CN114289561B - Large aluminum alloy cabin part shape correction tool and method - Google Patents
Large aluminum alloy cabin part shape correction tool and method Download PDFInfo
- Publication number
- CN114289561B CN114289561B CN202111660640.1A CN202111660640A CN114289561B CN 114289561 B CN114289561 B CN 114289561B CN 202111660640 A CN202111660640 A CN 202111660640A CN 114289561 B CN114289561 B CN 114289561B
- Authority
- CN
- China
- Prior art keywords
- cabin
- aluminum alloy
- tool
- section
- piece
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Straightening Metal Sheet-Like Bodies (AREA)
- Forging (AREA)
Abstract
The invention relates to a large aluminum alloy cabin part shape correction tool and a method, belongs to the technical field of machining, and solves the problem that the existing cold shape correction or hot shape correction method cannot solve the problem that the large aluminum alloy cabin part is deformed locally. A large aluminum alloy cabin piece shape correcting tool comprises a cabin inner wall supporting component and a cabin outer wall supporting component; the cabin inner wall supporting assembly comprises at least one first supporting tool, and the first supporting tool is arranged in the cabin barrel and is used for supporting the inner space of the large aluminum alloy cabin piece; the cabin outer wall supporting assembly comprises at least one second supporting tool and at least one third supporting tool; the second supporting tool is arranged outside the cabin section cylinder body and is used for supporting the appearance surface of the concave area of the aluminum alloy cabin section piece; the third support tool is sleeved on the appearance surface of the aluminum alloy cabin section piece. The tool and the method improve the precision of the large aluminum alloy cabin section piece and meet the precision index requirements of the large aluminum alloy cabin section piece in the field of manufacturing high-end equipment such as aerospace and the like.
Description
Technical Field
The invention belongs to the technical field of machining, and particularly relates to a large aluminum alloy cabin part shape correcting tool and method.
Background
The aluminum alloy has the advantages of low density, high specific strength, corrosion resistance, excellent electric conduction and heat conduction performance and the like, is widely applied to the aerospace field, and the bearing structures such as the cabin section of the aircraft and the like mainly comprise the aluminum alloy. In order to meet the requirement of light weight, the aluminum alloy cabin sections are mostly of special-shaped surface structures. The structure is easy to form residual stress with asymmetric distribution characteristics in the processing procedures of turning, welding and the like due to the weak rigidity and the sensitivity of shape accuracy to temperature and stress, and the aluminum alloy cabin section part is directly caused to generate local deformation with different degrees. The cabin section is an important component part on the spacecraft, and the assembly and the flying performance of the spacecraft are directly influenced by the size precision of the cabin section, so that the engineering has higher size requirements on cabin section parts. The deformation of the cabin section can be repaired by adopting a shape correction method, so that the scrapping of parts is avoided.
The current common shaping methods include cold shaping and hot shaping. The cold correction is mainly to correct the deformation of the part by using mechanical external force. The thermal correction mainly uses the stress relaxation principle to eliminate the deformation of the parts. For the local deformation condition of the aluminum alloy part, a cold shaping method is adopted, mechanical force is locally applied to the deformed part at room temperature, and larger rebound and residual stress and even fracture are generated in the shaping process; and (3) carrying out heat treatment on the part again under the high-temperature condition by adopting a heat correction method, correcting deformation by using a stress relaxation principle, and causing deformation of other parts due to the excessively high temperature, thereby affecting the mechanical properties of the part. The current common shape correction method can not solve the problem of local deformation of aluminum alloy parts.
Disclosure of Invention
In view of the analysis, the invention provides a large aluminum alloy cabin part shape correction tool and a large aluminum alloy cabin part shape correction method with the height of more than 1 meter and the diameter of more than 0.5 meter, wherein a cold shape correction and hot shape correction combined method is adopted according to the size and deformation condition of the part, acting force is applied under the room temperature condition, stress removal annealing treatment is carried out under the stress effect, the deformation of the part is corrected while the stress is removed, and the dimensional accuracy of the part is improved.
The aim of the invention is mainly realized by the following technical scheme:
the invention provides a large aluminum alloy cabin piece shape correcting tool which comprises a cabin inner wall supporting component and a cabin outer wall supporting component; the cabin inner wall supporting assembly comprises at least one first supporting tool, and the first supporting tool is arranged in the cabin barrel and is used for supporting the inner space of the large aluminum alloy cabin piece;
the cabin outer wall supporting assembly comprises at least one second supporting tool and at least one third supporting tool;
the second supporting tool is arranged outside the cabin section cylinder body and is used for supporting the appearance surface of the concave area of the aluminum alloy cabin section piece; the third support tool is sleeved on the appearance surface of the aluminum alloy cabin section piece.
Further, the first support tool comprises a first pressing block, a first screw rod, a nut, a second screw rod and a second pressing block;
the outer end surfaces of the first pressing block and the second pressing block are in contact with the inner wall of the large aluminum alloy cabin section piece, and the shape of the outer end surface is the same as the inner wall surface of the large aluminum alloy cabin section piece;
the two ends of the nut are respectively matched with one end of the first screw rod and one end of the second screw rod, so that the first screw rod and the second screw rod can shrink or stretch out simultaneously.
Further, the first screw rod and the first pressing block and the second screw rod and the second pressing block are in convex-concave self-adaptive fit.
Further, the first screw rod and the matching ends of the first pressing block, the second screw rod and the second pressing block are spherical pressure heads, and pits are correspondingly matched at the center positions of the first pressing block and the second pressing block.
Further, the third support tool is formed by connecting a first cabin section external adapting section and a second cabin section external adapting section, and two ends of the first cabin section external adapting section and two ends of the second cabin section external adapting section are respectively connected through bolt assemblies.
Further, a limiting block is arranged between the connecting part of the first cabin section external adapting section and the second cabin section external adapting section.
Further, the limiting piece is a hollow column, and the limiting piece penetrates through a bolt in the bolt assembly.
Further, the first support tool, the second support tool and the third support tool are made of 45# steel, and are subjected to quenching and tempering heat treatment.
In addition, the invention also provides a method for correcting the shape of the large aluminum alloy cabin section piece, which comprises the following steps:
step 1, designing and manufacturing a large aluminum alloy cabin piece shape correcting tool;
step 2, assembling and annealing a large aluminum alloy cabin piece shaping tool;
and 3, measuring after the large aluminum alloy cabin piece is shaped.
In the step 2, the annealing treatment is that the material is sent into an annealing furnace at room temperature, the temperature is raised to 120+/-10 ℃ at the speed of 4-7 ℃/min, the heat is preserved for 4 hours, and then the furnace door is opened for air cooling to the room temperature.
Compared with the prior art, the invention can at least realize one of the following technical effects:
(1) According to the large aluminum alloy cabin part shape correcting tool and method provided by the invention, the tool for the large aluminum alloy cabin part is designed, the mechanical pre-tightening force is applied in advance to perform preliminary shape correction on the deformation part, so that the deformation amount is reduced, and the pre-tightening force can reduce the deformation caused by stress; and then carrying out low-temperature stress relief annealing treatment on the part under the stress effect, correcting the deformation of the part while removing the stress, and improving the dimensional accuracy of the part.
(2) By utilizing the tool and the method provided by the invention, the problem of deformation of a large aluminum alloy cabin section part with the height of more than 1 meter and the diameter of more than 0.5 meter can be solved, the forming efficiency of the part is improved, the deformation of the part caused by the processing and testing processes is reduced, the production period of the part is shortened, the manufacturing cost is reduced, and the production efficiency is improved.
(3) By the aid of the tool and the method, the precision of the large aluminum alloy cabin section piece with the height of more than 1 meter and the diameter of more than 0.5 meter is improved, and the precision index requirements of the large aluminum alloy cabin section piece in the field of manufacturing high-end equipment such as aerospace are met.
Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention may be realized and attained by the structure particularly pointed out in the written description and drawings.
Drawings
The drawings are only for purposes of illustrating particular embodiments and are not to be construed as limiting the invention, like numbers referring to like parts throughout the drawings.
FIG. 1 is a block diagram of a first support tooling;
FIG. 2 is a schematic view of section A-A of FIG. 1;
FIG. 3 is a block diagram of a screw in the first support tooling;
FIG. 4 is an assembly view of a second support tooling and a third support tooling;
FIG. 5 is a top view of the third support tooling of FIG. 4;
FIG. 6 is a front view of a deformation of a large aluminum alloy cabin piece before shape correction;
FIG. 7 is a left side view of a deformation of a large aluminum alloy cabin piece before shape correction;
FIG. 8 is a front view of a large aluminum alloy cabin piece dimensional assembly;
FIG. 9 is a left side view of a dimensional assembly of a large aluminum alloy cabin segment piece;
in the figure, 1-first support tool, 11-first briquetting, 12-first screw rod, 13-nut, 14-second screw rod, 15-second briquetting, 2-second support tool, 3-third support tool, 31-first cabin section external adaptation section, 32-second cabin section external adaptation section, 33-bolt assembly, 34-limiting block, 35-rib plate, 4-large-scale aluminum alloy cabin section piece.
Detailed Description
The following describes a large aluminum alloy bay piece sizing fixture and method in further detail in connection with specific embodiments, which are for comparison and explanation purposes only, and the invention is not limited to these embodiments.
The large-scale aluminum alloy cabin section piece is widely applied to the aerospace field, and fig. 6 and 7 are schematic structural diagrams of the aluminum alloy cabin section piece, wherein the diameter is 1000mm, the height is 1426mm, the wall thickness is 5mm, the cabin section piece is of a hollow cylindrical structure with two open ends, the cylindrical structure is provided with an indent region, the indent region is formed by integrally and radially indent part of a circumferential section, and the diameter of the cylinder body is convergent along the axial direction of the cylinder body. The structure is easy to form residual stress with asymmetric distribution characteristics in the processing procedures of turning, welding and the like due to the weak rigidity and the sensitivity of shape accuracy to temperature and stress, and the aluminum alloy cabin section part is directly caused to generate local deformation with different degrees. The cabin section is an important component part on the spacecraft, and the assembly and the flying performance of the spacecraft are directly influenced by the size precision of the cabin section, so that the engineering has higher size requirements on cabin section parts.
Aiming at the deformation cabin piece with complex shape, the large aluminum alloy cabin piece shape correcting tool provided by the invention comprises a cabin inner wall supporting component and a cabin outer wall supporting component;
the cabin inner wall supporting assembly comprises at least one first supporting tool 1; the first supporting tool 1 is arranged in the cabin barrel and is used for supporting the inner space of the aluminum alloy cabin piece 4;
the cabin outer wall supporting assembly comprises at least one second supporting tool 2 and at least one third supporting tool 3;
the second supporting tool 2 is arranged outside the cabin section cylinder body and is used for supporting the concave area outline surface of the aluminum alloy cabin section piece 4; the third supporting tool 3 is sleeved on the appearance surface of the aluminum alloy cabin section piece 4.
The aluminum alloy cabin piece shape correcting tool adopts the combination of the cabin inner wall supporting component and the cabin outer wall supporting component.
Specifically, as shown in fig. 1-2, the first support tool 1 includes a first press block 11, a first screw 12, a nut 13, a second screw 14, and a second press block 15;
the two ends of the nut 13 are respectively matched with one end of the first screw rod 12 and one end of the second screw rod 14, and the first screw rod 12 and the second screw rod 14 are simultaneously contracted or extended by screwing in or screwing out the first screw rod 12 and the second screw rod 14.
The other end of the first screw 12 is connected with the first pressing block 11, and the other end of the second screw 14 is connected with the second pressing block 15.
The first support frock 1 is cabin section inner wall supporting component, arranges the cabin section barrel inside in, is used for supporting the inner space of aluminum alloy cabin section spare 4, when first support frock 1 and aluminum alloy cabin section spare 4 are assembled, in order to maintain the cabin section inner wall and can form stable bearing structure with the cabin section inner wall, the outer terminal surface shape and the large-scale aluminum alloy cabin section spare 4 of the outer terminal surface shape of first briquetting 11, the second briquetting 15 of contact with the cabin section inner wall are the same.
Specifically, the first pressing block 11 and the second pressing block 15 each comprise a rectangular inner pressing block and a rectangular outer pressing block which are tightly combined, such as a square shape, wherein the inner pressing blocks are contacted and matched with a screw rod, and the screw rod is perpendicular to the contact surface of the inner pressing blocks; the outer pressing block is contacted and matched with the inner wall of the cabin section, and the contact surface of the outer pressing block is a protective pressing block imitating the inner shape surface of the cabin section.
In the invention, the other end of the first screw rod 12 is connected with the first pressing block 11, the other end of the second screw rod 14 is connected with the second pressing block 15, and considering the convenience of assembling the first pressing block 11 and the second pressing block 15 with the screws, the first screw rod 12 and the second screw rod 14 both comprise a thread section and a smooth section, the thread section is matched with the nut 13, and the smooth section is matched with the pressing block. The smooth section is smaller in diameter than the threaded section so that the smooth section is free to pass into and out of the nut 13 during the calibration.
Accordingly, in order to facilitate the operation in the shaping, a convex-concave self-adaptive fit is provided between the first screw 12 and the first press block 11, and between the second screw 14 and the second press block 15. Illustratively, the mating ends of the smooth section of the screw and the press block are spherical indenters, and a pit matching the spherical indenters is correspondingly arranged in the center of the press block, and fig. 3 is a structural diagram of the second screw 14. The pressing blocks at the two ends of the first supporting tool act on the inner surface of the large aluminum alloy cabin part 4 to form two acting forces in opposite directions to open the inner cavity of the cabin part, so that the contact surface of the first screw 12 and the pressing block in the first pressing block 11 and the contact surface of the second screw 14 and the pressing block in the second pressing block 15 are in a vertical relationship. However, the shape of the cabin piece is complex and changeable, so the area and the shape of the outer pressing blocks of the first pressing block 11 and the second pressing block 15 which are contacted with the inner shape of the large-scale aluminum alloy cabin piece are determined according to the shape of the contact surface of the cabin piece. In order to achieve simultaneous contraction or simultaneous expansion of the first screw 12 and the second screw 14, the threads of the first screw 12 and the second screw 14 are provided as threads of opposite rotational directions, if the first screw 12 is a left-handed thread, the second screw 14 is a right-handed thread; conversely, if the first screw 12 is right-handed, the second screw 14 is left-handed. The length of the nut 13 is determined according to the actual condition of the shape correcting workpiece, and the sum of the lengths of the first screw 12 and the second screw 14 is illustratively not more than 1/2 of the length of the nut 13. In order to match the first screw 12 and the second screw 14, threads with opposite rotation directions are arranged at two ends of the nut. When in correction, the screws at the two ends synchronously apply compression or relaxation by rotating the hexagonal nuts, so that the screws at the two ends shrink to be smaller than the inner cavity of the correction front cabin section for the convenience of assembly before correction; in order to meet the requirement of shape correction, the length of the screws at the two ends when the screws are extended is not smaller than the size of the inner cavity of the shape-correcting rear cabin section piece. The third support tool 3 is a cabin outer wall support assembly and is sleeved on the appearance surface of the aluminum alloy cabin part 4 and used for external dimension of the aluminum alloy cabin part. Specifically, the third support fixture 3 is composed of a first cabin section external adapting section 31 and a second cabin section external adapting section 32, and two ends of the first cabin section external adapting section 31 and two ends of the second cabin section external adapting section 32 are respectively connected through bolt assemblies.
In order to reinforce the first cabin exterior adapting section 31 and the second cabin exterior adapting section 32, rib plates are added to the transition sections of the arc portions and the connecting portions of the first cabin exterior adapting section 31 and the second cabin exterior adapting section 32. Illustratively, 35 in fig. 4 and 5 is one of the ribs of the first cabin outer adapting section 31, and the first cabin outer adapting section 31 and the second cabin outer adapting section 32 have two ribs, respectively.
Wherein the second cabin exterior adapting section 32 comprises an aluminum alloy cabin piece conformal arc section and a straight line section, the length of the straight line section is the same as the width of the concave area. The second cabin outer adapting section 32 is sleeved on the outer wall surface of the aluminum alloy cabin and spans the concave area of the aluminum alloy cabin. Because the third support tool 3 needs to be in shape matching with the first support tool 1 and the second support tool 2, the first support tool 1 is arranged in the cabin barrel and used for supporting the inner space of the aluminum alloy cabin piece 4, the second support tool 2 is arranged outside the cabin barrel and used for supporting the shape surface of the concave area of the aluminum alloy cabin piece 4, in order to prevent the first support tool 1 and the second support tool 2 from excessively correcting the shape and enlarge the shape surface of the aluminum alloy cabin piece 4, the third support tool 3 is sleeved on the shape surface of the aluminum alloy cabin piece 4 so as to maintain the size standard of the shape surface.
In addition, because the first support tooling 1 needs to be matched with the third support tooling 3 in shape, the axial height of the first pressing block 11 outer pressing block and the second pressing block 15 outer pressing block of the first support tooling 1 along the axial lead of the aluminum alloy cabin section piece 4 is not greater than the height of the external adapting section of the cabin section of the third support tooling 3, and the lengths of the first pressing block 11 outer pressing block and the second pressing block 15 outer pressing block are determined according to the circumferential length of the aluminum alloy cabin section piece 4 needing to be shaped. The length and width dimensions of the inner pressing blocks of the first pressing block 11 and the inner pressing blocks of the second pressing block 15 are about 1/2-2/3 of that of the outer pressing block so as to maintain the balance of the pressure of each point of the contact surface during the correction. The first cabin section external adapting section 31 is sleeved on the convex arc part of the aluminum alloy cabin section piece, and two ends of the first cabin section external adapting section 31 are connected with two ends of the second cabin section external adapting section 32 to form a closed annular external surface for jointly maintaining the aluminum alloy cabin section piece.
The second support tool 2 is a cabin outer wall support assembly and is arranged outside the cabin barrel and used for supporting the concave area appearance surface of the aluminum alloy cabin piece 4. Therefore, the second supporting tool 2 comprises the contour following section of the concave area so as to realize effective supporting of the concave area.
The second support tooling 2 is in shape-following contact with the shape surface of the concave area of the outer wall of the cabin section, a contact surface is arranged between the second support tooling 2 and the third support tooling 3, and the contact surface is designed to be a plane for facilitating the production and shape correction of the tooling, so the second support tooling 2 further comprises a plane section, and in addition, a reinforcing rib is arranged inside a cavity of the second support tooling 2 for reinforcing the bearing capacity of the second support tooling 2 during shape correction.
When the support device is used, the first support tools 1 and the second support tools 2 are required to be matched with the third support tools 3 in shape, namely, each first support tool 1 is required to be provided with one third support tool 3 and one-to-one correspondence common shape, and each second support tool 2 is required to be provided with one first support tool 1, one third support tool 3 and one-to-one correspondence common shape.
Specifically, when the shape of the concave area of the aluminum alloy cabin part is required to be in a shape, a second supporting tool 2 is assembled in the concave area of the aluminum alloy cabin part, a first supporting tool 1 is assembled in the position corresponding to the concave area in the cabin barrel, and a third supporting tool 3 is sleeved on the shape of the concave area of the aluminum alloy cabin part.
When the number of the appearance surfaces of the concave areas of the aluminum alloy cabin piece to be maintained is multiple, the second support tools 2 are assembled in the concave areas of the aluminum alloy cabin piece, the first support tools 1 are assembled in the positions corresponding to the concave areas in the cabin barrel, and the third support tools 3 are sleeved on the appearance surfaces of the corresponding positions of the concave areas of the aluminum alloy cabin piece.
When the number of the outline surfaces of the concave areas of the aluminum alloy cabin part needing dimension is 1 or more, a second support tool 2 is assembled in the concave area of the aluminum alloy cabin part, a first support tool 1 is assembled in the position corresponding to the concave area in the cabin barrel, and a third support tool 3 is sleeved on the outline surface of the position corresponding to the concave area of the aluminum alloy cabin part; and one or more first supporting tools 1 are arranged in the aluminum alloy cabin section parts of other non-concave areas needing dimension, and one or more third supporting tools 3 are sleeved outside the aluminum alloy cabin section parts of the corresponding parts.
Exemplary, as shown in fig. 4, an assembly diagram of the second support tool and the third support tool is shown in fig. 5, which is a top view of the third support tool, the third support tool is provided with a first cabin section external adapting section and a second cabin section external adapting section according to the external surface of the large aluminum alloy cabin section part, two parts are connected with two ends through a bolt assembly, the shape of the bolt assembly is similar to that of a throat hoop, and the number of the bolt assemblies is determined according to the axial height of the third support tool. Illustratively, 33 in fig. 4 and 5 is one set of bolt assemblies, and 2 sets of bolt assemblies are used at each end of the first cabin outer adapting section 31 and the second cabin outer adapting section 32, for a total of 4 sets of bolt assemblies.
Specifically, the third support fixture 3 is provided with a stopper between the connection parts of the first cabin section external adapting section 31 and the second cabin section external adapting section 32. The limiting block has the function of preventing the dimension force from being excessively large, leaving partial gaps, and being convenient for effective compaction. Illustratively, the stop is a hollow cylinder through which the bolt in the bolt assembly passes. In fig. 5, 34 is one of the limiting members, and the number of the limiting members is equal to the number of the bolt assemblies, namely, 4 limiting members are provided at the connecting portions of the two ends of the first cabin section external adapting section 31 and the second cabin section external adapting section 32.
Specifically, the materials of the first support tool 1, the second support tool 2 and the third support tool 3 are 45# steel, and the materials are subjected to tempering heat treatment.
The invention also provides a shape correction method adopting the large aluminum alloy cabin part tool, which comprises the following steps:
step 1, designing and manufacturing a large aluminum alloy cabin piece shape correcting tool;
step 2, assembling and annealing a large aluminum alloy cabin piece shaping tool;
and 3, measuring after the large aluminum alloy cabin piece is shaped.
In the step 1, according to the specific requirement that the large-scale aluminum alloy cabin section piece needs to be shaped, the first support tool 1, the second support tool 2 and the third support tool 3 are designed and manufactured, and the number and the size of each part of tools are determined according to the actual condition of the shaping.
In the step 2, the sizing tool and the large aluminum alloy cabin section piece are cleaned and dried by acetone, assembled together and put into an annealing furnace for annealing treatment. Specifically, the annealing treatment is that the material is sent into an annealing furnace under the room temperature condition, the temperature is raised to 120+/-10 ℃ at the speed of 4-7 ℃/min, the heat is preserved for 4 hours, and then the furnace door is opened for air cooling to the room temperature.
In step 3, a profile surface scanning instrument is used for measuring the large-sized aluminum alloy cabin section part, and the precision machining requirement is confirmed to be met.
By using the shape correction method of the large aluminum alloy cabin part tool, the deformation is reduced to 1mm, the production efficiency is improved, the production cost is reduced, the precision of the large aluminum alloy cabin part is improved, and the precision index requirements of the large aluminum alloy cabin part in the field of manufacturing high-end equipment such as aerospace are met.
Example 1
Fig. 6 and 7 are views of a large aluminum alloy cabin part on a certain spacecraft, wherein the large aluminum alloy cabin part is provided with two openings at two ends, the diameter is 1000mm, the height is 1426mm, the wall thickness is 5mm, an inverted U-shaped concave area is formed on the appearance surface of one end, the inverted U-shaped concave area can shrink 3-4 mm inwards in the production and processing process, and the back surface collapses downwards by 1-2 mm, so that the size of a part is out of tolerance.
The method comprises the following steps of:
step 1, designing and manufacturing a first supporting tool 4 sleeve I, II, III and IV by using 45# steel according to the size of the large aluminum alloy cabin section piece, and a second supporting tool 1 sleeve and a third supporting tool 4 sleeve A, B, C, D;
the sizes of the 4 sets of first supporting tools are respectively as follows:
and I: the thickness of the first pressing block is 20mm, the length is 150mm, the width is 150mm, the thickness of the outer pressing block is 20mm, the length is 300mm, and the width is 300mm; the length of the first screw rod 12 is 50mm, the right-handed thread M12×1.5mm, and the head is a hemispherical pressure head; the length of the second screw 14 is 50mm, the left-hand thread M12×1.5mm, and the head is a hemispherical press head; the nut is hexagonal, the side length is 15mm, the nut length is 520mm, one end internal thread is matched with the first screw rod 12, and the other end internal thread is matched with the second screw rod 14; the thickness of the second pressing block is 20mm, the length is 150mm, the width is 150mm, the thickness of the outer pressing block is 20mm, the length is 300mm, and the width is 300mm.
II: the thickness of the first pressing block is 20mm, the length is 150mm, the width is 150mm, the thickness of the outer pressing block is 20mm, the length is 300mm, and the width is 300mm; the length of the first screw rod 12 is 30mm, the right-handed thread M12×1.5mm, and the head is a hemispherical pressure head; the length of the second screw 14 is 50mm, the left-hand thread M12×1.5mm, and the head is a hemispherical press head; the nut is hexagonal, the side length is 15mm, the nut length is 220mm, one end internal thread is matched with the first screw rod 12, and the other end internal thread is matched with the second screw rod 14; the thickness of the second pressing block is 20mm, the length is 150mm, the width is 150mm, the thickness of the outer pressing block is 20mm, the length is 300mm, and the width is 300mm.
III: the thickness of the first pressing block is 20mm, the length is 150mm, the width is 150mm, the thickness of the outer pressing block is 20mm, the length is 300mm, and the width is 300mm; the length of the first screw rod 12 is 30mm, the right-handed thread M12×1.5mm, and the head is a hemispherical pressure head; the length of the second screw 14 is 50mm, the left-hand thread M12×1.5mm, and the head is a hemispherical press head; the nut is hexagonal, the side length is 15mm, the nut length is 240mm, one end internal thread is matched with the first screw rod 12, and the other end internal thread is matched with the second screw rod 14; the thickness of the second pressing block is 20mm, the length is 150mm, the width is 150mm, the thickness of the outer pressing block is 20mm, the length is 300mm, and the width is 300mm.
IV: the thickness of the first pressing block is 20mm, the length is 150mm, the width is 150mm, the thickness of the outer pressing block is 20mm, the length is 300mm, and the width is 300mm; the length of the first screw rod 12 is 30mm, the right-handed thread M12×1.5mm, and the head is a hemispherical pressure head; the length of the second screw 14 is 50mm, the left-hand thread M12×1.5mm, and the head is a hemispherical press head; the nut is hexagonal, the side length is 15mm, the nut length is 260mm, one end internal thread is matched with the first screw rod 12, and the other end internal thread is matched with the second screw rod 14; the thickness of the second pressing block is 20mm, the length is 150mm, the width is 150mm, the thickness of the outer pressing block is 20mm, the length is 300mm, and the width is 300mm.
The 1 set of second support tool is a cabin section piece inverted U-shaped opening support tool, and the specific machining size is as follows: the wall thickness is 20mm, the height is 50mm, the length of the plane section is 500mm, the arc length of the top is 250mm, the arc length of the two sides is 350mm, and the length of the middle reinforcing rib is 300mm.
4 third support tooling dimensions:
a: the thickness of the external adapting section of the first cabin section is 20mm, the arc length is 1300mm, and the height is 50mm; the thickness of the external adapting section of the second cabin section is 20mm, the length of the plane section is 500mm, the arc lengths of the two sides of the plane section are 400mm, and the height is 50mm; the 4 groups of bolt assemblies are M12 and have the length of 50mm; the limiting block is a hollow cylinder, the outer diameter is 15mm, the inner diameter is 13mm, and the length is 30mm.
B: the thickness of the external adapting section of the first cabin section is 20mm, the arc length is 1400mm, and the height is 50mm; the external adapting section of the second cabin section is 20mm thick, 1000mm long and 50mm high; the 4 groups of bolt assemblies are M12 and have the length of 50mm.
C: the thickness of the external adapting section of the first cabin section is 20mm, the arc length is 1500mm, and the height is 50mm; the external adapting section of the second cabin section is 20mm thick, 1100mm long and 50mm high; the 4 groups of bolt assemblies are M12 and have the length of 50mm.
D: the thickness of the outer adapting section of the first cabin section is 20mm, the arc length is 1650mm, and the height is 50mm; the thickness of the outer adapting section of the second cabin section is 20mm, the arc length is 1650mm, and the height is 50mm; the 4 groups of bolt assemblies are M12 and have the length of 50mm.
Step 2, assembling and annealing a large aluminum alloy cabin piece shaping tool;
fig. 8 and 9 are assembly drawings of a tool for correcting the shape of a large aluminum alloy cabin section piece. Cleaning and airing the sizing tool and the large aluminum alloy cabin section piece by using acetone; a first support tool I is arranged in a cabin cavity of the cabin section part corresponding to the cabin section part, and a third support tool A is sleeved on the outer wall hoop 1 of the cabin body corresponding to the cabin section part; and first support tools II, III and IV are arranged in the cabin of the rest cabin section parts needing to be corrected, and a third support tool B, C, D is sleeved corresponding to the cabin outer wall hoop 3.
And (3) feeding the materials into an annealing furnace at room temperature, heating to 120 ℃ at a speed of 5 ℃/min, preserving heat for 4 hours, and then opening a furnace door for air cooling to room temperature.
And 3, measuring after the large aluminum alloy cabin piece is shaped.
And measuring the large aluminum alloy cabin section part by using a surface scanning instrument, wherein the deformation is in the range of 0.1-0.8 mm.
The present invention is not limited to the above-mentioned embodiments, and any changes or substitutions that can be easily understood by those skilled in the art within the technical scope of the present invention are intended to be included in the scope of the present invention.
Claims (4)
1. The large aluminum alloy cabin piece shaping tool is characterized by comprising a cabin inner wall supporting component and a cabin outer wall supporting component, wherein the large aluminum alloy cabin piece is an aluminum alloy cabin piece with the height of more than 1 meter and the diameter of more than 0.5 meter; the cabin inner wall supporting assembly comprises at least one first supporting tool (1), and the first supporting tool (1) is arranged in the cabin barrel and is used for supporting the inner space of the large aluminum alloy cabin piece (4);
the cabin outer wall supporting assembly comprises at least one second supporting tool (2) and at least one third supporting tool (3);
the second supporting tool (2) is arranged outside the cabin section cylinder body and is used for supporting the shape surface of the concave area of the aluminum alloy cabin section piece (4); the third supporting tool (3) is sleeved on the appearance surface of the aluminum alloy cabin section piece (4);
the first supporting tool (1) comprises a first pressing block (11), a first screw rod (12), a nut (13), a second screw rod (14) and a second pressing block (15);
the outer end surfaces of the first pressing block (11) and the second pressing block (15) are in contact with the inner wall of the large aluminum alloy cabin section piece (4), and the shape of the outer end surface is the same as the inner wall surface of the large aluminum alloy cabin section piece (4);
two ends of the nut (13) are respectively matched with one end of the first screw (12) and one end of the second screw (14), so that the first screw (12) and the second screw (14) shrink or stretch out simultaneously;
the first screw (12) and the first pressing block (11) and the second screw (14) and the second pressing block (15) are in convex-concave self-adaptive fit;
the third support tool (3) is formed by connecting a first cabin section external adapting section (31) and a second cabin section external adapting section (32), and two ends of the first cabin section external adapting section (31) and two ends of the second cabin section external adapting section (32) are respectively connected through bolt assemblies;
a limiting block is arranged between the connecting part of the first cabin section external adapting section (31) and the second cabin section external adapting section (32);
and the first support tool (1), the second support tool (2) and the third support tool (3) are made of 45# steel, and subjected to quenching and tempering heat treatment.
2. The large aluminum alloy cabin piece sizing tool according to claim 1, wherein the matching ends of the first screw (12) and the first pressing block (11), the second screw (14) and the second pressing block (15) are spherical pressing heads, and pits are correspondingly matched in the central positions of the first pressing block (11) and the second pressing block (15).
3. The tooling for sizing a large aluminum alloy cabin piece according to claim 1, wherein the limiting block is a hollow column, and the limiting block is penetrated in a bolt in the bolt assembly.
4. A method for shaping a large aluminum alloy cabin part, which is characterized by adopting the large aluminum alloy cabin part shaping tool as claimed in any one of claims 1-3, and comprising the following steps:
step 1, designing and manufacturing a large aluminum alloy cabin piece shape correcting tool;
step 2, assembling and annealing a large aluminum alloy cabin piece shaping tool;
step 3, measuring after the large aluminum alloy cabin piece is shaped;
in the step 2, the annealing treatment is that the material is sent into an annealing furnace at room temperature, the temperature is raised to 120+/-10 ℃ at the speed of 4-7 ℃/min, the heat is preserved for 4 hours, and then the material is cooled to the room temperature by opening a furnace door.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111660640.1A CN114289561B (en) | 2021-12-30 | 2021-12-30 | Large aluminum alloy cabin part shape correction tool and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111660640.1A CN114289561B (en) | 2021-12-30 | 2021-12-30 | Large aluminum alloy cabin part shape correction tool and method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114289561A CN114289561A (en) | 2022-04-08 |
| CN114289561B true CN114289561B (en) | 2023-10-17 |
Family
ID=80974088
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111660640.1A Active CN114289561B (en) | 2021-12-30 | 2021-12-30 | Large aluminum alloy cabin part shape correction tool and method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114289561B (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2068277A (en) * | 1980-01-24 | 1981-08-12 | Transequip Ltd | Method and apparatus for straightening plate pallets |
| JPS59120014U (en) * | 1983-02-03 | 1984-08-13 | トヨタ自動車株式会社 | Trimming press type with strain relief mechanism |
| US5007279A (en) * | 1989-03-16 | 1991-04-16 | Miall Derek L | Cylinder head straightener |
| FR2691387A1 (en) * | 1992-05-21 | 1993-11-26 | Gaz De France | Tool for restoring cylindrical shape to plastic pipe which has been deformed - has two concave cylindrical jaws operated by screw mechanism or power cylinder |
| RU91901U1 (en) * | 2009-10-20 | 2010-03-10 | Государственное образовательное учреждение высшего профессионального образования Нижегородский государственный технический университет им. Р.Е. Алексеева (НГТУ) | STAND FOR EDITING CAR DRIVES |
| KR20100130424A (en) * | 2009-06-03 | 2010-12-13 | 주식회사 스틸플라워 | Device for correcting round of large caliber steel pipe |
| CN108118271A (en) * | 2017-12-08 | 2018-06-05 | 北京星航机电装备有限公司 | A kind of allotype aluminum alloy bay section method for controlling heat treatment deformation |
| CN207655672U (en) * | 2017-12-26 | 2018-07-27 | 大连船舶重工集团舾装有限公司 | Elbow port rounding machine |
| CN214263356U (en) * | 2020-12-15 | 2021-09-24 | 西南铝业（集团）有限责任公司 | Pressure straightening auxiliary device for U-shaped aluminum alloy hanger |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150013406A1 (en) * | 2013-07-09 | 2015-01-15 | General Electric Company | System and method for removing dents from a wind turbine tower |
| CN110238241B (en) * | 2019-06-27 | 2020-07-17 | 合肥工业大学 | Multi-cavity special-shaped double-layer thin-wall section pipe fitting correction robot |
-
2021
- 2021-12-30 CN CN202111660640.1A patent/CN114289561B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2068277A (en) * | 1980-01-24 | 1981-08-12 | Transequip Ltd | Method and apparatus for straightening plate pallets |
| JPS59120014U (en) * | 1983-02-03 | 1984-08-13 | トヨタ自動車株式会社 | Trimming press type with strain relief mechanism |
| US5007279A (en) * | 1989-03-16 | 1991-04-16 | Miall Derek L | Cylinder head straightener |
| FR2691387A1 (en) * | 1992-05-21 | 1993-11-26 | Gaz De France | Tool for restoring cylindrical shape to plastic pipe which has been deformed - has two concave cylindrical jaws operated by screw mechanism or power cylinder |
| KR20100130424A (en) * | 2009-06-03 | 2010-12-13 | 주식회사 스틸플라워 | Device for correcting round of large caliber steel pipe |
| RU91901U1 (en) * | 2009-10-20 | 2010-03-10 | Государственное образовательное учреждение высшего профессионального образования Нижегородский государственный технический университет им. Р.Е. Алексеева (НГТУ) | STAND FOR EDITING CAR DRIVES |
| CN108118271A (en) * | 2017-12-08 | 2018-06-05 | 北京星航机电装备有限公司 | A kind of allotype aluminum alloy bay section method for controlling heat treatment deformation |
| CN207655672U (en) * | 2017-12-26 | 2018-07-27 | 大连船舶重工集团舾装有限公司 | Elbow port rounding machine |
| CN214263356U (en) * | 2020-12-15 | 2021-09-24 | 西南铝业（集团）有限责任公司 | Pressure straightening auxiliary device for U-shaped aluminum alloy hanger |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114289561A (en) | 2022-04-08 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105107917B (en) | A kind of tank Loadings On Hemispherical Shell manufacturing process for improving mechanical property | |
| CN107513677B (en) | A kind of spheroid shape face tank aluminium alloy Loadings On Hemispherical Shell method for controlling heat treatment deformation | |
| US20210362880A1 (en) | Adjustable internal support restraint device for roundness control of cabin component | |
| CN105107915A (en) | Technological method for precise spinning forming of large magnesium alloy thin-walled cylindrical part | |
| CN112475806B (en) | QCr0.8 alloy large-size conical-cylindrical ring forming process | |
| CN102489952A (en) | Method for manufacturing titanium alloy thick-wall pressure-resistant cylinder body | |
| CN106903204A (en) | Multi-angle conical shell rotary press modelling method | |
| CN107984175A (en) | A kind of processing method of ultra-thin titanium alloy spherical parts | |
| CN112775370A (en) | Short-process preparation method for titanium and titanium alloy pipes | |
| CN104894357A (en) | Method for preventing U-shaped gear part from machining deformation and supporting checking tool | |
| CN114289561B (en) | Large aluminum alloy cabin part shape correction tool and method | |
| KR100918612B1 (en) | The manufacturing method for a flow formed pressure vessel using a thick plate preform prepared by welding | |
| CN114290005A (en) | Machining deformation control device and method for thin-wall titanium alloy welded cylinder | |
| CN106956110A (en) | A kind of processing method of hexagon socket head cap screw | |
| CN110743979B (en) | Thermal bulging die for arc-shaped concave surface of titanium alloy thin-wall cylindrical part and working method | |
| CN109604966B (en) | Integral forming method for storage box barrel section with grid ribs in inner cavity | |
| CN111136121A (en) | Hot-expanding cold-forging repair device and repair method | |
| Guo et al. | Research on multi-pass hot spinning based on finite element simulation and experiment for aluminum alloy component | |
| CN112474856A (en) | Extruded section shape correction die and shape correction method thereof | |
| CN107723436A (en) | A kind of device and method for preventing heat treatment of workpieces deformation | |
| Guo et al. | Influence of mandrel on the forming quality of bending L-shaped hollow parts | |
| CN215657164U (en) | Clamp for shaping cotton spinning ring | |
| CN100519063C (en) | Clip method of flattener support roll outside lane | |
| CN210208123U (en) | Medical titanium alloy special-shaped wire hot drawing die | |
| CN112548010B (en) | Preparation method of titanium alloy elliptical ring material |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |