CN117445439A - Composite material star-sensitive beam forming die and preparation method thereof - Google Patents
Composite material star-sensitive beam forming die and preparation method thereof Download PDFInfo
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- CN117445439A CN117445439A CN202311485533.9A CN202311485533A CN117445439A CN 117445439 A CN117445439 A CN 117445439A CN 202311485533 A CN202311485533 A CN 202311485533A CN 117445439 A CN117445439 A CN 117445439A
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- sensitive
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- 239000002131 composite material Substances 0.000 title claims abstract description 61
- 238000002360 preparation method Methods 0.000 title abstract description 8
- 229920002379 silicone rubber Polymers 0.000 claims abstract description 53
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 48
- 238000003754 machining Methods 0.000 claims abstract description 14
- 239000002184 metal Substances 0.000 claims abstract description 10
- 239000004945 silicone rubber Substances 0.000 claims description 19
- 229910000831 Steel Inorganic materials 0.000 claims description 8
- 238000012545 processing Methods 0.000 claims description 8
- 239000010959 steel Substances 0.000 claims description 8
- 238000010438 heat treatment Methods 0.000 claims description 6
- 238000000034 method Methods 0.000 claims description 6
- 238000005086 pumping Methods 0.000 claims description 6
- 239000003795 chemical substances by application Substances 0.000 claims description 3
- 239000011248 coating agent Substances 0.000 claims description 3
- 238000000576 coating method Methods 0.000 claims description 3
- 238000001816 cooling Methods 0.000 claims description 3
- 238000003825 pressing Methods 0.000 claims description 3
- 239000011347 resin Substances 0.000 claims description 3
- 229920005989 resin Polymers 0.000 claims description 3
- 238000007711 solidification Methods 0.000 claims description 3
- 230000008023 solidification Effects 0.000 claims description 3
- 239000007787 solid Substances 0.000 claims description 2
- 238000000748 compression moulding Methods 0.000 claims 2
- 238000000465 moulding Methods 0.000 abstract description 5
- 239000000835 fiber Substances 0.000 abstract description 3
- 230000001502 supplementing effect Effects 0.000 abstract 1
- 230000007547 defect Effects 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 230000003071 parasitic effect Effects 0.000 description 1
- 238000012805 post-processing Methods 0.000 description 1
- 239000000523 sample Substances 0.000 description 1
- 238000002791 soaking Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/345—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using matched moulds
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Moulds For Moulding Plastics Or The Like (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The invention provides a composite star-sensitive beam forming die and a preparation method thereof, wherein the die structure comprises a bottom plate, a silicon rubber core die, reinforcing rib splicing blocks, outer splicing blocks, a positioning plate and a die sleeve; the locating plate and the splice block are assembled in a modularized manner through screw locating; the main body part is heated to expand and pressurize the silicon rubber for molding, and the reinforcing rib is laterally complemented by the silicon rubber to meet molding requirements; and a proper amount of machining allowance is designed on the mounting surface of the cross beam, and the spatial position relationship between the mounting surface and the star-sensitive mounting surface is ensured through post-machining. According to the invention, the forming mould is positioned by modularly designing the metal splicing blocks of the reinforcing ribs, the forming quality of the reinforcing ribs is ensured by a silicon rubber lateral pressure supplementing principle, the profile precision is realized by designing machining allowance for the mounting surface of the cross beam, the continuity of fibers is ensured, and the prepared composite star-sensitive cross beam has good apparent quality and high internal quality.
Description
Technical Field
The invention relates to the technical field of mold design and preparation methods of composite structural members, in particular to a composite star-sensitive beam forming mold and a preparation method thereof.
Background
The star sensor is an optical attitude control sensor, can accurately know the position of a satellite and the attitude condition in space, and is used for navigating and controlling the attitude of the satellite. The pointing error of the star sensor is mainly caused by deformation, such as thermal deformation, of a star sensor bracket (hereinafter referred to as a star sensor bracket) caused by the influence of space environment. The star sensor support is used for connecting a star sensor and a supporting structure in a satellite assembly, and has the characteristics of light weight, high rigidity, small creep and high thermal stability, and a high-modulus carbon fiber composite material is generally adopted as a main body material of the star sensor support.
Because the single-probe star sensor has limited view field, the space distribution of the observation vector is denser, the parasitic light interference reduces the reliability of the system, and in order to overcome the defects, a plurality of star sensors are usually required to be installed, and work independently and are mutually backed up, so that the gesture measurement precision and reliability can be improved.
The on-orbit pointing precision of the star sensor is improved, the on-orbit pointing precision is significant to high-precision remote sensing satellites, and the integrated design of a plurality of star-sensitive brackets is more beneficial to the thermal stability of the star-sensitive installation link aiming at the pointing requirement of higher precision. The composite star-sensitive cross beam integrates a plurality of star-sensitive bracket heads on the cross beam through an integrated forming method, and a certain spatial position relation is required to be ensured between a cross beam mounting surface and a star-sensitive mounting surface of the composite star-sensitive cross beam, wherein the cross beam mounting surface is a connecting mounting surface of the star-sensitive cross beam and a supporting structure. Meanwhile, in order to ensure high precision and high stability of the head parts of the star-sensitive brackets, the rigidity of the head parts of the star-sensitive brackets can be improved by adding reinforcing ribs from the structural design. However, the molding and processing difficulty of the composite material is obviously increased, so that not only is the continuous and undamaged fiber at each part ensured, but also the molding quality of the reinforcing rib, including the space position of the reinforcing rib and the internal quality of the reinforcing rib, are required to meet the requirements.
Patent document CN107442667a discloses a fourth crossbeam moulded die, including upper die base, die holder, four angles of upper die base lower surface are provided with four stand alone type guide pillar guide pin bushing, be provided with first backing plate in the die cavity in the middle of the upper die base, first backing plate side is provided with first terrace die insert, first terrace die insert side is provided with the second backing plate, second backing plate side is provided with the second terrace die insert, the upper die base below is provided with the die holder, the die holder die cavity both ends are provided with spacing post, the center is provided with the liftout board in the die cavity of die holder, liftout board one side is provided with the die cavity insert, the liftout board opposite side is provided with the baffle, the long limit edge of die cavity of die holder is provided with first staple bolt.
For the composite material with dense reinforcing ribs and complex molded surfaces, a method for designing the silicone rubber core mold by using the silicone rubber core mold is generally adopted, and the method has the defects that the surface of the composite material formed by expanding the silicone rubber core mold is uneven, the processing standard is difficult to find, the processing amount is large, and the transmission of force is not directly influenced by the reinforcing ribs, so that improvement is needed.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a composite star-sensitive beam forming die and a preparation method thereof.
The invention provides a composite material star-sensitive beam forming die, which comprises: the composite material star-sensitive cross beam, a bottom plate, a silicon rubber core die, a reinforcing rib splicing block, an outer splicing block, a positioning plate and a die sleeve;
the silicon rubber core mould structure is a metal core mould, solid silicon rubber is coated outside the metal core mould structure, the metal core mould is positioned on the bottom plate by using screws, the composite material star-sensitive cross beam is positioned at the outer side of the silicon rubber core mould, and reinforcing rib splicing blocks at two sides of the silicon rubber core mould are connected with the positioning plate by using screws; the reinforcing rib splicing blocks at the two sides of the non-silicone rubber core mold are connected with the outer splicing blocks through screws, and the reinforcing rib splicing blocks are placed into the mold sleeve after the structure is assembled.
Preferably, the composite star-sensitive cross beam comprises a plurality of star-sensitive bracket heads, the plurality of star-sensitive bracket heads are integrated on the cross beam, and a preset number of reinforcing ribs are distributed on the periphery of the star-sensitive bracket heads.
Preferably, the composite star-sensitive cross beam is designed with a machining allowance of 0.3-0.5 mm on the mounting surface.
Preferably, the composite star-sensitive beam forming die is matched with the die in advance through preheating.
Preferably, the composite star-sensitive beam forming die is heated by a silicone rubber core die and is internally expanded to provide lateral force, and surplus resin is extruded to the reinforcing ribs.
Preferably, a metal core mold is opened on the silicon rubber core mold.
Preferably, positioning grooves or positioning holes are formed in the bottom plate and the outer spliced blocks.
Preferably, limit bosses are added on the bottom plate and the die sleeve.
Preferably, the composite star-sensitive beam forming die adopts a structure mode of combining a steel die with the internal expansion of a silicon rubber core die, wherein the non-reinforcing rib position adopts the silicon rubber core die to heat and expand and press for forming, and the reinforcing rib position adopts a steel-to-steel die assembly and press for forming.
The preparation method of the composite material star-sensitive cross beam provided by the invention comprises the following steps:
step S1: coating a release agent on the surfaces of the silicon rubber core mold, the reinforcing rib splicing blocks and the outer splicing blocks;
step S2: mounting a silicon rubber core mould at the beam on a bottom plate, paving a processing layer prepreg, paving an overall layer prepreg, and performing vacuum pre-pumping after the paving is finished;
step S3: pre-soaking and layering the rest of the surfaces of the silicon rubber core mold and the reinforcing rib splicing blocks, and performing vacuum pre-pumping after layering;
step S4: connecting the layered reinforcing rib splice with a locating plate through a screw to form a modularized locating group;
step S5: installing a plurality of groups of modularized positioning groups and the rest of silicone rubber core molds in the step S3 on a bottom plate, and combining the modularized positioning groups and the rest of silicone rubber core molds at the beam;
step S6: installing a die sleeve on the bottom plate by using screws, and installing the outer splicing blocks into the die sleeve;
step S7: placing the composite material star-sensitive beam forming die on a press, heating to soften the prepreg and pressing the prepreg to form a die;
step S8: continuously heating the press to a solidification point, preserving heat for a preset time, cooling, and demolding the composite material star-sensitive cross beam;
step S9: the composite star-sensitive cross beam is installed into a machining tool, and the machining layer of the mounting surface of the cross beam is machined, so that the precision of the mounting surface and the spatial position relationship between the mounting surface and the star-sensitive mounting surface are ensured.
Compared with the prior art, the invention has the following beneficial effects:
(1) The reinforcing rib is formed by adopting a steel die, the inner side silicon rubber core die is heated to expand inwards to provide lateral force, surplus resin is extruded to the reinforcing rib, the internal quality of the reinforcing rib is ensured, and meanwhile, the reinforcing rib is straight and bright, and the apparent state is good;
(2) The positioning block is used for positioning the reinforcing rib splicing blocks to realize modularized positioning, so that each reinforcing rib group is ensured to be not deviated, and the position degree of the reinforcing rib is high;
(3) The beam mounting surface is designed with a processing layer, the mounting surface precision can be ensured through post processing, and meanwhile, the whole layer of fibers are not damaged.
Drawings
Other features, objects and advantages of the present invention will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:
FIG. 1 is a schematic structural view of a forming die of a composite star-sensitive cross beam;
FIG. 2 is a perspective view of a composite star-sensitive cross beam of the present invention;
FIG. 3 is a perspective view of a modular positioning group of a composite star-sensitive beam forming die;
FIG. 4 is a perspective view of the positioning of a molding die bottom plate and a silicone rubber core die of the composite star-sensitive cross beam of the invention;
FIG. 5 is a schematic view of a processing layer of a composite star-sensitive cross beam in a composite star-sensitive cross beam forming die according to the invention;
in the figure: 1-a composite star-sensitive cross beam; 2-a bottom plate; 3-silicone rubber core; 4-splicing reinforcing ribs; 5-outer tiles; 6, positioning a plate; 7-die sleeve.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the present invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications could be made by those skilled in the art without departing from the inventive concept. These are all within the scope of the present invention.
Examples
The invention provides a composite star-sensitive beam forming die, which is shown in figures 1-5, and comprises a composite star-sensitive beam 1, a bottom plate 2, a silicon rubber core die 3, reinforcing rib blocks 4, outer blocks 5, a positioning plate 6 and a die sleeve 7.
The forming die adopts a structural form of combining a steel die with the internal expansion of a silicon rubber core die, wherein the non-reinforcing rib position adopts the silicon rubber core die to heat and expand and press for forming, and the reinforcing rib position adopts steel to mold the steel for forming.
The reinforcing rib splicing blocks are connected with the positioning plates through screws to form modularized positioning groups, and positioning of each reinforcing rib group at the space position is achieved.
And the metal core mould is arranged on the silicon rubber core mould, and the positioning grooves or the positioning holes are arranged on the bottom plate and the outer splicing blocks, so that the degree of freedom of the silicon rubber core mould is reduced, and the uniformity of the wall thickness of the composite material star-sensitive cross beam is ensured.
The reinforcing rib splicing blocks are connected with the outer splicing blocks by screws to be hung tightly, so that the positioning accuracy is improved.
And limiting bosses are added on the bottom plate and the die sleeve, so that the die assembly precision is improved, and the deformation of the die sleeve caused by the expansion of the silicone rubber core die is reduced.
And a proper amount of machining allowance is designed on the mounting surface of the cross beam, and the spatial position relation between the mounting surface and the star-sensitive mounting surface is ensured through post-machining.
The invention provides a preparation method of a composite star-sensitive beam, which adopts a composite star-sensitive beam forming die and specifically comprises the following steps:
s1, coating a release agent on the surfaces of the silicon rubber core mold, the reinforcing rib splicing blocks and the outer splicing blocks;
s2, mounting a silicon rubber core mould at the beam on a bottom plate, paving a processing layer prepreg, paving an integral layer prepreg, and performing vacuum pre-pumping after the paving is finished;
s3, performing prepreg paving on the surfaces of the rest of the silicon rubber core mold and the reinforcing rib splicing blocks, and performing vacuum pre-pumping after the paving is completed;
s4, connecting the reinforcing rib spliced blocks after layering with a locating plate through screws to form a modularized locating group;
s5, installing a plurality of modularized positioning groups and other silicon rubber core molds on the bottom plate, and combining the modularized positioning groups and the rest silicon rubber core molds with the beam silicon rubber core molds;
s6, installing the die sleeve on the bottom plate by using screws, and installing the outer splicing blocks into the die sleeve.
And S7, placing the composite material star-sensitive beam forming die on a press, heating to soften the prepreg and pressing the die.
S8, continuously heating the press to a solidification point, preserving heat for a period of time, cooling, and demolding the composite material star-sensitive cross beam.
S9, loading the composite star-sensitive cross beam into a machining tool, and ensuring the precision of the mounting surface and the spatial position relationship between the mounting surface and the star-sensitive mounting surface through machining a machining layer of the mounting surface of the cross beam.
Those skilled in the art will appreciate that the systems, apparatus, and their respective modules provided herein may be implemented entirely by logic programming of method steps such that the systems, apparatus, and their respective modules are implemented as logic gates, switches, application specific integrated circuits, programmable logic controllers, embedded microcontrollers, etc., in addition to the systems, apparatus, and their respective modules being implemented as pure computer readable program code. Therefore, the system, the apparatus, and the respective modules thereof provided by the present invention may be regarded as one hardware component, and the modules included therein for implementing various programs may also be regarded as structures within the hardware component; modules for implementing various functions may also be regarded as being either software programs for implementing the methods or structures within hardware components.
The foregoing describes specific embodiments of the present invention. It is to be understood that the invention is not limited to the particular embodiments described above, and that various changes or modifications may be made by those skilled in the art within the scope of the appended claims without affecting the spirit of the invention. The embodiments of the present application and features in the embodiments may be combined with each other arbitrarily without conflict.
Claims (10)
1. A composite star-sensitive beam forming die, comprising: the composite material star-sensitive cross beam (1), a bottom plate (2), a silicon rubber core mould (3), reinforcing rib splicing blocks (4), outer splicing blocks (5), a positioning plate (6) and a mould sleeve (7);
the silicon rubber core mold (3) is of a metal core mold, solid silicon rubber is coated outside the metal core mold, the metal core mold is positioned on the bottom plate (2) by using screws, the composite material star-sensitive cross beam (1) is positioned at the outer side of the silicon rubber core mold (3), and reinforcing rib splicing blocks (4) at two sides of the silicon rubber core mold (3) are connected with the positioning plate (6) by using screws; the reinforcing rib splicing blocks (4) at two sides of the non-silicone rubber core mold (3) are connected with the outer splicing blocks (5) through screws, and the non-silicone rubber core mold is placed into the mold sleeve (7) after the above structure is assembled.
2. The composite star-sensitive cross beam forming die according to claim 1, wherein the composite star-sensitive cross beam (1) comprises a plurality of star-sensitive bracket heads, the plurality of star-sensitive bracket heads are integrated on the cross beam, and a preset number of reinforcing ribs are distributed on the periphery of the star-sensitive bracket heads.
3. The composite star-sensitive beam forming die according to claim 1, wherein the composite star-sensitive beam (1) is designed with a machining allowance of 0.3-0.5 mm on a mounting surface.
4. The composite star-sensitive beam forming die of claim 1, wherein the composite star-sensitive beam forming die is clamped in advance by preheating.
5. The composite star-sensitive beam forming die according to claim 1, wherein the composite star-sensitive beam forming die is raised in temperature by a silicone rubber core die (3) to provide a lateral force, and the surplus resin is extruded to the reinforcing ribs.
6. The composite star-sensitive beam forming die according to claim 1, wherein a metal core die is provided on the silicone rubber core die (3).
7. The composite star-sensitive cross beam forming die according to claim 1, wherein positioning grooves or positioning holes are formed in the bottom plate (2) and the outer splicing blocks (5).
8. The composite star-sensitive beam forming die according to claim 1, wherein limit bosses are added on the bottom plate (2) and the die sleeve (7).
9. The composite star-sensitive beam forming die according to claim 1, wherein the composite star-sensitive beam forming die adopts a structural form of combining a steel die with the internal expansion of a silicone rubber core die (3), wherein the non-reinforcing rib position adopts the temperature rise internal expansion compression molding of the silicone rubber core die (3), and the reinforcing rib position adopts the die assembly compression molding of steel.
10. A method for preparing a composite star-sensitive cross beam, which is characterized by adopting the composite star-sensitive cross beam forming die as claimed in any one of claims 1-9, comprising the following steps:
step S1: coating release agents on the surfaces of the silicon rubber core mold (3), the reinforcing rib splicing blocks (4) and the outer splicing blocks (5);
step S2: a silicon rubber core mould (3) at the beam is mounted on a bottom plate (2), then a processing layer prepreg is paved, then an integral layer prepreg is paved, and vacuum pre-pumping is carried out after the paving is completed;
step S3: performing prepreg layering on the surfaces of the rest of the silicone rubber core mold (3) and the reinforcing rib splicing blocks (4), and performing vacuum pre-pumping after layering is completed;
step S4: connecting the layered reinforcing rib splice blocks (4) with the locating plate (6) through screws to form a modularized locating group;
step S5: installing a plurality of groups of modularized positioning groups and the rest of silicone rubber core molds (3) in the step S3 on a bottom plate, and combining the modularized positioning groups with the silicone rubber core molds (3) at the beam;
step S6: installing a die sleeve (7) on the bottom plate (2) by using screws, and installing the outer splicing blocks (5) into the die sleeve (7);
step S7: placing the composite material star-sensitive beam forming die on a press, heating to soften the prepreg and pressing the prepreg to form a die;
step S8: continuously heating the press to a solidification point, preserving heat for a preset time, then cooling, and demoulding the composite material star-sensitive cross beam (1);
step S9: the composite star-sensitive cross beam (1) is installed in a machining tool, and the machining layer of the mounting surface of the cross beam is machined, so that the precision of the mounting surface and the spatial position relationship between the mounting surface and the star-sensitive mounting surface are ensured.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311485533.9A CN117445439A (en) | 2023-11-08 | 2023-11-08 | Composite material star-sensitive beam forming die and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311485533.9A CN117445439A (en) | 2023-11-08 | 2023-11-08 | Composite material star-sensitive beam forming die and preparation method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117445439A true CN117445439A (en) | 2024-01-26 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311485533.9A Pending CN117445439A (en) | 2023-11-08 | 2023-11-08 | Composite material star-sensitive beam forming die and preparation method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117445439A (en) |
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2023
- 2023-11-08 CN CN202311485533.9A patent/CN117445439A/en active Pending
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