CN113555836B - Telescopic cable device for aircraft wire interconnection system - Google Patents
Telescopic cable device for aircraft wire interconnection system Download PDFInfo
- Publication number
- CN113555836B CN113555836B CN202110756663.6A CN202110756663A CN113555836B CN 113555836 B CN113555836 B CN 113555836B CN 202110756663 A CN202110756663 A CN 202110756663A CN 113555836 B CN113555836 B CN 113555836B
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- rocking arm
- long
- connecting rod
- box
- short
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02G—INSTALLATION OF ELECTRIC CABLES OR LINES, OR OF COMBINED OPTICAL AND ELECTRIC CABLES OR LINES
- H02G11/00—Arrangements of electric cables or lines between relatively-movable parts
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02G—INSTALLATION OF ELECTRIC CABLES OR LINES, OR OF COMBINED OPTICAL AND ELECTRIC CABLES OR LINES
- H02G11/00—Arrangements of electric cables or lines between relatively-movable parts
- H02G11/006—Arrangements of electric cables or lines between relatively-movable parts using extensible carrier for the cable, e.g. self-coiling spring
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- Mutual Connection Of Rods And Tubes (AREA)
- Electric Cable Arrangement Between Relatively Moving Parts (AREA)
Abstract
The utility model provides a flexible cable device for aircraft electric wire interconnected system, with return bend one end and the slat base fixed connection that is fixed in on the slat, the return bend other end is articulated with the connecting rod end of connecting rod line box, the line box end of connecting rod line box is articulated through coupling assembling with long rocking arm one end, short rocking arm both ends all are equipped with wire winding box and the long rocking arm other end and short rocking arm and articulate with the wire winding box of short rocking arm one end homonymy, the short rocking arm other end is articulated with the fixing base of locating on the fixed wing with the wire winding box that corresponds the end, the cable that clamps in the cable draw-in groove on the slat base is through the return bend, the connecting rod line box, long rocking arm, wind out behind short rocking arm and two wire winding boxes between by short rocking arm and the fixing base. The invention realizes large-range motion track expansion of the cable by single rotation of multiple degrees of freedom of the joint, and the cable rotates along with the joint when the joint rotates, thereby playing a role in protecting the cable, being simple, light and handy, being convenient for processing, reducing the product cost and ensuring the information transmission in the flight process of the airplane.
Description
Technical Field
The invention belongs to the technical field of installation of aircraft electric wire harnesses, and particularly relates to a telescopic cable device for an aircraft electric wire interconnection system.
Background
The flex cable arrangement is part of the C919 aircraft wire interconnect system. Its main function is to provide electrical connections for an anti-icing temperature sensor mounted on the leading edge of the fixed wing to the slat pitch sensor and the detection sensor. The front edge space of the airplane fixed wing is narrow, the wire interconnection system is complex, and the telescopic cable device is designed for protecting wires to be smooth without bending. Current telescoping device is in the use, appears the jamming fracture many times, and maintenance cost is expensive, and is with high costs, is as application number: 201911170475.4, the name of which is "rocker arm type movement cable mechanism" (hereinafter referred to as comparison file), discloses a novel rocker arm type movement cable mechanism for arranging an electric wire harness in a narrow space such as an airplane wing, although the novel rocker arm type movement cable mechanism can meet the requirement of wiring in the narrow space of the airplane wing, and the protection effect is achieved while the cable is stretched, in the using process, because the comparison file adopts two spatial connecting rods and three kinematic pairs, the rotation and stretching movement aspects have certain limitation, so that the flexibility is limited; furthermore, because the aircraft wire interconnection system moves frequently, the telescopic rod is prone to failure in the using process, so that the maintenance and repair times are increased, and the cost of the cable telescopic protection device is increased.
Disclosure of Invention
The technical problem solved by the invention is as follows: the utility model provides a flexible cable device for aircraft electric wire interconnected system adopts the flexible cable device of five kinematic pairs, makes the cable realize motion orbit on a large scale flexible through the rotation of joint multi freedom, and the cable is followed and is rotated when the joint rotates, plays the effect of protection cable, and is succinct light and handy, and the processing of being convenient for has reduced product cost, has guaranteed the information transmission of aircraft flight in-process.
The technical scheme adopted by the invention is as follows: a flexible cable device for aircraft electric wire interconnected system, including return bend, connecting rod line box, long rocking arm and short rocking arm, return bend one end with be fixed in slat base fixed connection on the slat, the return bend other end is articulated with the connecting rod end of connecting rod line box, the line box end of connecting rod line box is articulated through coupling assembling with long rocking arm one end, short rocking arm both ends all are equipped with wire winding box and the long rocking arm other end and short rocking arm and articulated with the wire winding box of short rocking arm one end homonymy, the short rocking arm other end is articulated with the fixing base of locating on the fixed wing with the wire winding box that corresponds the end, the cable that clamps in the cable draw-in groove on the slat base is around going out behind the wire winding box between short rocking arm and the fixing base behind return bend, connecting rod line box, long rocking arm, short rocking arm and two wire winding boxes.
The bending pipe is an arc-shaped long rod of a U-shaped structure with turning edges at two ends of an opening in the cross section, cables arranged in the bending pipe are bound and fixed on the bending pipe, two heat-shrinkable sleeves are sleeved on the bending pipe, one of the heat-shrinkable sleeves is heated and then is subjected to heat shrinkage and fixed in the middle of the bending pipe, and the other heat-shrinkable sleeve positioned at the base of the slat is heated and then is used for fixing a C-shaped label attached to the bending pipe on the bending pipe.
Furthermore, the connecting rod line box is of an integrated structure consisting of a hollow connecting rod and a line box, the end part of the connecting rod line box is hinged with the other end of the bent pipe through a pin shaft and bushings arranged on two sides of the connecting rod, a through hole vertical to the axis of the pin shaft is arranged on the pin shaft, and a safety rod which is inserted into the through hole on the pin shaft and used for preventing the pin shaft from loosening is arranged at the other end of the bent pipe; the cable fixed in the elbow is pressed in the wire groove of the wire box after the elbow groove of the connecting rod and is led out from the wire outlet groove at one end of the wire box.
Further, coupling assembling includes ball bearing, ball bearing installs in the mounting groove in the line box to it is articulated with long rocking arm one end with the line box end of connecting rod line box through the bush with the long round pin axle of ball bearing adaptation, long rocking arm one end is equipped with and pegs graft with the radial through-hole of long round pin axle spindle nose and is used for preventing the not hard up bumper of long round pin axle.
Further, short rocking arm one end and the wire winding box and the long rocking arm other end of the same end, the short rocking arm other end and the wire winding box and the fixing base of the same end all through the pin bush of wire winding box both sides and with the long round pin axle of pin bush adaptation articulated, all be equipped with on short rocking arm one end and the fixing base and peg graft with the radial through-hole that corresponds punishment round pin axle head and be used for preventing the not hard up bumper bar of long round pin axle, the epaxial cover of long round pin is equipped with the spacing piece that is used for injecing contained angle between short rocking arm and the long rocking arm, spacing piece one end both sides border joint is on short rocking arm, and just spacing piece other end one side along with the laminating of long rocking arm side.
Furthermore, the bumper bar comprises two connection end rod bodies and a middle section rod body which is connected with the two connection end rods through an arc transition section and a connection end rod body at one end of the middle section rod body, and the two connection end rod bodies of the bumper bar are perpendicular to each other.
Furthermore, a connecting plate is fixed at one end of the bent pipe, a notch corresponding to the opening position on the side wall of the bent pipe is formed in the plate surface on one side of the connecting plate, and four corners of the plate surface of the connecting plate are fixedly connected with the slat base through screws.
Compared with the prior art, the invention has the advantages that:
1. according to the technical scheme, the telescopic cable device with five kinematic pairs is adopted, so that the cable realizes large-range motion track expansion through the rotation of multiple degrees of freedom of the joint, and the cable rotates along with the joint when the joint rotates, so that the cable is protected;
2. according to the technical scheme, the connecting rod wire box of the integrated structure consisting of the hollow connecting rod and the wire box is arranged between the bent pipe and the long rocker arm, so that the reliability and the smoothness of the rotating tracks of the bent pipe and the long rocker arm are ensured, and the follow-up property of a cable is improved;
3. according to the technical scheme, the limit piece is arranged at the hinged position of the long rocker arm and the short rocker arm, wherein the two side edges of one end of the limit piece are clamped on the short rocker arm, and one side edge of the other end of the limit piece is attached to the side edge of the long rocker arm, so that the included angle between the short rocker arm and the long rocker arm is limited, the only movement track of the telescopic cable device is ensured, and the movement process is smooth and has no clamping stagnation;
4. the technical scheme has the advantages of simple structure, simplicity, lightness, convenience in processing, reduction in product cost and guarantee of information transmission in the flight process of the airplane.
Drawings
FIG. 1 is an exploded view of the present invention;
fig. 2 is a schematic structural view after the present invention is installed.
Detailed Description
In the following, an embodiment of the present invention will be described in conjunction with fig. 1-2, so as to clearly and completely describe the technical solutions, and it is obvious that the described embodiment is only a part of the embodiment of the present invention, but not all of the embodiment.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are used merely for convenience in describing the present invention and for simplicity in description, but do not indicate or imply that the device or element so referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention.
The telescopic cable device for the aircraft wire interconnection system comprises a bent pipe 1, a connecting rod line box 2, a long rocker arm 3 and a short rocker arm 4, wherein one end of the bent pipe 1 is fixedly connected with a slat base 5 fixed on a slat, specifically, a connecting plate 18 is fixed at one end of the bent pipe 1, a notch corresponding to an opening position on the side wall of the bent pipe 1 is formed in the plate surface on one side of the connecting plate 18, and four corners of the plate surface of the connecting plate 18 are fixedly connected with the slat base 5 through screws 19; the other end of the elbow 1 is hinged with the connecting rod end of the connecting rod line box 2, the line box end of the connecting rod line box 2 is hinged with one end of the long rocker arm 3 through a connecting assembly, two ends of the short rocker arm 4 are both provided with winding boxes 6, the other end of the long rocker arm 3 is hinged with the short rocker arm 4 and the winding box 6 which is arranged on the same side of one end of the short rocker arm 4, the other end of the short rocker arm 4 is hinged with the winding box 6 on the corresponding end and a fixing seat 7 arranged on the fixed wing, and a cable 8 clamped in a cable clamping groove on the slat base 5 is wound out through the winding box 6 between the short rocker arm 4 and the fixing seat 7 after passing through the elbow 1, the connecting rod line box 2, the long rocker arm 3, the short rocker arm 4 and the two winding boxes 6; in the structure, the telescopic cable device with five kinematic pairs is adopted, so that the cable realizes large-range motion track expansion through the rotation of multiple degrees of freedom of the joint, and the cable rotates along with the joint when the joint rotates, thereby playing a role in protecting the cable;
the specific shape of the elbow 1 is as follows: the section shape of the elbow 1 is an arc-shaped long rod with a U-shaped structure with inward-turned edges at two ends of an opening, a cable 8 arranged in the elbow 1 is bound and fixed on the elbow 1, two heat-shrinkable sleeves 9 are sleeved on the elbow 1, one of the heat-shrinkable sleeves 9 is fixed in the middle of the elbow 1 in a heat-shrinkable way after being heated, and the other heat-shrinkable sleeve 9 positioned at the slat base 5 fixes a C-shaped label 10 attached to the elbow 1 on the elbow 1 after being heated.
The concrete structure of the connecting rod line box 2 is as follows: the connecting rod line box 2 is of an integrated structure consisting of a hollow connecting rod 2-1 and a line box 2-2, the end part of the connecting rod 2-1 of the connecting rod line box 2 is hinged with the other end of the elbow pipe 1 through a pin shaft 11 and a bush 12 arranged at two sides of the connecting rod 2-1, the pin shaft 11 is provided with a through hole vertical to the axis of the pin shaft, and the other end of the elbow pipe 1 is provided with a safety rod 13 which is inserted into the through hole on the pin shaft 11 and used for preventing the pin shaft 11 from loosening; the cable 8 fixed in the elbow 1 is pressed in a wire groove of the wire box 2-2 coiled behind the bending groove of the connecting rod 2-1 and led out from a wire outlet groove at one end of the wire box 2-2; in the structure, the connecting rod wire box 2 of an integrated structure consisting of the hollow connecting rod 2-1 and the wire box 2-2 is arranged between the elbow 1 and the long rocker 3, so that the reliability and the fluency of the rotating tracks of the elbow 1 and the long rocker 3 are ensured, and the follow-up property of a cable is improved;
the concrete structure of coupling assembling is as follows: the connecting assembly comprises a ball bearing 14, the ball bearing 14 is installed in an installation groove in the line box 2-2, the line box end of the connecting rod line box 2 is hinged to one end of the long rocker arm 3 through a bushing 12 and a long pin shaft 15 matched with the ball bearing 14, and a safety rod 13 which is connected with a radial through hole of a shaft head of the long pin shaft 15 in an inserting mode and used for preventing the long pin shaft 15 from loosening is arranged at one end of the long rocker arm 3.
The connection structure of the two ends of the short rocker arm 4 is as follows: one end of the short rocker arm 4 is hinged to a winding box 6 and the other end of the long rocker arm 3 at the same end, the other end of the short rocker arm 4 is hinged to the winding box 6 and a fixing seat 7 at the same end through pin sleeves 17 on two sides of the winding box 6 and a long pin shaft 15 matched with the pin sleeves 17, a safety rod 13 which is inserted into a radial through hole of a long pin shaft 15 shaft head corresponding to the short rocker arm 4 and used for preventing the long pin shaft 15 from loosening is arranged on each of one end of the short rocker arm 4 and the fixing seat 7, a limiting piece 16 used for limiting an included angle between the short rocker arm 4 and the long rocker arm 3 is sleeved on the long pin shaft 15, two side edges of one end of the limiting piece 16 are clamped on the short rocker arm 4, one side edge of the other end of the limiting piece 16 is attached to the side edge of the long rocker arm 3, and the maximum included angle between the short rocker arm 4 and the long rocker arm 3 is limited along with the change of the rotation positions of the short rocker arm 4 and the long rocker arm 3; among the above-mentioned structure, when using, receive 8 torsional influences of cable, make contained angle between short rocking arm 4 and the long rocking arm 3 too big and the singular point appears, lead to the movement track to change failure even, consequently, in order to solve this problem, specially set up spacing piece 9 to the contained angle between short rocking arm 4 of restriction and the long rocking arm 3 guarantees that the flexible cable device movement track is unique, and the motion process is unobstructed does not have the jamming.
The specific shape of the bumper 13 is as follows: the bumper 13 comprises two link body of rod and the interlude body of rod of passing through the arc changeover portion with two link rods and being connected perpendicularly with the link body of rod of one end wherein, two link body of rod mutually perpendicular settings of bumper 13.
The technical scheme has the advantages of simple structure, simplicity, lightness, convenience in processing, reduction in product cost and guarantee of information transmission in the flight process of the airplane.
The above-mentioned embodiments are only preferred embodiments of the present invention, and should not be used to limit the scope of the present invention, so that all equivalent changes made by the contents of the claims of the present invention should be included in the scope of the claims of the present invention.
Claims (5)
1. A flexible cable device for aircraft electric wire interconnected system which characterized in that: the slat base is characterized by comprising an elbow (1), a connecting rod line box (2), a long rocker (3) and a short rocker (4), wherein one end of the elbow (1) is fixedly connected with a slat base (5) fixed on a slat, the other end of the elbow (1) is hinged with the connecting rod end of the connecting rod line box (2), the line box end of the connecting rod line box (2) is hinged with one end of the long rocker (3) through a connecting assembly, winding boxes (6) are arranged at two ends of the short rocker (4), the other end of the long rocker (3) is hinged with the short rocker (4) and the winding box (6) at the same side with one end of the short rocker (4), the other end of the short rocker (4) is hinged with the winding box (6) at the corresponding end and a fixing seat (7) arranged on a fixing wing, and a cable (8) clamped in a cable clamping groove in the slat base (5) is wound out of the winding box (6) between the short rocker (4) and the fixing seat (7) through the elbow (1), the connecting rod line box (2), the long rocker (3), the short rocker (4) and the two winding box (6);
the section of the bent pipe (1) is an arc-shaped long rod with a U-shaped structure, two ends of the opening of which are provided with turned edges, cables (8) arranged in the bent pipe (1) are bound and fixed on the bent pipe (1), two heat-shrinkable sleeves (9) are sleeved on the bent pipe (1), one heat-shrinkable sleeve (9) is heated and then is subjected to heat shrinkage and fixed in the middle of the bent pipe (1), and the other heat-shrinkable sleeve (9) positioned at the slat base (5) is heated and then is used for fixing a C-shaped label (10) attached to the bent pipe (1) on the bent pipe (1);
short rocking arm (4) one end and wire winding box (6) and long rocking arm (3) the other end with the end, short rocking arm (4) the other end all through wire winding box (6) both sides and with long round pin axle (15) of round pin cover (17) adaptation with wire winding box (6) and fixing base (7) articulated, all be equipped with on short rocking arm (4) one end and fixing base (7) with correspond the radial through-hole grafting of punishment long round pin axle (15) spindle nose and be used for preventing not hard up bumper bar (13) of long round pin axle (15), the cover is equipped with spacing piece (16) that are used for injecing contained angle between short rocking arm (4) and long rocking arm (3) on long round pin axle (15), spacing piece (16) one end both sides border joint is on short rocking arm (4), and spacing piece (16) other end one side border laminates along with long rocking arm (3) side border.
2. The retractable cable assembly for an aircraft wire interconnection system of claim 1, wherein: the connecting rod line box (2) is of an integrated structure consisting of a hollow connecting rod (2-1) and a line box (2-2), the end part of the connecting rod (2-1) of the connecting rod line box (2) is hinged with the other end of the bent pipe (1) through a pin shaft (11) and bushings (12) arranged on two sides of the connecting rod (2-1), a through hole vertical to the axis of the pin shaft (11) is formed in the pin shaft (11), and a safety rod (13) which is inserted into the through hole in the pin shaft (11) and is used for preventing the pin shaft (11) from loosening is arranged at the other end of the bent pipe (1); the cable (8) fixed in the elbow (1) is pressed in a wire groove of the wire inlet box (2-2) after the bent groove of the connecting rod (2-1) and is led out from a wire outlet groove at one end of the wire box (2-2).
3. The retractable cable assembly for an aircraft wire interconnection system of claim 2, wherein: coupling assembling includes ball bearing (14), ball bearing (14) are installed in the mounting groove in line box (2-2) to it is articulated with the line box end of connecting rod line box (2) and long rocking arm (3) one end through bush (12) and long round pin axle (15) with ball bearing (14) adaptation, long rocking arm (3) one end is equipped with and pegs graft with the radial through-hole of long round pin axle (15) spindle nose and is used for preventing not hard up bumper (13) of long round pin axle (15).
4. A retractable cable assembly for an aircraft wire interconnection system as claimed in claim 2 or claim 3, wherein: the bumper bar (13) is composed of two connecting end bar bodies and a middle section bar body which is connected with the two connecting end bar bodies through an arc transition section and is vertically connected with the connecting end bar body at one end, and the two connecting end bar bodies of the bumper bar (13) are perpendicular to each other.
5. The retractable cable assembly for an aircraft wire interconnect system of claim 4 wherein: a connecting plate (18) is fixed to one end of the bent pipe (1), a notch corresponding to an opening position on the side wall of the bent pipe (1) is formed in the plate surface on one side of the connecting plate (18), and four corners of the plate surface of the connecting plate (18) are fixedly connected with the slat base (5) through screws (19).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110756663.6A CN113555836B (en) | 2021-07-05 | 2021-07-05 | Telescopic cable device for aircraft wire interconnection system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110756663.6A CN113555836B (en) | 2021-07-05 | 2021-07-05 | Telescopic cable device for aircraft wire interconnection system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113555836A CN113555836A (en) | 2021-10-26 |
| CN113555836B true CN113555836B (en) | 2023-03-03 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110756663.6A Active CN113555836B (en) | 2021-07-05 | 2021-07-05 | Telescopic cable device for aircraft wire interconnection system |
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| Country | Link |
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| CN (1) | CN113555836B (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1338506A1 (en) * | 2002-02-15 | 2003-08-27 | Fairchild Dornier GmbH | Airplane wing with slat and Krueger flap |
| EP2733064A1 (en) * | 2012-11-16 | 2014-05-21 | Dassault Aviation | Mobile device for guiding a cable, and aircraft including such a device |
| CN104426113A (en) * | 2013-09-10 | 2015-03-18 | 空中客车德国运营有限责任公司 | Arrangement for guiding a cable, wing having the arrangement and aircraft having the wing |
| CN110641682A (en) * | 2019-11-26 | 2020-01-03 | 中国商用飞机有限责任公司 | Rocker arm type motion cable mechanism |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060038088A1 (en) * | 2004-08-23 | 2006-02-23 | Dodson Robert T | Aircraft wing |
| US7249735B2 (en) * | 2005-06-30 | 2007-07-31 | The Boeing Company | Translating conduit apparatus for an airplane or equipment |
| GB0807626D0 (en) * | 2008-04-25 | 2008-06-04 | Ultra Electronics Ltd | Routing of cables |
| GB201011378D0 (en) * | 2010-07-06 | 2010-08-18 | Ultra Electronics Ltd | Linkage for guiding a flexible cable |
| US9016637B2 (en) * | 2012-02-10 | 2015-04-28 | The Boeing Company | High-positioned 3-position variable camber krueger |
-
2021
- 2021-07-05 CN CN202110756663.6A patent/CN113555836B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1338506A1 (en) * | 2002-02-15 | 2003-08-27 | Fairchild Dornier GmbH | Airplane wing with slat and Krueger flap |
| EP2733064A1 (en) * | 2012-11-16 | 2014-05-21 | Dassault Aviation | Mobile device for guiding a cable, and aircraft including such a device |
| CN104426113A (en) * | 2013-09-10 | 2015-03-18 | 空中客车德国运营有限责任公司 | Arrangement for guiding a cable, wing having the arrangement and aircraft having the wing |
| CN110641682A (en) * | 2019-11-26 | 2020-01-03 | 中国商用飞机有限责任公司 | Rocker arm type motion cable mechanism |
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| Publication number | Publication date |
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| CN113555836A (en) | 2021-10-26 |
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