CN107053696A - The forming method of high-precision satellite sensor crossbeam - Google Patents
The forming method of high-precision satellite sensor crossbeam Download PDFInfo
- Publication number
- CN107053696A CN107053696A CN201710055096.5A CN201710055096A CN107053696A CN 107053696 A CN107053696 A CN 107053696A CN 201710055096 A CN201710055096 A CN 201710055096A CN 107053696 A CN107053696 A CN 107053696A
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- CN
- China
- Prior art keywords
- crossbeam
- reinforcement
- laying
- piece
- forming method
- 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.)
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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
-
- 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
- B29C37/00—Component parts, details, accessories or auxiliary operations, not covered by group B29C33/00 or B29C35/00
- B29C37/02—Deburring or deflashing
-
- 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
Abstract
The present invention provides a kind of forming method of high-precision satellite sensor crossbeam, comprises the following steps：The first step, prepares reinforcement；Second step, the respectively overall laying after laying in the soft mould core for installing crossbeam and the quick head of star；3rd step, carries out overall laying, and form piece after the reinforcement prepared is positioned on product；4th step, by tooling drawing by piece be put into it is framed in, overall matched moulds is in place；5th step, the product after matched moulds is positioned on hot press, heating pressurization precuring；6th step, takes off framed, piece and soft mode core rod, takes out blank；7th step, the clean blank of flash, deburred is put into baking oven and post-processed.The present invention has advantages below：Add the molding mode of post processing using the integral precuring of the quick crossbeam of star and reinforcement, technical process is easy, the complicated star sensor beam strength of many muscle produced is high, and mounting surface angle is accurate, while meeting the requirement of loss of weight.Detected by ultrasonic nondestructive test instrument, Forming Quality is stable.
Description
Technical field
The present invention relates to the forming method of composite material structural member, and in particular to a kind of shaping side of satellite sensor crossbeam
Method.
Background technology
Star sensor is a kind of satellite three-axis attitude measurement apparatus, and star sensor crossbeam is the installation according to star sensor
The matched mounting bracket of angle design, is the key component in satellite assembly part.It is general on satellite to configure three even more
Multi-star sensor, in order to reduce effective erection space, reduces the relativeness change between multiple star sensors, improves satellite
The positioning precision of attitude determination accuracy and payload, increasing product design is that can install multiple star sensors simultaneously
Integral support.Generally, the star sensor'support of this many mounting surfaces take carrier head, rack body and reinforcement each respectively into
Type, the method preparation for being glued assembling.But it is complicated to be glued assembling process, and process efficiency is low, product ontology low intensity.
Patent document (the application number of entitled " a kind of composite material star sensor support and preparation method thereof "：
2013263208.8；Publication number：CN3343868A a kind of forming method of RTM injecting glues) is provided.Although this forming method can one
It is body formed, but product structure is relatively regular, simple, and heavier-weight after shaping, it is impossible to realize the satellite sensitive of many muscle labyrinths
The shaping of device crossbeam.
The content of the invention
For defect of the prior art, present invention aims at provide one kind to overcome existing satellite sensor crossbeam to be molded
The shaping of technology plus the high accuracy for being glued assembling technology procedure complexity, the deficiency that labyrinth RTM injecting glues can not be realized and defect
The forming method of satellite sensor crossbeam.
In order to solve the above technical problems, the present invention provides a kind of forming method of high-precision satellite sensor crossbeam, including
Following steps：The first step, prepares reinforcement；
Second step, the respectively overall laying after laying in the soft mould core for installing crossbeam and the quick head of star；
3rd step, carries out overall laying, and form piece after the reinforcement prepared is positioned on product；
4th step, by tooling drawing by piece be put into it is framed in, overall matched moulds is in place；
5th step, the product after matched moulds is positioned on hot press, heating pressurization precuring；
6th step, takes off framed, piece and soft mode core rod, takes out blank；
7th step, the clean blank of flash, deburred is put into baking oven and post-processed.
Preferably, in the first step, the prepreg for preparing reinforcement is high modulus carbon fiber, modulus >=540GPa, single monolayer thick
Spend for 0.1mm.
Preferably, in the 7th step, temperature in baking oven rises to 180 DEG C ± 2 DEG C from room temperature, and heating rate is 0.5 DEG C/
Min~1.5 DEG C/min, 3h is incubated when temperature reaches 180 DEG C ± 2 DEG C, and temperature is then reduced to 50 DEG C ± 2 DEG C, turned off
Power supply, natural cooling.
Compared with prior art, the present invention has advantages below：After being added using the quick crossbeam of star and the integral precuring of reinforcement
The molding mode of processing, technical process is easy, and the complicated star sensor beam strength of many muscle produced is high, mounting surface angle essence
Standard, while meeting the requirement of loss of weight.Detected by ultrasonic nondestructive test instrument, meet C grades of standards, Forming Quality in GJB2895-97
It is stable.
Brief description of the drawings
By reading the detailed description made with reference to the following drawings to non-limiting example, further feature mesh of the invention
And advantage will become more apparent upon.
Fig. 1 is the high-precision satellite sensor beam structure schematic diagram one of the present invention；
Fig. 2 is the high-precision satellite sensor beam structure schematic diagram two of the present invention；
Fig. 3 is the high-precision satellite sensor crossbeam reinforcing rib structure schematic diagram of the present invention.
In figure：
The quick head of 1- reinforcement 2- crossbeam 3- stars
Embodiment
With reference to specific embodiment, the present invention is described in detail.Following examples will be helpful to the technology of this area
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that to the ordinary skill of this area
For personnel, without departing from the inventive concept of the premise, some changes can also be made and changed.
As shown in FIG. 1 to 3, the forming method of the high-precision satellite sensor crossbeam of the present invention, including：
It is prepared by the first step, preset reinforcement：As shown in figure 3, shaping laminate, is solidified using press, will by product design
Ask and process 8 various sizes of reinforcements, specific placement location is as shown in 1 in Fig. 1,2.
Second step, overall laying：Crossbeam, the quick head of star are installed integrally to spread after laying certain thickness in soft mould core respectively
Layer；Laying 1.5mm on 4 soft modes of crossbeam, matched moulds rear cross beam entirety laying 1mm, with laying on the quick head soft mode of clock star are installed
1.5mm；Crossbeam and overall laying 1mm after the quick head matched moulds of star will be installed.Laying process fiber is continuous, does not allow along machine direction
Overlap joint.Ply stacking-sequence is that quasi-isotropic laying [0/90/+45/-45] ns, n is period, behalf symmetric layups；
3rd step, overall laying：Overall laying, is finally reached after the reinforcement prepared is positioned at product reinforcement
Design requirement thickness；As shown in Figure 1, 2, overlay thickness is 0.5mm to reinforcement placement location；
4th step, it is die-filling：By tooling drawing by die piece be put into it is framed in, overall matched moulds is in place；
5th step, solidification：Product after matched moulds is placed on hot press, heating pressurization precuring；
6th step, the demoulding：Framed, piece and soft mode core rod are taken off, blank is taken out；
7th step, post processing：The clean blank of flash, deburred is put into baking oven and post-processed.Post-processed
Cheng Wei：Room temperature~180 ± 2 DEG C, 0.5~1.5 DEG C/min of heating rate；180 ± 2 DEG C of insulation 3h；180 ± 2 DEG C~50 ± 2 DEG C,
Close power supply, natural cooling.
By the quick crossbeam of star obtained by embodiment, detected by ultrasonic nondestructive test instrument, meet C grades of marks in GJB2895-97
It is accurate.
The specific embodiment of the present invention is described above.It is to be appreciated that the invention is not limited in above-mentioned
Particular implementation, those skilled in the art can make a variety of changes or change within the scope of the claims, this not shadow
Ring the substantive content of the present invention.In the case where not conflicting, feature in embodiments herein and embodiment can any phase
Mutually combination.
Claims (3)
1. a kind of forming method of high-precision satellite sensor crossbeam, it is characterised in that comprise the following steps：
The first step, prepares reinforcement；
Second step, the respectively overall laying after laying in the soft mould core for installing crossbeam and the quick head of star；
3rd step, carries out overall laying, and form piece after the reinforcement prepared is positioned on product；
4th step, by tooling drawing by piece be put into it is framed in, overall matched moulds is in place；
5th step, the product after matched moulds is positioned on hot press, heating pressurization precuring；
6th step, takes off framed, piece and soft mode core rod, takes out blank；
7th step, the clean blank of flash, deburred is put into baking oven and post-processed.
2. the forming method of high-precision satellite sensor crossbeam according to claim 1, it is characterised in that in the first step,
The prepreg for preparing reinforcement is high modulus carbon fiber, and modulus >=540GPa, thickness in monolayer is 0.1mm.
3. the forming method of high-precision satellite sensor crossbeam according to claim 1, it is characterised in that in the 7th step,
Temperature in baking oven rises to 180 DEG C ± 2 DEG C from room temperature, and heating rate is 0.5 DEG C/min~1.5 DEG C/min, when temperature reaches
3h is incubated at 180 DEG C ± 2 DEG C, temperature is then reduced to 50 DEG C ± 2 DEG C, power supply, natural cooling is turned off.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710055096.5A CN107053696B (en) | 2017-01-24 | 2017-01-24 | The forming method of high-precision satellite sensor crossbeam |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710055096.5A CN107053696B (en) | 2017-01-24 | 2017-01-24 | The forming method of high-precision satellite sensor crossbeam |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107053696A true CN107053696A (en) | 2017-08-18 |
| CN107053696B CN107053696B (en) | 2019-10-08 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710055096.5A Active CN107053696B (en) | 2017-01-24 | 2017-01-24 | The forming method of high-precision satellite sensor crossbeam |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111941874A (en) * | 2020-07-24 | 2020-11-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Integrated forming method for composite material reinforced pipeline |
| CN113211829A (en) * | 2021-04-13 | 2021-08-06 | 上海复合材料科技有限公司 | Integral forming method suitable for head of bracket with built-in polygonal box |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103343868A (en) * | 2013-06-27 | 2013-10-09 | 北京卫星制造厂 | Composite material star sensor support and preparation method thereof |
-
2017
- 2017-01-24 CN CN201710055096.5A patent/CN107053696B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103343868A (en) * | 2013-06-27 | 2013-10-09 | 北京卫星制造厂 | Composite material star sensor support and preparation method thereof |
Non-Patent Citations (1)
| Title |
|---|
| 屠善澄 等: "《卫星姿态动力学与控制》", 30 September 2003, 中国宇航出版社 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111941874A (en) * | 2020-07-24 | 2020-11-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Integrated forming method for composite material reinforced pipeline |
| CN113211829A (en) * | 2021-04-13 | 2021-08-06 | 上海复合材料科技有限公司 | Integral forming method suitable for head of bracket with built-in polygonal box |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107053696B (en) | 2019-10-08 |
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