CN108749022A - A kind of laying method of excipient composite material antenna reflector - Google Patents
A kind of laying method of excipient composite material antenna reflector Download PDFInfo
- Publication number
- CN108749022A CN108749022A CN201810383719.6A CN201810383719A CN108749022A CN 108749022 A CN108749022 A CN 108749022A CN 201810383719 A CN201810383719 A CN 201810383719A CN 108749022 A CN108749022 A CN 108749022A
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- China
- Prior art keywords
- piecemeal
- honeycomb core
- prepreg
- paving
- covering
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- 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.)
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Classifications
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- 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
- B29C70/342—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 isostatic pressure
-
- 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
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Aerials With Secondary Devices (AREA)
Abstract
The present invention provides a kind of laying methods of excipient composite material antenna reflector, covering prepreg is cut into the narrowband of one fixed width, laying angle is controlled using technique model, ensure prepreg overlay angular deviation within ± 3 °, edge joint position uses docking mode, honeycomb core uses piecemeal joining method, center is 1 piece of round piecemeal, splice for uniform fan piecemeal on periphery, it is placed along the big direction of curvature in fan-shaped piecemeal core direction, the present invention is from covering laying method, honeycomb core combination etc. improves traditional molding methods, be conducive to cut down the accumulation of residual stress, reduce cavity, the mass defects such as layering and fold.Improve the machining accuracy and surface quality of product.
Description
Technical field
The present invention relates to the molding of excipient antenna reflector manufacture, especially a kind of excipient composite material antenna reflector
Laying method.
Background technology
Currently, advanced composite material has become the preferred material of space remote sensing technology satellite antenna, opposite traditional material, multiple
Condensation material has many advantages, such as that light weight, specific strength and specific modulus height, endurance, designability are strong, to space remote sensing technology system
The promotion of system performance plays an important role.
Excipient composite material antenna reflector is a kind of free-form surface reflector, compares usual reflector, and excipient antenna is anti-
Emitter cannot use the complete information in an accurate expression type face of digital analytic equation, shape to be generally irregular shape, bent
Rate changes very greatly.There is higher gain compared to usual reflector, signal transmission is reliable and stable, has been widely used for communication and defends
The modern advanceds such as star, radar and astrosurveillance field.
Currently, the excipient antenna reflector of honeycomb sandwich construction mainly selects autoclave molding method, it is general using tradition
Secondary curing moulding process.In conventional method, the inside and outside covering prepreg flood paving in tooling respectively, after in autoclave
Interior one-step solidification moulding, inside and outside covering is combined with honeycomb core after going out tank demoulding, rear to carry out secondary curing molding, is carried out after going out tank
Demoulding finishing.Using this process, since excipient antenna reflector surface curvature is larger, when covering flood paving each interlayer not
Easily easily there is the defects of cavity, layering, fold in compacting, interlayer.In addition, when covering is combined with honeycomb core, honeycomb core uses flood
Paving, in Curvature varying large area, honeycomb core is bonded difficulty with mould tire and easy tos produce larger residual stress, holds after product solidification
Easily there is buckling deformation, influences the machining accuracy and surface quality of product.
In order to solve the deficiency in traditional excipient antenna reflector forming method, raising reflector machining accuracy and quality,
It is badly in need of a kind of novel moulding technique.
Invention content：
The present invention develops a kind of novel excipient composite material antenna reflector laying method, compares conventional method product
It is molded rear profile face precision higher, surface quality is more preferable.
A kind of laying method of excipient composite material antenna reflector carries out paving molding using covering prepreg, including
Following steps：
Covering prepreg is cut into the narrowband of one fixed width by 1-1, and width is 40mm~60mm, and length is practical with product
Paving length is consistent；
The narrowbands 1-2 carry out paving according to layout design machine direction, and laying angle is controlled using technique model, ensure pre-
Within ± 3 °, edge joint position uses docking mode, carries out vacuumizing pressure per one layer of prepreg of paving for leaching material laying angular deviation
It is real, so that prepreg is bonded completely with mould fetalism face；
After the completion of 1-3 pavings, carries out one-step solidification moulding respectively in autoclave, taken off after inside and outside covering forming
Mould；
The inside and outside coverings of 1-4 are combined with honeycomb core in tooling, and honeycomb core uses piecemeal joining method, center 1
Block circle piecemeal, periphery are spliced for uniform fan piecemeal, and fan-shaped piecemeal core direction is placed along the big direction of curvature, honeycomb core
Stitching position is filled using foamed glue, one layer of glued membrane of paving between inside and outside covering and honeycomb core, and compacting is vacuumized after the completion of combination；
After the completion of the inside and outside coverings of 1-5 are combined with honeycomb core, secondary curing molding is carried out in autoclave；
1-6 antenna reflectors carry out ageing treatment after going out tank, rear demoulding finishing.
The present invention improves traditional molding methods from covering laying method, honeycomb core combination etc., narrow
The accumulation for being conducive to cut down residual stress with paving method, reduces the mass defects such as cavity, layering and fold.Honeycomb core piecemeal splices
Method is avoided cannot be bonded using whole paving honeycomb core with mould tire completely, is generated buckling deformation, is increased so as to cause residual stress
Big problem improves the machining accuracy and surface quality of product.The technology is given birth in civilian, militay space flight satellite development
Have begun to apply in production, as Asia-Pacific, goddess in the moon's series of satellites antenna development in used this technology, engineer application to show
Design requirement is reached using the type face precision of the technology excipient antenna reflector, stable signal transmission and reliability obviously carry
Height has opened up the manufacturing technology of Modern Satellite antenna.
Description of the drawings：
Fig. 1 is covering paving schematic diagram
3 pieces of splicing method schematic diagrames of Fig. 2 honeycomb cores
The 5 pieces of splicing method signals of Fig. 3 honeycomb cores
The 7 pieces of splicing method signals of Fig. 4 honeycomb cores
Explanation is numbered in figure：1--- toolings, the narrowbands 2---, 3--- circle honeycomb pellets, 4--- are fan-shaped
Piecemeal, 5-- honeycomb core pieces.
Specific implementation mode：
The laying method of excipient composite material antenna reflector is described further with reference to example figure.According to this
Prepreg, is cut into the narrowband 2 of one fixed width by method before covering prepreg paving, width is 40mm~60mm, length and production
The practical paving length of product is consistent, and narrowband 2 carries out paving according to layout design machine direction in tooling 1 when paving, uses technique
Model controls laying angle, ensures prepreg overlay angular deviation within ± 3 °, edge joint position uses docking mode (Fig. 1), often
One layer of prepreg of paving carries out vacuumizing compacting, so that prepreg is bonded completely with mould fetalism face, avoids entrained air bubbles between laying.
After the completion of paving, carries out one-step solidification moulding respectively in autoclave, demoulded after inside and outside covering forming.Covering and honeycomb
Core anabolic process is combined (attached drawing 2~4) using piecemeal splicing method, and reflector center position is round honeycomb pellet 3, periphery
For the fan-shaped piecemeal 4 uniformly placed, 4 core direction of fan-shaped piecemeal is placed along the big direction of curvature, and honeycomb core stitching position makes
It is filled with foamed glue.Depending on the quantity of fan-shaped piecemeal is according to reflector projection bore, projection bore is bigger, and piecemeal is more, attached drawing 2
~4 be respectively 3 pieces of honeycomb core, 5 pieces, 7 pieces of splicing methods.One layer of glued membrane of paving between inside and outside covering and honeycomb core is taken out after the completion of combination
Vacuum debulk.After the completion of inside and outside covering is combined with honeycomb core, secondary curing molding is carried out in autoclave.Last antenna-reflected
Device carries out ageing treatment after going out tank, rear demoulding finishing.
Embodiment：Carbon fiber excipient antenna reflector
Product design requirement：Reflector skin material is carbon fiber prepreg, and honeycomb core is to have hole aluminium honeycomb core, glued membrane
Medium temperature glued membrane, projection bore are 1500mm, it is desirable that type face precision R.M.S≤0.25mm.
1, paving：Carbon fiber prepreg is cut to the narrowband 2 of width 40mm using CNC cutting machine, length is with practical paving
It pastes subject to length.Tooling 1 be ready to complete after carry out the paving of covering prepreg (see Fig. 1), every narrowband 2 according to design requirement fibre
It ties up direction and carries out paving, 2 piece of narrowband uses docking mode, strictly controls laying angle using technique model in splicing,
It carries out vacuumizing compacting after the completion of every layer of prepreg paving.
2, one-step solidification：After the completion of the inside and outside covering paving of reflector, one-step solidification moulding is carried out respectively in autoclave.
3, it demoulds：After the completion of covering solidification, goes out tank and demoulded.
4, it combines：Inside and outside covering is combined with honeycomb core in tooling.Honeycomb core combination is using 5 pieces of splicing methods (see figure
3), center is the round honeycomb core 3 of 1 piece of Φ 400mm, and periphery is the sectored cell core 4 of 4 equal portions, 4 core item of sectored cell core
Direction is placed along the big direction of tooling Curvature varying, and 5 position of honeycomb core piece is filled using foamed glue, inside and outside covering and honeycomb
One layer of glued membrane of paving between core vacuumizes compacting after the completion of combination.
5, secondary curing：After the completion of covering is combined with honeycomb core, secondary curing molding is carried out in autoclave.
6, demoulding finishing：Product carries out ageing treatment after going out tank, rear demoulding finishing.
The carbon fiber excipient antenna reflector processed using the above method, is proved, type face precision can through multiple production practices
Reach within 0.2mm, the defects of product surface quality is good, no cavity, layering, fold occurs, and product quality is in order, full
Sufficient product design requirement.
Claims (1)
1. a kind of laying method of excipient composite material antenna reflector carries out paving molding, feature using covering prepreg
It is following steps：
Covering prepreg is cut into the narrowband of one fixed width by 1-1, and width is 40mm~60mm, length and the practical paving of product
Length is consistent；
The narrowbands 1-2 carry out paving according to layout design machine direction, control laying angle using technique model, ensure prepreg
Within ± 3 °, edge joint position uses docking mode for laying angular deviation, carries out vacuumizing compacting per one layer of prepreg of paving, make
Prepreg is bonded completely with mould fetalism face；
After the completion of 1-3 pavings, carries out one-step solidification moulding respectively in autoclave, demoulded after inside and outside covering forming；
The inside and outside coverings of 1-4 are combined with honeycomb core in tooling, and it is 1 piece of circle that honeycomb core, which uses piecemeal joining method, center,
Shape piecemeal, periphery are spliced for uniform fan piecemeal, and fan-shaped piecemeal core direction is placed along the big direction of curvature, honeycomb core splicing
Position is filled using foamed glue, one layer of glued membrane of paving between inside and outside covering and honeycomb core, and compacting is vacuumized after the completion of combination；
After the completion of the inside and outside coverings of 1-5 are combined with honeycomb core, secondary curing molding is carried out in autoclave；
1-6 antenna reflectors carry out ageing treatment after going out tank, rear demoulding finishing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810383719.6A CN108749022A (en) | 2018-04-25 | 2018-04-25 | A kind of laying method of excipient composite material antenna reflector |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810383719.6A CN108749022A (en) | 2018-04-25 | 2018-04-25 | A kind of laying method of excipient composite material antenna reflector |
Publications (1)
| Publication Number | Publication Date |
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| CN108749022A true CN108749022A (en) | 2018-11-06 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810383719.6A Pending CN108749022A (en) | 2018-04-25 | 2018-04-25 | A kind of laying method of excipient composite material antenna reflector |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109719969A (en) * | 2018-12-29 | 2019-05-07 | 北京航天天美科技有限公司 | Laying method on type face mould tool |
| CN111196048A (en) * | 2018-11-19 | 2020-05-26 | 航天特种材料及工艺技术研究所 | Forming method of large-size special-shaped structure/heat-proof integrated component and integrated component |
| CN112248494A (en) * | 2020-09-08 | 2021-01-22 | 江苏航宇航空装备制造有限公司 | Method for molding multi-embedded-part sandwich antenna housing |
| CN112537047A (en) * | 2020-11-17 | 2021-03-23 | 西安飞机工业（集团）有限责任公司 | Forming and assembling method for composite material reflector |
| CN114131957A (en) * | 2021-11-12 | 2022-03-04 | 湖北三江航天红阳机电有限公司 | Mold for large-size RTM product and preparation method of RTM product |
| CN114131950A (en) * | 2021-11-05 | 2022-03-04 | 中材科技（阜宁）风电叶片有限公司 | Method for laying wind power blade skin |
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| CN101769417A (en) * | 2008-12-29 | 2010-07-07 | 陶春有 | Curve special stainless steel cellular board and molding method thereof |
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| CN111196048A (en) * | 2018-11-19 | 2020-05-26 | 航天特种材料及工艺技术研究所 | Forming method of large-size special-shaped structure/heat-proof integrated component and integrated component |
| CN111196048B (en) * | 2018-11-19 | 2022-03-04 | 航天特种材料及工艺技术研究所 | Forming method of large-size special-shaped structure/heat-proof integrated component and integrated component |
| CN109719969A (en) * | 2018-12-29 | 2019-05-07 | 北京航天天美科技有限公司 | Laying method on type face mould tool |
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| CN112248494A (en) * | 2020-09-08 | 2021-01-22 | 江苏航宇航空装备制造有限公司 | Method for molding multi-embedded-part sandwich antenna housing |
| CN112537047A (en) * | 2020-11-17 | 2021-03-23 | 西安飞机工业（集团）有限责任公司 | Forming and assembling method for composite material reflector |
| CN112537047B (en) * | 2020-11-17 | 2022-05-27 | 西安飞机工业（集团）有限责任公司 | Forming and assembling method for composite material reflector |
| CN114131950A (en) * | 2021-11-05 | 2022-03-04 | 中材科技（阜宁）风电叶片有限公司 | Method for laying wind power blade skin |
| CN114131957A (en) * | 2021-11-12 | 2022-03-04 | 湖北三江航天红阳机电有限公司 | Mold for large-size RTM product and preparation method of RTM product |
| CN114131957B (en) * | 2021-11-12 | 2023-12-19 | 湖北三江航天红阳机电有限公司 | Mold for large-size RTM product and preparation method of RTM product |
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Application publication date: 20181106 |
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