CN203689967U - Ignition cable for spaceflight - Google Patents
Ignition cable for spaceflight Download PDFInfo
- Publication number
- CN203689967U CN203689967U CN201320637439.6U CN201320637439U CN203689967U CN 203689967 U CN203689967 U CN 203689967U CN 201320637439 U CN201320637439 U CN 201320637439U CN 203689967 U CN203689967 U CN 203689967U
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- layer
- ignition cable
- cable
- conductors
- space flight
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Abstract
The utility model discloses an ignition cable for spaceflight. The ignition cable includes a plurality of conductors. The conductors are coated with tetrafluoroethylene propylene copolymer insulating layers to form insulating wire cores. The insulating wire cores are twisted into a harness to form a cable core. A cable core is wrapped with a non-woven fabric wrapping layer, a polyurethane sheath layer and an integrated fireproof layer in sequence. The integrated fireproof layer includes a fireproof cotton blanket wrapping layer, a wrapping layer, an aramid fiber yarn braiding layer and a nickel plated annealed copper wire braiding layer from inside to outside in sequence. The design of the ignition cable is novel. With the integrated fireproof layer, the ignition cable is proved by experiments to be able to withstand a burning test of a gasoline burner for 2 minutes at a temperature of 1100-1200 DEG C and stop burning within 30s after the fire is removed, so that the fireproof performance of the ignition cable is improved. In addition, the ignition cable has the advantages of flexibility, high strength, impact resistance, and the like.
Description
Technical field:
The utility model relates to electric wire, relates in particular to a kind of space flight firing cable.
Background technology:
In recent years, along with the raising of aeronautical and space technology communication technology of satellite, need continuous currency rocket launching communication satellite to be served to the track of appointment.Due to improving constantly of lift-off technology.Also more and more higher with the requirement of firing cable to transmitting.
Common firing cable can not meet the requirement of refractory temperature, therefore, needs designer to design a kind of high strength, resistant to elevated temperatures novel space flight firing cable.
Utility model content:
In order to make up prior art problem, the purpose of this utility model is to provide a kind of space flight firing cable, and structural design novelty has improved the refractory temperature of cable in the time of satellite igniting transmitting greatly, meets the demand of actual environment.
The technical solution of the utility model is as follows:
Space flight firing cable, comprise many conductors, it is characterized in that: many described conductors are all coated with fluorinated ethylene propylene copolymer insulating barrier outward and form insulated wire cores, the mutual stranded bunchy of insulated wire cores forms cable core, cable core is coated with nonwoven fabrics lapping layer, urethane jacket layer, Comprehensive Preventing fire bed outward successively, and Comprehensive Preventing fire bed is followed successively by fire-resistant cotton blanket lapping layer, Mica tape layer, aramid fiber yarn braid, nickel plating annealed copper wire braid from inside to outside.
Described space flight firing cable, is characterized in that: many described conductors all adopt the tin annealed copper wire bundle strand that 7 diameters are 0.25mm to form.
Described space flight firing cable, is characterized in that: the nominal thickness of described fluorinated ethylene propylene copolymer insulating barrier is 0.2～0.3mm.
Described space flight firing cable, is characterized in that: the count of described aramid fiber yarn braid is not less than 90%.
The utility model has the advantages that:
The utility model structural design novelty, by the design of Comprehensive Preventing fire bed, experiment can stand 1100 ℃～1200 ℃ burning tests of benzine blow lamp 2 minutes, remove after flame and naturally extinguish in 30s, improve fire resistance, in addition, also there is the features such as softness, intensity be high, shock-resistant.
Accompanying drawing explanation:
Fig. 1 is structural representation of the present utility model.
Embodiment:
Referring to Fig. 1:
Space flight firing cable, comprise many conductors 1, many outer 2 one-tenth insulated wire cores of fluorinated ethylene propylene copolymer insulating barrier structure that are all coated with of conductor 1, the mutual stranded bunchy of insulated wire cores forms cable core, cable core is coated with nonwoven fabrics lapping layer 3, urethane jacket layer 4, Comprehensive Preventing fire bed outward successively, and Comprehensive Preventing fire bed is followed successively by fire-resistant cotton blanket lapping layer 5, Mica tape layer 6, aramid fiber yarn braid 7, nickel plating annealed copper wire braid 8 from inside to outside.
The nominal thickness of fluorinated ethylene propylene copolymer insulating barrier 2 is 0.2～0.3mm.
The count of aramid fiber yarn braid 7 is not less than 90%.
The utility model material therefor and physical dimension:
1. conductor: adopt tin annealed copper wire composition, conductor structure 7/0.25mm;
2. insulation: adopt FEP, insulation nominal thickness 0.25mm;
3. wrapped: wrapped nonwoven fabrics after total stranding;
4. sheath: adopt flame retardant polyurethane, external diameter 12.0mm;
5. Comprehensive Preventing fire bed
A) the outer fire-resistant blanket+mica tape of wrapped one deck of cable;
B) braiding one deck aramid fiber, count is not less than 90%;
C) outermost layer braiding one deck nickel plating annealed copper wire, count is not less than 85%;
D) Comprehensive Preventing fire bed external diameter: maximum outside diameter 16.0mm.
Claims (4)
1. a space flight firing cable, comprise many conductors, it is characterized in that: many described conductors are all coated with fluorinated ethylene propylene copolymer insulating barrier outward and form insulated wire cores, the mutual stranded bunchy of insulated wire cores forms cable core, cable core is coated with nonwoven fabrics lapping layer, urethane jacket layer, Comprehensive Preventing fire bed outward successively, and Comprehensive Preventing fire bed is followed successively by fire-resistant cotton blanket lapping layer, Mica tape layer, aramid fiber yarn braid, nickel plating annealed copper wire braid from inside to outside.
2. space flight firing cable according to claim 1, is characterized in that: many described conductors all adopt the tin annealed copper wire bundle strand that 7 diameters are 0.25mm to form.
3. space flight firing cable according to claim 1, is characterized in that: the nominal thickness of described fluorinated ethylene propylene copolymer insulating barrier is 0.2～0.3mm.
4. space flight firing cable according to claim 1, is characterized in that: the count of described aramid fiber yarn braid is not less than 90%.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320637439.6U CN203689967U (en) | 2013-10-15 | 2013-10-15 | Ignition cable for spaceflight |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320637439.6U CN203689967U (en) | 2013-10-15 | 2013-10-15 | Ignition cable for spaceflight |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203689967U true CN203689967U (en) | 2014-07-02 |
Family
ID=51011841
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320637439.6U Expired - Fee Related CN203689967U (en) | 2013-10-15 | 2013-10-15 | Ignition cable for spaceflight |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203689967U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107887066A (en) * | 2017-11-03 | 2018-04-06 | 芜湖航天特种电缆厂股份有限公司 | Magnaflux, high temperature resistant harness |
-
2013
- 2013-10-15 CN CN201320637439.6U patent/CN203689967U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107887066A (en) * | 2017-11-03 | 2018-04-06 | 芜湖航天特种电缆厂股份有限公司 | Magnaflux, high temperature resistant harness |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140702 Termination date: 20151015 |
|
| EXPY | Termination of patent right or utility model |