CN104514086A - Fiber rope used for guided missile covering and manufacturing method thereof - Google Patents
Fiber rope used for guided missile covering and manufacturing method thereof Download PDFInfo
- Publication number
- CN104514086A CN104514086A CN201310448942.1A CN201310448942A CN104514086A CN 104514086 A CN104514086 A CN 104514086A CN 201310448942 A CN201310448942 A CN 201310448942A CN 104514086 A CN104514086 A CN 104514086A
- Authority
- CN
- China
- Prior art keywords
- rope
- viscose
- carbon fiber
- based carbon
- twist
- 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
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Classifications
-
- D—TEXTILES; PAPER
- D07—ROPES; CABLES OTHER THAN ELECTRIC
- D07B—ROPES OR CABLES IN GENERAL
- D07B1/00—Constructional features of ropes or cables
- D07B1/02—Ropes built-up from fibrous or filamentary material, e.g. of vegetable origin, of animal origin, regenerated cellulose, plastics
-
- D—TEXTILES; PAPER
- D04—BRAIDING; LACE-MAKING; KNITTING; TRIMMINGS; NON-WOVEN FABRICS
- D04C—BRAIDING OR MANUFACTURE OF LACE, INCLUDING BOBBIN-NET OR CARBONISED LACE; BRAIDING MACHINES; BRAID; LACE
- D04C1/00—Braid or lace, e.g. pillow-lace; Processes for the manufacture thereof
- D04C1/02—Braid or lace, e.g. pillow-lace; Processes for the manufacture thereof made from particular materials
- D04C1/04—Carbonised or like lace
-
- D—TEXTILES; PAPER
- D02—YARNS; MECHANICAL FINISHING OF YARNS OR ROPES; WARPING OR BEAMING
- D02J—FINISHING OR DRESSING OF FILAMENTS, YARNS, THREADS, CORDS, ROPES OR THE LIKE
- D02J13/00—Heating or cooling the yarn, thread, cord, rope, or the like, not specific to any one of the processes provided for in this subclass
-
- D—TEXTILES; PAPER
- D04—BRAIDING; LACE-MAKING; KNITTING; TRIMMINGS; NON-WOVEN FABRICS
- D04C—BRAIDING OR MANUFACTURE OF LACE, INCLUDING BOBBIN-NET OR CARBONISED LACE; BRAIDING MACHINES; BRAID; LACE
- D04C1/00—Braid or lace, e.g. pillow-lace; Processes for the manufacture thereof
- D04C1/06—Braid or lace serving particular purposes
- D04C1/12—Cords, lines, or tows
-
- D—TEXTILES; PAPER
- D07—ROPES; CABLES OTHER THAN ELECTRIC
- D07B—ROPES OR CABLES IN GENERAL
- D07B1/00—Constructional features of ropes or cables
- D07B1/14—Ropes or cables with incorporated auxiliary elements, e.g. for marking, extending throughout the length of the rope or cable
- D07B1/147—Ropes or cables with incorporated auxiliary elements, e.g. for marking, extending throughout the length of the rope or cable comprising electric conductors or elements for information transfer
-
- D—TEXTILES; PAPER
- D07—ROPES; CABLES OTHER THAN ELECTRIC
- D07B—ROPES OR CABLES IN GENERAL
- D07B2201/00—Ropes or cables
- D07B2201/10—Rope or cable structures
- D07B2201/1096—Rope or cable structures braided
-
- D—TEXTILES; PAPER
- D07—ROPES; CABLES OTHER THAN ELECTRIC
- D07B—ROPES OR CABLES IN GENERAL
- D07B2205/00—Rope or cable materials
- D07B2205/30—Inorganic materials
- D07B2205/3007—Carbon
-
- D—TEXTILES; PAPER
- D07—ROPES; CABLES OTHER THAN ELECTRIC
- D07B—ROPES OR CABLES IN GENERAL
- D07B2401/00—Aspects related to the problem to be solved or advantage
- D07B2401/20—Aspects related to the problem to be solved or advantage related to ropes or cables
- D07B2401/202—Environmental resistance
- D07B2401/2035—High temperature resistance
-
- D—TEXTILES; PAPER
- D10—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
- D10B—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
- D10B2101/00—Inorganic fibres
- D10B2101/10—Inorganic fibres based on non-oxides other than metals
- D10B2101/12—Carbon; Pitch
-
- D—TEXTILES; PAPER
- D10—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
- D10B—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
- D10B2201/00—Cellulose-based fibres, e.g. vegetable fibres
- D10B2201/20—Cellulose-derived artificial fibres
- D10B2201/22—Cellulose-derived artificial fibres made from cellulose solutions
- D10B2201/24—Viscose
Landscapes
- Engineering & Computer Science (AREA)
- Textile Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Yarns And Mechanical Finishing Of Yarns Or Ropes (AREA)
- Ropes Or Cables (AREA)
Abstract
A fiber rope used for guided missile covering and a manufacturing method thereof are disclosed. The rope comprises a rope sheath and a rope core disposed in the rope sheath. The rope sheath is an outer sheath braided by viscose-based carbon fibre strands, with one half of the strands being in an S-twist direction and the rest of the strands being in a Z-twist direction. The rope core is a viscose-based carbon fibre filament aggregate. A product of the method is better in high-temperature performance and safety performance.
Description
Technical field
The present invention relates to field of rope, specifically a kind of cordage coated for guided missile and preparation method thereof.
Background technology
Can produce high temperature during MISSILE LAUNCHING, efficiency that general material is high temperature resistant is difficult to the demand meeting several ten thousand degree, if the accuracy that guided missile does not have " Heat-preventing clothes " that it can be made to strike target declines, guided missile even can be made aloft to reveal.Viscose-based carbon fiber is sticky is be raw material with viscose, and obtained through the high-temperature heat treatment of more than 800 DEG C in non-oxidizing atmosphere again after Low Temperature Heat Treatment take carbon as the fibrous material of Main Ingredients and Appearance, and it is high temperature resistant reaches several ten thousand and spend and cracking do not occur.At present, viscose-based carbon fiber is not also applied to netting field.
Summary of the invention
The object of the invention is: a kind of resistant to elevated temperatures cordage coated for guided missile and preparation method thereof is provided.
Technical scheme of the present invention is: for the cordage that guided missile is coated, include rope skin and the wire rope core being arranged at rope intracutaneous portion, rope skin is set to be twisted with the fingers by half S twist with the fingers to viscose-based carbon fiber rope strand and half Z the outer sleeve body woven to viscose-based carbon fiber rope strand, and wire rope core is set to viscose-based carbon fiber long filament aggregate.
Preferably, rope skin adopts 24 rope strand braidings to form, and wherein S twists with the fingers to viscose-based carbon fiber rope strand is 12, and Z sth. made by twisting is 12 to viscose-based carbon fiber rope strand.
For the preparation method of the coated cordage of guided missile, realize as follows:
1) selection: rope skin chooses viscose-based carbon fiber long filament, and its specification is 840D-3000D, and wire rope core chooses viscose-based carbon fiber long filament, and its specification is 1000D;
2) doubling: adopt 6-9 root viscose-based carbon fiber long filament be 1 strand;
3) twist thread: the viscose-based carbon fiber long filament after doubling is twisted by twisting machine, twisting machine driving belt degree of tightness is consistent, and every threads must be controlled by tension regulator, and timing measures its rotating speed and the twist;
4) knit in advance: the viscose-based carbon fiber filament yarns after being twisted by twisting machine is knitted in advance on full-automatic pre-loom, half rope strand be S twist with the fingers to, half rope strand be Z twist with the fingers to, be made into the bobbin meeting two volume machine spindle size at a high speed in advance, the outer sleeve body of obtained rope skin;
5) HEAT SETTING: by the viscose-based carbon fiber long filament after twisting by steam forming machine when temperature 120-130 DEG C, pressure 0.1-0.15Mpa HEAT SETTING 30-80 minute, obtained wire rope core;
6) rope is become: rope leather block closes wire rope core weaving forming.
The invention has the beneficial effects as follows: structure is simple, have employed the structure that rope intracutaneous arranges wire rope core, rope skin adopts viscose-based carbon fiber long filament half S to twist with the fingers and twists with the fingers outer sleeve body to braiding to, half Z, rope is made to can be used for guided missile coated, side guided missile put on " Heat-preventing clothes " can resistance to several ten thousand degree high temperature, security performance is higher.
Accompanying drawing explanation
Fig. 1 is the present invention for the structural representation of the coated cordage of guided missile.
Detailed description of the invention
Describe the present invention below in conjunction with the drawings and specific embodiments, as Fig. 1 the present invention is used for shown in the structural representation of the coated cordage of guided missile, this is used for the coated cordage of guided missile, include rope skin 1 and the wire rope core 2 being arranged at rope skin 1 inside, rope skin 1 is set to be twisted with the fingers by half S twist with the fingers to viscose-based carbon fiber rope strand and half Z the outer sleeve body woven to viscose-based carbon fiber rope strand, and wire rope core 2 is set to viscose-based carbon fiber long filament aggregate.Rope skin 1 adopt can resistance to several ten thousand degree high temperature viscose-based carbon fiber monofilament.
The present embodiment, rope skin 1 adopts 24 rope strand braidings to form, and wherein S twists with the fingers to viscose-based carbon fiber rope strand is 12, and Z sth. made by twisting is 12 to viscose-based carbon fiber rope strand.
This is used for the preparation method of the coated cordage of guided missile, realizes as follows:
1) selection: rope skin 1 chooses viscose-based carbon fiber long filament, and its specification is 840D-3000D, and wire rope core 2 chooses viscose-based carbon fiber long filament, and its specification is 1000D;
2) doubling: adopt 6-9 root viscose-based carbon fiber long filament be 1 strand;
3) twist thread: the viscose-based carbon fiber long filament after doubling is twisted by twisting machine, twisting machine driving belt degree of tightness is consistent, and every threads must be controlled by tension regulator, and timing measures its rotating speed and the twist, and the twist is determined according to yarn size;
4) knit in advance: the viscose-based carbon fiber filament yarns after being twisted by twisting machine is knitted in advance on full-automatic pre-loom, half rope strand be S twist with the fingers to, half rope strand be Z twist with the fingers to, be made into the bobbin meeting two volume machine spindle size at a high speed in advance, the outer sleeve body of obtained rope skin 1;
5) HEAT SETTING: by the viscose-based carbon fiber long filament after twisting by steam forming machine when temperature 120-130 DEG C, pressure 0.1-0.15Mpa HEAT SETTING 30-80 minute, obtained wire rope core 2;
6) rope is become: rope skin 1 is in conjunction with wire rope core 2 weaving forming, and wherein the doubling of wire rope core is consistent with rope skin with twisting;
Embodiment 1:
1) selection: rope skin 1 chooses viscose-based carbon fiber long filament, and its specification is 840 D, and wire rope core 2 chooses viscose-based carbon fiber long filament, and its specification is 1000D;
2) doubling: adopt 6 viscose-based carbon fiber long filaments and be 1 strand, and become 24 strands;
3) twist thread: the viscose-based carbon fiber long filament after doubling is twisted by twisting machine, twisting machine driving belt degree of tightness is consistent, and every threads must be controlled by tension regulator, and timing measures its rotating speed and the twist, and the twist is determined according to yarn size;
4) knit in advance: the viscose-based carbon fiber filament yarns after being twisted by twisting machine is knitted in advance on full-automatic pre-loom, 12 strands for S twist with the fingers to, 12 strands for Z twist with the fingers to, be made into the bobbin meeting two volume machine spindle size at a high speed in advance, obtain the outer sleeve body of skin 1 of restricting;
5) HEAT SETTING: by the viscose-based carbon fiber long filament after twisting by steam forming machine HEAT SETTING 45 minutes when temperature 120 DEG C, pressure 0.12Mpa, obtained wire rope core 2;
6) rope is become: rope skin 1 is in conjunction with wire rope core 2 weaving forming.
Embodiment 2:
1) selection: rope skin 1 chooses viscose-based carbon fiber long filament, and its specification is 1000 D, and wire rope core 2 chooses viscose-based carbon fiber long filament, and its specification is 1000D;
2) doubling: adopt 7 viscose-based carbon fiber long filaments and be 1 strand, and become 24 strands;
3) twist thread: the viscose-based carbon fiber long filament after doubling is twisted by twisting machine, twisting machine driving belt degree of tightness is consistent, and every threads must be controlled by tension regulator, and timing measures its rotating speed and the twist, and the twist is determined according to yarn size;
4) knit in advance: the viscose-based carbon fiber filament yarns after being twisted by twisting machine is knitted in advance on full-automatic pre-loom, 12 strands for S twist with the fingers to, 12 strands for Z twist with the fingers to, be made into the bobbin meeting two volume machine spindle size at a high speed in advance, obtain the outer sleeve body of skin 1 of restricting;
5) HEAT SETTING: by the viscose-based carbon fiber long filament after twisting by steam forming machine HEAT SETTING 60 minutes when temperature 150 DEG C, pressure 0.13Mpa, obtained wire rope core 2;
6), Cheng Sheng: rope skin 1 is in conjunction with wire rope core 2 weaving forming.
Embodiment 3:
1) selection: rope skin 1 chooses viscose-based carbon fiber long filament, and its specification is 3000 D, and wire rope core 2 chooses viscose-based carbon fiber long filament, and its specification is 1000D;
2) doubling: adopt 9 viscose-based carbon fiber long filaments and be 1 strand, and become 24 strands;
3) twist thread: the viscose-based carbon fiber long filament after doubling is twisted by twisting machine, twisting machine driving belt degree of tightness is consistent, and every threads must be controlled by tension regulator, and timing measures its rotating speed and the twist, and the twist is determined according to yarn size;
4) knit in advance: the viscose-based carbon fiber filament yarns after being twisted by twisting machine is knitted in advance on full-automatic pre-loom, 12 strands for S twist with the fingers to, 12 strands for Z twist with the fingers to, be made into the bobbin meeting two volume machine spindle size at a high speed in advance, obtain the outer sleeve body of skin 1 of restricting;
5) HEAT SETTING: by the viscose-based carbon fiber long filament after twisting by steam forming machine HEAT SETTING 80 minutes when temperature 130 DEG C, pressure 0.15Mpa, obtained wire rope core 2;
6), Cheng Sheng: rope skin 1 is in conjunction with wire rope core 2 weaving forming.
Certainly, above-mentioned explanation is not limitation of the present invention, and the present invention is also not limited in above-mentioned citing, and the change that those skilled in the art make in essential scope of the present invention also should belong to protection scope of the present invention.
Claims (3)
1. one kind for the coated cordage of guided missile, it is characterized in that, include rope skin (1) and be arranged at the inner wire rope core (2) of rope skin (1), described rope skin (1) is set to be twisted with the fingers by half S twist with the fingers to viscose-based carbon fiber rope strand and half Z the outer sleeve body woven to viscose-based carbon fiber rope strand, and described wire rope core (2) is set to viscose-based carbon fiber long filament aggregate.
2. the cordage coated for guided missile according to claim 1, is characterized in that, described rope skin (1) adopts 24 rope strand braidings to form, and wherein S twists with the fingers to viscose-based carbon fiber rope strand is 12, and Z sth. made by twisting is 12 to viscose-based carbon fiber rope strand.
3. for a preparation method for the coated cordage of guided missile, it is characterized in that, realize as follows:
1) selection: viscose-based carbon fiber long filament chosen by rope skin (1), and its specification is 840D-3000D, and wire rope core (2) chooses viscose-based carbon fiber long filament, and its specification is 1000D;
2) doubling: adopt 6-9 root viscose-based carbon fiber long filament be 1 strand;
3) twist thread: the viscose-based carbon fiber long filament after doubling is twisted by twisting machine, twisting machine driving belt degree of tightness is consistent, and every threads must be controlled by tension regulator, and timing measures its rotating speed and the twist;
4) knit in advance: the viscose-based carbon fiber filament yarns after being twisted by twisting machine is knitted in advance on full-automatic pre-loom, half rope strand be S twist with the fingers to, half rope strand be Z twist with the fingers to, be made into the bobbin meeting two volume machine spindle size at a high speed in advance, the outer sleeve body of obtained rope skin (1);
5) HEAT SETTING: by the viscose-based carbon fiber long filament after twisting by steam forming machine when temperature 120-130 DEG C, pressure 0.1-0.15Mpa HEAT SETTING 30-80 minute, obtained wire rope core (2);
6) rope is become: rope skin (1) is in conjunction with wire rope core (2) weaving forming.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310448942.1A CN104514086A (en) | 2013-09-28 | 2013-09-28 | Fiber rope used for guided missile covering and manufacturing method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310448942.1A CN104514086A (en) | 2013-09-28 | 2013-09-28 | Fiber rope used for guided missile covering and manufacturing method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104514086A true CN104514086A (en) | 2015-04-15 |
Family
ID=52789943
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310448942.1A Pending CN104514086A (en) | 2013-09-28 | 2013-09-28 | Fiber rope used for guided missile covering and manufacturing method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104514086A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110983611A (en) * | 2019-11-25 | 2020-04-10 | 鲁普耐特集团有限公司 | Power rope based on core integrated technology and manufacturing method thereof |
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| CN202401336U (en) * | 2011-04-24 | 2012-08-29 | 马鞍山市宝林机械设备制造有限公司 | Heat setting mechanism for rope |
| CN103306149A (en) * | 2013-06-13 | 2013-09-18 | 泰安鲁普耐特塑料有限公司 | Carbon fiber rope and manufacturing method thereof |
| CN103306148A (en) * | 2013-05-24 | 2013-09-18 | 山东鲁普科技有限公司 | Aramid fiber compound rope and manufacture method thereof |
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2013
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Patent Citations (7)
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| US20040265582A1 (en) * | 2003-06-30 | 2004-12-30 | Connolly Thomas J. | High temperature search line |
| JP2006188805A (en) * | 2004-12-10 | 2006-07-20 | Toray Ind Inc | Braided product for heating element |
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| CN202401336U (en) * | 2011-04-24 | 2012-08-29 | 马鞍山市宝林机械设备制造有限公司 | Heat setting mechanism for rope |
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Non-Patent Citations (1)
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110983611A (en) * | 2019-11-25 | 2020-04-10 | 鲁普耐特集团有限公司 | Power rope based on core integrated technology and manufacturing method thereof |
| CN110983611B (en) * | 2019-11-25 | 2023-09-29 | 鲁普耐特集团有限公司 | Power rope based on core integrated technology and manufacturing method thereof |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20150415 |