CN204323706U - The metal honeycomb core composite material single plate structure of electrostatic prevention - Google Patents
The metal honeycomb core composite material single plate structure of electrostatic prevention Download PDFInfo
- Publication number
- CN204323706U CN204323706U CN201420770452.3U CN201420770452U CN204323706U CN 204323706 U CN204323706 U CN 204323706U CN 201420770452 U CN201420770452 U CN 201420770452U CN 204323706 U CN204323706 U CN 204323706U
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- metal
- embedded part
- composite material
- wire
- honeycomb core
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Abstract
This patent discloses a kind of metal honeycomb core composite material single plate structure of electrostatic prevention, this structure by connecting the method for wire between composite material plate metal embedded part and aluminium honeycomb, all metal embedded part wires are connected together, realize the electrostatic prevention target that veneer any two points resistance value is less than 10 Ω, solve metal honeycomb core composite material veneer local and integral insulation, the Insulation Problems particularly between metal embedded part.The advantage of this patent is the local and the integral insulation problem that it solve metal honeycomb core composite panel, alleviates satellite surface and inner electrostatic defending pressure.
Description
Technical field:
This patent relates to a kind of metal honeycomb core composite material single plate structure of electrostatic prevention, is specifically related to a kind of carbon fiber skin aluminium honeycomb core composite material single plate structure of electrostatic prevention.
Background technology:
Geostationary orbit satellite, particularly geostationary orbit three axis stable platform satellite, surface and inside are faced with serious charging, electric discharge and relevant electromagnetic interference problem.When the insulator of inside satellite is charged to the electric discharge critical value higher than this insulating material by the direct effect of solar plasma ray, just static discharge phenomenon can be there is.This electric discharge phenomena gently then can form interference to the Sensitive Apparatus of surrounding, cause equipment operation irregularity; Heavy then low-voltage device and Sensitive Apparatus can be damaged, directly threaten the safe in operation of capacity weight and satellite.
Measured data shows, composite structure surface and inner turn-on effect generally do not reach expection requirement.Between embedded part and embedded part there is very large uncertainty in conducting state, and maximum resistance can reach more than 100M Ω.Between any two embedded parts that this and satellite electrostatic prevention design regulation require, to be less than the index of 10 Ω far apart for resistance value.
Summary of the invention:
This patent proposes a kind of metal honeycomb core composite material single plate structure of electrostatic prevention.Solve the problem of composite structure surface and inner electrostatic prevention
As shown in Figure 1, what wherein conduct electricity has the structure of composite material bending block: covering 1, metal beehive 3, metal embedded part 5, and nonconducting have: foamed glue 4, glued membrane 2, fire coat 6.Non-conductive between composite panel embedded part and embedded part is because various glue is by these conductors insulation.According to practical experience, metal beehive 3 and covering 1 are conductings, because area of contact is large, as long as metal beehive 3 has a place to puncture, glued membrane 2 is connected with covering 1 will conducting.And the on-state rate of metal embedded part 5 is lower, be because there is fire coat 6 on metal embedded part 5 surface, have foamed glue 4 around, upper and lower surface has glued membrane 2.In sum, as long as by metal embedded part 5 and metal beehive 3 conducting, just can realize the conducting between metal embedded part 5 and covering 1 and all the other embedded parts, also just achieve whole plate conducting.According to this Analysis on Mechanism, only need to utilize plain conductor 7 by metal embedded part 5 and neighbouring metal beehive 3 conducting, just can realize whole plate conducting.
This patent passes through the fire coat 6 removing metal embedded part 5 between metal embedded part 5 and contiguous metal beehive 3, and increases wire 7 to realize conducting, and wire 7 is the common metal core wire removing insulating barrier; Metal beehive 3 by covering 1 mutual conduction, thus realizes mutual conduction between any embedded part of veneer, and resistance value is less than 10 Ω.
Beneficial effect: the advantage of this patent is the local and the integral insulation problem that it solve metal honeycomb core composite panel, alleviates satellite surface and inner electrostatic defending pressure.
Accompanying drawing illustrates:
Fig. 1 is composite material honeycomb plate structure: wherein: 1, covering; 2, glued membrane; 3, metal beehive; 4, foamed glue; 5, metal embedded part; 6, fire coat.
Fig. 2 embedded part punches and twines wire: wherein: 7, wire; 8, conducting resinl.
Fig. 3 is that thin-walled embedded part is directly wound around wire.
Detailed description of the invention
1. wire 7 prepares: select the common metal core wire removing insulating barrier.
2. metal embedded part 5 conducts electricity and implements
Metal embedded part 5 connects wire 7.Type of attachment has 2 kinds:
The first, directly spile (can adjust size according to diameter of wire) on metal embedded part 5, and passed from aperture by wire 7, winding is tightened, and on aperture and kinking place point conducting resinl 8, as shown in Figure 2.
The second, the thin-wall metal embedded part 5 punched for not having space, adopts the mode being directly wound around wire 7, notes polishing off the fire coat 6 being wound around position, as shown in Figure 3.
Conduct test to the metal embedded part 5 completing conduction enforcement, metal embedded part 5 and wire 7 end should be in conducting state, and conducting resistance is less than 10 Ω.
3. veneer conduction is implemented:
The metal embedded part 5 implemented is put into the bending block before solidification by normal procedure, cuts the honeycomb wall of the metal beehive 3 near wire 7, wire 7 reserved on metal embedded part 5 is sticked in the honeycomb wall of incision, and the upper conducting resinl 8 of point is fixed.
All metal embedded part 5 and metal beehive 3 whether conducting (resistance value is less than 10 ohm) is checked after enforcement.If one-hundred-percent inspection is qualified, continue to carry out according to bending block normal process.Otherwise repair, until all meet turn-on condition.
The casing of certain model remote sensing instrument carbon fiber skin aluminium honeycomb core composite panel composition is tested, conduction process implementing is completed by the art of this patent, it is as follows that rear conduction check result developed by veneer: altogether prepare veneer 8 pieces, measure embedded part 658 place, wherein 602 places (91.5%) within 10 Ω, 10 ~ 100 Ω 41 places (6.2%), 9 places (1.3%) of not conducting.Through later stage conductive processing, 100% conducting can be reached.
Claims (2)
1. the metal honeycomb core composite material single plate structure of an electrostatic prevention, it comprises covering (1), glued membrane (2), metal beehive (3), foamed glue (4), metal embedded part (5), metal embedded part fire coat (6), wire (7), conducting resinl (8), it is characterized in that:
Be conducted with wire (7) between described metal embedded part (5) and metal beehive (3), described wire (7) is the common metal core wire removing insulating barrier, winding is tightened in the aperture on metal embedded part (5), and on kinking place point, conducting resinl (8) makes conducting resistance be less than 10 Ω.
2. the metal honeycomb core composite material single plate structure of a kind of electrostatic prevention according to claim 1, is characterized in that: described metal embedded part (5) and wire are wound around position and polish off fire coat (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420770452.3U CN204323706U (en) | 2014-12-09 | 2014-12-09 | The metal honeycomb core composite material single plate structure of electrostatic prevention |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420770452.3U CN204323706U (en) | 2014-12-09 | 2014-12-09 | The metal honeycomb core composite material single plate structure of electrostatic prevention |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204323706U true CN204323706U (en) | 2015-05-13 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420770452.3U Withdrawn - After Issue CN204323706U (en) | 2014-12-09 | 2014-12-09 | The metal honeycomb core composite material single plate structure of electrostatic prevention |
Country Status (1)
| Country | Link |
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| CN (1) | CN204323706U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104527995A (en) * | 2014-12-09 | 2015-04-22 | 中国科学院上海技术物理研究所 | Antistatic metal honeycomb core composite material veneer structure |
| CN107264837A (en) * | 2017-05-18 | 2017-10-20 | 上海卫星工程研究所 | The Induced by Space Electrostatic Discharges protection design method of satellite large-scale composite material truss |
| CN110925283A (en) * | 2019-11-22 | 2020-03-27 | 西安飞机工业（集团）有限责任公司 | Forming method for array antenna metal plate core glue array panel |
-
2014
- 2014-12-09 CN CN201420770452.3U patent/CN204323706U/en not_active Withdrawn - After Issue
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104527995A (en) * | 2014-12-09 | 2015-04-22 | 中国科学院上海技术物理研究所 | Antistatic metal honeycomb core composite material veneer structure |
| CN104527995B (en) * | 2014-12-09 | 2016-08-24 | 中国科学院上海技术物理研究所 | A kind of metal honeycomb core composite single plate structure of antistatic |
| CN107264837A (en) * | 2017-05-18 | 2017-10-20 | 上海卫星工程研究所 | The Induced by Space Electrostatic Discharges protection design method of satellite large-scale composite material truss |
| CN107264837B (en) * | 2017-05-18 | 2020-03-06 | 上海卫星工程研究所 | Space electrostatic discharge protection design method for large composite material truss of satellite |
| CN110925283A (en) * | 2019-11-22 | 2020-03-27 | 西安飞机工业（集团）有限责任公司 | Forming method for array antenna metal plate core glue array panel |
| CN110925283B (en) * | 2019-11-22 | 2021-07-16 | 西安飞机工业（集团）有限责任公司 | Forming method for array antenna metal plate core glue array panel |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20150513 Effective date of abandoning: 20160824 |
|
| AV01 | Patent right actively abandoned |
Granted publication date: 20150513 Effective date of abandoning: 20160824 |
|
| C25 | Abandonment of patent right or utility model to avoid double patenting |