CN114130895A - Slide rail type-based shape correction process and device for airplane parts - Google Patents
Slide rail type-based shape correction process and device for airplane parts Download PDFInfo
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- 238000000034 method Methods 0.000 title claims abstract description 55
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- 229910001069 Ti alloy Inorganic materials 0.000 claims abstract description 122
- 239000000463 material Substances 0.000 claims abstract description 23
- 238000004806 packaging method and process Methods 0.000 claims abstract description 8
- 238000002360 preparation method Methods 0.000 claims abstract description 8
- 238000012216 screening Methods 0.000 claims abstract description 7
- 238000001514 detection method Methods 0.000 claims description 31
- 238000004513 sizing Methods 0.000 claims description 9
- 230000009467 reduction Effects 0.000 claims description 4
- 230000000994 depressogenic effect Effects 0.000 claims 2
- 238000004519 manufacturing process Methods 0.000 abstract description 8
- 239000011265 semifinished product Substances 0.000 abstract description 5
- 238000003825 pressing Methods 0.000 description 5
- 238000005520 cutting process Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 238000003754 machining Methods 0.000 description 4
- 238000007493 shaping process Methods 0.000 description 4
- 230000007704 transition Effects 0.000 description 4
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- 238000011160 research Methods 0.000 description 2
- 229910045601 alloy Inorganic materials 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D35/00—Combined processes according to or processes combined with methods covered by groups B21D1/00 - B21D31/00
- B21D35/002—Processes combined with methods covered by groups B21D1/00 - B21D31/00
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D37/00—Tools as parts of machines covered by this subclass
- B21D37/10—Die sets; Pillar guides
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
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Abstract
The invention relates to the technical field of airplane parts and discloses a slide rail-based shape correction process and a slide rail-based shape correction device for airplane parts, wherein the shape correction process and the slide rail-based shape correction device comprise titanium alloy, and the brand number of the titanium alloy is TB 2; the preparation process comprises the following working steps: the first step is as follows: screening materials; the second step is that: performing primary stamping; the third step: correcting the shape of the titanium alloy; the fourth step: secondary stamping; the fifth step: performing process notching; and a sixth step: and (6) detecting and packaging. According to the invention, a semi-finished product is obtained after the first stretching forming, meanwhile, because the radius of the fillet on the first stretching male die is larger, redundant parts are arranged at the corners of the titanium alloy during the stretching of the titanium alloy, so that the redundant parts at the fillet provide the deformation of the titanium alloy during the second stretching, the second stretching into a final part is facilitated, after the second stretching forming is finished, the quality of the part is effectively improved, a qualified part meeting the standard can be formed, and the success rate of aircraft part manufacturing is improved by performing 2 times of stretching forming on the titanium alloy.
Description
Technical Field
The invention relates to the technical field of airplane parts, in particular to a slide rail type-based shape correcting process and device for airplane parts.
Background
The aviation industry refers to industries engaged in research, development, manufacturing and other related services of aircraft, and products thereof include aircraft, engines, components, airborne equipment, and the like. The aviation industry is closely related to the status of the big country, China develops the aviation industry, enhances national defense strength of the country, is a powerful guarantee for national safety, and moreover, the development of the aviation industry promotes the promotion of scientific technology and national economic level. On the stage of competition in the world today, the powerful aviation industry is always an indispensable weapon. The aerospace industry is typically a high-tech, high-risk, high-value-added strategic industry that integrates knowledge-intensive, technology-intensive, and capital-intensive into a whole, and its design and manufacture involves numerous industries including machine manufacturing, electronics, materials engineering, automation, information software, instrumentation, and the like. In the world, the strong nations invest a large amount of capital and related resources for a long time to develop research on aeronautical science and technology. The powerful aviation industry is an important foundation for keeping the international social status of a country, is an important mark of the modern industrial level and the national economic strength, and is the concrete embodiment of the status of a large country.
Part of existing airplane parts in the market at present generally adopt a drop forming mode, and the drop forming is a sheet metal forming process for pressing a metal sheet into a required curved surface part by utilizing the impact of a drop hammer. The traditional process adopts single-time stretch forming, and easily has the defects of low production efficiency, high rejection rate, low part precision and the like.
Therefore, a slide rail type shape correcting process and device for airplane parts are provided.
Disclosure of Invention
The invention mainly solves the technical problems in the prior art and provides a slide rail-based shape correction process and device for airplane parts.
In order to achieve the purpose, the invention adopts the following technical scheme that the slide rail-based sizing process for the airplane parts comprises titanium alloy, wherein the titanium alloy is TB 2;
the preparation process comprises the following working steps:
the first step is as follows: screening materials;
the second step is that: performing primary stamping;
the third step: correcting the shape of the titanium alloy;
the fourth step: secondary stamping;
the fifth step: performing process notching;
and a sixth step: and (6) detecting and packaging.
Preferably, the titanium alloy in the first step has a size extending outward by 30mm with respect to the edge of the part, and the titanium alloy has an elastic modulus E of 66000MPa and a yield strength σs79Mpa, the poisson ratio of titanium alloy is 0.3, the shape factor of titanium alloy is 0.625, and R45＝0.748，R900.694, the stress-strain of the titanium alloy satisfies the equation σ K (e)0+ε)n。
Preferably, in the second step, the titanium alloy is placed in the die, the maximum hydraulic pressure is set to be 40-60MPa, the blank holder force is set to be 30-40KN, the punch stamping speed is set to be 5-8mm/s, the friction coefficient is set to be mu-0.05, the radius of the fillet on the first punch is 2 times of the radius of the fillet on the female die, and the downward moving distance of the first punch is two 1/2 times of the height of the part.
Preferably, in the third step, the side wall of the titanium alloy in the female die is punched once by the first punch at a side pressure of 40-60KN, a punch punching speed of 5-8mm/s and a friction coefficient of 0.05.
Preferably, in the fourth step, the titanium alloy is placed in the die, the maximum hydraulic pressure is set to be 40-60MPa, the clamping force is set to be 30-40KN, the punch stamping speed is set to be 5-8mm/s, the friction coefficient is set to be 0.05, the convex part of the second punch is completely the same as the shape of the inner part of the female die, the second punch moves downwards for the same distance as the height of the part, and the titanium alloy is completely stamped in one step.
Preferably, in the fifth step, the titanium alloy after the secondary stamping is placed into a drawn plate, a process hole is reserved in the drawn plate, the edge pressure is set to be 25-30KN, the stamping speed is set to be 5-8mm/s, the friction coefficient is set to be 0.05, and the part is cut out of the titanium alloy plate.
Preferably, in the sixth step, the minimum wall thickness and the maximum wall thickness of the part are detected, the reduction rate of the part is obtained, and if the reduction rate of the part is less than 30%, the part is qualified and packaged.
The utility model provides an aircraft spare part is with school shape device based on slide rail formula, includes base, detection device, pneumatic cylinder and controller, fixed mounting has the fixed plate on the lateral wall of base, and a lateral wall fixed mounting who is close to the base on the fixed plate has detection device, and the one end fixed mounting that detection device was kept away from to the top wall of base has the die, and pneumatic cylinder fixed mounting is close to a lateral wall top of base on the fixed plate, and the output fixed mounting of pneumatic cylinder has the connecting plate.
Preferably, the bottom of the connecting plate is fixedly provided with a first male die, the radius of a fillet of a downward convex part on the first male die is 2 times larger than that of a fillet of an internal concave part of the female die, the bottom wall surface of the connecting plate is fixedly provided with a second male die, the downward convex part on the second male die is attached to the internal concave part of the female die, and the controller is fixedly arranged on the side wall of the base.
Advantageous effects
The invention provides a slide rail type-based shape correction process and device for airplane parts. The method has the following beneficial effects:
(1) according to the slide rail type-based shape correction process and device for the aircraft parts, the molded surface of the transition mold keeps the molded surface curvature of the original part, and the fillet radius and the stretching depth of the convex mold and the concave mold are increased, so that the transition mold has the function of storing materials. Obtain semi-manufactured goods after the first stretch forming, simultaneously because fillet radius is great on the first tensile terrace die, so titanium alloy is when tensile, corner on the titanium alloy has unnecessary part, when making the second time tensile, fillet department has unnecessary part to provide titanium alloy's deformation, make things convenient for the second time to stretch into final part, after the secondary stretch forming, the part quality is improved effectively, can form the qualified part that accords with the standard, through carrying out 2 stretch forming to titanium alloy, the success rate of aircraft part preparation has been improved.
(2) According to the slide rail-based shape correction process and device for the aircraft parts, by increasing the edge pressing force, although the edge of the male die can inhibit the wrinkling trend of the titanium alloy, the tensile stress at the edge of the male die is increased, the flowing of materials is inhibited, the materials at the edge of the male die cannot smoothly flow into a round angle, the materials at the edge of the male die cannot be effectively supplied along with the gradual stretching of the materials, the internal materials of the parts can be obviously thinned, the tensile crack trend is increased, and the wall thickness distribution of the parts is uneven; the blank holder power reduces, and the edge tangential compressive stress of terrace die increases, and the trend of corrugating will increase, not only can influence the part and take shape the quality, still can increase the wearing and tearing of mould. Therefore, the edge pressing force is limited to be between 30KN and 40KN, and the forming quality of the part is prevented from being influenced.
(3) According to the slide rail type airplane part shape correcting process and device, the stamping speed is limited to be 5-8mm/s, the downward moving speed of the male die is increased, the titanium alloy can be molded in a short time, and the manufacturing speed of parts is increased.
(4) According to the slide rail type airplane part shape correcting process and device, the titanium alloy die after secondary drawing is placed into the drawn plate with the process holes, parts are cut off from the titanium alloy plate, the process holes and the process cuts are added at the positions with the maximum tensile stress, and in order to enable materials to flow reasonably, the shapes of the process holes and the process cuts are matched with the edge shapes of the local deformation positions. Therefore, the stress state during forming can be changed, the local deformation is reduced, the material of the easy-to-break area is supplemented, and the effect of improving the success rate is achieved.
(5) According to the sliding rail type-based shape correcting process and device for the aircraft parts, the titanium alloy is stretched for the first time through the first male die, so that the titanium alloy is in a semi-finished product state, then the outline of the semi-finished product titanium alloy plate is consolidated through the shape correcting process, and the situation that the titanium alloy plate is damaged in the secondary stretching process is avoided.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. It should be apparent that the drawings in the following description are merely exemplary, and that other embodiments can be derived from the drawings provided by those of ordinary skill in the art without inventive effort.
The structures, ratios, sizes, and the like shown in the present specification are only used for matching with the contents disclosed in the specification, so as to be understood and read by those skilled in the art, and are not used to limit the conditions that the present invention can be implemented, so that the present invention has no technical significance, and any structural modifications, changes in the ratio relationship, or adjustments of the sizes, without affecting the effects and the achievable by the present invention, should still fall within the range that the technical contents disclosed in the present invention can cover.
FIG. 1 is a front view of a slide rail-based alignment device for aircraft parts according to the present invention;
FIG. 2 is a cross-sectional view of a slide-rail-based alignment device for aircraft parts according to the present invention;
FIG. 3 is a schematic view of the shape of a second male die of the present invention.
Illustration of the drawings:
1. a base; 2. a fixing plate; 3. a detection device; 4. a female die; 5. a hydraulic cylinder; 6. a connecting plate; 7. a first male die; 8. a second male die; 9. and a controller.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The first embodiment is as follows: a shaping process for a slide rail-based airplane part comprises a titanium alloy, wherein the titanium alloy is TB 2.
The preparation process comprises the following working steps:
the first step is as follows: screening materials, wherein the size of the titanium alloy is that the titanium alloy extends outwards by 30mm by taking the edge of a part as a reference, the elastic modulus of the titanium alloy is E66000 MPa, and the yield strength is sigmas79Mpa, the poisson ratio of titanium alloy is 0.3, the shape factor of titanium alloy is 0.625, and R45＝0.748，R900.694, the stress-strain of the titanium alloy satisfies the equation σ K (e)0+ε)n；
The second step is that: the method comprises the following steps of performing primary stamping, namely putting titanium alloy into a die, setting the maximum hydraulic pressure to be 40MPa, setting the blank holder force to be 40KN, setting the stamping speed of a male die to be 5mm/s, setting the friction coefficient to be 0.05, setting the radius of a fillet on a first male die to be 2 times of the radius of the fillet on a female die, and setting the downward moving distance of the first male die to be two 1/2 of the height of a part;
the third step: the titanium alloy is corrected, the side pressure is 50KN, the punch stamping speed is 5mm/s, the friction coefficient is 0.05, and the side wall of the titanium alloy in the female die is stamped for one time through the first punch;
the fourth step: secondary stamping, namely putting the titanium alloy into a die, setting the maximum hydraulic pressure to be 40MPa, setting the blank holder force to be 40KN, setting the stamping speed of a male die to be 5mm/s, setting the friction coefficient to be 0.05, enabling the shape of the convex part of a second male die to be completely the same as the shape of the inner part of a female die, enabling the downward moving distance of the second male die to be the same as the height of a part, and carrying out primary complete stamping on the titanium alloy;
the fifth step: a process notch, namely putting the titanium alloy subjected to secondary stamping into a stretched plate, reserving a process hole in the stretched plate, setting the edge pressure to be 25KN, setting the stamping speed to be 5mm/s, setting the friction coefficient to be 0.05, and cutting the part from the titanium alloy plate;
and a sixth step: and detecting the package, detecting the minimum wall thickness and the maximum wall thickness of the part to obtain the thinning rate of the part, and packaging the part if the thinning rate of the part is less than 30 percent.
A slide rail type shape correcting device for airplane parts comprises a base 1, a detection device 3, a hydraulic cylinder 5 and a controller 9, wherein a fixing plate 2 is fixedly installed on the side wall of the base 1, the detection device 3 is fixedly installed on one side wall surface, close to the base 1, of the fixing plate 2, the detection device 3 is used for detecting titanium alloy before machining, the detection device 3 can also be used for detecting the thickness of a machined part, a concave die 4 is fixedly installed at one end, far away from the detection device 3, of the top wall surface of the base 1, the hydraulic cylinder 5 is fixedly installed at the top end, close to the base 1, of one side wall surface of the fixing plate 2, a connecting plate 6 is fixedly installed at the output end of the hydraulic cylinder 5, a first convex die 7 is fixedly installed at the bottom of the connecting plate 6, the radius of a downward convex part on the first convex die 7 is 2 times larger than the radius of a concave part inside the concave part of the concave die 4, the bottom wall of the connecting plate 6 is fixedly provided with a second male die 8, a downward convex part on the second male die 8 is mutually attached to a concave part inside the female die 4, and a controller 9 is fixedly arranged on the side wall of the base 1 and controls the detection device 3 and the hydraulic cylinder 5 through the controller 9.
Example two: a shaping process for a slide rail-based airplane part comprises a titanium alloy, wherein the titanium alloy is TB 2.
The preparation process comprises the following working steps:
the first step is as follows: screening materials, wherein the size of the titanium alloy is that the titanium alloy extends outwards by 30mm by taking the edge of a part as a reference, the elastic modulus of the titanium alloy is E66000 MPa, and the yield strength is sigmas79Mpa, the poisson ratio of titanium alloy is 0.3, the shape factor of titanium alloy is 0.625, and R45＝0.748，R900.694, the stress-strain of the titanium alloy satisfies the equation σ K (e)0+ε)n；
The second step is that: the method comprises the following steps of performing primary stamping, namely putting titanium alloy into a die, setting the maximum hydraulic pressure to be 50MPa, setting the blank holder force to be 40KN, setting the stamping speed of a male die to be 7mm/s, setting the friction coefficient to be 0.05, setting the radius of a fillet on a first male die to be 2 times of the radius of the fillet on a female die, and setting the downward moving distance of the first male die to be two 1/2 of the height of a part;
the third step: the titanium alloy is corrected, the side pressure is 50KN, the punch stamping speed is 5mm/s, the friction coefficient is 0.05, and the side wall of the titanium alloy in the female die is stamped for one time through the first punch;
the fourth step: secondary stamping, namely putting the titanium alloy into a die, setting the maximum hydraulic pressure to be 50MPa, setting the blank holder force to be 40KN, setting the stamping speed of a male die to be 6mm/s, setting the friction coefficient to be 0.05, enabling the shape of the convex part of a second male die to be completely the same as the shape of the inner part of a female die, enabling the downward moving distance of the second male die to be the same as the height of a part, and carrying out primary complete stamping on the titanium alloy;
the fifth step: a process notch, namely putting the titanium alloy subjected to secondary stamping into a stretched plate, reserving a process hole in the stretched plate, setting the edge pressure to be 25KN, setting the stamping speed to be 5mm/s, setting the friction coefficient to be 0.05, and cutting the part from the titanium alloy plate;
and a sixth step: and detecting the package, detecting the minimum wall thickness and the maximum wall thickness of the part to obtain the thinning rate of the part, and packaging the part if the thinning rate of the part is less than 30 percent.
A slide rail type shape correcting device for airplane parts comprises a base 1, a detection device 3, a hydraulic cylinder 5 and a controller 9, wherein a fixing plate 2 is fixedly installed on the side wall of the base 1, the detection device 3 is fixedly installed on one side wall surface, close to the base 1, of the fixing plate 2, the detection device 3 is used for detecting titanium alloy before machining, the detection device 3 can also be used for detecting the thickness of a machined part, a concave die 4 is fixedly installed at one end, far away from the detection device 3, of the top wall surface of the base 1, the hydraulic cylinder 5 is fixedly installed at the top end, close to the base 1, of one side wall surface of the fixing plate 2, a connecting plate 6 is fixedly installed at the output end of the hydraulic cylinder 5, a first convex die 7 is fixedly installed at the bottom of the connecting plate 6, the radius of a downward convex part on the first convex die 7 is 2 times larger than the radius of a concave part inside the concave part of the concave die 4, the bottom wall of the connecting plate 6 is fixedly provided with a second male die 8, a downward convex part on the second male die 8 is mutually attached to a concave part inside the female die 4, and a controller 9 is fixedly arranged on the side wall of the base 1 and controls the detection device 3 and the hydraulic cylinder 5 through the controller 9.
Example three: a shaping process for a slide rail-based airplane part comprises a titanium alloy, wherein the titanium alloy is TB 2.
The preparation process comprises the following working steps:
the first step is as follows: screening materials, wherein the size of the titanium alloy is that the titanium alloy extends outwards by 30mm by taking the edge of a part as a reference, the elastic modulus of the titanium alloy is E66000 MPa, and the yield strength is sigmas79Mpa, the poisson ratio of titanium alloy is 0.3, the shape factor of titanium alloy is 0.625, and R45＝0.748，R900.694, the stress-strain of the titanium alloy satisfies the equation σ K (e)0+ε)n；
The second step is that: the method comprises the following steps of performing primary stamping, namely putting titanium alloy into a die, setting the maximum hydraulic pressure to be 55MPa, setting the blank holder force to be 35KN, setting the stamping speed of a male die to be 7mm/s, setting the friction coefficient to be 0.05, setting the radius of a fillet on a first male die to be 2 times of the radius of the fillet on a female die, and setting the downward moving distance of the first male die to be two 1/2 of the height of a part;
the third step: the titanium alloy is corrected, the side pressure is 55KN, the punch stamping speed is 5mm/s, the friction coefficient is 0.05, and the side wall of the titanium alloy in the female die is stamped for one time through the first punch;
the fourth step: secondary stamping, namely putting the titanium alloy into a die, setting the maximum hydraulic pressure to be 55MPa, setting the blank holder force to be 35KN, setting the stamping speed of a male die to be 7mm/s, setting the friction coefficient to be 0.05, enabling the shape of the convex part of a second male die to be completely the same as the shape of the inner part of a female die, enabling the downward moving distance of the second male die to be the same as the height of a part, and carrying out primary complete stamping on the titanium alloy;
the fifth step: a process notch, namely putting the titanium alloy subjected to secondary stamping into a stretched plate, reserving a process hole in the stretched plate, setting the edge pressure to be 28KN, setting the stamping speed to be 7mm/s, setting the friction coefficient to be 0.05, and cutting the part from the titanium alloy plate;
and a sixth step: and detecting the package, detecting the minimum wall thickness and the maximum wall thickness of the part to obtain the thinning rate of the part, and packaging the part if the thinning rate of the part is less than 30 percent.
A slide rail type shape correcting device for airplane parts comprises a base 1, a detection device 3, a hydraulic cylinder 5 and a controller 9, wherein a fixing plate 2 is fixedly installed on the side wall of the base 1, the detection device 3 is fixedly installed on one side wall surface, close to the base 1, of the fixing plate 2, the detection device 3 is used for detecting titanium alloy before machining, the detection device 3 can also be used for detecting the thickness of a machined part, a concave die 4 is fixedly installed at one end, far away from the detection device 3, of the top wall surface of the base 1, the hydraulic cylinder 5 is fixedly installed at the top end, close to the base 1, of one side wall surface of the fixing plate 2, a connecting plate 6 is fixedly installed at the output end of the hydraulic cylinder 5, a first convex die 7 is fixedly installed at the bottom of the connecting plate 6, the radius of a downward convex part on the first convex die 7 is 2 times larger than the radius of a concave part inside the concave part of the concave die 4, the bottom wall of the connecting plate 6 is fixedly provided with a second male die 8, a downward convex part on the second male die 8 is mutually attached to a concave part inside the female die 4, and a controller 9 is fixedly arranged on the side wall of the base 1 and controls the detection device 3 and the hydraulic cylinder 5 through the controller 9.
Example four: a shaping process for a slide rail-based airplane part comprises a titanium alloy, wherein the titanium alloy is TB 2.
The preparation process comprises the following working steps:
the first step is as follows: screening materials, wherein the size of the titanium alloy is that the titanium alloy extends outwards by 30mm by taking the edge of a part as a reference, the elastic modulus of the titanium alloy is E66000 MPa, and the yield strength is sigmas79Mpa, titaniumThe Poisson ratio of the alloy is 0.3, the allotype coefficient of the titanium alloy is 0.625, and R45＝0.748，R900.694, the stress-strain of the titanium alloy satisfies the equation σ K (e)0+ε)n；
The second step is that: the method comprises the following steps of performing primary stamping, namely putting titanium alloy into a die, setting the maximum hydraulic pressure to be 60MPa, setting the blank holder force to be 30KN, setting the stamping speed of a male die to be 8mm/s, setting the friction coefficient to be 0.05, setting the radius of a fillet on a first male die to be 2 times of the radius of the fillet on a female die, and setting the downward moving distance of the first male die to be two 1/2 of the height of a part;
the third step: the titanium alloy is corrected, the side pressure is 60KN, the punch stamping speed is 8mm/s, the friction coefficient is 0.05, and the side wall of the titanium alloy in the female die is stamped for one time through the first punch;
the fourth step: secondary stamping, namely putting the titanium alloy into a die, setting the maximum hydraulic pressure to be 60MPa, setting the blank holder force to be 30KN, setting the stamping speed of a male die to be 8mm/s, setting the friction coefficient to be 0.05, enabling the shape of the convex part of a second male die to be completely the same as the shape of the inner part of a female die, enabling the downward moving distance of the second male die to be the same as the height of a part, and carrying out primary complete stamping on the titanium alloy;
the fifth step: a process notch, namely putting the titanium alloy subjected to secondary stamping into a stretched plate, reserving a process hole in the stretched plate, setting the edge pressure to be 30KN, setting the stamping speed to be 8mm/s, setting the friction coefficient to be 0.05, and cutting the part from the titanium alloy plate;
and a sixth step: and detecting the package, detecting the minimum wall thickness and the maximum wall thickness of the part to obtain the thinning rate of the part, and packaging the part if the thinning rate of the part is less than 30 percent.
A slide rail type shape correcting device for airplane parts comprises a base 1, a detection device 3, a hydraulic cylinder 5 and a controller 9, wherein a fixing plate 2 is fixedly installed on the side wall of the base 1, the detection device 3 is fixedly installed on one side wall surface, close to the base 1, of the fixing plate 2, the detection device 3 is used for detecting titanium alloy before machining, the detection device 3 can also be used for detecting the thickness of a machined part, a concave die 4 is fixedly installed at one end, far away from the detection device 3, of the top wall surface of the base 1, the hydraulic cylinder 5 is fixedly installed at the top end, close to the base 1, of one side wall surface of the fixing plate 2, a connecting plate 6 is fixedly installed at the output end of the hydraulic cylinder 5, a first convex die 7 is fixedly installed at the bottom of the connecting plate 6, the radius of a downward convex part on the first convex die 7 is 2 times larger than the radius of a concave part inside the concave part of the concave die 4, the bottom wall of the connecting plate 6 is fixedly provided with a second male die 8, a downward convex part on the second male die 8 is mutually attached to a concave part inside the female die 4, and a controller 9 is fixedly arranged on the side wall of the base 1 and controls the detection device 3 and the hydraulic cylinder 5 through the controller 9.
The working principle of the invention is as follows:
in the invention, the transition model surface keeps the profile curvature of the original part, and the fillet radius and the stretching depth of the convex die and the concave die are increased, so that the transition die has the function of storing materials. Obtain semi-manufactured goods after the first stretch forming, simultaneously because fillet radius is great on the first tensile terrace die, so titanium alloy when tensile, there is unnecessary part in the corner on the titanium alloy, when making tensile the second time, fillet department has unnecessary part to provide titanium alloy's deformation, makes things convenient for the tensile final part of one-time. After the secondary stretch forming is finished, the quality of the part is effectively improved, qualified parts meeting the standard can be formed, and the success rate of aircraft part manufacturing is improved by performing 2 times of stretch forming on the titanium alloy.
According to the invention, by increasing the edge pressing force, although the edge of the male die can inhibit the wrinkling tendency of the titanium alloy, the tensile stress at the edge of the male die is increased, so that the flowing of the material is inhibited, the material at the edge of the male die cannot smoothly flow into a round angle, the material at the edge of the male die cannot be effectively supplied along with the gradual stretching of the material, the material in the part can be obviously thinned, the tensile crack tendency is increased, and the wall thickness distribution of the part is not uniform; the blank holder power reduces, and the edge tangential compressive stress of terrace die increases, and the trend of corrugating will increase, not only can influence the part and take shape the quality, still can increase the wearing and tearing of mould. Therefore, the edge pressing force is limited to be between 30KN and 40KN, and the forming quality of the part is prevented from being influenced.
According to the invention, the stamping speed is limited to be between 5mm/s and 8mm/s, the downward moving speed of the male die is increased, so that the titanium alloy can be molded in a short time, and the manufacturing speed of parts is increased.
According to the invention, the titanium alloy die after the second drawing is placed into the drawn plate with the process hole, so that the part is cut off from the titanium alloy plate, the process hole and the process notch are added at the position with the maximum tensile stress, and in order to enable the material to flow reasonably, the shapes of the process hole and the process notch are adapted to the edge shape of the local deformation position. Therefore, the stress state during forming can be changed, the local deformation is reduced, the material of the easy-to-break area is supplemented, and the effect of improving the success rate is achieved.
According to the invention, the titanium alloy is stretched for the first time through the first male die, so that the titanium alloy is in a semi-finished product state, and then the outline of the semi-finished product titanium alloy plate is consolidated through the shape correction process, so that the titanium alloy plate is prevented from being damaged in the secondary stretching process.
The foregoing shows and describes the general principles and broad features of the present invention and advantages thereof. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are described in the specification and illustrated only to illustrate the principle of the present invention, but that various changes and modifications may be made therein without departing from the spirit and scope of the present invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (9)
1. A slide rail type based sizing process for airplane parts comprises titanium alloy and is characterized in that: the titanium alloy is TB 2;
the preparation process comprises the following working steps:
the first step is as follows: screening materials;
the second step is that: performing primary stamping;
the third step: correcting the shape of the titanium alloy;
the fourth step: secondary stamping;
the fifth step: performing process notching;
and a sixth step: and (6) detecting and packaging.
2. The slide rail-based sizing process for aircraft parts according to claim 1, wherein: the titanium alloy in the first step has the size of 30mm extending outwards based on the edge of the part, the elastic modulus E of the titanium alloy is 66000MPa, and the yield strength is sigmas79Mpa, the poisson ratio of titanium alloy is 0.3, the shape factor of titanium alloy is 0.625, and R45＝0.748，R900.694, the stress-strain of the titanium alloy satisfies the equation σ K (e)0+ε)n。
3. The slide rail-based sizing process for aircraft parts according to claim 1, wherein: and in the second step, the titanium alloy is placed in a die, the maximum hydraulic pressure is set to be 40-60MPa, the blank holder force is set to be 30-40KN, the stamping speed of the male die is set to be 5-8mm/s, the friction coefficient is set to be 0.05, the radius of a fillet on the first male die is 2 times of the radius of the fillet on the female die, and the downward moving distance of the first male die is two 1/2 times of the height of the part.
4. The slide rail-based sizing process for aircraft parts according to claim 1, wherein: in the third step, the side pressure is 40-60KN, the punch stamping speed is 5-8mm/s, the friction coefficient is 0.05, and the side wall of the titanium alloy in the female die is stamped by the first punch for one time.
5. The slide rail-based sizing process for aircraft parts according to claim 1, wherein: and fourthly, putting the titanium alloy into a die, setting the maximum hydraulic pressure to be 40-60MPa, setting the blank holder force to be 30-40KN, setting the stamping speed of the male die to be 5-8mm/s, setting the friction coefficient to be 0.05, enabling the shape of the convex part of the second male die to be completely the same as the shape of the inner part of the female die, enabling the downward movement distance of the second male die to be the same as the height of the part, and completely stamping the titanium alloy for one time.
6. The slide rail-based sizing process for aircraft parts according to claim 1, wherein: and in the fifth step, the titanium alloy after secondary stamping is placed into a stretched plate, a process hole is reserved in the stretched plate, the edge pressure is set to be 25-30KN, the stamping speed is set to be 5-8mm/s, the friction coefficient is set to be 0.05, and the part is cut out of the titanium alloy plate.
7. The slide rail-based sizing process for aircraft parts according to claim 1, wherein: and detecting the minimum wall thickness and the maximum wall thickness of the part in the sixth step to obtain the reduction rate of the part, and packaging the part if the reduction rate of the part is less than 30 percent.
8. The utility model provides an aircraft spare part is with school shape device based on slide rail formula, includes base (1), detection device (3), pneumatic cylinder (5) and controller (9), its characterized in that: fixed mounting has fixed plate (2) on the lateral wall of base (1), and a side wall fixed mounting who is close to base (1) on fixed plate (2) has detection device (3), and the one end fixed mounting that detection device (3) were kept away from to the top wall of base (1) has die (4), and pneumatic cylinder (5) fixed mounting is close to a side wall top of base (1) on fixed plate (2), and the output fixed mounting of pneumatic cylinder (5) has connecting plate (6).
9. The slide rail-based sizing device for aircraft parts according to claim 8, wherein: the bottom fixed mounting of connecting plate (6) has first terrace die (7), and the fillet department radius of the downward bulge on first terrace die (7) is 2 times bigger than die (4) inside depressed part, and the bottom wall fixed mounting of connecting plate (6) has second terrace die (8), and the downward bulge and die (4) inside depressed part are laminated each other on second terrace die (8), and controller (9) fixed mounting is on the lateral wall of base (1).
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050257862A1 (en) * | 2004-05-21 | 2005-11-24 | Kabushiki Kaisha Kobe Seiko Sho(Kobe Steel, Ltd.) | Production method of warm- or hot-formed product |
| CN102075040A (en) * | 2010-12-30 | 2011-05-25 | 浙江胜华波电器股份有限公司 | One-step multi-station method for stretching machining enclosure and enclosure stretcher |
| CN107139517A (en) * | 2017-06-19 | 2017-09-08 | 中南大学 | A kind of drawing and forming device and method of the non-axisymmetric parts of difficult-to-deformation material |
| CN107774796A (en) * | 2017-10-10 | 2018-03-09 | 东莞凯路汽车工业有限公司 | The stretch forming process of copper alloy shock-absorbing sleeve |
| CN207756716U (en) * | 2017-12-29 | 2018-08-24 | 四川明日宇航工业有限责任公司 | The drawing die of funnel part for aircraft engine |
| CN110293151A (en) * | 2019-06-03 | 2019-10-01 | 西安飞机工业（集团）有限责任公司 | A kind of straightening method of titanium alloy sliding rail class part notch deformation |
| CN110449516A (en) * | 2019-08-15 | 2019-11-15 | 安徽工业大学 | A kind of anti-corrugation cupping tool of depth cylinder part and technique |
| CN112474984A (en) * | 2020-09-30 | 2021-03-12 | 成都飞机工业（集团）有限责任公司 | Method for deep drawing and forming sheet metal part of airplane cap-shaped fairing |
-
2021
- 2021-12-01 CN CN202111451589.3A patent/CN114130895B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050257862A1 (en) * | 2004-05-21 | 2005-11-24 | Kabushiki Kaisha Kobe Seiko Sho(Kobe Steel, Ltd.) | Production method of warm- or hot-formed product |
| CN102075040A (en) * | 2010-12-30 | 2011-05-25 | 浙江胜华波电器股份有限公司 | One-step multi-station method for stretching machining enclosure and enclosure stretcher |
| CN107139517A (en) * | 2017-06-19 | 2017-09-08 | 中南大学 | A kind of drawing and forming device and method of the non-axisymmetric parts of difficult-to-deformation material |
| CN107774796A (en) * | 2017-10-10 | 2018-03-09 | 东莞凯路汽车工业有限公司 | The stretch forming process of copper alloy shock-absorbing sleeve |
| CN207756716U (en) * | 2017-12-29 | 2018-08-24 | 四川明日宇航工业有限责任公司 | The drawing die of funnel part for aircraft engine |
| CN110293151A (en) * | 2019-06-03 | 2019-10-01 | 西安飞机工业（集团）有限责任公司 | A kind of straightening method of titanium alloy sliding rail class part notch deformation |
| CN110449516A (en) * | 2019-08-15 | 2019-11-15 | 安徽工业大学 | A kind of anti-corrugation cupping tool of depth cylinder part and technique |
| CN112474984A (en) * | 2020-09-30 | 2021-03-12 | 成都飞机工业（集团）有限责任公司 | Method for deep drawing and forming sheet metal part of airplane cap-shaped fairing |
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