CN201590506U - Control cable for engine - Google Patents
Control cable for engine Download PDFInfo
- Publication number
- CN201590506U CN201590506U CN2009202709341U CN200920270934U CN201590506U CN 201590506 U CN201590506 U CN 201590506U CN 2009202709341 U CN2009202709341 U CN 2009202709341U CN 200920270934 U CN200920270934 U CN 200920270934U CN 201590506 U CN201590506 U CN 201590506U
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- Prior art keywords
- cable
- electric connector
- branch
- engine
- ripple cover
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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.)
- Expired - Lifetime
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Abstract
The utility model provides a control cable for engine, which comprises a main cable (13) with a plurality of branched cables (10). The branched cables are branched from the main cable. The respective external surface of the branched cables is coated by a wave-proof sleeve (18). The external surface of the main cable is also coated by a wave-proof sleeve (11). Particularly, The compression joint between the wave-proof sleeve of the main cable and the wave-proof sleeve of each branched cable is realized through a configuration that the inner sleeves are matched with the outer sleeve. The configuration is characterized in that: the inner sleeves (15) are sleeved on the branched cables; the respective wave-proof sleeve of the branched cable, which is provided at the main cable end and is adjacent to the inner sleeve, is coiled and coated on the inner sleeve; the wave-proof sleeve of the main cable coats the coiled wave-proof sleeve of the branched cable; The outer sleeve (16) is compression-jointed with the wave-proof sleeve of the main cable at a position corresponding with the inner sleeve. The control cable of the utility model has the following advantages: improving interference resistance, improving the layout of cables and reducing the weight of cable.
Description
Technical field
The utility model relates to a kind of control cable, particularly, relates to a kind of control cable that is used for engine, and more specifically, this control cable can be applicable to the engine of aircraft.
Background technology
The processing of engine cable is with reference to HB 6438-2005 " the aircraft wire harness is processed general requirement ", and ZH83723 series is the round electric connector of anti-the environment, and its contact is connected the crimping mode that adopts with lead.The attached housing of tail (ground connection) of the anti-ripple socket electric connector of branch cable adopts the mode of crimping, a receipts processing method of screen is adopted in the processing of the screen of the lead in the branch cable, the other end of the screen of the lead in the branch cable adopts the mode of automatic welded metal joints (band solder ring) welding to link to each other with the attached housing of the tail of electric connector, the anti-ripple cover of leader cable and the mode that adopts crimping that is connected between the anti-ripple of each branch cable overlaps.
There are the following problems in the prior art: the existing control cable that is used for whirlpool axle Engine Series does not match with aircraft engine on overall dimension; The existing control cable that is used for whirlpool axle Engine Series, gross mass does not satisfy the requirement of aircraft engine; The existing processing that is used for the anti-ripple cover (containing screen) of control cable of whirlpool axle Engine Series can't be satisfied the requirement of the bonding resistance of aircraft engine control cable smaller or equal to 30m Ω; Lead on the existing control cable that is used for whirlpool axle Engine Series can't satisfy the requirement of the lead heart yearn and the capacitance between the screen (mounting panel) of engine control cable; Fire-resistnt wire on the existing control cable that is used for whirlpool axle Engine Series can't satisfy the requirement of external diameter, quality and the shielding properties of engine control cable fire-resistnt wire.Existing electric connector and the tail that is used on the axle Engine Series control cable of whirlpool is attached, can't satisfy the requirement of the attached and electric connector housing electric conductivity of the desired electric connector band of engine control cable shading ring, curved formula and straight formula tail less than 5m Ω.
The utility model content
The utility model is devoted to overcome the above-mentioned defective of prior art just and is made.The utility model aims to provide a kind of control cable that is used for engine, the crimping between attached with the electric connector tail of its anti-ripple cover that can optimize the crimping between the anti-ripple cover of anti-ripple cover of leader cable and branch cable and optimize branch cable, and the overall dimension of strict this cable of control reach raising cable antijamming capability and alleviate the purpose of the quality of cable.
In embodiment of the present utility model, a kind of control cable that is used for engine is provided, and it comprises the leader cable with many branch cables, and branch cable is told from leader cable, all be coated with anti-ripple cover on the many branch cables outer surface separately, also be coated with anti-ripple cover on the outer surface of leader cable.Especially, crimping between the anti-ripple cover that the layout that matches with inner and outer ring realizes leader cable overlaps with the anti-ripple of each branch cable, above-mentioned being arranged as: inside race is enclosed within on the many branch cables, branch cable be positioned at the leader cable end and anti-ripple cover turnup that be adjacent to inside race separately is coated on the inside race, the anti-ripple that the anti-ripple cover of leader cable is coated on the branch cable turnup puts, and outer collar is crimped on leader cable in the position corresponding to inside race anti-ripple puts.
Preferably, according to the control cable that is used for engine of the present utility model, wherein, be enclosed with heat-shrinkable T bush on the outer surface of the anti-ripple cover of leader cable.
Preferably, according to the control cable that is used for engine of the present utility model, wherein, be crimped on electric connector tail being connected between enclosing the anti-ripple cover of realizing branch cable and electric connector tail accordingly being attached by outer collar.
Preferably, according to the control cable that is used for engine of the present utility model, wherein, engine is an aeromotor, branch cable comprises first group of branches cable of telling from first end of leader cable and the second group of branches cable of telling from second end of leader cable, the first group of branches cable connects the first group of electric connector that is used to connect Motronic control maps control device and aircraft transducer separately, and the second group of branches cable connects the second group of electric connector that is used to connect each annex of engine separately; And mounting panel, be installed in the first end place.
Preferably, according to the control cable that is used for engine of the present utility model, wherein, comprise first electric connector that is connected to first speed probe in second group of electric connector, and first electric connector uses length to be 1082mm to 1097mm to the branch cable of mounting panel.
Preferably, according to the control cable that is used for engine of the present utility model, wherein, first electric connector uses length to be 1092mm to the branch cable of mounting panel.
Preferably, according to the control cable that is used for engine of the present utility model, wherein, comprise second electric connector that is connected to second speed probe in second group of electric connector, and second electric connector uses length to be 1215mm to 1230mm to the branch cable of mounting panel.
Preferably, according to the control cable that is used for engine of the present utility model, wherein, second electric connector uses length to be 1225mm to the branch cable of mounting panel.
Preferably, according to the control cable that is used for engine of the present utility model, wherein, the nominal outside diameter of the second anti-ripple cover at the thickest section place of leader cable is 15.0mm.
Preferably, according to the control cable that is used for engine of the present utility model, wherein, the external diameter of the heat-shrinkable T bush at the thickest section place of the first group of branches cable is 19.1mm.
The utlity model has following technique effect:
According to the layout that control cable of the present utility model adopts the metal inner and outer ring to match the anti-ripple cover of leader cable and the anti-ripple cover of branch cable are carried out crimping, and by tail attached be connected of outer collar with anti-ripple cover with the corresponding electric connector of branch cable, satisfy the requirement that control cable desired bonding performance is not more than 30m Ω, improved the cable antijamming capability.In addition, the overall dimension of control cable of the present utility model satisfies the requirement of aircraft engine interworking, and cabling is more smooth and easy, and has reached the requirement that the control cable quality is not more than 2000g.
Should be appreciated that above generality is described and the following detailed description is all enumerated and illustrative, purpose is in order to provide further instruction to claimed the utility model.
Description of drawings
Accompanying drawing described herein is used to provide further understanding of the present utility model, constitutes the application's a part, and illustrative examples of the present utility model and explanation thereof are used to explain the utility model, do not constitute improper qualification of the present utility model.In the accompanying drawings:
Fig. 1 shows the profile schematic diagram according to the control cable that is used for engine of the utility model preferred embodiment;
Fig. 2 shows the cutaway view in A-A cross section among Fig. 1; And
Fig. 3 shows the schematic diagram that the crimping between the anti-ripple cover of the anti-ripple cover of leader cable and branch cable is arranged.
Embodiment
Describe embodiment of the present utility model in detail below in conjunction with accompanying drawing.It should be noted that hereinafter only the utility model feature unlike the prior art to be described,, just do not given unnecessary details here for the technical characterictic that can find in the prior art.
At first with reference to Fig. 1, mainly comprise leader cable 13 according to the control cable that is used for engine of the present utility model with many branch cables 10, wherein branch cable 10 is told from leader cable 13, lead in the branch cable 10 is a shielded conductor, have 1 two core shielded conductor or three-core shielding lead or four-core shielded conductor in the branch cable that has, have 3 two core shielded conductors in the branch cable that has, have 2 three-core shielding leads in the branch cable that has.(branch cable that reference number 10 is schematically pointed out among the figure has 1 two core lead all to be coated with conductor 101,102 in each branch cable 10, certainly it also may be three cores or quad), and all be coated with anti-ripple cover 18 on branch cable 10 outer surfaces, also be coated with anti-ripple cover 11 (referring to Fig. 2 and Fig. 3) on the outer surface of leader cable 13.Branch cable comprises first group of branches cable of telling from first end of leader cable 13 28,19 and the second group of branches cable 20-25 that tells from second end of leader cable 13, the first group of branches cable connects each in first group of electric connector separately, and the second group of branches cable connects in second group of electric connector each separately.Wherein, first group of electric connector comprises three electric connector XS1-XS3, illustrate with reference number 27,26,1 respectively, wherein electric connector XS2, XS3 are connected to that Motronic control maps control device EECU (Engine Electronic ControlUnit) goes up and electric connector XS1 is connected on the aircraft T1 transducer; Second group of electric connector comprises a plurality of electric connectors, only introduces three at this, i.e. first electric connector 8, second electric connector 9 and the 3rd electric connector 29, and these three electric connector XS5, XS10, XS7 are connected to three speed probes.It should be noted that for ease of understanding drawing reference numeral 2-7 represents that respectively contract cover, sign sleeve pipe, mounting panel, label, clip and tail of mould is attached.
With reference to Fig. 2 and shown in Figure 3, the utility model difference with the prior art is, all be coated with anti-ripple cover 11 and heat-shrinkable T bush 12 on the outer surface of leader cable 13 each section, in each bifurcation, the anti-ripple cover 11 that the layout that matches with the inner and outer ring of suitable specification realizes leader cable 13 and the anti-ripple of branch cable overlap the crimping between 18, above-mentioned being arranged as: inside race 15 is enclosed within on the many branch cables 10, these branch cables 10 be arranged in leader cable end (is right-hand member at Fig. 3) and anti-ripple cover 18 equal turnups that be adjacent to inside race 15 separately are coated on the inside race 15, the anti-ripple cover 11 of leader cable 13 is enclosed within on the anti-ripples cover 18 of branch cable 10 turnups (promptly being enclosed within on the end 17 of anti-ripple cover 18), outer collar 16 is crimped on the anti-ripple cover 11 of leader cable 13 in the position corresponding to inside race 15, and the heat-shrinkable T bush 12 of leader cable is enclosed within on the outer collar 16.It should be noted that the heat-shrinkable T bush of drawing reference numeral 14 expression branch cables for ease of understanding.
Like this, use dexterously several specifications inside race (carbide alloy, under crimped status, have indeformable ability), with the matching used outer collar of inside race (soft silver or smart copper, under crimped status, have deformation ability), the anti-ripple cover 11 of the anti-ripple cover 18 of branch cable and leader cable 13 has been carried out crimping, the crimping resistance between the anti-ripple cover that reduces branch cable as far as possible overlaps with the anti-ripple of leader cable.
Be similar to said structure, utilize between anti-ripple cover that outer collar (soft silver or smart copper, have deformation ability under crimped status) will be on each branch cable and the electric connector tail attached 7 and carry out crimping, what it will be appreciated by those skilled in the art that is that electric connector tail attached 7 is equivalent to inside race.Therefore, reduced crimping resistance between the attached and anti-ripple cover of electric connector tail by said structure, thereby satisfied of the requirement of the bonding resistance of engine control cable, guaranteed the shield effectiveness of control cable smaller or equal to 30m Ω.
In addition, present embodiment is also according to each annex rigging position relation of aircraft engine, design control cable overall dimension, particularly, use length by the control branch cable realizes, to be reduced to 1092mm by 1105mm from the branch cable size of mounting panel 4 to first electric connector XS5 (by reference number 8 indications), to be decreased to 1225mm by 1240mm from the branch cable size of mounting panel 4 to second electric connector XS10 (by reference number 9 indications), thereby satisfy the overall dimension requirement of aircraft engine control cable.
In addition, for the quality requirement that satisfies the engine control cable (should smaller or equal to 2000g, dry and not have under the situation of obstruction), the anti-ripple that has reduced the thickest section place of leader cable 13 overlaps 11 diameter specifications, and its nominal outside diameter is reduced to 15.0mm by 18.0mm; And having reduced the external diameter of heat-shrinkable T bush 12 at the thickest section place of the first group of branches cable 28, external diameter changed 19.1mm into by 25.4mm before it shrank, and made that the gross mass of control cable is lighter, cabling is more smooth and easy, reached the requirement of control cable overall dimension.
As can be seen from the above description, by the improvement of present embodiment, realized improving the cable antijamming capability and optimize the cable layout, alleviate the purpose of cable quality control cable.
The above is a preferred embodiment of the present utility model only, is not limited to the utility model, and for a person skilled in the art, the utility model can have various changes and variation.All within spirit of the present utility model and principle, any modification of being done, be equal to replacement, improvement etc., all should be included within the protection range of the present utility model.
Claims (10)
1. control cable that is used for engine, comprise leader cable (13) with many branch cables (10), described branch cable (10) is told from described leader cable (13), all be coated with anti-ripple cover (18) on described branch cable (10) outer surface separately, also be coated with anti-ripple cover (11) on the outer surface of described leader cable (13)
It is characterized in that, the layout that matches with inner and outer ring realizes the crimping between the anti-ripple cover (18) of the anti-ripple cover (11) of described leader cable (13) and described branch cable, described being arranged as: inside race (15) is enclosed within on the described branch cable (10), described branch cable (10) separately be positioned at the leader cable end and anti-ripple cover (18) turnup that be adjacent to described inside race (15) is coated on the inside race (15), the anti-ripple cover (11) of described leader cable (13) is coated on the anti-ripple cover (18) of described branch cable (10) turnup, and outer collar (16) is crimped on the anti-ripple cover (11) of described leader cable (13) in the position corresponding to inside race (15).
2. the control cable that is used for engine according to claim 1 is characterized in that, is enclosed with heat-shrinkable T bush (12) on the outer surface of the anti-ripple cover (11) of described leader cable (13).
3. the control cable that is used for engine according to claim 1 is characterized in that, is crimped on electric connector tail being connected between enclosing the anti-ripple cover (18) of realizing described branch cable (10) and electric connector tail accordingly being attached by outer collar.
4. according to the described control cable that is used for engine of claim 1 to 3, it is characterized in that, described engine is an aeromotor, described branch cable comprises first group of branches cable of telling from first end of described leader cable (13) and the second group of branches cable of telling from second end of described leader cable (13), the first group of branches cable connects the first group of electric connector that is used to connect Motronic control maps control device and aircraft transducer separately, and the second group of branches cable connects the second group of electric connector that is used to connect each annex of engine separately; And mounting panel (4), be installed in the described first end place.
5. the control cable that is used for engine according to claim 4, it is characterized in that, comprise first electric connector (8) that is connected to first speed probe in described second group of electric connector, and described first electric connector (8) uses length to be 1082mm to 1097mm to the branch cable of described mounting panel (4).
6. the control cable that is used for engine according to claim 5 is characterized in that, described first electric connector (8) uses length to be 1092mm to the branch cable of described mounting panel (4).
7. the control cable that is used for engine according to claim 4, it is characterized in that, comprise second electric connector (9) that is connected to second speed probe in described second group of electric connector, and described second electric connector (9) uses length to be 1215mm to 1230mm to the branch cable of described mounting panel (4).
8. the control cable that is used for engine according to claim 7 is characterized in that, described second electric connector (9) uses length to be 1225mm to the branch cable of described mounting panel (4).
9. the control cable that is used for engine according to claim 1 is characterized in that, the nominal outside diameter of the second anti-ripple cover (11) at the thickest section place of described leader cable (13) is 15.0mm.
10. the control cable that is used for engine according to claim 2 is characterized in that, the external diameter of the heat-shrinkable T bush (12) at the thickest section place of the described first group of branches cable (28) is 19.1mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009202709341U CN201590506U (en) | 2009-12-02 | 2009-12-02 | Control cable for engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009202709341U CN201590506U (en) | 2009-12-02 | 2009-12-02 | Control cable for engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201590506U true CN201590506U (en) | 2010-09-22 |
Family
ID=42750298
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009202709341U Expired - Lifetime CN201590506U (en) | 2009-12-02 | 2009-12-02 | Control cable for engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201590506U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102280189A (en) * | 2011-08-15 | 2011-12-14 | 南京全信传输科技股份有限公司 | Redundant heavy-current power supply cable assembly and assembly method thereof |
| CN105576573A (en) * | 2015-12-13 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft landing gear line protection method |
| CN106477093A (en) * | 2016-11-22 | 2017-03-08 | 天津航空机电有限公司 | A kind of binding post welds the binding method of wire harness |
-
2009
- 2009-12-02 CN CN2009202709341U patent/CN201590506U/en not_active Expired - Lifetime
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102280189A (en) * | 2011-08-15 | 2011-12-14 | 南京全信传输科技股份有限公司 | Redundant heavy-current power supply cable assembly and assembly method thereof |
| CN102280189B (en) * | 2011-08-15 | 2012-08-22 | 南京全信传输科技股份有限公司 | Redundant heavy-current power supply cable assembly and assembly method thereof |
| CN105576573A (en) * | 2015-12-13 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft landing gear line protection method |
| CN105576573B (en) * | 2015-12-13 | 2018-06-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of undercarriage line protection method |
| CN106477093A (en) * | 2016-11-22 | 2017-03-08 | 天津航空机电有限公司 | A kind of binding post welds the binding method of wire harness |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20100922 |