CN217492806U

CN217492806U - Aviation dimple drill

Info

Publication number: CN217492806U
Application number: CN202221274551.3U
Authority: CN
Inventors: 高泉飞
Original assignee: Suzhou Ahno Precision Cutting Technology Co ltd
Current assignee: Suzhou Ahno Precision Cutting Technology Co ltd
Priority date: 2022-05-25
Filing date: 2022-05-25
Publication date: 2022-09-27
Anticipated expiration: 2032-05-25

Abstract

The utility model relates to an aviation dimple drill, which comprises a cutter handle and a cutter body, wherein the cutter body comprises a first cutting edge part and a second cutting edge part which are arranged along the axial direction, and the diameter of the first cutting edge part is larger than that of the first cutting edge part; the first cutting edge part is also provided with a plurality of chamfering edges; the second cutting edge part is also provided with a plurality of drilling cutting edges; the first cutting edge part and the second cutting edge part are respectively provided with a first chip groove and a second chip groove. The utility model sets the diameter of the first cutting edge part to be larger than that of the second cutting edge part, and sets the chamfering blade on the first cutting edge part and the drilling blade on the second cutting edge part, thereby being capable of completing the chamfering process while drilling, effectively improving the working efficiency, occupying less tool magazine positions and reducing the processing cost; through setting up the first chip groove and the second chip groove that are linked together, can enough guarantee the chip removal performance, can promote the rigidity of drilling cutting edge again.

Description

Aviation dimple drill

Technical Field

The utility model relates to a drilling tool technical field especially relates to an aviation is with counter boring brill.

Background

The novel high-temperature curing epoxy resin aramid fiber composite material (aramid fiber for short) is more and more widely applied in the field of aviation due to excellent performances of high strength, high modulus, high temperature resistance, acid and alkali resistance, light specific weight, good toughness and the like. The aramid fiber composite material for the aircraft skin has complex structure performance and high processing difficulty. Most adopt the dimple to bore among the prior art and process on aramid fiber combined material, the processing step is shown in fig. 4, and it is 20 drilling bottom holes that the fluted drill was first, then uses chamfer milling cutter 30 to carry out rough machining to the chamfer, uses chamfer milling cutter 30 to carry out the finish machining to the chamfer at last. The steps not only occupy the tool magazine position, but also need tool changing in the machining process, so that the working efficiency is lower, and three different tools need to be used for machining in the machining process, so that the machining cost is higher.

SUMMERY OF THE UTILITY MODEL

Therefore, the aviation countersink drill is required to be provided with a process of chamfering while drilling, so that the working efficiency is effectively improved, less tool magazine is occupied, the machining cost can be reduced, and the chip removal performance is ensured.

An aviation countersink drill, comprising:

a knife handle;

the cutter body is coaxial with the cutter handle and is arranged at one end of the cutter handle; the cutter body comprises a first cutting edge part and a second cutting edge part which are arranged along the axial direction, and the diameter of the first cutting edge part is larger than that of the first cutting edge part; the first cutting edge part is also provided with a plurality of chamfering blades; the second cutting edge part is also provided with a plurality of drilling blades;

first chip groove, second chip groove have been seted up respectively on the first cutting edge portion the second cutting edge portion, first chip groove with the second chip groove is linked together, just first chip groove with the core of second chip groove is thick different.

In one embodiment, a drilling knife face is formed at one end of the drilling knife edge, which is far away from the knife handle, and at least two grooves are formed on the drilling knife face.

The at least two grooves are formed in the drilling knife face, so that the shape of the cutting scraps can be improved, the phenomenon that the cutting scraps are difficult to clean due to the fact that the cutting scraps are wound on the knife handle is effectively avoided, and the working efficiency is improved.

In one embodiment, at least two of the grooves are staggered in the extending direction of the grooves.

In one embodiment, the chamfer edge has a plurality of flank surfaces thereon.

Through set up a plurality of back knife faces on the chamfer cutting edge, can improve the rigidity of chamfer cutting edge, can effectively prevent to appear vibrations or the cutter body phenomenon of collapsing because of the chamfer cutting edge rigidity is not enough.

In one embodiment, a vibration reduction edge band is further arranged between the chamfer cutting edge and the second chip discharge groove.

Through setting up the damping margin, can play the vibration line phenomenon that reduces to produce when processing to can improve the effect of the chamfer department roughness on processing surface.

In one embodiment, the chamfer cutting edge has a rake face on which a correction cutting edge is provided.

In one embodiment, the axial rake angle of the correcting edge is 8-13 °.

In one embodiment, the drilling cutting edge, the chamfering cutting edge, the first chip groove and the second chip groove are all helical structures.

In one embodiment, the first flute in a spiral shape is formed between two adjacent chamfer edges.

In one embodiment, the second flutes in a spiral shape are formed between two adjacent drilling cutting edges.

In the scheme, the diameter of the first cutting edge part is larger than that of the second cutting edge part, the chamfering blade is arranged on the first cutting edge part, and the drilling blade is arranged on the second cutting edge part, so that the chamfering process can be completed while drilling, the working efficiency is effectively improved, the tool magazine is less in occupied space, and the processing cost can be reduced; through setting up the first chip groove and the second chip groove that are linked together, and the core of first chip groove and second chip groove is thick different, can guarantee that the drilling cutting edge can not be too narrow and influence the rigidity of drilling cutting edge, guarantees that the chamfer cutting edge can not be too wide and influence the chip removal performance, and control cutting flow direction to realize high efficiency cutting.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this application, are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification.

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly described below, and it is obvious that the drawings in the description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained without creative efforts.

Fig. 1 is a schematic structural view of an aviation countersink drill according to an embodiment of the present invention during operation;

fig. 2 is a schematic structural view of an aviation dimple drill according to an embodiment of the present invention;

fig. 3 is a bottom view of the aircraft countersink drill according to an embodiment of the present invention;

fig. 4 is the structural schematic diagram of the aviation countersink drill shown in the prior art in the utility model at the work.

Description of the reference numerals

10. Drilling a dimple for aviation; 100. a knife handle; 200. a cutter body; 210. a first cutting edge portion; 211. a chamfering blade; 2111. a flank face; 2112. a rake face; 2113. correcting the cutting edge; 212. a first chip discharge groove; 213. a vibration-damping margin; 220. a second cutting edge portion; 221. a drilling blade; 2211. drilling a cutter face; 2212. a groove; 222. a second chip groove; 300. a workpiece to be processed;

20. a twist drill; 30. provided is a chamfer milling cutter.

Detailed Description

In order to make the above objects, features and advantages of the present invention more comprehensible, embodiments of the present invention are described in detail below with reference to the accompanying drawings. In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. The present invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein, as those skilled in the art will be able to make similar modifications without departing from the spirit and scope of the present invention.

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 at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.

In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," and "fixed" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.

In the present application, unless expressly stated or limited otherwise, the first feature may be directly on or directly under the second feature or indirectly via intermediate members. Also, a first feature "on," "above," and "over" a second feature may be directly on or obliquely above the second feature, or simply mean that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.

It will be understood that when an element is referred to as being "secured to" or "disposed on" another element, it can be directly on the other element or intervening elements may also be present. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may also be present. The terms "vertical," "horizontal," "upper," "lower," "left," "right," and the like as used herein are for illustrative purposes only and do not denote a unique embodiment.

Referring to fig. 1 and 2, an embodiment of the present invention provides an aviation dimple drill 10, which includes a tool holder 100 and a tool body 200, wherein the tool body 200 is coaxial with the tool holder 100 and is disposed at one end of the tool holder 100. The cutter body 200 includes a first cutting edge portion 210 and a second cutting edge portion 220 arranged along the axial direction, and the second cutting edge portion 220 is arranged at one end of the first cutting edge portion 210 away from the cutter holder 100. First cutting edge portion 210, second cutting edge portion 220 and handle of a knife 100 are the integrated into one piece structure, can guarantee the joint strength of first cutting edge portion 210, second cutting edge portion 220 and handle of a knife 100, and is not fragile in the use, and when cutter body 200 drills, relative motion can not take place between first cutting edge portion 210 and the second cutting edge portion 220, very big reduction the vibration range of socket drill, improve the cutting effect of socket drill.

Specifically, the diameter of the first cutting edge portion 210 is greater than the diameter of the second cutting edge portion 220, so that the cutter body 200 forms a stepped structure. The diameters of the first cutting edge portion 210 and the second cutting edge portion 220 are set according to the size of the hole to be drilled, and the present application does not limit the diameters. Illustratively, the diameter of the first cutting edge portion 210 is 10mm and the diameter of the second cutting edge portion 220 is 4 mm.

The first cutting edge portion 210 is further provided with a plurality of chamfering edges 211. The second cutting edge portion 220 is further provided with a plurality of drilling blades 221. The drilling blade 221 and the drilling blade 221 are both helical structures. The sizes of the drilling blade 221 and the helix angle of the drilling blade 221 may be set according to the use requirement, and the application is not limited. Illustratively, the helix angle of the

drilling blade

221, 221 is 45 °.

Specifically, the chamfer cutting edges 211 are evenly distributed along the circumferential direction of the first cutting edge portion 210, and the boring cutting edges 221 are evenly distributed along the circumferential direction of the second cutting edge portion 220. Through setting up chamfer cutting edge 211 and drilling cutting edge 221, also can accomplish the process of chamfer when drilling, effectively improve work efficiency, it is few to occupy tool magazine position, and can reduce the processing cost.

The first cutting edge portion 210 is provided with a first chip groove 212, the second cutting edge portion 220 is provided with a second chip groove 222, the first chip groove 212 is communicated with the second chip groove 222, and the core thickness of the first chip groove 212 is different from that of the second chip groove 222. The first flute 212 and the second flute 222 are both helical structures, and the size of the helix angle of the first flute 212 and the second flute 222 can be set according to the use requirement, which is not limited in the application. Illustratively, the helix angle of the

drilling blade

221, 221 is 45 °.

In this embodiment, the number of the chamfering blade 211 and the drilling blade 221 is two, and a first flute 212 in a spiral shape is formed between two adjacent chamfering blades 211. A second flute 222 in a spiral shape is formed between two adjacent drilling blades 221.

The core thickness of the first flute 212 is set according to the diameter of the first cutting edge portion 210. The core thickness of the second flute 222 is set in accordance with the diameter of the second cutting edge portion 220. Illustratively, the diameter of the first cutting edge portion 210 is D1, the core thickness of the first flute 212 is D1, and D1 is 0.15D1-0.45D 1. The diameter of the second cutting edge portion 220 is D2, the core thickness of the second chip groove 222 is D2, and D2 is 0.15D2-0.45D 2. Specifically, D1 is 0.25D1, and D2 is 0.25D 2. That is, the core thickness of the first flute 212 is 2.5mm, and the core thickness of the second flute 222 is 1 mm. It should be noted that: the center of the first cutting edge portion 210 has a first core, the cross-sectional diameter of which is defined as the core thickness of the first flute 212. The center of the second cutting edge portion 220 has a second core having a cross-sectional diameter defined as the core thickness of the second flute 222.

It is to be understood that: if the core thickness of the first flute 212 and the second flute 222 is designed to be the same, and the diameter of the first cutting edge portion 210 is taken as a reference, the drilling edge 221 on the second cutting edge portion 220 is narrow, and the rigidity of the drilling edge 221 is affected. The chamfer edge 211 on the first cutting edge portion 210 is wider and the swarf discharging space is smaller, based on the diameter of the second cutting edge portion 220.

The first chip removal groove 212 is formed in the first cutting edge portion 210, the second chip removal groove 222 is formed in the second cutting edge portion 220, and the core thicknesses of the first chip removal groove 212 and the second chip removal groove 222 are different, so that the drill cutting edge 221 cannot be too narrow to affect the rigidity of the drill cutting edge 221, the chamfer cutting edge 211 cannot be too wide to affect chip removal, the chip removal performance is guaranteed, the cutting flow direction is controlled, the rigidity of the drill cutting edge 221 can be improved, and quick and efficient cutting is achieved.

Referring to fig. 1 and 2, according to some embodiments of the present application, optionally, a drilling tool face 2211 is formed at an end of the drilling blade 221 away from the tool shank 100, and at least two grooves 2212 are formed on the drilling tool face 2211. At least two grooves 2212 are arranged in a staggered manner in the extending direction thereof. Specifically, the size and the number of the grooves 2212 can be set according to the use requirement, and the application does not limit this.

Illustratively, in this embodiment, the drilling tool surface 2211 is provided with a first groove 2212, a second groove 2212 and a third groove 2212, the extending direction of the first groove 2212 is M1, the extending direction of the second groove 2212 is M2, the extending direction of the third groove 2212 is M3, and M1, M2 and M3 are staggered with each other.

In other embodiments, the drilling tool surface 2211 is provided with a first groove 2212 and a second groove 2212, the extending direction of the first groove 2212 is M1, the extending direction of the second groove 2212 is M2, and M1 and M2 are alternately arranged.

By arranging the at least two grooves 2212 on the drilling tool face 2211 and arranging the at least two grooves 2212 in the extending direction in a staggered manner, the shape of chips can be improved, the phenomenon that the chips are difficult to clean due to winding on the cutter handle 100 is effectively avoided, and the working efficiency is improved.

Referring to fig. 1 and 2, according to some embodiments of the present disclosure, optionally, the chamfer edge 211 has a plurality of relief surfaces 2111, and a vibration reduction land 213 is further disposed between the chamfer edge 211 and the second flute 222. The chamfer edge 211 has a multi-flank 2111 structure. The flank surface 2111 means: a tool face that interacts with and opposes a machining surface on the workpiece 300 to be machined. By setting the chamfering blade 211 to have a structure with multiple flank 2111, the rigidity of the chamfering blade 211 can be improved, and the phenomenon of vibration or breakage of the cutter body 200 due to insufficient rigidity of the chamfering blade 211 can be effectively prevented.

The width and angle of the damping margin 213 may be set according to the use requirement, which is not limited in this application. By providing the vibration reduction land 213, the chatter mark phenomenon generated during machining can be reduced, and the roughness of the chamfer on the machined surface can be improved.

Referring to fig. 1, 2 and 3, according to some embodiments of the present application, the chamfer edge 211 optionally has a rake face 2112, and the rake face 2112 is provided with a correction edge 2113. Rake face 2112 refers to: directly against the work surface on the work piece 300 to be machined being cut and controls the face along which the chips are discharged.

Specifically, the modified edge 2113 has an axial rake angle of 8 ° to 13 °. It should be noted that: the lower limit of the axial rake angle of the corrected blade 2113 should not be less than 8 °, otherwise the chip discharge direction is easily suppressed, the torque of the cutter body 200 is drastically increased, and the risk of chipping of the cutter body 200 is easily increased, the upper limit of the axial rake angle of the corrected blade 2113 is related to the helix angle of the chamfered blade 211, the upper limit of the axial rake angle of the corrected blade 2113 should not exceed the helix angle of the chamfered blade 211, otherwise a land cannot be formed or the land structure is incomplete. In the present embodiment, the axial rake angle of the corrected blade 2113 is 10 °, and the corrected land axial angle is also 10 °.

The correction blade 2113 is arranged on the front blade face 2112 of the chamfering blade 211 to control the bending size formed by cutting, so that the chip state is effectively controlled, the problem of chip winding which possibly occurs during cutting is effectively avoided, stable and reliable cutting processing is ensured, and the processing efficiency is effectively improved.

The technical features of the embodiments described above may be arbitrarily combined, and for the sake of brevity, all possible combinations of the technical features in the embodiments described above are not described, but should be considered as being within the scope of the present specification as long as there is no contradiction between the combinations of the technical features.

The above-mentioned embodiments only represent some embodiments of the present invention, and the description thereof is specific and detailed, but not to be construed as limiting the scope of the present invention. It should be noted that, for those skilled in the art, without departing from the spirit of the present invention, several variations and modifications can be made, which are within the scope of the present invention. Therefore, the protection scope of the present invention should be subject to the appended claims.

Claims

1. An aviation countersink drill, comprising:

a knife handle;

2. The aircraft countersink drill according to claim 1, wherein a drilling cutter face is formed at one end of the drilling cutter edge, which is far away from the cutter handle, and at least two grooves are formed in the drilling cutter face.

3. The aircraft countersink drill according to claim 2, wherein at least two of said grooves are staggered in the direction of extension thereof.

4. The aircraft countersink drill according to claim 1, wherein said chamfer edge has a plurality of relief surfaces.

5. The aircraft countersink drill according to claim 1, wherein a vibration reduction land is further provided between the chamfer edge and the second chip groove.

6. The aircraft countersink drill according to claim 1, wherein said chamfer edge has a rake face, and a correction edge is provided on said rake face.

7. The aircraft countersink drill according to claim 6, wherein said correction blade has an axial rake angle of 8 ° to 13 °.

8. The aircraft countersink drill according to claim 1, wherein the drill blade, the chamfer blade, the first chip groove, and the second chip groove are all helical structures.

9. The aircraft countersink drill according to claim 1, wherein a spiral first chip groove is formed between two adjacent chamfer cutting edges.

10. The aircraft countersink drill according to claim 1, wherein a spiral second chip groove is formed between two adjacent drilling blades.