CN113182563A

CN113182563A - Hole expanding cutter for machining thin skin of airplane

Info

Publication number: CN113182563A
Application number: CN202110509215.6A
Authority: CN
Inventors: 王伟; 邢欣; 幸锐; 张璐; 韩文彪
Original assignee: AVIC Xian Aircraft Industry Group Co Ltd
Current assignee: AVIC Xian Aircraft Industry Group Co Ltd
Priority date: 2021-05-10
Filing date: 2021-05-10
Publication date: 2021-07-30

Abstract

The application discloses reamer for thin skin processing of aircraft, reamer cutting part adopts the design of many steps, and every step all has locates radial cutting edge and locates axial week sword, through distributing big cutting allowance to every step, realizes that the technology of traditional multistep reaming merges, has improved machining efficiency. By matching with structural designs such as a three-tooth linear type cutter groove and multiple steps, on one hand, the quality defect caused by vibration of a thin skin during reaming is reduced, on the other hand, excellent cutting performance of the cutter during processing of composite materials, aluminum alloys, titanium alloys and special-shaped laminated layers of the composite materials, the aluminum alloys and the titanium alloys is ensured, and the universality of the cutter is improved.

Description

Hole expanding cutter for machining thin skin of airplane

Technical Field

The application relates to the technical field of design and manufacture of numerical control cutters, in particular to a multi-step reamer for machining thin skin of an airplane.

Background

Thin-walled parts account for a relatively large proportion of aircraft assembly hole making requirements, with skin panels having a thickness of 0.8-5mm being most typical. Therefore, the machining efficiency of the thin-wall parts greatly influences the assembly progress of the airplane.

The traditional manual drilling, expanding and reaming has more cutter specifications due to a multi-step hole making strategy, although the number of cutters can be reduced by increasing the reaming allowance, the overlarge reaming allowance can generate larger cutting force, so that the problems of skin deformation, rough aperture, cutter vibration, cutter clamping and the like are caused, and even the quality hidden troubles of composite material layering, burning, metal ablation and the like are brought. In order to avoid the problems, an operator can only use the traditional multi-cutter hole making scheme to reduce the hole expanding allowance, and the processing efficiency is greatly influenced.

Therefore, the development of a special cutter special for the thin skin of the airplane with high efficiency and high quality stability is urgently needed.

Disclosure of Invention

The application aims to solve the problem that a cutter in a traditional structure form cannot meet the requirements of efficient and high-quality hole making of thin-wall parts of an airplane, and provides a hole expanding cutter for machining thin skins of the airplane. The cutting part of the reaming cutter adopts a multi-step design, large allowance cutting is distributed to each step, the combination of the traditional multi-step reaming process is realized, and the design of a three-tooth linear type cutter groove is matched, so that on one hand, the quality defect caused by vibration of a thin skin during reaming is reduced, on the other hand, the excellent cutting performance of the cutter during processing of composite materials, aluminum alloys, titanium alloys and special-shaped laminated layers thereof is ensured, the airplane thin-wall parts can be efficiently reamed by reaming with large removal amount, and the processing efficiency and the processing quality are greatly improved.

In order to achieve the purpose, the technical scheme adopted by the application is as follows:

a reamer for machining thin skin of an airplane structurally comprises a cutter handle and a cutting part in the front of the cutter handle, wherein the cutting part comprises a drill point, a cutting edge, a peripheral edge connected with the cutting edge and a three-tooth linear cutter groove, the cutting part is designed in a multi-step mode, and each step is provided with a cutting edge arranged in the radial direction and a peripheral edge arranged in the axial direction.

The cutting allowance of the last step of the cutting part is set to be 0.3-0.7 mm, the cutting allowances of the rest steps are set to be 0.8-1.2 mm, and the diameter tolerance of the last step is-0.007 mm.

The angle gamma of the sharp corner of the drill point is 85 degrees, the back angle adopts a relieving form, and the back angle alpha is 13-15 degrees.

The cutting angle delta of the cutting edge is 30 degrees, the width f of the cutting edge is 0.25-0.4 mm, and the back angle adopts a double back angle structure, wherein the first back angle alpha 1 is 12 degrees, and the second back angle alpha 2 is 25 degrees.

The peripheral edge rake angle δ 1 is 3 to 5 °, the edge strip width f1 is 0.3 to 0.5mm, and the relief angle adopts a double relief angle structure, wherein the first relief angle α 3 is 15 °, and the second relief angle α 4 is 30 °.

The helix angle β of the tool flutes is 0 °.

The thickness of the cutter core of the cutting part is 0.35d, d is the diameter of the first step, and the back taper of the cutter core is (0.8-1.0)/100 mm.

The multi-step cutting tool has the advantages that due to the multi-step design of the cutting part, large allowance cutting is distributed to each step, cutting force can be effectively reduced, cutting heat is reduced, the defects of tool vibration, tool clamping, low aperture roughness and the like caused by large allowance hole making are overcome, risks of lamination burning and composite material layering are reduced, and the tool is strong in universality, light in cutting and simple in process. Therefore, the method is easy to popularize and has great practical value.

This application is described in further detail below with reference to the example drawings.

Drawings

FIG. 1 is a schematic structural diagram of a reamer for machining thin skin of an aircraft

FIG. 2 is a schematic diagram of the A-A section structure of a reamer used for processing thin skin of an airplane

FIG. 3 is a schematic diagram of a B-B section structure of a reamer for machining thin skin of an airplane

FIG. 4 is a schematic view of a C-C section structure of a reamer for machining thin skin of an airplane

FIG. 5 is an enlarged schematic view of the cutting edge of a reamer for machining thin aircraft skin

FIG. 6 is a schematic diagram of the use of a reamer for machining thin skins of aircraft

The numbering in the figures illustrates: 1-tool handle, 2-cutting part, 3-drill tip, 4-cutting edge, 5-peripheral edge, 6-tool groove, 7-thin skin part, 8-initial hole, 9-tool core thickness and 10-tool tooth.

Detailed Description

As shown in fig. 1, the reamer for machining thin skin of an airplane is composed of a cutter handle 1 and a cutting part 2 arranged at the front part of the cutter handle 1; wherein the cutting part 2 comprises a drill tip 3, a cutting edge 4, a peripheral edge 5 connected with the cutting edge 4 and a three-tooth linear type cutter groove 6; the cutting part 2 is designed in a multi-step mode, each step is provided with a cutting edge 4 arranged in the radial direction and a peripheral edge 5 arranged in the axial direction, and compared with a traditional edge type, the multi-step edge type is that a single large-allowance cutting edge is distributed to a plurality of cutting edges 4; the angle gamma of the sharp corner of the drill point 3 is 85 degrees.

As shown in fig. 2, the peripheral edge 5 has a rake angle δ 1 of 3 to 5 °, a width f1 of 0.3 to 0.5mm, and a relief angle of a double relief angle structure, in which the first relief angle α 3 is 15 °, and the second relief angle α 4 is 30 °. The thickness 9 of the cutter core of the cutting part 2 is 0.35d, d is the diameter of the first step, the back taper 10 of the cutter core is (0.8-1.0)/100 mm, and the number of the cutter teeth 10 is equal to three.

As shown in fig. 3, the relief angle of the drill tip 3 is in the form of a tooth, and the relief angle α is 13 to 15 °.

As shown in fig. 4, the width f of the cutting edge 4 and the cutting strip is 0.25 to 0.4mm, and the relief angle is a double relief angle structure in which the first relief angle α 1 is 12 ° and the second relief angle α 2 is 25 °.

As shown in fig. 5, the cutting edge 4 has a cutting angle δ of 30 °.

When the pneumatic drill chuck is used, as shown in fig. 6, in the first step, the tool shank 1 is inserted into the pneumatic drill chuck, the outer circle of the tool shank 1 is tightly attached to the inner wall of the pneumatic drill chuck by using a chuck key, and whether the phenomena of slipping and loosening exist is checked; secondly, inserting a drill tip 3 of the cutter into the primary hole 8, wherein the drill tip 3 is in interference fit with the primary hole 8; thirdly, opening an air drilling trigger to ream the thin skin part 7, sequentially enabling each cutting edge 4 and each peripheral edge 5 to pass through the thin skin part 7, and slowly withdrawing the cutter cutting part 2 out of the thin skin part 7 after finishing reaming; and fourthly, after the pore diameter is observed to be free of burrs and the roughness is qualified, the pore diameter is checked by a special measuring tool (plug gauge) or an internal micrometer, and after the pore diameter is qualified, the pore making is finished.

Claims

1. The utility model provides a reamer for thin covering processing of aircraft which characterized in that: the cutting part comprises a drill point, a cutting edge, a peripheral edge connected with the cutting edge and a three-tooth linear cutter groove;

the angle gamma of the sharp corner of the drill point is 85 degrees, the rear angle adopts a relieving form, and the rear angle alpha is 13-15 degrees;

the cutting angle delta of the cutting edge is 30 degrees, the width f of the cutting edge is 0.25-0.4 mm, and the back angle adopts a double back angle structure, wherein the first back angle alpha 1 is 12 degrees, and the second back angle alpha 2 is 25 degrees;

the peripheral edge front angle delta 1 is 3-5 degrees, the edge strip width f1 is 0.3-0.5 mm, and the back angle adopts a double back angle structure, wherein the first back angle alpha 3 is 15 degrees, and the second back angle alpha 4 is 30 degrees;

the helix angle β of the tool flutes is 0 °.

2. The reamer for machining the thin skin of the aircraft according to claim 1, wherein: the cutting part is designed to be multi-step, each step is provided with a cutting edge arranged on the radial direction and a peripheral edge arranged on the axial direction, the cutting allowance of the last step is set to be 0.3-0.7 mm, and the cutting allowances of the rest steps are set to be 0.8-1.2 mm.

3. The reamer for machining the thin skin of the aircraft according to claim 1, wherein: the thickness of the cutter core of the cutting part is 0.35d, d is the diameter of the first step, and the back taper of the cutter core is 0.8-1.0/100 mm.

4. The reamer for machining the thin skin of the aircraft according to claim 1, wherein: the diameter tolerance of the last step of the cutting portion is-0.007 mm.