CN109551686A - Antenna reflector composite material skin molding die suitable for satellite - Google Patents
Antenna reflector composite material skin molding die suitable for satellite Download PDFInfo
- Publication number
- CN109551686A CN109551686A CN201811253064.7A CN201811253064A CN109551686A CN 109551686 A CN109551686 A CN 109551686A CN 201811253064 A CN201811253064 A CN 201811253064A CN 109551686 A CN109551686 A CN 109551686A
- Authority
- CN
- China
- Prior art keywords
- reinforcing rib
- composite material
- material skin
- molding die
- satellite
- 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.)
- Pending
Links
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
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/38—Moulds or cores; Details thereof or accessories therefor characterised by the material or the manufacturing process
- B29C33/3842—Manufacturing moulds, e.g. shaping the mould surface by machining
-
- 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
- B29C33/34—Moulds or cores; Details thereof or accessories therefor movable, e.g. to or from the moulding station
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/34—Electrical apparatus, e.g. sparking plugs or parts thereof
- B29L2031/3456—Antennas, e.g. radomes
Abstract
The present invention provides a kind of antenna reflector composite material skin molding die suitable for satellite, mold design thinkings are as follows: reinforcing rib is welded at mold generally welding structure, the type face back side, and mold bottom uses supported at three point, and lifting point is arranged on reinforcing rib；Present invention determine that supporting point uses ball head structure, specifying reinforcing rib is arc, hollow out among reinforcing rib, and the reinforcing rib at lifting point thickens；The present invention is directed to satellite high-precision reflector composite material skin shaping mould, develop a kind of mould structure is light, heterogeneity phantom uniformly, lifting transhipment deformation is small, adapts to the die design method of any workbench.
Description
Technical field
The present invention relates to mold design, and in particular, to the antenna reflector composite material skin suitable for satellite forms
Mold.More particularly, to a kind of design side of high-precision antenna reflector composite material skin molding die suitable for satellite
Method.
Background technique
Antenna reflector composite material skin is as antenna reflector important composition part, and the precision in type face is by direct shadow
Ring antenna reflector type face precision, and the type face accuracy relation of reflector the imaging precision of Statellite antenna.Molding
Mold is as the basis for guaranteeing antenna-reflected type face precision in antenna reflector composite material skin forming process, molding die
Structural stability design it is most important.
Currently, the composite material skin molding die of high-precision reflector is mostly cast structure, the reinforcing rib of mold is side
Shape and arrange at groined type, which results in mould structure heavinesses, and the utilization rate of reinforcing rib is low, the structural stability of molding die with
The time uncertain variation can occur；Secondly mold is in use face contact with flat surface, so that mold is in difference
Flat surface on support stress point also change correspondingly, this will affect the type face precision of mold；And the design of lifting point is unreasonable
The precision of die face is allowed to receive large effect in hoisting process.
Therefore in order to guarantee high-precision reflector composite material skin molding die type face precision, the invention proposes
New design method.
Summary of the invention
For the defects in the prior art, the object of the present invention is to provide a kind of antenna reflector suitable for satellite is compound
Material covering forming mold.
A kind of antenna reflector composite material skin molding die suitable for satellite provided according to the present invention, the day
The generally welding structure of line reflection device composite material skin molding die, bottom use supported at three point, and reinforcing rib is arc, is added
Hollow out among strengthening tendons, lifting point are arranged on reinforcing rib, and the reinforcing rib at lifting point thickens.
Preferably, supporting point uses ball head structure, and the center of the reinforcing rib of arc is overlapped with mold center of gravity, in lifting point
The heart is overlapped with mold center of gravity.
Preferably, reinforcing rib with a thickness of 10mm, the Rib Thickness at lifting point is 15mm.
Preferably, it is processed on the basis of three supporting points when the antenna reflector composite material skin molding die is processed
Monolithic devices face.
Compared with prior art, the present invention have it is following the utility model has the advantages that
1, the arc hollow out reinforcing rib that the present invention uses improves the stock utilization of reinforcing rib, so that mold is more light
Just, and engraved structure is conducive to the heterogeneity phantom of mold.
2, the present invention makes mold be identical three points support on any workbench using supported at three point, guarantees
Mold forced position on any workbench is identical, to ensure that type face precision of the mold on any workbench.
3, lifting point is arranged at reinforcing rib by the present invention, so that mold deflection in lifting transport process is minimum.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon:
Fig. 1 is the antenna reflector composite material skin forming die structure schematic diagram that the present invention is suitable for satellite；
Fig. 2 is the antenna reflector composite material skin molding die supporting point arrangement signal that the present invention is suitable for satellite
Figure；
Fig. 3 is that the present invention shows suitable for the antenna reflector composite material skin molding die arc hollow out reinforcing rib of satellite
It is intended to；
Fig. 4 is the antenna reflector composite material skin molding die lifting point arrangement signal that the present invention is suitable for satellite
Figure.
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, several changes and improvements can also be made.These belong to the present invention
Protection scope.
The invention discloses a kind of setting for high-precision antenna reflector composite material skin molding die suitable for satellite
Meter method, mold design thinking are as follows: reinforcing rib is welded at mold generally welding structure, the type face back side, and mold bottom uses at 3 points
Support, lifting point is arranged on reinforcing rib；Present invention determine that supporting point uses ball head structure, specifying reinforcing rib is arc, is reinforced
Hollow out among muscle, the reinforcing rib at lifting point thicken；The present invention is directed to satellite high-precision reflector composite material skin shaping mould,
Develop a kind of mould structure is light, heterogeneity phantom uniformly, lifting transhipment deformation is small, adapts to the mold design of any workbench
Method.
Below by preference, using a kind of typical high-precision reflector composite material skin as example, by using 3 points
Support, arc hollow out reinforcing rib, lifting point, which is arranged on reinforcing rib, solves mould structure heaviness, and the utilization rate of reinforcing rib is low
Under, workbench requires stringent, the big problem of the medium-sized face deflection of mold hoisting process.See Fig. 1, Fig. 2, which includes: type
Face 1, arc hollow out reinforcing rib 2, bulb support 3, hoisting ring 4.
1, mold materials select
S1, mold use Q235 integral solder.
2, mold design
S2, it determines molding surface size, then the position of supporting point is determined by calculation, guarantee that mold becomes under these three point supports
Shape amount is minimum, and guarantees that the center of three points and mold center of gravity are concentric simultaneously, and supporting point uses ball head structure, is welded on reinforcing rib
On, bulb surface smoothness is 1.6.
S3, design back side reinforcing rib, reinforcing rib centre hollow out, the position of reasonable Arrangement reinforcing rib, periphery is engraved using arc
Empty reinforcing rib 2, and the center of arc is overlapped with mold center of gravity, one end of arc is overlapped with supporting point, reinforcing rib with a thickness of
10mm。
S4, design lifting point, lifting point are evenly arranged on around mold, are fixed on reinforcing rib, the center of lifting point and mold
Center of gravity is overlapped, and the Rib Thickness at lifting point is 15mm.
3, the processing of mold
After S5, mold integral solder are good, first process bottom bulb support, then by bulb support on the basis of process entire type
Face, guarantee type face precision meet the required precision of RMS0.05mm.
In the description of the present application, it is to be understood that term " on ", "front", "rear", "left", "right", " is erected at "lower"
Directly ", the orientation or positional relationship of the instructions such as "horizontal", "top", "bottom", "inner", "outside" is orientation based on the figure or position
Relationship is set, description the application is merely for convenience of and simplifies description, rather than the device or element of indication or suggestion meaning are necessary
It with specific orientation, is constructed and operated in a specific orientation, therefore should not be understood as the limitation to the application.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make a variety of changes or modify within the scope of the claims, this not shadow
Ring substantive content of the invention.In the absence of conflict, the feature in embodiments herein and embodiment can any phase
Mutually combination.
Claims (4)
1. a kind of antenna reflector composite material skin molding die suitable for satellite, which is characterized in that the antenna-reflected
The generally welding structure of device composite material skin molding die, bottom use supported at three point, and reinforcing rib is arc, in reinforcing rib
Between hollow out, lifting point is arranged on reinforcing rib, and the reinforcing rib at lifting point thickens.
2. the antenna reflector composite material skin molding die according to claim 1 suitable for satellite, feature exist
In supporting point uses ball head structure, and the center of the reinforcing rib of arc is overlapped with mold center of gravity, the center of lifting point and mold center of gravity
It is overlapped.
3. the antenna reflector composite material skin molding die according to claim 1 suitable for satellite, feature exist
In, reinforcing rib with a thickness of 10mm, the Rib Thickness at lifting point is 15mm.
4. the antenna reflector composite material skin molding die according to claim 1 suitable for satellite, feature exist
Monolithic devices face is processed on the basis of three supporting points when, the antenna reflector composite material skin molding die is processed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811253064.7A CN109551686A (en) | 2018-10-25 | 2018-10-25 | Antenna reflector composite material skin molding die suitable for satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811253064.7A CN109551686A (en) | 2018-10-25 | 2018-10-25 | Antenna reflector composite material skin molding die suitable for satellite |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109551686A true CN109551686A (en) | 2019-04-02 |
Family
ID=65865193
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811253064.7A Pending CN109551686A (en) | 2018-10-25 | 2018-10-25 | Antenna reflector composite material skin molding die suitable for satellite |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109551686A (en) |
Citations (9)
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|---|---|---|---|---|
| US20060227063A1 (en) * | 2005-04-07 | 2006-10-12 | Vanguard Composites Group, Inc. | Star-rib backing structure for a reflector system |
| AT503547B1 (en) * | 2006-05-16 | 2007-11-15 | Fischer Adv Components Gmbh | Mold for fiber-reinforced, plastic-composite aerospace components, comprises supported, fiber-reinforced composite with low coefficient of thermal expansion |
| CN103247864A (en) * | 2013-05-10 | 2013-08-14 | 中国电子科技集团公司第五十四研究所 | High-precision spinning antenna reflecting surface and manufacturing method thereof |
| CN203864033U (en) * | 2014-05-09 | 2014-10-08 | 浙江华荣航空装备有限公司 | Frame-type forming tooling for airplane composite material component |
| CN104393421A (en) * | 2014-12-11 | 2015-03-04 | 中国电子科技集团公司第五十四研究所 | Split type high-accuracy antenna reflector adopting all-composite material |
| CN105082556A (en) * | 2014-05-07 | 2015-11-25 | 上海航天设备制造总厂 | Von Karman shaped satellite fairing and moulding method thereof |
| CN107037567A (en) * | 2017-05-19 | 2017-08-11 | 北京空间机电研究所 | A kind of 3 bulbs combine radially cementing reflecting mirror support structure |
| CN107419749A (en) * | 2017-08-31 | 2017-12-01 | 中交第四航务工程局有限公司 | FS final spice transport base method for supporting and verification method |
| CN108666762A (en) * | 2018-05-11 | 2018-10-16 | 中国电子科技集团公司第五十四研究所 | A kind of high-precision lightweight triangle antenna panel and manufacturing method |
-
2018
- 2018-10-25 CN CN201811253064.7A patent/CN109551686A/en active Pending
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|---|---|---|---|---|
| US20060227063A1 (en) * | 2005-04-07 | 2006-10-12 | Vanguard Composites Group, Inc. | Star-rib backing structure for a reflector system |
| AT503547B1 (en) * | 2006-05-16 | 2007-11-15 | Fischer Adv Components Gmbh | Mold for fiber-reinforced, plastic-composite aerospace components, comprises supported, fiber-reinforced composite with low coefficient of thermal expansion |
| CN103247864A (en) * | 2013-05-10 | 2013-08-14 | 中国电子科技集团公司第五十四研究所 | High-precision spinning antenna reflecting surface and manufacturing method thereof |
| CN105082556A (en) * | 2014-05-07 | 2015-11-25 | 上海航天设备制造总厂 | Von Karman shaped satellite fairing and moulding method thereof |
| CN203864033U (en) * | 2014-05-09 | 2014-10-08 | 浙江华荣航空装备有限公司 | Frame-type forming tooling for airplane composite material component |
| CN104393421A (en) * | 2014-12-11 | 2015-03-04 | 中国电子科技集团公司第五十四研究所 | Split type high-accuracy antenna reflector adopting all-composite material |
| CN107037567A (en) * | 2017-05-19 | 2017-08-11 | 北京空间机电研究所 | A kind of 3 bulbs combine radially cementing reflecting mirror support structure |
| CN107419749A (en) * | 2017-08-31 | 2017-12-01 | 中交第四航务工程局有限公司 | FS final spice transport base method for supporting and verification method |
| CN108666762A (en) * | 2018-05-11 | 2018-10-16 | 中国电子科技集团公司第五十四研究所 | A kind of high-precision lightweight triangle antenna panel and manufacturing method |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
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| RJ01 | Rejection of invention patent application after publication | ||
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Application publication date: 20190402 |