CN115446550B - Machining method for U-shaped locating piece of aircraft standard tool - Google Patents
Machining method for U-shaped locating piece of aircraft standard tool Download PDFInfo
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- CN115446550B CN115446550B CN202211191378.5A CN202211191378A CN115446550B CN 115446550 B CN115446550 B CN 115446550B CN 202211191378 A CN202211191378 A CN 202211191378A CN 115446550 B CN115446550 B CN 115446550B
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- 238000003754 machining Methods 0.000 title claims abstract description 58
- 238000000034 method Methods 0.000 title claims abstract description 22
- 238000010791 quenching Methods 0.000 claims abstract description 13
- 230000000171 quenching effect Effects 0.000 claims abstract description 13
- 238000000137 annealing Methods 0.000 claims abstract description 7
- 238000003672 processing method Methods 0.000 claims abstract description 7
- 238000013461 design Methods 0.000 claims description 18
- 238000005520 cutting process Methods 0.000 claims description 15
- 238000010438 heat treatment Methods 0.000 claims description 13
- 238000004321 preservation Methods 0.000 claims description 10
- 239000002826 coolant Substances 0.000 claims description 6
- 239000003513 alkali Substances 0.000 claims description 3
- 238000001816 cooling Methods 0.000 claims description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 3
- 238000003466 welding Methods 0.000 claims description 2
- 238000012545 processing Methods 0.000 abstract description 10
- 238000012797 qualification Methods 0.000 abstract description 4
- 238000005457 optimization Methods 0.000 abstract description 2
- 238000004519 manufacturing process Methods 0.000 description 7
- 238000010586 diagram Methods 0.000 description 3
- 238000005496 tempering Methods 0.000 description 3
- 238000004458 analytical method Methods 0.000 description 2
- 230000001788 irregular Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000008030 elimination Effects 0.000 description 1
- 238000003379 elimination reaction Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 230000000877 morphologic effect Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 230000006032 tissue transformation Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P10/00—Technologies related to metal processing
- Y02P10/25—Process efficiency
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention discloses a processing method of a U-shaped locating piece of an aircraft standard tool, which comprises the following steps: step 1: coarse-row large-allowance treatment is carried out on the notch of the U-shaped positioning piece; step 2: at least one stay bar is arranged at the outer edge of the notch end of the U-shaped positioning piece; step 3: quenching the U-shaped positioning piece; step 4: annealing the U-shaped positioning piece; step 5: disassembling a stay bar at the end of the notch of the U-shaped positioning piece; step 6: the notch of the U-shaped locating piece is subjected to finish machining, and compared with the prior art, the U-shaped locating piece has the advantages that: due to the adoption of the optimization of the process method, the influence of structural factors on the release of the internal stress of the part is reduced, the mechanical processing one-time qualification rate of the U-shaped locating piece of the standard tool of the aircraft is improved, and the U-shaped locating piece is reliable in quality and efficient.
Description
Technical Field
The invention belongs to the technical field of standard tool manufacturing and overhaul, and relates to a processing method of a U-shaped locating piece of an aircraft standard tool.
Background
The standard tool is used for manufacturing process equipment or guaranteeing the coordinated three-dimensional size basis among the process equipment, the manufacturing precision is often higher than that of common process equipment, and the maintenance and preservation processes are quite strict.
Because the standard tool transfers the relative assembly relation by means of the three-dimensional size formed by the locating piece on the standard tool, the processing quality of the locating piece directly relates to the assembly quality of the tool. The U-shaped locating piece of the aircraft standard tool is used as a structural form which is most commonly applied to the aircraft standard tool, and is widely applied to the processing and manufacturing of intersection point locators of all component standard tools. Meanwhile, due to the reasons of high structural specificity, high machining precision and the like, various problems such as out-of-tolerance critical dimensions and the like often occur in the actual machining and manufacturing process, the quality of products is affected, and qualified standard tool positioning pieces cannot be delivered on schedule.
Because the machining out-of-tolerance of the U-shaped locating piece of the aircraft standard tool is mainly concentrated on the deformation of the U-shaped notch, the requirement of the size cannot be met, the U-shaped notch is machined by utilizing linear cutting equipment in the prior art, and the U-shaped notch is formed in one step, that is, the linear cutting process is a key process for judging whether the size of the notch is qualified or not. Analysis of the processing process shows that the problem of out-of-tolerance of the U-shaped notch size is mainly manifested in notch end closing (the root can meet 34H8, the end is smaller than 34H 8) and the requirements of parallelism 0.02 and notch width 34H8 cannot be met. The analysis reason is mainly that 45# steel materials are selected for the U-shaped locating piece in order to achieve the abrasion-resistant characteristic of the U-shaped locating piece of the aircraft standard tool, quenching treatment is carried out on the U-shaped locating piece, the quenching hardness reaches HRC 40-45, after quenching, the internal stress which is not released completely exists in the U-shaped locating piece, the procedure of cutting the U-shaped notch is a finish machining procedure, the stress in the part is released irregularly in the notch cutting process after heat treatment, and the U-shaped notch is deformed.
Disclosure of Invention
The purpose of the invention is that: the invention solves the problem of low one-time qualification rate of mechanical processing of the U-shaped locating piece of the standard tool of the airplane, and provides a processing method with reliable quality and high efficiency.
The technical proposal is that.
A processing method of a U-shaped locating piece of an aircraft standard tool comprises the following steps:
step 1: coarse-row large-allowance treatment is carried out on the notch of the U-shaped positioning piece;
step 2: at least one stay bar is arranged at the outer edge of the notch end of the U-shaped positioning piece;
step 3: quenching the U-shaped positioning piece;
step 4: annealing the U-shaped positioning piece;
step 5: disassembling a stay bar at the end of the notch of the U-shaped positioning piece;
step 6: and (5) carrying out finish machining on the notch of the U-shaped locating piece.
Further, in step 1, according to the notch design value a of the U-shaped positioning piece, the notch width of the U-shaped positioning piece is processed to 3/5~4/5 of the notch design value a, machining allowance is reserved on two sides of the notch of the U-shaped positioning piece, and the machining allowance is 1/5~2/5 of the notch design value a.
Further, in the step 1, machining is carried out to 5/7~6/7 of the notch design value a in the height range of 1/5 of the root of the notch of the U-shaped locating piece, machining allowance is reserved on two sides of the root of the notch of the U-shaped locating piece, and the machining allowance is 1/7~2/7 of the notch design value a.
Further, in step 2, three stay bars for supporting the notch are uniformly spot-welded at the outer edge of the notch end of the U-shaped positioning piece 1, wherein one stay bar 2 is spot-welded at the end, and one stay bar 2 for supporting the notch is spot-welded at the middle position of the end stay bar and the root of the U-shaped positioning piece 1 at two sides.
And step 3, quenching the U-shaped positioning piece, heating to 820-860 ℃, keeping the temperature for 80-120 min, and cooling the positioning piece to normal room temperature by adopting any one of oil, water and low-temperature alkali liquor as a cooling medium after the heat preservation is finished.
And step 4, tempering the U-shaped positioning piece, wherein the temperature is increased to 360-420 ℃, the heat preservation time is 130-180 min, and air can be used as a cooling medium to cool the positioning piece to normal room temperature after the heat preservation is finished.
Further, in the step 6, the U-shaped locating piece is clamped and clamped on the wire cutting to finish the notch, the notch is finished for 2-3 times, the stress is released uniformly, and the last feeding of the wire cutting meets the machining precision of the notch parallelism of 0.02 and the notch width 34H 8.
Further, the U-shaped locating piece is applied to a vertical-fin standard tool, the width of a notch of the U-shaped locating piece is processed to 24mm according to a notch design value of 34mm of the U-shaped locating piece, machining allowance is reserved on two sides of the notch of the U-shaped locating piece, one-side machining allowance is 5mm, machining allowance is reserved on two sides of the root of the notch of the U-shaped locating piece within a height range of 1/5 of the root of the notch of the U-shaped locating piece to 30mm, and one-side machining allowance is 2mm.
The beneficial effects are that:
compared with the prior art, the invention has the advantages that: due to the adoption of the optimization of the process method, the influence of structural factors on the release of the internal stress of the part is reduced, the mechanical processing one-time qualification rate of the U-shaped locating piece of the standard tool of the aircraft is improved, and the U-shaped locating piece is reliable in quality and efficient.
Drawings
FIG. 1 is a schematic diagram of the appearance of a U-shaped positioning piece of an aircraft standard tool;
FIG. 2 is a schematic diagram of the manufacturing dimensions of a U-shaped positioning piece of an aircraft standard tool;
FIG. 3 is a schematic diagram of the U-shaped locating piece notch margin elimination of the aircraft standard tooling;
FIG. 4 is a schematic view of a spot welding stay bar on a U-shaped positioning piece of an aircraft standard tool;
wherein: 1. u-shaped locating piece, 2, stay bar.
The specific embodiment is as follows:
the following detailed description of the embodiments of the present invention, such as the shape and construction of the components, the mutual positions and connection relationships between the components, the roles and working principles of the components, the manufacturing process and the operation and use method, etc., is provided to help those skilled in the art to more fully and accurately understand the concept, technical solution of the present invention by describing the embodiments in the following drawings:
examples
A processing method of a U-shaped locating piece 1 of an aircraft standard tool comprises the following steps:
step 1: coarse-row large-allowance treatment is carried out on the notch of the U-shaped positioning piece 1; according to the notch design value a of the U-shaped locating piece 1, the notch width of the U-shaped locating piece 1 is machined to 3/5~4/5 of the notch design value a, machining allowance is reserved on two sides of the notch of the U-shaped locating piece 1, follow-up finish machining precision is convenient to improve, the machining allowance is 1/5~2/5 of the notch design value a, the notch is guaranteed to be reserved with enough finish machining allowance, and follow-up finish machining requirements are met.
The U-shaped locating piece 1 notch root is processed to 5/7~6/7 of a notch design value a in the height range of 1/5, machining allowance is reserved on two sides of the U-shaped locating piece 1 notch root, the machining allowance is 1/7~2/7 of the notch design value a, the function of the step is to reduce U-shaped notch closing in during finish machining, the U-shaped notch is not easy to deform, the problem of out of tolerance exists in the U-shaped notch basically in size, and the requirements of parallelism 0.02 and notch width 34H8 can be met.
Step 2: at least one stay bar 2 is arranged at the outer edge of the notch end of the U-shaped positioning piece 1; specifically, three stay bars 2 used for supporting the notch are evenly spot-welded at the outer edge of the notch end of the U-shaped locating piece 1, wherein one stay bar 2 is spot-welded at the end, and one stay bar 2 used for supporting the notch is spot-welded at the middle position of the root of the U-shaped locating piece 1 and the end stay bar 2. The three supporting rods 2 used for supporting the notch are uniformly spot-welded at the outer edge of the notch end of the U-shaped positioning piece 1, so that irregular deformation of the notch caused by heating during heat treatment can be prevented, the three supporting rods 2 used for supporting the notch are made of high-temperature-resistant metal materials, deformation can not occur in the heat treatment process, the morphological requirement of the notch during heat treatment is better ensured, and the qualification rate of subsequent processing is improved.
Step 3: quenching the U-shaped positioning piece 1; quenching the U-shaped positioning piece 1, heating to 820-860 ℃, keeping the temperature for 80-120 min, and cooling the temperature of the positioning piece to normal room temperature by using any one of oil, water and low-temperature alkali liquor as a cooling medium after the heat preservation is finished. The hardness and wear resistance of the U-shaped locating piece 1 can be improved by quenching treatment, the strength and fatigue strength of the U-shaped locating piece 1 can be greatly improved by matching the quenching with the heating temperature and the heat preservation time, and the matching between the properties can be obtained to meet different use requirements.
Step 4: annealing the U-shaped positioning piece 1; tempering the U-shaped positioning piece 1, increasing the temperature to 360-420 ℃, keeping the temperature for 130-180 min, and reducing the temperature of the positioning piece to normal room temperature by adopting air as a cooling medium after the heat preservation is finished.
After quenching, the U-shaped locating piece 1 has internal stress which is not released completely, the procedure of cutting the U-shaped notch is a finish machining procedure, and after heat treatment, the stress in the part is released irregularly in the notch cutting process, so that the U-shaped notch is deformed. Therefore, by annealing the U-shaped positioning piece 1, the tissue stability of the U-shaped positioning piece 1 is improved, and the U-shaped positioning piece 1 is not subjected to tissue transformation in the use process, so that the geometric dimension and performance of the U-shaped positioning piece 1 are kept stable. In addition, the internal stress of the U-shaped positioner 1 is removed by annealing (tempering) treatment, so as to improve the usability of the U-shaped positioner 1 and stabilize the workpiece geometry.
Step 5: the stay bar 2 at the end of the notch of the U-shaped positioning piece 1 is disassembled, so that the width of the notch cannot be deformed severely and the sufficient machining allowance of the width of the notch is ensured before finish machining;
step 6: the notch of the U-shaped locating piece 1 is subjected to finish machining, specifically, the U-shaped locating piece 1 is clamped on a linear cutting device to finish machining the notch, the notch is subjected to finish machining for 2-3 times, the stress is uniformly released, and the last feeding of the linear cutting device meets the machining precision of the notch parallelism of 0.02 and the notch width 34H 8. Because the notch is still left with the surplus, in order to avoid taking the bad factor that the excessive stress concentration that forms the processingquality of volume of cutting a knife releases, so take and divide 2 ~ 3 times to carry out finish machining to the notch, ensure the even release of stress, last feed can satisfy notch parallelism 0.02 and notch width 34H 8's machining precision, the U type setting element 1 notch end binding off of last processing has not had the size problem of out of tolerance basically, satisfies the operation requirement.
In this embodiment, the U-shaped locating piece 1 is applied to a vertical tail standard tool, then according to the 34mm notch design value of the U-shaped locating piece 1, the notch width of the U-shaped locating piece 1 is processed to 24mm, machining allowance is reserved on two sides of the notch of the U-shaped locating piece 1, machining allowance on one side is 5mm, machining allowance is reserved on two sides of the root of the notch of the U-shaped locating piece 1 in a height range of 1/5 of the root of the notch of the U-shaped locating piece 1, and machining allowance is reserved on two sides of the root of the notch of the U-shaped locating piece 1, and machining allowance on one side is 2mm.
Embodiment two:
providing a processing method of a U-shaped positioning piece 1 of an aircraft standard tool;
firstly, after the appearance of a U-shaped locating piece 1 of an aircraft standard tool is machined and before heat treatment, a large allowance in a notch 34H8 in the drawing 2 is discharged, the U-shaped notch is machined to 24 according to the drawing 3, 5mm machining allowance is reserved on one side, the notch is ensured to be left with finishing allowance, in order to reduce the closing-up of the U-shaped notch during finishing, the position 1/5 of the height above the root of the notch is machined to 30mm, and 2mm finishing allowance is reserved on two sides; then, in order to prevent irregular deformation of the notch caused by heat treatment, as shown in fig. 4, three stay bars 2 for supporting the notch are uniformly spot-welded at the notch of the U-shaped positioning piece 1, wherein one stay bar 2 is spot-welded at the end, and one stay bar 2 for supporting the notch is spot-welded at the middle position of the end stay bar 2 and the root of the U-shaped positioning piece 1 at two sides; immediately after heat treatment (quenching), annealing treatment is carried out on the U-shaped positioning piece 1 so as to remove most of internal stress in the part, and the stable quality of subsequent finish machining is ensured and is not influenced by the internal stress; then, three supporting rods 2 for supporting the notch are polished, the width of the notch cannot be deformed severely, and the notch width is ensured to have enough machining allowance before finish machining; finally, the U-shaped locating piece 1 is clamped on the wire cutting to finish the notch, and as the notch is still provided with a 10mm allowance, in order to avoid the adverse factors of stress concentration release caused by cutting amount and multiple pairs of processing quality, the notch is finished for 2-3 times, so that the stress is uniformly released, and the processing precision of the notch parallelism 0.02 and the notch width 34H8 can be met by the last feeding.
While the invention has been described above with reference to the accompanying drawings, it will be apparent that the invention is not limited to the above embodiments, but is capable of being modified or applied directly to other applications without modification, as long as various insubstantial modifications of the method concept and technical solution of the invention are adopted, all within the scope of the invention.
Claims (3)
1. A processing method of a U-shaped locating piece of an aircraft standard tool is characterized by comprising the following steps of: the method comprises the following steps:
step 1: coarse-row large-allowance treatment is carried out on the notch of the U-shaped positioning piece; according to a notch design value a of the U-shaped positioning piece, the notch width of the U-shaped positioning piece is processed to 3/5~4/5 of the notch design value a, machining allowance is reserved on two sides of the notch of the U-shaped positioning piece, and the machining allowance is 1/5~2/5 of the notch design value a; machining the notch root of the U-shaped locating piece to 5/7~6/7 of a notch design value a within the height range of 1/5, and reserving machining allowance at two sides of the notch root of the U-shaped locating piece, wherein the machining allowance is 1/7~2/7 of the notch design value a;
step 2: at least one stay bar is arranged at the outer edge of the notch end of the U-shaped positioning piece;
step 3: quenching treatment is carried out on the U-shaped locating piece: heating to 820-860 ℃, keeping the temperature for 80-120 min, and cooling the temperature of the positioning piece to normal room temperature by using any one of oil, water and low-temperature alkali liquor as a cooling medium after the heat preservation is finished;
step 4: annealing treatment is carried out on the U-shaped positioning piece: the temperature is increased to 360-420 ℃, the heat preservation time is 130-180 min, and after the heat preservation is finished, air can be used as a cooling medium to cool the temperature of the positioning piece to normal room temperature;
step 5: disassembling a stay bar at the end of the notch of the U-shaped positioning piece;
step 6: finish machining is carried out on the notch of the U-shaped locating piece: and clamping the U-shaped positioning piece on the linear cutting to finish the notch, and carrying out finish machining on the notch for 2-3 times to ensure that the stress is released uniformly, wherein the last feeding of the linear cutting meets the machining precision of the notch parallelism of 0.02 and the notch width 34H 8.
2. The method for machining the U-shaped locating piece of the standard tool of the airplane according to claim 1 is characterized by comprising the following steps of: and 2, uniformly spot-welding three supporting rods for supporting the notch at the outer edge of the notch end of the U-shaped positioning piece, wherein one supporting rod is spot-welded at the end, and one supporting rod for supporting the notch is spot-welded at the middle position of the end supporting rod and the root of the U-shaped positioning piece at two sides.
3. The method for machining the U-shaped locating piece of the standard tool of the airplane according to claim 1 is characterized by comprising the following steps of: the U-shaped locating piece is applied to a vertical-tail standard tool, the width of a notch of the U-shaped locating piece is processed to 24mm according to a notch design value of the U-shaped locating piece by 34mm, machining allowance is reserved on two sides of the notch of the U-shaped locating piece, single-side machining allowance is 5mm, machining allowance is reserved on two sides of the root of the notch of the U-shaped locating piece within a height range of 1/5 of the root of the notch of the U-shaped locating piece to 30mm, and single-side machining allowance is 2mm.
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