CN115433887A - High-strength aluminum alloy structure-performance integrated forming method and application thereof - Google Patents
High-strength aluminum alloy structure-performance integrated forming method and application thereof Download PDFInfo
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- CN115433887A CN115433887A CN202210941196.9A CN202210941196A CN115433887A CN 115433887 A CN115433887 A CN 115433887A CN 202210941196 A CN202210941196 A CN 202210941196A CN 115433887 A CN115433887 A CN 115433887A
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
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- B05D7/00—Processes, other than flocking, specially adapted for applying liquids or other fluent materials to particular surfaces or for applying particular liquids or other fluent materials
- B05D7/14—Processes, other than flocking, specially adapted for applying liquids or other fluent materials to particular surfaces or for applying particular liquids or other fluent materials to metal, e.g. car bodies
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- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/002—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working by rapid cooling or quenching; cooling agents used therefor
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Abstract
The invention discloses a high-strength aluminum alloy structure-performance integrated forming method and application thereof, wherein the high-strength aluminum alloy plate which is in a W state after solution quenching is subjected to pre-hardening treatment for a long time to form a GPII area which is completely compatible with a matrix, has good plasticity and is beneficial to subsequent baking finish reinforcement; and after the forming is finished, the component is subjected to short-time paint baking treatment, the dislocation recovery is not obvious, and the dislocation generated in the forming process can provide more nucleation sites and deformation energy storage, so that the precipitation of a main strengthening phase is promoted, and the strength is further improved. And the structure stability of the plate at room temperature after pre-hardening and forming is good, and the natural aging can not cause phase transformation, so that the plate can be parked for a longer time, uniform batch production of plate suppliers and part processing manufacturers is facilitated, the process principle is different from that of the traditional T4P treatment method, and the effect is better. The invention not only can effectively improve the performance of the formed member, but also greatly improves the production efficiency.
Description
Technical Field
The invention relates to the technical field of plate processing, in particular to a high-strength aluminum alloy structure-performance integrated forming method and application thereof.
Background
Under the environment of energy conservation and emission reduction, the aluminum alloy with high specific strength is widely applied to the fields of automobiles, aerospace and the like. However, for high-strength aluminum alloy, the strength of strengthened plate materials such as T6 and T8 is high, the plasticity is poor, and the processing requirements of some parts cannot be met during cold forming. If warm forming or hot forming is adopted, the process is complex, the equipment and tooling cost is high, the precipitated phase in the forming process is not easy to control, and the precipitated phase is easy to be thick, so that the strength is reduced. Conventional cold forming usually adopts O-state plates with good plasticity, but the strength of a member is low after forming, subsequent strengthening treatment (solid solution and artificial aging) is also needed, but the precision is reduced due to deformation of the plates in the process of solid solution and water quenching, and the subsequent treatment time is long, so that the production is not facilitated. Therefore, a high-performance forming method for structure-performance integrated forming is urgently needed. In order to avoid the defects of low formability and bake hardenability of the conventional T4 state 6xxx aluminum alloy sheet due to the natural age hardening phenomenon, a T4P treatment method is often used for improving the cold formability of the 6xxx aluminum alloy sheet, the T4P treatment method is used for carrying out artificial aging for a short time (60-200 ℃ and 2-30 min) after solid solution, then carrying out natural aging for several days, and carrying out baking finish hardening treatment after forming. However, the precipitated phases after natural aging of the method are mainly atomic clusters and partial GP regions, the sheet formability is good, but the strength after forming is low, the structure state is unstable, and the performance of the sheet is greatly influenced by the parking time. And the method is not suitable for 2xxx and 7xxx high strength aluminum alloys.
Microwave antennas are rapidly developing as core devices for mobile communication network coverage, and with the start of 6G technology, such development will continue for a considerable period of time in the future.
Compared with other types of antennas, microwave antennas are widely used because they focus electromagnetic waves using a reflecting surface, providing the highest gain, the widest bandwidth, and the best angular resolution at the lowest cost.
Generally, the pointing error of the antenna is less than one tenth of the half-power beamwidth. The shape error and the structural strength of the reflecting surface, which is an important component of the microwave antenna, can greatly affect the pointing accuracy of the antenna. The shape error depends on the precision of the forming process of the reflecting surface, the structural strength depends on the material and the structure of the reflecting surface, and when the structural strength is low, the reflecting surface has weak capability of resisting environmental factors including gravity load, temperature load, wind load, inertia load and earthquake load, and the pointing precision of the antenna is reduced once deformation occurs.
For the heat-treatable aluminum alloy commonly used for the antenna, the commonly used strengthening method is T6 strengthening treatment, but the aluminum alloy is easy to deform in the T6 strengthening process, so that the pointing accuracy of the part is reduced.
Disclosure of Invention
Aiming at the problems, the structure-performance integrated forming method for the high-strength aluminum alloy and the application thereof are provided. According to the invention, the aluminum alloy plate is subjected to pre-hardening treatment before cold forming so as to control alloy precipitation and a GPII area which is consistent with a matrix and has a larger size, so that the cold forming performance is better; in the subsequent forming process, the dislocation interacts with a GPII (general purpose interface) region and the newly generated nano-stacking faults enable the formed member to have higher strength; more nucleation sites and deformation energy storage are provided due to dislocation generated by forming in the paint baking process, so that the phase transformation of a GPII region → a main strengthening phase is more sufficient, the size of a precipitated phase is smaller, the strength of a component is further improved, and the T6 state is far exceeded; in addition, the structure stability of the plate at room temperature after pre-hardening and forming is good, so the pre-hardening step can be finished by a plate supplier, and the subsequent production can be carried out after the processing manufacturer feeds, thereby shortening the production period; and the cold-formed plate can be parked for a plurality of days, and then batch paint baking and powder spraying treatment is uniformly carried out, so that the production efficiency is improved.
The specific technical scheme is as follows:
the first aspect of the invention provides a structure-performance integrated forming method for a high-strength aluminum alloy, which is characterized by comprising the following steps:
s1, carrying out solid solution and pre-hardening treatment on the high-strength aluminum alloy;
s2, parking the pre-hardened plate for forming;
s3, performing cold forming by using the pre-hardened plate, wherein the final deformation is within 25%;
and S4, performing unified paint baking and powder spraying treatment on the formed plate.
The structure-performance integrated forming method of the high-strength aluminum alloy is further characterized in that the solid solution and pre-hardening treatment in the step S1 specifically comprises the following steps: when the plate is 7xxx aluminum alloy, carrying out solution treatment at 460-490 ℃ for 30-50min, quenching, and then carrying out heat preservation in an aging furnace at 60-110 ℃ for 2-12h; when the plate is 6xxx aluminum alloy, carrying out solution treatment at 520-550 ℃ for 30-50min, quenching, and then carrying out heat preservation in an aging furnace at 110-160 ℃ for 2-12h; when the plate is 2xxx aluminum alloy, the plate is quenched after solution treatment at 490-530 ℃ for 30-50min, and then is kept warm in an aging furnace at 100-180 ℃ for 2-12h; wherein the plate transfer time before quenching is less than 10s, and the plate transfer time before pre-aging is less than 10min.
The structure-performance integrated forming method of the high-strength aluminum alloy is also characterized in that the 7000 series aluminum alloy after the solid solution and pre-hardening treatment in the step S1 forms a GPII area with the thickness of 1-2 atomic layers; the 6000 series aluminum alloy forms GPII regions of 1-30nm in length, which include initial β "and pre- β"; forming GPII area of 1-15nm length of 2000 series aluminum alloy; the GPII area formed by all the pre-hardened plates accounts for 60% -100%, and the GPII area is completely coherent with the aluminum matrix and has small obstruction to dislocation movement, so that the pre-hardened plates have high plasticity and can be used for subsequent cold forming.
The structure-performance integrated forming method for the high-strength aluminum alloy is also characterized in that the sheet material after being pre-hardened in the step S2 has good structural stability, can be stored within 18 months, and is convenient for sheet material storage and transportation of sheet material suppliers.
The structure-performance integrated forming method for the high-strength aluminum alloy is also characterized in that the structural performance of the formed component in the step S4 is stable, the precipitation temperature threshold of the subsequent strengthening phase is high, and the natural aging does not influence the precipitation phase, so that the component can be parked for 12 months, and the subsequent uniform paint baking and powder spraying treatment of a factory is facilitated.
The structure-performance integrated forming method for the high-strength aluminum alloy is also characterized in that the plate material after the paint baking in the step S4 is separated out of a main strengthening phase with small size, and the method specifically comprises the following steps: when the plate is 7xxx aluminum alloy, baking varnish for 10-30min at 170-220 ℃, and separating out an eta' phase with the size of 10-30 nm; when the plate is 6xxx aluminum alloy, baking varnish at 160-220 ℃ for 15-35min, and separating out a beta' phase with the size of 30-40 nm; when the plate is 2xxx aluminum alloy, baking varnish at 190-230 ℃ for 10-20min, and separating out theta' phase with the size of 20-30 nm. The dislocation recovery effect is not obvious in the paint baking process, a large amount of dislocations are generated in the cold forming process, more nucleation sites and deformation energy storage are provided for the strengthening phase, the precipitation threshold of the main strengthening phase is reduced, the strengthening phase is fully precipitated and has small size in the paint baking process, the strength of the component is further improved, and the component is far beyond the T6 state.
A second aspect of the present invention is to provide a use of a 6xxx aluminum alloy in satellite antenna reflector surface sectioning, having the feature that the 6xxx aluminum alloy is prepared according to the above-described preparation method.
The above application in satellite antenna reflecting surface split forming is characterized in that the split forming specifically comprises the following steps:
step S1, carrying out 535 ℃ solution treatment on the high-strength aluminum alloy for 30-50min, then quenching, and then carrying out heat preservation in an aging furnace at 110-160 ℃ for 2-12h, wherein the GPII area formed by pre-hardening the plate material accounts for 60% -100%, and the GPII area with the length of 1-30nm, which comprises initial beta and pre-beta, is formed in the plate material;
s2, parking the pre-hardened plate for forming;
s3, stamping and forming each melon petal by using the pre-hardened plate, wherein the final deformation is within 25%;
s4, uniformly baking varnish at 160-220 ℃ for 15-35min for the formed melon petals, and performing powder spraying treatment;
s5, welding edge strips, and assembling and forming: bolt holes are pre-drilled on the edge strips, so that the split parts are assembled and formed by bolts penetrating through the bolt holes, and the material of the edge strips is the same as that of the split parts;
s6, assembling a reinforcing rod to obtain a reflecting mask: utilize the bolt to wear to establish the stiffener and be fixed in on the strake, the stiffener provides the back with the strake jointly for the plane of reflection and supports.
The above application in satellite antenna reflecting surface split forming is characterized in that the split forming specifically comprises the following steps:
s1, carrying out 535 ℃ solution treatment on the high-strength aluminum alloy for 30-50min, then quenching, and then carrying out heat preservation in an aging furnace at 110-160 ℃ for 2-12h, wherein a GPII area formed by pre-hardening the plate material accounts for 60% -100%, and a GPII area with the length of 1-30nm is formed in the plate material and comprises initial beta 'and pre-beta';
s2, parking the pre-hardened plate for forming;
s3, stamping and forming each melon petal by using the pre-hardened plate, wherein the final deformation is within 25%;
s4, parking the formed plate for no more than 12 months;
s5, uniformly baking varnish at 160-220 ℃ for 15-35min, and performing powder spraying treatment on the formed melon petals;
s6, welding edge strips, assembling and forming: bolt holes are pre-drilled on the edge strips, so that the split parts are assembled and formed by bolts penetrating through the bolt holes, and the material of the edge strips is the same as that of the split parts;
step S7, assembling a reinforcing rod to prepare the reflecting mask: utilize the bolt to wear to establish the stiffener and be fixed in on the strake, the stiffener provides the back with the strake jointly for the plane of reflection and supports.
The above application in satellite antenna reflecting surface split forming is characterized in that the split forming specifically comprises the following steps:
s1, carrying out 535 ℃ solution treatment on the high-strength aluminum alloy for 30-50min, then quenching, and then carrying out heat preservation in an aging furnace at 110-160 ℃ for 2-12h, wherein a GPII area formed by pre-hardening the plate material accounts for 60% -100%, and a GPII area with the length of 1-30nm is formed in the plate material and comprises initial beta 'and pre-beta';
s2, parking the pre-hardened plate for forming;
s3, stamping and forming each melon petal by using the pre-hardened plate, wherein the final deformation is within 25%;
s4, parking the formed plate for no more than 12 months;
and S5, uniformly baking varnish at 160-220 ℃ for 15-35min, and performing powder spraying treatment on the formed melon petals.
The beneficial effect of above-mentioned scheme is:
1) The sheet material after the pre-hardening treatment and the cold forming has good structure stability at room temperature, and the natural aging does not influence precipitated phases and dislocation; the pre-hardening step is finished by a plate supplier, and the blank can be stored at room temperature for no more than 18 months, so that the blank is convenient for batch production and supply of manufacturers; the processing factory can directly use the plate material to process, and can stand for several days to carry out batch baking finish powder spraying treatment after the processing is finished, thereby simplifying the processing steps of parts and improving the production efficiency on the whole;
2) GPII areas which are larger in size, good in stability and completely coherent with the matrix are separated out from the pre-hardened plate, the formability is good, the subsequent baking finish process is facilitated to separate out a strengthening phase, the GPII area tissues interact with dislocations in the forming process, the processing and hardening capacity of the formed component is improved, and meanwhile, a large number of nano-level faults are generated in the deformation process, so that the strength of the formed component is further improved;
3) Dislocation generated in cold forming provides more nucleation sites and deformation energy storage, so that the phase transformation of a GPII area → a main strengthening phase is more sufficient in the paint baking process, the size of a precipitated phase is smaller, the strength of a component is further improved and far exceeds a T6 state, subsequent artificial strengthening treatment is not needed after forming, the production period is shortened, and the deformation problem easily existing in solid solution and water quenching is avoided;
4) The method is used for processing the reflecting mask, the split forming is adopted for facilitating the transportation, the design of the reinforcing rod can be used for connecting and reinforcing the reflecting surface, the structure and the assembly process are simplified, and the cost is lower.
Drawings
FIG. 1 is a schematic flow diagram of an integrated forming process provided in an embodiment of the present invention;
FIG. 2 is a schematic diagram of the front and back sides of a reflective surface provided in an embodiment of the present invention;
FIG. 3 is a schematic view of a single melon petal of a reflective surface provided in an embodiment of the present invention;
FIG. 4 is a schematic side wall connection of a reflective surface provided in an embodiment of the present invention;
fig. 5 is a schematic structural view of a reinforcing bar provided in an embodiment of the present invention.
In the drawings: 1. a reflective surface melon flap; 2. connecting by bolts and screws; 3. a reinforcing bar; 101. a side wall; 102. a reflective mask; 103. a through hole; 201. a screw; 202. and (4) bolts.
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.
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.
The invention is further described with reference to the following drawings and specific examples, which are not intended to be limiting.
As shown in fig. 1, the method for integrally forming a structure and performance of a high-strength aluminum alloy provided in an embodiment of the present invention includes the following steps:
s1, carrying out solid solution and pre-hardening treatment on the high-strength aluminum alloy;
s2, parking the pre-hardened plate for forming;
s3, performing cold forming by using the pre-hardened plate, wherein the final deformation is within 25%;
and S4, uniformly baking the paint on the formed plate, and performing powder spraying treatment.
The method is characterized in that 6xxx series aluminum alloy is applied to the processing of the reflecting surface of the satellite antenna after solid solution and pre-hardening treatment, and the method comprises the following specific steps:
step S1, carrying out 535 ℃ solution treatment on the high-strength aluminum alloy for 30-50min, then quenching, and then carrying out heat preservation in an aging furnace at 110-160 ℃ for 2-12h, wherein the GPII area formed by pre-hardening the plate material accounts for 60% -100%, and the GPII area with the length of 1-30nm, which comprises initial beta and pre-beta, is formed in the plate material;
s2, parking the pre-hardened plate for forming;
s3, stamping and forming each melon petal by using the pre-hardened plate, wherein the final deformation is within 25%;
s4, uniformly baking varnish at 160-220 ℃ for 15-35min, and performing powder spraying treatment on the formed melon petals;
s5, welding edge strips, and assembling and forming;
and S6, assembling the reinforcing rod to obtain the reflecting mask.
The processing steps of the satellite reflecting surface can also be as follows:
step S1, carrying out 535 ℃ solution treatment on the high-strength aluminum alloy for 30-50min, then quenching, and then carrying out heat preservation in an aging furnace at 110-160 ℃ for 2-12h, wherein the GPII area formed by pre-hardening the plate material accounts for 60% -100%, and the GPII area with the length of 1-30nm, which comprises initial beta and pre-beta, is formed in the plate material;
s2, parking the pre-hardened plate for forming;
s3, stamping and forming each melon petal by using the pre-hardened plate, wherein the final deformation is within 25%;
s4, parking the formed plate for no more than 12 months;
s5, uniformly baking varnish at 160-220 ℃ for 15-35min for the formed melon petals, and performing powder spraying treatment;
s6, welding edge strips, and assembling and forming;
and S7, assembling the reinforcing rod to obtain the reflecting mask.
The processing steps of the satellite reflecting surface can also be as follows:
s1, welding a high-strength aluminum alloy plate into a whole plate by friction stir welding, carrying out 535 ℃ solution treatment on the welded plate for 30-50min, then quenching, then carrying out heat preservation in an aging furnace at 110-160 ℃ for 2-12h, wherein the GPII area formed by pre-hardening the plate accounts for 60% -100%, and GPII areas with the length of 1-30nm are formed in the plate and comprise initial beta and pre-beta;
s2, parking the pre-hardened plate for forming;
s3, stamping and forming each melon petal by using the pre-hardened plate, wherein the final deformation is within 25%;
s4, parking the formed plate for no more than 12 months;
and S5, uniformly baking varnish at 160-220 ℃ for 15-35min on the formed reflecting surface, and performing powder spraying treatment.
The corresponding processing parameters and the performance of the treated plate are shown in the following table:
the T6 state physical property parameters of the material are shown in the following table:
| material | Tensile strength | Yield strength |
| 7075 | 565 | 491 |
| 7A09 | 580 | 520 |
| 6061 | 290 | 240 |
| 6005 | 295 | 263 |
| 2219 | 424 | 284 |
| 2024 | 470 | 325 |
Compared with the prior art, the strength of the plate processed by the integrated forming method disclosed by the invention is far beyond the T6 state, so that the pointing accuracy of the subsequent forming reflecting mask can be ensured.
While the invention has been described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes in form and detail may be made therein without departing from the spirit and scope of the invention.
Claims (10)
1. A high-strength aluminum alloy structure-performance integrated forming method is characterized by comprising the following steps:
s1, carrying out solid solution and pre-hardening treatment on the high-strength aluminum alloy;
s2, parking the pre-hardened plate for forming;
s3, performing cold forming by using the pre-hardened plate, wherein the final deformation is within 25%;
and S4, performing unified paint baking and powder spraying treatment on the formed plate.
2. The structure-performance integrated forming method of the high-strength aluminum alloy as claimed in claim 1, wherein the solid solution and pre-hardening treatment in the step S1 is specifically: when the plate is 7xxx aluminum alloy, carrying out solution treatment at 460-490 ℃ for 30-50min, quenching, and then carrying out heat preservation in an aging furnace at 60-110 ℃ for 2-12h; when the plate is 6xxx aluminum alloy, carrying out solution treatment at 520-550 ℃ for 30-50min, quenching, and then carrying out heat preservation in an aging furnace at 110-160 ℃ for 2-12h; when the plate is 2xxx aluminum alloy, the plate is quenched after solution treatment at 490-530 ℃ for 30-50min, and then is insulated for 2-12h at 100-180 ℃ in an aging furnace; wherein the plate transfer time before quenching is less than 10s, and the plate transfer time before pre-aging is less than 10min.
3. The structure-performance integrated forming method of high-strength aluminum alloy according to claim 1, wherein the 7000-series aluminum alloy after the solution and pre-hardening treatment in the step S1 forms a GPII region with a thickness of 1-2 atomic layers; the 6000 series aluminum alloy forms GPII regions of 1-30nm in length, which include initial β "and pre- β"; forming GPII area of 1-15nm length of 2000 series aluminum alloy; the GPII area formed by all the pre-hardened plates accounts for 60% -100%, and the GPII area is completely coherent with the aluminum matrix and has small obstruction to dislocation movement, so that the pre-hardened plates have high plasticity and can be used for subsequent cold forming.
4. The structure-performance integrated forming method of the high-strength aluminum alloy according to claim 1, wherein in the step S2, the pre-hardened plate has good structural stability, so that the plate can be stored within 18 months, and the plate storage and transportation of a plate supplier are facilitated.
5. The structure-performance integrated forming method of the high-strength aluminum alloy according to claim 1, wherein the structural performance of the formed member in the step S4 is stable, the precipitation temperature threshold of the subsequent strengthening phase is high, and the natural aging does not affect the precipitation phase, so that the member can be parked for 12 months, and the subsequent uniform baking finish and powder spraying treatment of a factory is facilitated.
6. The structure-performance integrated forming method of the high-strength aluminum alloy according to claim 1, wherein the plate material after the baking finish in the step S4 is precipitated with a main strengthening phase with a small size, specifically: when the plate is 7xxx aluminum alloy, baking varnish for 10-30min at 170-220 ℃, and separating out an eta' phase with the size of 10-30 nm; when the plate is 6xxx aluminum alloy, baking varnish for 15-35min at 160-220 ℃, and separating out a beta' phase with the size of 30-40 nm; when the plate is 2xxx aluminum alloy, baking varnish is carried out for 10-20min at the temperature of 190-230 ℃, and the precipitated phase is a theta' phase with the size of 20-30 nm. The dislocation recovery effect is not obvious in the paint baking process, a large number of dislocations are generated in the cold forming process, more nucleation sites and deformation energy storage are provided for the strengthening phase, the precipitation threshold of the main strengthening phase is reduced, the strengthening phase is fully precipitated and has small size in the paint baking process, the strength of the component is further improved, and the component is far beyond the T6 state.
Use of a 6xxx aluminum alloy for satellite dish reflector splitting, wherein the 6xxx aluminum alloy is prepared according to the preparation method of any one of claims 1-6.
8. Use in satellite antenna reflecting surface beamforming according to claim 7, wherein said beamforming specifically comprises the following steps:
s1, carrying out 535 ℃ solution treatment on the high-strength aluminum alloy for 30-50min, then quenching, and then carrying out heat preservation in an aging furnace at 110-160 ℃ for 2-12h, wherein a GPII area formed by pre-hardening the plate material accounts for 60% -100%, and a GPII area with the length of 1-30nm is formed in the plate material and comprises initial beta 'and pre-beta';
s2, parking the pre-hardened plate for forming;
s3, stamping and forming each melon petal by using the pre-hardened plate, wherein the final deformation is within 25%;
s4, uniformly baking varnish at 160-220 ℃ for 15-35min, and performing powder spraying treatment on the formed melon petals;
s5, welding edge strips, and assembling and forming: bolt holes are pre-drilled on the edge strips, so that the split parts are assembled and formed by bolts penetrating through the bolt holes, and the material of the edge strips is the same as that of the split parts;
s6, assembling a reinforcing rod to obtain a reflecting mask: utilize the bolt to wear to establish the stiffener and be fixed in on the strake, the stiffener provides the back with the strake jointly for the plane of reflection and supports.
9. Use in satellite antenna reflecting surface beamforming according to claim 7, wherein said beamforming specifically comprises the following steps:
s1, carrying out 535 ℃ solution treatment on the high-strength aluminum alloy for 30-50min, then quenching, and then carrying out heat preservation in an aging furnace at 110-160 ℃ for 2-12h, wherein a GPII area formed by pre-hardening the plate material accounts for 60% -100%, and a GPII area with the length of 1-30nm is formed in the plate material and comprises initial beta 'and pre-beta';
s2, parking the pre-hardened plate for forming;
s3, stamping and forming each melon petal by using the pre-hardened plate, wherein the final deformation is within 25%;
s4, parking the formed plate for no more than 12 months;
s5, uniformly baking varnish at 160-220 ℃ for 15-35min, and performing powder spraying treatment on the formed melon petals;
s6, welding edge strips, assembling and forming: bolt holes are pre-drilled on the edge strips, so that the split parts are assembled and formed by bolts penetrating through the bolt holes, and the material of the edge strips is the same as that of the split parts;
s7, assembling a reinforcing rod to obtain a reflecting mask: utilize the bolt to wear to establish the stiffener and be fixed in on the strake, the stiffener provides the back with the strake jointly for the plane of reflection and supports.
10. Use in satellite antenna reflecting surface beamforming according to claim 7, wherein said beamforming specifically comprises the following steps:
step S1, carrying out 535 ℃ solution treatment on the high-strength aluminum alloy for 30-50min, then quenching, and then carrying out heat preservation in an aging furnace at 110-160 ℃ for 2-12h, wherein the GPII area formed by pre-hardening the plate material accounts for 60% -100%, and the GPII area with the length of 1-30nm, which comprises initial beta and pre-beta, is formed in the plate material;
s2, parking the pre-hardened plate for forming;
s3, stamping and forming each melon petal by using the pre-hardened plate, wherein the final deformation is within 25%;
s4, parking the formed plate for no more than 12 months;
and S5, uniformly baking varnish at 160-220 ℃ for 15-35min, and performing powder spraying treatment on the formed melon petals.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| JP2009161851A (en) * | 2007-12-11 | 2009-07-23 | Furukawa-Sky Aluminum Corp | Aluminum alloy sheet for cold press forming, method for manufacturing the same, and cold press forming method for aluminum alloy sheet |
| CN105063522A (en) * | 2010-09-08 | 2015-11-18 | 美铝公司 | 6xxx aluminum alloys, and methods for producing the same |
| CN105441837A (en) * | 2016-01-07 | 2016-03-30 | 北京科技大学 | Treatment method for improving forming properties and strengths of 7xxx-series aluminium alloy thin plates |
| CN108193101A (en) * | 2018-01-04 | 2018-06-22 | 北京工业大学 | Er, Zr, Si microalloying Al-Mg-Cu alloys and its thermomechanical treatment process |
| CN113426869A (en) * | 2021-06-08 | 2021-09-24 | 武汉理工大学 | Thermoforming method for satellite communication antenna mask |
| CN114525459A (en) * | 2022-02-24 | 2022-05-24 | 武汉理工大学 | Forming method of aluminum alloy section frame |
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2022
- 2022-08-08 CN CN202210941196.9A patent/CN115433887A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2009161851A (en) * | 2007-12-11 | 2009-07-23 | Furukawa-Sky Aluminum Corp | Aluminum alloy sheet for cold press forming, method for manufacturing the same, and cold press forming method for aluminum alloy sheet |
| CN105063522A (en) * | 2010-09-08 | 2015-11-18 | 美铝公司 | 6xxx aluminum alloys, and methods for producing the same |
| CN105441837A (en) * | 2016-01-07 | 2016-03-30 | 北京科技大学 | Treatment method for improving forming properties and strengths of 7xxx-series aluminium alloy thin plates |
| CN108193101A (en) * | 2018-01-04 | 2018-06-22 | 北京工业大学 | Er, Zr, Si microalloying Al-Mg-Cu alloys and its thermomechanical treatment process |
| CN113426869A (en) * | 2021-06-08 | 2021-09-24 | 武汉理工大学 | Thermoforming method for satellite communication antenna mask |
| CN114525459A (en) * | 2022-02-24 | 2022-05-24 | 武汉理工大学 | Forming method of aluminum alloy section frame |
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