CN103009006B - Method for making space remote sensor bracket and space remote sensor bracket - Google Patents
Method for making space remote sensor bracket and space remote sensor bracket Download PDFInfo
- Publication number
- CN103009006B CN103009006B CN201210571528.5A CN201210571528A CN103009006B CN 103009006 B CN103009006 B CN 103009006B CN 201210571528 A CN201210571528 A CN 201210571528A CN 103009006 B CN103009006 B CN 103009006B
- Authority
- CN
- China
- Prior art keywords
- remote sensor
- space remote
- sensor bracket
- decomposition
- aluminum
- 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
- 238000000034 method Methods 0.000 title claims abstract description 52
- 238000000354 decomposition reaction Methods 0.000 claims abstract description 60
- 239000002131 composite material Substances 0.000 claims abstract description 47
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 44
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 44
- 238000003466 welding Methods 0.000 claims abstract description 28
- 239000000919 ceramic Substances 0.000 claims abstract description 20
- 238000004458 analytical method Methods 0.000 claims abstract description 18
- 230000008569 process Effects 0.000 claims abstract description 11
- 238000012545 processing Methods 0.000 claims abstract description 8
- 238000004519 manufacturing process Methods 0.000 claims description 40
- 238000010438 heat treatment Methods 0.000 claims description 28
- 230000035882 stress Effects 0.000 claims description 27
- 230000032683 aging Effects 0.000 claims description 24
- 238000000137 annealing Methods 0.000 claims description 23
- 229910000679 solder Inorganic materials 0.000 claims description 20
- 238000005219 brazing Methods 0.000 claims description 17
- 238000000227 grinding Methods 0.000 claims description 13
- FJMNNXLGOUYVHO-UHFFFAOYSA-N aluminum zinc Chemical compound [Al].[Zn] FJMNNXLGOUYVHO-UHFFFAOYSA-N 0.000 claims description 11
- 238000003754 machining Methods 0.000 claims description 11
- 229910001297 Zn alloy Inorganic materials 0.000 claims description 10
- 238000001816 cooling Methods 0.000 claims description 10
- 229910003460 diamond Inorganic materials 0.000 claims description 9
- 239000010432 diamond Substances 0.000 claims description 9
- 239000000945 filler Substances 0.000 claims description 8
- 229910052751 metal Inorganic materials 0.000 claims description 8
- 239000002184 metal Substances 0.000 claims description 8
- 238000005520 cutting process Methods 0.000 claims description 6
- 238000005498 polishing Methods 0.000 claims description 4
- 238000004140 cleaning Methods 0.000 claims description 3
- 238000001035 drying Methods 0.000 claims description 3
- 238000003801 milling Methods 0.000 claims description 3
- 239000011248 coating agent Substances 0.000 claims description 2
- 238000000576 coating method Methods 0.000 claims description 2
- 238000002844 melting Methods 0.000 claims description 2
- 230000008018 melting Effects 0.000 claims description 2
- 229910000838 Al alloy Inorganic materials 0.000 abstract description 11
- 229910001069 Ti alloy Inorganic materials 0.000 abstract description 7
- 239000000956 alloy Substances 0.000 abstract description 4
- 239000004411 aluminium Substances 0.000 abstract 6
- 239000011159 matrix material Substances 0.000 description 11
- 239000000463 material Substances 0.000 description 5
- 230000004907 flux Effects 0.000 description 3
- 238000003384 imaging method Methods 0.000 description 3
- 238000009715 pressure infiltration Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000008595 infiltration Effects 0.000 description 2
- 238000001764 infiltration Methods 0.000 description 2
- 239000007769 metal material Substances 0.000 description 2
- 239000002245 particle Substances 0.000 description 2
- 238000004663 powder metallurgy Methods 0.000 description 2
- 230000000630 rising effect Effects 0.000 description 2
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 description 2
- 229910010271 silicon carbide Inorganic materials 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000003679 aging effect Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 229910010293 ceramic material Inorganic materials 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000012937 correction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000011068 loading method Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000000704 physical effect Effects 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000005476 soldering Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Landscapes
- Investigating Or Analyzing Materials By The Use Of Ultrasonic Waves (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
Abstract
The invention discloses a method for making a space remote sensor bracket and the space remote sensor bracket, which are designed for solving the problems that an existing space remote sensor bracket made of a common aluminium alloy or titanium alloy material has poor performance and an aluminium-based composite material process cannot be used for making a large-scale three-dimensional component. The method for making the space remote sensor bracket comprises the following specific steps of: the step 1, by physical model analysis, decomposing the space remote sensor bracket which needs to be made into a plurality of decomposition components which meet the physical and mechanical characteristics required by the space remote sensor bracket; the step 2, processing an aluminium-based composite material blank and making the aluminium-based composite material blank into the decomposition components; and the step 3, combining and welding the made decomposition components into the required space remote sensor bracket by a tool, wherein aluminium-based composite material is ceramic-containing aluminium-based composite material. The space remote sensor bracket is a spliced structure formed by connecting a plurality of decomposition components made of the ceramic-containing aluminium-based composite material by a tool combining and welding method.
Description
Technical Field
The invention relates to a manufacturing method of a space remote sensor bracket and the space remote sensor bracket.
Background
The aluminum-based composite material containing the ceramic generally has low density formed by ceramic micro powder and a metal material, and has the advantages of low expansion and high stability of a ceramic material, low plasticity and good thermal conductivity of the metal material and the like, so that the aluminum-based composite material is suitable for aerospace equipment such as a space remote sensor bracket and the like.
The following three methods are generally used for preparing the aluminum matrix composite material:
1: pressureless infiltration;
2: pressure infiltration;
3: powder metallurgy.
The three methods can prepare the silicon carbide particle reinforced aluminum alloy composite material with high volume fraction (more than 40 percent of ceramic volume content), have very good physical properties and are very suitable for preparing space remote sensor supports. However, the three methods have the limitation that the process cannot manufacture large three-dimensional components.
The size of the non-pressure infiltration in the aluminum alloy infiltration direction is difficult to break through 180 mm.
Pressure infiltration makes it difficult for the high volume fraction aluminum alloy composite produced to reach 300mm in all three directions.
The powder metallurgy method for preparing a single-piece material blank of more than 500kg is also very difficult, the three-dimensional size cannot reach 500mm simultaneously, and the large blank material has more defects of loose inside and the like.
However, large three-dimensional remote sensor supports such as 800 × 600 are a trend in aerospace technology applications such as meteorological satellites.
Therefore, how to replace the traditional aluminum alloy or titanium alloy material with poor performance by the aluminum alloy composite material to be applied to the space sensor bracket is a problem which needs to be solved in the current space remote sensor manufacturing process.
Disclosure of Invention
In order to overcome the problems, the invention provides a method for manufacturing a large-scale space remote sensor bracket made of an aluminum-based composite material containing ceramic and the space remote sensor bracket.
In order to achieve the purpose, the manufacturing method of the space remote sensor bracket comprises the following specific steps:
step 1: decomposing a space remote sensor bracket required to be manufactured into a plurality of decomposition components meeting the required physical and mechanical properties through physical model analysis;
step 2: processing an aluminum-based composite material blank containing ceramic and manufacturing the aluminum-based composite material blank into the decomposition component;
and step 3: and combining and welding the manufactured decomposition components into the space remote sensor bracket required to be manufactured through the tool.
Furthermore, the method for manufacturing the decomposition member in the step 2 adopts a light-weight machining method;
the lightweight machining method specifically comprises the following steps:
step M1: grinding the aluminum-based composite material blank on a grinding machine by using a diamond grinding wheel to achieve the process size;
step M2: cutting the outline of the needed decomposition component by a linear cutting method;
step M3: and (3) on a milling machine, groove machining is carried out on the decomposition member by adopting a polycrystalline diamond cutter or a diamond grinding head.
Further, the step 2 further includes a step of performing stress relief heat treatment on the decomposition member after the decomposition member is processed.
Further, the stress relief aging heat treatment adopts a precise annealing method; the precise annealing method sequentially comprises three decomposition steps of annealing, aging and annealing;
the annealing is as follows: heating the decomposition member to 220-230 ℃ at a heating rate of 2-4 ℃/min and keeping for 11-13hr, and naturally cooling to room temperature;
the aging is as follows: heating the decomposition member to 150-160 ℃ at a temperature rising rate of 0.75-1.25 ℃/min, cooling to-115-125 ℃ at a temperature falling rate of 1.5-2.5 ℃/min, and keeping for 2hr +/-10 min.
Further, the stress relief aging heat treatment comprises two times of the precise annealing method.
Further, the welding method in the step 3 is brazing; and the brazing filler metal is aluminum-zinc alloy brazing filler metal.
Further, the brazing comprises the following steps:
step N1: cleaning and drying the welding part of the decomposition component to be welded;
step N2: melting the aluminum-zinc alloy solder and then coating the melted aluminum-zinc alloy solder on the welding part;
step N3: applying 19 to 21khz ultrasonic waves to the decomposition member coated with the brazing filler metal for 4.5 to 5.5 min;
step N4: assembling all decomposition components by using a tool, heating to 345 ℃ and 355 ℃, and naturally cooling after keeping for 8-12 min.
Further, the manufacturing method of the space remote sensor bracket is also provided with a step of removing residual solder after the step 3; and the step of removing the residual solder is to polish the residual solder by adopting manual polishing or a machine tool, and the polished thickness is not more than 1 mm.
Further, after the step 3 is completed, the method also comprises the step of performing stress relief aging heat treatment again.
In order to achieve the purpose, the space remote sensor support is a splicing structure formed by connecting a plurality of decomposing components formed by ceramic-containing aluminum matrix composite materials by a tool combination and welding method.
The manufacturing method of the space remote sensor bracket and the space remote sensor bracket have the beneficial effects that:
1. the invention relates to a method for manufacturing a space remote sensor bracket and the space remote sensor bracket, which are characterized in that an aluminum matrix composite material with small density, low expansion coefficient, high stability, good plasticity and good heat conductivity is adopted to manufacture the space remote sensor bracket.
Compared with the traditional titanium alloy space remote sensor bracket, the mass is reduced by 45 percent, so that the emission cost is reduced; the stability and the thermal control performance are improved by 50 percent, so that the precision loss caused by mechanical vibration and thermal circulation in the operation process is reduced, and the imaging quality of a satellite cloud picture or a ground image of a space remote sensor is ensured;
compared with common aluminum alloy, the thermal expansion coefficient is reduced, so that the high precision and the high imaging quality of the space remote sensor can be still maintained under the action of thermal load.
2. According to the manufacturing method of the space remote sensor bracket and the space remote sensor bracket, the space remote sensor bracket required to be manufactured is decomposed into a plurality of decomposition components, and a splicing structure is formed through tool combination or welding; the problem that the existing manufacturing process of the aluminum-based composite material cannot be used for forming large-scale three-dimensional construction is solved. On the basis of ensuring the physical characteristics of the manufactured space remote sensor bracket to meet through finite element mechanical analysis and modal analysis, the manufactured space remote sensor bracket is successfully manufactured by adopting the aluminum-based composite material, so that the manufactured space remote sensor bracket has the advantages of light weight, good heat conductivity, high stability, high accuracy and the like due to the material characteristics; further, the method is beneficial to mass production by adopting general equipment, simplifies the manufacturing, and reduces the manufacturing cost, the emission cost, the operation maintenance cost and the like.
Drawings
FIG. 1 is a flow chart of a method for manufacturing a bracket of a space remote sensor according to a first embodiment of the present invention;
FIG. 2 is a perspective view of a space remote sensor holder according to a second embodiment of the present invention;
FIG. 3 is a view of the components of the space remote sensor holder of FIG. 2, shown exploded;
FIG. 4 is a flow chart of a lightweight machining process according to a second embodiment of the present invention;
FIG. 5 is a flow chart of a brazing process according to a fourth embodiment of the present invention.
Detailed Description
The invention is further described with reference to the accompanying drawings.
The first embodiment is as follows:
as shown in fig. 1, the manufacturing method of the spatial remote sensor bracket of the embodiment includes the following specific steps:
step 1: decomposing a space remote sensor bracket required to be manufactured into a plurality of decomposition components meeting the required physical and mechanical properties through physical model analysis;
wherein,
the physical model analysis comprises physical model analysis such as finite element mechanical analysis, modal analysis and the like, and the intensity can be verified through simulation calculation and modal frequency analysis is carried out;
the decomposing element can be a plate-shaped element or a tubular element;
step 2: processing an aluminum-based composite material blank and manufacturing the aluminum-based composite material blank into the decomposition component;
and step 3: and combining and welding the manufactured decomposition component into the space remote sensor bracket required to be manufactured through a tool, wherein the aluminum matrix composite material is a ceramic-containing aluminum matrix composite material.
In the manufacturing method of the space remote sensor bracket, the space remote sensor bracket to be manufactured is firstly decomposed into a plurality of decomposed components through physical model analysis, the decomposed components are manufactured by aluminum matrix composite blanks, and then the space remote sensor bracket is formed through tool combination or welding, so that the problem that a large three-dimensional component cannot be directly manufactured by the aluminum matrix composite in the prior art is solved, and the space remote sensor bracket manufactured by the aluminum matrix composite which is small in density, low in expansion coefficient, high in stability, good in plasticity and good in heat conductivity is more superior to the space performance manufactured by the traditional common aluminum alloy material or titanium alloy material, and has the advantages of simple manufacturing process, low cost, suitability for batch generation, further reduction of emission cost and the like.
Example two:
the manufacturing method of the space remote sensor bracket comprises the following specific steps:
as shown in fig. 2-3, step 1: decomposing a space remote sensor bracket (the space remote sensor bracket shown in figure 1) to be manufactured into 8 decomposition components meeting the required physical and mechanical properties through physical model analysis; and the decomposition member is a plate-shaped member;
step 2: processing an aluminum-based composite material blank and manufacturing the aluminum-based composite material blank into the plate-shaped component;
and step 3: and combining and welding the manufactured plate-shaped members into the space remote sensor bracket required to be manufactured through a tool.
Wherein, the manufacturing of the decomposition component sequentially comprises light-weight machining and stress relief aging heat treatment.
As shown in fig. 4, the lightweight machining further includes the following steps:
step S1: grinding the aluminum-based composite material blank on a grinding machine by using a diamond grinding wheel to achieve the process size;
step S2: cutting the outline of the needed decomposition component by a linear cutting method;
step S3: and (3) on a milling machine, groove machining is carried out on the decomposition member by adopting a polycrystalline diamond cutter or a diamond grinding head.
And the mechanical processing is adopted, the technical process is mature, the processing efficiency is high, and the mass flow line production can be realized.
Example three:
in the embodiment, on the basis of the second embodiment, the step of stress relief aging heat treatment is further determined;
the stress relief aging heat treatment adopts a precise annealing method; the precise annealing method sequentially comprises three decomposition steps of annealing, aging and annealing;
the annealing is as follows: heating the decomposition member to 220-230 deg.C (preferably 225 deg.C) at a temperature rising rate of 2-4 deg.C/min (preferably 3 deg.C/min 0) for 11-13hr (preferably 12hr), and naturally cooling to room temperature;
the aging is as follows: the decomposition member is heated to 150 to 160 ℃ (preferably 155 ℃) at a heating rate of 0.75 to 1.25 ℃/min (preferably 1.00 ℃/min), and is cooled to-115 to-125 ℃ (-120 ℃) at a cooling rate of 1.5 to 2.5 ℃/min, preferably for 2hr +/-10 min (preferably 2 hr).
In a specific implementation process, the decomposition components are placed in a high-temperature furnace to carry out the annealing and aging steps, and in order to further ensure the annealing and aging effects, the furnace temperature uniformity is usually kept to be about +/-3 ℃.
In order to ensure product stability and high accuracy in dimension and shape, residual stress is generated in the decomposition member during machining of the decomposition member, and in the present embodiment, the residual stress is removed by stress aging heat treatment. Furthermore, the stress relief aging heat treatment in the embodiment adopts the precise annealing method particularly proposed by the invention, and the effect is remarkable. The uniform difference of stress fields of the once annealed decomposition component is reduced by 30%, and the average stress value of the decomposition component can be reduced by 35% by carrying out the once aging treatment.
Through the aluminum matrix composite that accurate annealing method was handled through this embodiment, surface residual stress is steerable in 50Mpa, for traditional material preparation, surface residual stress keeps the titanium alloy remote sensor support at 100Mpa, has very showing promotion to can guarantee to decompose the holistic dimensional stability height between the component and the space remote sensor who forms by its combination. In addition, due to the high stability, the size and the shape can keep high precision after an environment temperature test and a transition test, and extra correction is not needed; after the space remote sensor support is launched and lifted off, precision loss caused by mechanical vibration and thermal cycle is greatly reduced, and therefore imaging quality of shot images such as satellite cloud pictures and ground images is further guaranteed.
As a further optimization of this embodiment, the precise annealing process may be repeated once again according to the precision requirement of the fabricated bracket of the spatial remote sensor, so as to further eliminate the residual stress on the surface of the decomposition member, thereby further improving the shape and size of the decomposition member.
Example four:
the manufacturing method of the space remote sensor bracket comprises the following specific steps:
step 1: decomposing a space remote sensor bracket required to be manufactured into a plurality of decomposition components meeting the required physical and mechanical properties through physical model analysis;
step 2: processing an aluminum-based composite material blank and manufacturing the aluminum-based composite material blank into the decomposition component;
and step 3: and combining and welding the manufactured decomposition components into the space remote sensor bracket required to be manufactured through the tool. The welding method adopts brazing, and the welding flux is aluminum-zinc alloy welding flux.
The brazing temperature is low, and the residual stress formed during welding is small, so that the integral precision of the space remote sensor support after the spliced structure is formed is not influenced.
In order to obtain better welding effect, the brazing method of the embodiment is different from the ordinary welding, and comprises the following steps (as shown in fig. 5):
step 1: cleaning and drying the welding part of the decomposition component to be welded;
step 2: after the aluminum-zinc alloy solder is melted, the aluminum-zinc alloy solder is coated on the welding position, and the aluminum-zinc alloy solder is melted at a high speed usually at 350 ℃;
and step 3: setting 19-21 khz ultrasonic waves on the decomposition component coated with the aluminum-zinc solder, and generally preferably 20 khz; the duration is 4.5-5.5 min; the connection of the brazing filler metal and the decomposing element can be further reinforced through the loading of the ultrasonic waves;
and 4, step 4: assembling all the decomposition components by utilizing a tool assembly, heating to 345-355 ℃, keeping for 8-12min, and naturally cooling for 10 min. The brazing filler metal is melted again at a high temperature and then all the decomposition members in contact therewith are joined together to form an integral body in a spliced structure.
So far, the space remote sensor bracket is manufactured.
In a specific implementation process, the volume content of the ceramic of the aluminum-based composite material is generally 5-70%, the volume content of the ceramic of the high-volume-fraction aluminum-based composite material is more than 40%, and in order to further ensure the performance of the manufactured space remote sensor bracket, the high-volume-fraction aluminum-based composite material is preferably selected, namely the aluminum-based composite material with the volume content of the ceramic of more than 40% is selected.
Example five:
in this embodiment, on the basis of the previous embodiment, in order to further ensure the high precision and low residual stress performance of the space remote sensor holder manufactured by the method for manufacturing a space remote sensor holder according to the present invention, a stress relief aging heat treatment is performed again after the welding is performed, so as to further reduce the residual stress on the surface of the space remote sensor holder. The stress-relief aging heat treatment can be carried out by adopting a common aging treatment or the precise annealing method described in the third embodiment.
As a further improvement of this embodiment, the manufacturing method of the space remote sensor bracket of this embodiment further includes a step of removing the residual solder after completing the soldering; and the step of removing the residual solder is to polish the residual solder by adopting manual polishing or a machine tool, and the polished thickness is not more than 1 mm.
And polishing redundant welding flux, further ensuring the high precision of the shape and the size of the space remote sensor bracket, further improving the performance of the space remote sensor bracket, and setting the polished thickness to be less than 1mm in order not to generate new residual stress.
In a specific implementation, the second stress aging heat treatment can be arranged before the step of removing the residual solder or after the step of removing the residual solder. But preferably after the removal of the residual solder in order to prevent the grinding to be too thick from causing new residual stress.
The space remote sensor bracket manufactured by the manufacturing method of the space remote sensor bracket provided by the embodiment takes a 800mm three-dimensional splicing member as an example, the space remote sensor bracket is placed at room temperature for 6 months, and the parallelism, perpendicularity and form and position precision of the space remote sensor bracket are kept within the range of 5um, which is far higher than those of space remote sensor brackets manufactured by common aluminum alloy and titanium alloy.
The first embodiment:
the spatial remote sensor support is a splicing structure formed by connecting a plurality of decomposing components formed by ceramic-containing aluminum matrix composite materials by a tool combination and welding method.
The space remote sensor bracket of the embodiment is different from the traditional space remote sensor bracket,
firstly, the materials are different, and the ceramic-containing aluminum matrix composite material adopted in the embodiment is preferably a high volume fraction aluminum composite material with the ceramic volume content of more than 40%, such as silicon carbide particle reinforced aluminum alloy composite material, rather than the traditional common aluminum alloy and titanium alloy; the aluminum-based composite material containing the ceramic has the characteristics of low expansion rate and high stability of the ceramic, good plasticity of aluminum, low density and good thermal conductivity, so that the especially manufactured space remote sensor bracket has the advantages of high specific rigidity and specific strength, low expansion coefficient, good thermal conductivity, good temperature uniformity, high hot hole precision and the like;
secondly, the spatial remote sensor support is a splicing structure formed by connecting a plurality of decomposition components obtained by physical model analysis in a tool combination and welding manner; therefore, the problem that the aluminum-based composite material containing the ceramic can not be directly used for forming a large three-dimensional member and can not be used for manufacturing a space remote sensor bracket is solved. The space remote sensor bracket is decomposed into a plurality of decomposition frameworks meeting the requirements of physical characteristics by adopting a physical model such as UG or PROE software through finite element mechanical simulation analysis or modal analysis and the like, so that the ceramic-containing aluminum-based composite material can be adopted, and the splicing structure can simultaneously meet the requirements of various characteristics of the space remote sensor bracket through the physical model analysis and subsequent steps such as stress relief, brazing and the like.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are also included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope defined by the claims.
Claims (5)
1. A manufacturing method of a space remote sensor bracket is characterized by comprising the following specific steps:
step 1: decomposing a space remote sensor bracket required to be manufactured into a plurality of decomposition components meeting the required physical and mechanical properties through physical model analysis;
step 2: processing an aluminum-based composite material blank containing ceramic and manufacturing the aluminum-based composite material blank into the decomposition component;
and step 3: assembling and welding the manufactured decomposition component into a space remote sensor bracket required to be manufactured through a tool;
the method for manufacturing the decomposition member in the step 2 adopts a lightweight machining method;
the lightweight machining method specifically comprises the following steps:
step M1: grinding the aluminum-based composite material blank on a grinding machine by using a diamond grinding wheel to achieve the process size;
step M2: cutting the outline of the needed decomposition component by a linear cutting method;
step M3: on a milling machine, groove machining is carried out on the decomposition member by adopting a polycrystalline diamond cutter or a diamond grinding head;
the step 2 further comprises the step of performing stress relief aging heat treatment on the decomposition component after the decomposition component is processed;
the stress relief aging heat treatment adopts a precise annealing method; the precise annealing method sequentially comprises three decomposition steps of annealing, aging and annealing;
the annealing is as follows: heating the decomposition member to 220-230 ℃ at a heating rate of 2-4 ℃/min and keeping for 11-13hr, and naturally cooling to room temperature;
the aging is as follows: heating the decomposition component to 150-160 ℃ at a heating rate of 0.75-1.25 ℃/min, cooling to-115-125 ℃ at a cooling rate of 1.5-2.5 ℃/min, and keeping for 2hr +/-10 min;
the stress-relief aging heat treatment comprises two times of the precise annealing method.
2. A method for manufacturing a bracket of a space remote sensor according to claim 1, wherein the welding method in the step 3 is brazing; and the brazing filler metal is aluminum-zinc alloy brazing filler metal.
3. A method of fabricating a space remote sensor holder according to claim 2, wherein the brazing further comprises the steps of:
step N1: cleaning and drying the welding part of the decomposition component to be welded;
step N2: melting the aluminum-zinc alloy solder and then coating the melted aluminum-zinc alloy solder on the welding part;
step N3: applying 19 to 21khz ultrasonic waves to the decomposition member coated with the brazing filler metal for 4.5 to 5.5 min;
step N4: assembling all decomposition components by using a tool, heating to 345 ℃ and 355 ℃, and naturally cooling after keeping for 8-12 min.
4. The manufacturing method of the space remote sensor bracket according to claim 1, wherein the manufacturing method of the space remote sensor bracket is further provided with a step of removing residual solder after the step 3; and the step of removing the residual solder is to polish the residual solder by adopting manual polishing or a machine tool, and the polished thickness is not more than 1 mm.
5. A space remote sensor holder manufacturing method according to claim 2, 3 or 4, further comprising a step of stress relief aging heat treatment again after the step 3 is completed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210571528.5A CN103009006B (en) | 2012-12-25 | 2012-12-25 | Method for making space remote sensor bracket and space remote sensor bracket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210571528.5A CN103009006B (en) | 2012-12-25 | 2012-12-25 | Method for making space remote sensor bracket and space remote sensor bracket |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103009006A CN103009006A (en) | 2013-04-03 |
| CN103009006B true CN103009006B (en) | 2015-05-06 |
Family
ID=47958410
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210571528.5A Active CN103009006B (en) | 2012-12-25 | 2012-12-25 | Method for making space remote sensor bracket and space remote sensor bracket |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103009006B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108204885B (en) * | 2018-01-30 | 2019-12-20 | 北京空间机电研究所 | Method for verifying stability of titanium alloy precise optical supporting structure |
| CN109317930A (en) * | 2018-11-14 | 2019-02-12 | 广西玉柴重工有限公司 | A kind of abnormity bearing stand manufacturing method and its bearing support |
| CN113609728B (en) * | 2021-07-28 | 2024-01-26 | 盐城工学院 | Laser ultrasonic elliptical vibration simulation method for particle reinforced titanium-based composite material |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07284856A (en) * | 1994-04-15 | 1995-10-31 | Showa Alum Corp | Manufacture of bent article |
| CN1907643A (en) * | 2006-08-22 | 2007-02-07 | 机械科学研究总院 | Layered manufacturing method of metal parts |
| CN102632347A (en) * | 2012-01-09 | 2012-08-15 | 西安交通大学 | Aluminium matrix composite, brazing filler metal for aluminium alloy and brazing method |
-
2012
- 2012-12-25 CN CN201210571528.5A patent/CN103009006B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07284856A (en) * | 1994-04-15 | 1995-10-31 | Showa Alum Corp | Manufacture of bent article |
| CN1907643A (en) * | 2006-08-22 | 2007-02-07 | 机械科学研究总院 | Layered manufacturing method of metal parts |
| CN102632347A (en) * | 2012-01-09 | 2012-08-15 | 西安交通大学 | Aluminium matrix composite, brazing filler metal for aluminium alloy and brazing method |
Non-Patent Citations (3)
| Title |
|---|
| 张人佶,卢清萍等.基于CAD/CAM/RPM的快速模具制造技术.《计算机辅助设计与制造》.2000,(第4期),第8-9页. * |
| 高体份SiC/Al复合材料在星载遥感器中应用;王永宪等;《红外与激光工程》;20110731;第40卷(第7期);第1299-1304页 * |
| 高体积分数SiC颗粒增强铝基复合材料的超声波钎焊;张洋等;《焊接》;20081231(第8期);第29-31页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103009006A (en) | 2013-04-03 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US11833615B2 (en) | Method for preparing multiple-material variable-rigidity component by efficient collaborative additive manufacturing | |
| CN104715091B (en) | A kind of method for quickly forming and manufacturing of aluminium alloy periodic lattice porous structure | |
| CN103009006B (en) | Method for making space remote sensor bracket and space remote sensor bracket | |
| CN110614364A (en) | Manufacturing method of large-sized thin-wall annular inner cavity casing part with complex structure | |
| US20170333995A1 (en) | Method for connecting workpieces which are produced from a raw material using an additive manufacturing process` | |
| Tiismus et al. | Challenges of additive manufacturing of electrical machines | |
| CN105154701A (en) | Method for preparing high temperature titanium alloy by adopting selective laser melting rapid formation technique | |
| CN106041075B (en) | A kind of high energy beam increasing material manufacturing method of metal parts hanging structure | |
| CN108326317B (en) | TiAl alloy and Ti2Method for preparing annular part from AlNb powder | |
| CN109746453B (en) | Laser repair method and device | |
| CN105127755A (en) | Workpiece forming and reinforcing composite machining device and method | |
| CN105252001B (en) | A kind of laser forming manufacturing process of titanium alloy integrated impeller blade | |
| CN104004982B (en) | A kind of titanium alloy component stablizes heat treatment process method | |
| CN104014922B (en) | A kind of hard alloy and the quick diffusion welding method of steel | |
| JP6491859B2 (en) | Sputtering target manufacturing method and sputtering target | |
| JP2007160403A (en) | Repair method for propagating epitaxial crystal structure | |
| CN108247050A (en) | A kind of large scale load gimbal integral manufacturing method | |
| CN106270889A (en) | A kind of add the method that TC4 and Ceramic brazing performance are improved in foam copper intermediate layer | |
| CN104923785A (en) | Electric arc 3D printing device and method for magnesium alloy tubular structural components | |
| CN105479007A (en) | Defect mending method for casting Ti3A1-type alloy plate disk by laser beam welding | |
| CN106735224A (en) | A kind of porous metal structure part hot melt drop printing deposition method for preparing and device | |
| JP2010277022A (en) | Optical device | |
| CN107234239B (en) | The arc deposited laser of robot pose control forges increasing material manufacturing method and equipment | |
| CN109663918A (en) | A kind of manufacturing process of TC4 alloy covering-frame structure | |
| CN108500274A (en) | A kind of integrally formed miniature annular element being connected in series with and 3D printing method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address |
Address after: 226000 91 Hexing Road, Nantong Economic and Technological Development Zone, Jiangsu Province Patentee after: Jiangsu Chiyu Aerospace Technology Co.,Ltd. Address before: No. 198 Yungang Road, Fengtai District, Beijing 100072 Patentee before: BEIJING CHIYU KONGTIAN TECHNOLOGY DEVELOPMENT Co.,Ltd. |
|
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: Room 402-2, building 2, No. 81, Chengxin Road, Qishan Industrial Park, Xikou Town, Fenghua District, Ningbo City, Zhejiang Province, 315000 (Jizhi Yungu Industrial Park) Patentee after: Zhejiang Chiyu sky Technology Co.,Ltd. Address before: 226000 91 Hexing Road, Nantong Economic and Technological Development Zone, Jiangsu Province Patentee before: Jiangsu Chiyu Aerospace Technology Co.,Ltd. |
|
| CP03 | Change of name, title or address | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of invention: Method for Making Space Remote Sensor Supports and Space Remote Sensor Supports Effective date of registration: 20230831 Granted publication date: 20150506 Pledgee: Zhejiang Tailong Commercial Bank Co.,Ltd. Ningbo Fenghua sub branch Pledgor: Zhejiang Chiyu sky Technology Co.,Ltd. Registration number: Y2023980054710 |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right |