members 5 can be fixedly connected together by aligning the insertion through holes 11 of the ring members 5 with the screw holes at the tops of the ring members 5 adjacent below the insertion through holes and screwing bolts, and after screwing the bolts into the insertion through holes 11, the heads of the bolts are inserted into the ring members 5 and do not extend out of the tops of the ring members 5.
Further, the shaft rod 1 is provided with a limiting edge 12 extending along the length direction of the shaft rod, and the inner annular wall of the annular member 5 is provided with a limiting groove 13 matched with the limiting edge 12. It should be understood that the limiting rib 12 and the limiting groove 13 cooperate to limit the ring-shaped member 5, so as to prevent the ring-shaped member 5 from rotating relative to the shaft rod 1; simultaneously, can transmit 3 power that transmit for axostylus axostyle 1 of mount table to whole axostylus axostyle 1, rather than concentrating on the bottom of axostylus axostyle 1 to play the guard action to axostylus axostyle 1, avoid axostylus axostyle 1 to take place to warp.
Although specific embodiments of the present invention have been described above, it will be appreciated by those skilled in the art that changes and modifications may be made to these embodiments without departing from the principles and spirit of the invention, and these changes and modifications are intended to fall within the scope of the invention.
Claims (7)
1. The utility model provides an aircraft structure acute angle processing cutter which characterized in that: the connecting rod comprises a shaft rod (1), wherein a connecting lug (2) is arranged at the bottom end of the shaft rod (1);
the mounting table (3) is fixed on the shaft lever (1), a groove (4) for accommodating the connecting lug (2) is formed in the bottom of the mounting table (3), and a threaded hole matched with the connecting lug (2) is formed in the bottom of the mounting table (3);
the annular parts (5) are provided with a plurality of types with different outer diameters, the annular parts (5) are coaxially and fixedly connected to form the mounting table (3), and the outer diameters of the annular parts (5) increase progressively in a linear mode from top to bottom;
the mounting grooves (6) are uniformly distributed on the peripheral side of the annular piece (5) and communicated with the upper surface and the lower surface of the annular piece (5);
the milling element (7) is fixed in the mounting groove (6) and the milling edge of the milling element (7) extends out of the mounting groove (6), and the milling edge of the milling element (7) extends obliquely upwards along the side surface of the mounting table (3).
2. The acute angle machining tool for the aircraft structural part as claimed in claim 1, wherein: the milling element (7) is strip-shaped or sheet-shaped, and two long sides of the milling element (7) respectively form a milling edge of the milling element to realize twice use of the milling element (7); milling element (7) and setting up first bar hole (8) that extend along its length direction, mounting groove (6) set up the screw hole with first bar hole (8) adaptation, milling element (7) pass through the bolt fastening in mounting groove (6).
3. The acute angle machining tool for the aircraft structural part as claimed in claim 2, wherein: the mounting groove (6) is narrow inside and wide outside and is open, the milling element (7) is fixed on one surface of the mounting groove (6) facing to the rotating direction, and the residual space in the mounting groove (6) where the milling element (7) is not arranged constitutes a waste material channel.
4. The acute angle machining tool for the aircraft structural part as claimed in claim 3, wherein: the bottom of the milling element (7) is provided with an angle milling piece (9), and the milling edge of the angle milling piece (9) is flush with the milling edge of the milling element (7); the angle milling piece (9) is provided with a second strip-shaped hole (10) and is fixedly connected with the milling element (7) and the mounting groove (6) through bolts.
5. The acute angle machining tool for the aircraft structural part as claimed in claim 4, wherein: the angle milling piece (9) is of an acute-angle isosceles triangle structure, and two waist edges of the angle milling piece (9) respectively form milling edges of the angle milling piece and are used twice for milling the angle milling piece (9).
6. The acute angle machining tool for the aircraft structural part as claimed in claim 5, wherein: the top of the ring-shaped piece (5) is provided with a plurality of embedded through holes (11) and threaded holes, and the embedded through holes (11) of the ring-shaped piece (5) are correspondingly matched with the threaded holes in the top of the adjacent ring-shaped piece (5) below the ring-shaped piece.
7. The acute angle machining tool for the aircraft structural part as claimed in claim 6, wherein: the shaft lever (1) is provided with a limiting edge (12) extending along the length direction of the shaft lever, and the inner annular wall of the annular piece (5) is provided with a limiting groove (13) matched with the limiting edge (12).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920970960.9U CN210188619U (en) | 2019-06-26 | 2019-06-26 | Acute angle machining tool for aircraft structural part |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920970960.9U CN210188619U (en) | 2019-06-26 | 2019-06-26 | Acute angle machining tool for aircraft structural part |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210188619U true CN210188619U (en) | 2020-03-27 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920970960.9U Active CN210188619U (en) | 2019-06-26 | 2019-06-26 | Acute angle machining tool for aircraft structural part |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210188619U (en) |
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2019
- 2019-06-26 CN CN201920970960.9U patent/CN210188619U/en active Active
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Address after: No.18, Xingong Avenue, Xindu Industrial Zone, Chengdu, Sichuan 610000 Patentee after: Chengdu Yuyuan aviation Intelligent Manufacturing Co.,Ltd. Address before: No.18, Xingong Avenue, Xindu Industrial Zone, Chengdu, Sichuan 610500 Patentee before: CHENGDU YUYUAN AVIATION COMPONENT MANUFACTURING Co.,Ltd. |