阅读说明：本技术 一种航空用高强铝合金厚板整体结构件的加工方法 (Machining method of integral structural member of high-strength aluminum alloy thick plate for aviation ) 是由 任伟才 王强 王洪伍 吴沂哲 李岳峰 闫洪达 宁宁 李艺萌 于 2021-07-15 设计创作，主要内容包括：一种航空用高强铝合金厚板整体结构件的加工方法。具体涉及高强铝合金厚板整体结构件的加工方法。本发明是为了解决现有技术的加工量较大,并且粗、精加工连续进行,导致加工后出现结构件变形超差甚至开裂,同时也存在典型零件机加工合格率低的问题,采用一种航空用高强铝合金厚板整体结构件的加工方法。一种航空用高强铝合金厚板整体结构件的加工方法,它包括以下步骤：步骤一、确定厚板加工基准面：步骤二、选择不同工序所用刀具：步骤三、对厚板进行一次开粗型面：步骤四、对厚板进行自然时效处理：步骤五、对厚板进行二次开粗型面：步骤六、对厚板进行全型精加工：步骤七、钳工：步骤八、校验。用于航空航天数控加工技术领域。(A method for processing an integral structural member of a high-strength aluminum alloy thick plate for aviation. In particular to a processing method of a high-strength aluminum alloy thick plate integral structural member. The invention aims to solve the problems that in the prior art, the machining amount is large, the rough machining and the finish machining are continuously carried out, the deformation of a structural part is out of tolerance and even cracks occur after machining, and the machining yield of typical parts is low. A processing method of an integral structural member of a high-strength aluminum alloy thick plate for aviation comprises the following steps: step one, determining a thick plate processing datum plane: step two, selecting cutters used in different procedures: step three, performing primary rough profile opening on the thick plate: step four, carrying out natural aging treatment on the thick plate: step five, performing secondary rough profile opening on the thick plate: step six, performing full-mold finish machining on the thick plate: step seven, bench work: and step eight, checking. The method is used for the technical field of aerospace numerical control machining.)

1. A processing method of an integral structural member of a high-strength aluminum alloy thick plate for aviation is characterized by comprising the following steps: it comprises the following steps:

step one, determining a thick plate processing datum plane:

taking the blanked thick plate outline dimension plane as a processing reference plane;

step two, selecting cutters used in different procedures:

selecting a D32R0 cutter, a D63R0.8 cutter, a D20R0 cutter, a D12R6 ball cutter and a D10R0 cutter;

step three, performing primary rough profile opening on the thick plate:

the upper surface and the lower surface of the thick plate are machined and removed by 1.0-2.0 mm, the machining thickness is 50mm, the flatness is not more than +/-0.1 mm, a D32R0 cutter is selected, the upper surface of the thick plate faces to the cutter, each cutter is cut downwards by 0.5-1.0 mm, the whole digital-analog uniform allowance is 2mm, the periphery of the thick plate is finely machined to be used as a reference edge (2), the machined surface is marked with the machined surface (1), the machined surface (1) is rotated by 180 degrees around an X axis, the reference edge (2) is straightened and centered, a D63R0.8 cutter is selected, the lower surface of the thick plate is subjected to tool setting, the cutting depth of each cutter is 0.5mm, and the whole digital-analog uniform allowance is 2 mm;

step four, carrying out natural aging treatment on the thick plate:

placing the thick plate with the rough molded surface opened in the third step on a flat position to release the residual stress through natural aging;

step five, performing secondary rough profile opening on the thick plate:

after residual stress of the thick plate in the step four is released, secondary rough profile forming is carried out on the thick plate, a machining surface (1) is marked upwards, centering is carried out according to a benchmark, the removing amount of the upper surface is 0.5mm, a D20R0 cutter is selected, the upper surface is opposite to the cutter, the cutting depth of each cutter is 0.1-0.3 mm, the uniform allowance of a digital model is 0.3mm, a D12R6 ball cutter is selected for full-profile finish machining, the machining surface (1) rotates 180 degrees around the X axis, centering is carried out according to a benchmark edge (2), the lower surface is aligned, a D20R0 cutter is selected, the cutting depth of each cutter is 0.3mm, and the full-profile allowance of the digital model is 0.3 mm;

step six, performing full-mold finish machining on the thick plate:

after secondary rough profile forming is carried out on the thick plate, performing full-profile finish machining by using a D12R6 ball cutter with the step of 0.10-0.15 mm per cutter, cutting off the periphery by using a D10R0 cutter, and reserving four connecting ribs;

step seven, bench work:

cutting off the connecting ribs along the cut-off part in a smooth manner, and trimming and polishing the cut-off connecting ribs;

step eight, checking:

if the standard is met after the verification, the processing is finished;

and if the standard is not met after the verification, continuously repeating the steps from the first step to the seventh step, and then verifying the standard until the standard is met, and finishing the processing.

2. The processing method of the integral structural member of the thick high-strength aluminum alloy plate for aviation according to claim 1, characterized in that: and step three, cutting the thick molded surface once, wherein the cutting depth of each cutter is 0.5 mm.

3. The processing method of the integral structural member of the thick high-strength aluminum alloy plate for aviation according to claim 1 or 2, wherein the processing method comprises the following steps: and step three, processing and removing 1.0mm of the upper surface and the lower surface of the medium plate of the primary rough profile, cutting down to 0.3mm in each cutter in the five-time rough profile, and performing full-profile finish machining by using a D12R6 ball cutter with the step per cutter of 0.15mm in the six-time full-profile finish machining.

4. The machining method of the integral structural member of the thick high-strength aluminum alloy plate for aviation according to claim 3, characterized in that: and step three, processing and removing 2.0mm of the upper surface and the lower surface of the medium plate of the primary rough profile, cutting down to 0.1mm in each cutter in the five-time rough profile, and performing full-profile finish machining by using a D12R6 ball cutter with the step per cutter of 0.1mm in the six-time full-profile finish machining.

5. The machining method of the integral structural member of the thick high-strength aluminum alloy plate for aviation according to claim 4, wherein the machining method comprises the following steps: and the time of natural aging in the fourth step is 72 h.

6. The processing method of the integral structural member of the thick high-strength aluminum alloy plate for aviation according to claim 5, wherein the processing method comprises the following steps: and fifthly, cutting the lower cutting depth of each cutter in the rough molded surface twice to be 0.15 mm.

7. The processing method of the integral structural member of the thick high-strength aluminum alloy plate for aviation according to claim 6, wherein the processing method comprises the following steps: and in the six-step full-mold finish machining, the D12R6 ball cutter is selected to perform full-mold finish machining with the step of each cutter being 0.1 mm.

Technical Field

The invention relates to the technical field of aerospace numerical control machining, in particular to a machining method of an integral structural member of a high-strength aluminum alloy thick plate for aviation.

Background

At present, a high-strength aluminum alloy thick plate for aviation is an Al-Zn-Mg-Cu alloy, a large amount of residual stress is introduced into the alloy due to temperature gradient in the heat treatment process, the surface of the thick plate in a final state is generally subjected to L-direction partial stress of about-30-22 MPa and T-direction partial stress of about 55-24 MPa, so that when a large host factory processes the integral structural member of the alloy, due to the existence of the residual stress, the upper and lower surface deformation convex parts of the thick plate need to be processed through multiple times of turning during rough processing, the total processed thickness of the upper and lower surfaces reaches 14-20 mm, the processing amount is large, and rough processing and finish processing are continuously carried out, so that the problems of structural member deformation, over-difference, cracking and the like often occur after processing, meanwhile, the deformation stability of the thick plate after processing is poor, the general deformation amount is 4-8mm, and the processing qualification rate is extremely low. The surface residual stress of the processed integral structural part is in a tensile stress state, the residual stress value is detected to be about 93-165 MPa in the L direction, about 78-127 MPa in the T direction, and the integral stress level is high.

In conclusion, the whole structural member of the aluminum alloy thick plate in the prior art has large processing amount, and the rough processing and the finish processing are continuously performed, so that the structural member is deformed out of tolerance and even cracked after being processed, and meanwhile, the problem of low machining pass rate of typical parts also exists.

Disclosure of Invention

The invention aims to solve the problems that in the prior art, the machining amount is large, the rough machining and the finish machining are continuously carried out, the deformation of a structural part is out of tolerance and even cracks occur after machining, and the machining yield of typical parts is low.

The technical scheme of the invention is as follows:

a processing method of an integral structural member of a high-strength aluminum alloy thick plate for aviation comprises the following steps:

step one, determining a thick plate processing datum plane:

taking the blanked thick plate outline dimension plane as a processing reference plane;

step two, selecting cutters used in different procedures:

selecting a D32R0 cutter, a D63R0.8 cutter, a D20R0 cutter, a D12R6 ball cutter and a D10R0 cutter;

step three, performing primary rough profile opening on the thick plate:

the upper surface and the lower surface of the thick plate are machined and removed by 1.0-2.0 mm, the machining thickness is 50mm, the flatness is not more than +/-0.1 mm, a D32R0 cutter is selected, the upper surface of the thick plate faces to the cutter, each cutter is cut downwards by 0.5-1.0 mm, the whole digital-analog type uniform allowance is 2mm, the periphery of the thick plate is finely machined to be used as a reference edge, the machined surface is marked, the machined surface is rotated by 180 degrees around an X axis, the reference edge is straightened and centered, a D63R0.8 cutter is selected, the lower surface of the thick plate is subjected to tool setting, the lower cutting depth of each cutter is 0.5mm, and the whole digital-analog type uniform allowance is 2 mm;

step four, carrying out natural aging treatment on the thick plate:

placing the thick plate with the rough molded surface opened in the third step on a flat position to release the residual stress through natural aging;

step five, performing secondary rough profile opening on the thick plate:

after residual stress of the thick plate in the step four is released, secondary rough molding is carried out on the thick plate, the machined surface is marked to be 1 upward, centering is carried out according to a benchmark, the removing amount of the upper surface is 0.5mm, a D20R0 cutter is selected, the upper surface is opposite to the cutter, the lower cutting depth of each cutter is 0.1-0.3 mm, full-mold finish machining is carried out according to the uniform allowance of a digital model and a D12R6 ball cutter is selected, the machined surface is rotated 180 degrees around the X axis, centering is carried out according to the benchmark edge, the lower surface is opposite to the cutter, a D20R0 cutter is selected, the lower cutting depth of each cutter is 0.3mm, and the full-mold allowance of the digital model is 0.3 mm;

step six, performing full-mold finish machining on the thick plate:

after secondary rough profile forming is carried out on the thick plate, performing full-profile finish machining by using a D12R6 ball cutter with the step of 0.10-0.15 mm per cutter, cutting off the periphery by using a D10R0 cutter, and reserving four connecting ribs;

step seven, bench work:

cutting off the connecting ribs along the cut-off part in a smooth manner, and trimming and polishing the cut-off connecting ribs;

step eight, checking:

if the standard is met after the verification, the processing is finished;

and if the standard is not met after the verification, continuously repeating the steps from the first step to the seventh step, and then verifying the standard until the standard is met, and finishing the processing.

Compared with the prior art, the invention has the following effects:

firstly, the integral structural member of the high-strength aluminum alloy thick plate for aviation processed by the invention does not need to be turned over for many times during rough processing, the machining amount of the component can be reduced, meanwhile, the component is naturally aged after rough processing to release residual stress, the problems of deformation, out-of-tolerance, even cracking and the like of the component during machining can be avoided, and meanwhile, the machining qualified rate is improved to more than 90%.

Secondly, the surface residual stress of the integral structural part processed by the method is still in a tensile stress state, the value of the residual stress is about 70-133 MPa in the L direction, the value of the residual stress is about 47-109 MPa in the T direction, and the integral residual stress is reduced to a greater extent.

Drawings

FIG. 1 is a schematic view of a plank of the present invention.

Detailed Description

The first embodiment is as follows: the present embodiment will be described with reference to fig. 1, and the method for processing an integral structural member of a thick high-strength aluminum alloy plate for aviation according to the present embodiment includes the steps of:

step one, determining a thick plate processing datum plane:

taking the blanked thick plate outline dimension plane as a processing reference plane;

step two, selecting cutters used in different procedures:

selecting a D32R0 cutter, a D63R0.8 cutter, a D20R0 cutter, a D12R6 ball cutter and a D10R0 cutter;

step three, performing primary rough profile opening on the thick plate:

the upper surface and the lower surface of the thick plate are machined and removed by 1.0-2.0 mm, the machining thickness is 50mm, the flatness is not more than +/-0.1 mm, a D32R0 cutter is selected, the upper surface of the thick plate faces to the cutter, each cutter is cut downwards by 0.5-1.0 mm, the numerical model full-type uniform allowance is 2mm, the periphery of the thick plate is finely machined to be used as a reference edge 2, the machined surface is marked as a machined surface 1, the machined surface 1 is rotated by 180 degrees around an X axis, the reference edge 2 is straightened and centered, a D63R0.8 cutter is selected, the lower surface of the thick plate is subjected to tool setting, the cutting depth of each cutter is 0.5mm, and the numerical model full-type uniform allowance is 2 mm;

step four, carrying out natural aging treatment on the thick plate:

placing the thick plate with the rough molded surface opened in the third step on a flat position to release the residual stress through natural aging;

step five, performing secondary rough profile opening on the thick plate:

after residual stress of the thick plate in the fourth step is released, secondary rough molding is conducted on the thick plate, the machined surface is marked upwards, centering is conducted according to a benchmark, the upper surface removing amount is 0.5mm, a D20R0 cutter is selected, the upper surface is opposite to the cutter, the lower cutting depth of each cutter is 0.1-0.3 mm, a D12R6 ball cutter is selected to conduct full-mold finish machining according to the uniform digital-analog remaining amount of 0.3mm, the machined surface 1 rotates 180 degrees around the X axis, centering is conducted according to a benchmark edge 2, the lower surface is opposite to the cutter, a D20R0 cutter is selected, the lower cutting depth of each cutter is 0.3mm, and the full-mold remaining amount of the digital-analog molding surface is 0.3 mm;

step six, performing full-mold finish machining on the thick plate:

after secondary rough profile forming is carried out on the thick plate, performing full-profile finish machining by using a D12R6 ball cutter with the step of 0.10-0.15 mm per cutter, cutting off the periphery by using a D10R0 cutter, and reserving four connecting ribs;

step seven, bench work:

cutting off the connecting ribs along the cut-off part in a smooth manner, and trimming and polishing the cut-off connecting ribs;

step eight, checking:

if the standard is met after the verification, the processing is finished;

and if the standard is not met after the verification, continuously repeating the steps from the first step to the seventh step, and then verifying the standard until the standard is met, and finishing the processing.

The step of setting the thickness of the three thick plates to be 1.0-2.0 mm is to remove the defect of surface oxide skin, and the periphery of the smooth thick plate is used as a reference edge to be turned over for positioning.

The second embodiment is as follows: referring to fig. 1, the present embodiment will be described, wherein the depth of cut per blade in the rough surface is 0.5mm in the third step of the present embodiment. The rest is the same as the first embodiment.

The third concrete implementation mode: in the third step of the embodiment, the upper and lower surfaces of the medium plate with the rough profile are machined and removed by 1.0mm, in the fifth step, the lower cutting of each cutter in the rough profile is 0.3mm, and in the sixth step, the step of each cutter of a D12R6 ball cutter is 0.15mm in step for full-profile finish machining. The others are the same as in the first or second embodiment.

The fourth concrete implementation mode: referring to fig. 1, the embodiment is described, in the third step of the embodiment, the upper and lower surfaces of the medium plate with the rough profile are machined and removed by 2.0mm, in the fifth step, the rough profile is cut down by 0.1mm per knife, and in the sixth step, the full-profile finish machining is performed by selecting a D12R6 ball knife with 0.1mm per knife step. The others are the same as the first, second or third embodiments.

The fifth concrete implementation mode: the present embodiment will be described with reference to fig. 1, and the time for natural aging in step four of the present embodiment is 72 hours. The others are the same as the first, second, third or fourth embodiments.

The sixth specific implementation mode: referring to fig. 1, the embodiment is described, in which the upper and lower surfaces of the medium plate in the rough profile are machined and removed by 2.0mm in the third step, and the depth of each blade in the rough profile is 0.15mm in the fifth step. The other embodiments are the same as the first, second, third, fourth or fifth embodiments.

The seventh embodiment: referring to fig. 1, the present embodiment will be described, and in the six-step full finishing of the present embodiment, the full finishing is performed with a D12R6 ball cutter with a step of 0.1mm per cutter. The other embodiments are the same as the first, second, third, fourth, fifth or sixth embodiments.

The present invention has been described in terms of the preferred embodiments, but it is not limited thereto, and any simple modification, equivalent change and modification made to the above embodiments according to the technical spirit of the present invention will still fall within the technical scope of the present invention.