CN105576573A - Aircraft landing gear line protection method - Google Patents
Aircraft landing gear line protection method Download PDFInfo
- Publication number
- CN105576573A CN105576573A CN201510932910.8A CN201510932910A CN105576573A CN 105576573 A CN105576573 A CN 105576573A CN 201510932910 A CN201510932910 A CN 201510932910A CN 105576573 A CN105576573 A CN 105576573A
- Authority
- CN
- China
- Prior art keywords
- wire harness
- line protection
- undercarriage
- protection method
- deconcentrator
- 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.)
- Granted
Links
Classifications
-
- 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
- H02G3/00—Installations of electric cables or lines or protective tubing therefor in or on buildings, equivalent structures or vehicles
- H02G3/02—Details
- H02G3/04—Protective tubing or conduits, e.g. cable ladders or cable troughs
- H02G3/0406—Details thereof
-
- 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
- H02G3/00—Installations of electric cables or lines or protective tubing therefor in or on buildings, equivalent structures or vehicles
- H02G3/02—Details
- H02G3/08—Distribution boxes; Connection or junction boxes
Abstract
The invention discloses an aircraft landing gear line protection method. The aircraft landing gear line protection method comprises the following steps that independent line protection has the following concrete steps that step 1: clustering is performed on cables requiring arrangement of common connecting plugs of multiple cables; step 2: each wire harness is wound by a binding belt; step 3: all the wire harnesses are sleeved in a bellows respectively; step 4: all the wire harnesses are sleeved in a wave preventing sleeve respectively; step 5: multiple shielding line deconcentrators are manufactured, each shielding line deconcentrator is provided with one input end, and the wire harnesses enter the input end of each shielding line deconcentrator and then shunted to stretch out of each output end of the shielding line deconcentrator; step 6: all the wireless harnesses are sleeved in a thermal shrinkable bushing; and step 7: the end parts of all the wire harnesses are respectively connected with the plugs. According to the aircraft landing gear line protection method, electromagnetic protection, mechanical protection and sealed waterproof protection can be realized simultaneously.
Description
Technical field
The present invention relates to undercarriage technical field, particularly relate to a kind of undercarriage line protection method.
Background technology
Wire harness is generally made up of electric wire, cable and plug, socket etc.Wire harness as Aircraft Electrical System connection and control hinge, it can normally, reliably working, depend on Combination Design and the protection Design of wire harness, and comprehensive, the reliable combination of wire harness, protection Design, directly have influence on the flight safety of aircraft.
Large aircraft landing gear cabin electrical interconnect system strand design is all problem the most key in Aircraft Electrical System strand design all the time.At present, home and abroad large transport airplane all use only the method that protection is considered in local under complex environment in landing gear compartment electrical interconnect system wire harness protection Design, substantially belongs to blank for the corrosion protection of aircraft and water-tight protection.
Therefore, wish a kind of technical scheme to overcome or at least alleviate at least one above-mentioned defect of prior art.
Summary of the invention
The object of the present invention is to provide a kind of undercarriage line protection method to overcome or at least alleviate at least one the above-mentioned defect in prior art.
For achieving the above object, the invention provides a kind of undercarriage line protection method, described aircraft comprises multiple undercarriage, each undercarriage is provided with the many cables be communicated on aircraft distinct device, described undercarriage line protection method comprises the steps: many cables on each described undercarriage to carry out line protection separately, the described line protection that carries out separately is specially following steps: step 1: carry out boundling by needing the cable arranging the common plug be connected in multiple cable, thus form many wire harness, the corresponding plug of every bar wire harness, step 2: each wire harness after described step 2 is wound around respectively by bandage, step 3: each wire harness after described step 3 processes is inserted in bellows respectively, step 4: each wire harness after described step 4 processes is inserted in anti-ripple cover respectively, step 5: make multiple shielding deconcentrator, each described shielding deconcentrator has an input, shunts after the wire harness after described step 4 processes enters the input shielding deconcentrator described in each, thus stretches out from each output of shielding deconcentrator, step 6: each wire harness after described step 5 processes is inserted in heat-shrinkable T bush, step 7: the end of each wire harness after described step 6 processes is connected with plug respectively.
Preferably, described undercarriage line protection method comprises further: step 8: pin tail annex is carried out bonding.
Preferably, the bellows in described step 3 is polytetrafluoroethylbellows bellows.
Preferably, the anti-ripple cover in described step 4 is the anti-ripple cover of high density.
Preferably, the shielding deconcentrator in described step 5 adopts metal structure, and the output of described shielding deconcentrator is one or more.
Preferably, the end of the wire harness in described step 7 and plug junction are provided with buttock line and press from both sides, and the end of described wire harness and described plug junction outer setting have mould to contract overlaps.
Preferably, pin tail annex is carried out bonding concrete grammar be in described step 8: all adopt to be tied up by memory ring and reach 360 ° of EMI/RFI bondings protections, adopts mould contracting cover to realize water-tight protection simultaneously.
Undercarriage line protection method of the present invention can realize electromagnetic protection simultaneously, and mechanical protection and water-tight protection, solve following problem:
1) wire harness in landing gear compartment region is positioned at because affecting larger by electromagnetic environment and lightning effects, require that the electromagnetic interference of landing gear compartment wire harness, HIRF protection and lightning protection should meet the requirements, and the shielding of circuit junction must not be interrupted and guarantee the normal work of system under installation state, like this, the Combination Design of landing gear compartment wire harness and protection are one of design key technology;
2) aircraft is in the process of take-off and landing, and the wire harness in landing gear compartment region is exposed outside aircraft cabin, and wire harness will have very strong lightning protection function and the explosion function of preventing rotor; When aircraft is parked in ground simultaneously, may have ponding and splash, like this, the Combination Design of landing gear compartment wire harness and waterproof protective etc. are also one of design key technology;
3) the different wire harness of landing gear compartment is arranged on different undercarriage wheel position respectively, there are many wire harness again in each wheel simultaneously, the cable equipment that whereabouts is different again in every root wire harness, so requirement will have shielding conductor to divide device to the trend of wire harness and installation.Shielding deconcentrator will realize 360 ° with conductive cable contacts interface energy and shield and be connected.The simultaneously vibrations of aircraft when landing and impact comparatively strong, landing gear compartment harness wiring deconcentrator used will have stronger shockproof properties;
4) designing requirement of landing gear compartment wire harness can realize 360 ° of full-shields and extraordinary shielding continuity, be required to meet again seaworthiness (seaworthiness clause the 25.1701st article definition EWIS) requirement, this has many key technologies to belong at home at manufacture view to break through first.
Accompanying drawing explanation
Fig. 1 is the schematic flow sheet of undercarriage line protection method according to a first embodiment of the present invention.
Fig. 2 is the part-structure schematic diagram of the wire harness adopting the undercarriage line protection method gained shown in Fig. 1.
Fig. 3 is the part-structure schematic diagram of the wire harness adopting the undercarriage line protection method gained shown in Fig. 1.
Reference numeral:
| 1 | Bandage | 4 | Heat-shrinkable T bush |
| 2 | Bellows | 5 | Shielding deconcentrator |
| 3 | Anti-ripple cover |
Embodiment
For making object of the invention process, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Described embodiment is the present invention's part embodiment, instead of whole embodiments.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the present invention, and can not limitation of the present invention be interpreted as.Based on the embodiment in the present invention, those of ordinary skill in the art, not making the every other embodiment obtained under creative work prerequisite, belong to the scope of protection of the invention.Below in conjunction with accompanying drawing, embodiments of the invention are described in detail.
In describing the invention; it will be appreciated that; term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear", "left", "right", " vertically ", " level ", " top ", " end " " interior ", " outward " etc. instruction orientation or position relationship be based on orientation shown in the drawings or position relationship; be only the present invention for convenience of description and simplified characterization; instead of instruction or imply indication device or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as limiting the scope of the invention.
Fig. 1 is the schematic flow sheet of undercarriage line protection method according to a first embodiment of the present invention.
Fig. 2 is the part-structure schematic diagram of the wire harness adopting the undercarriage line protection method gained shown in Fig. 1.
Fig. 3 is the part-structure schematic diagram of the wire harness adopting the undercarriage line protection method gained shown in Fig. 1.
Aircraft comprises multiple undercarriage, each undercarriage is provided with the many cables be communicated on aircraft distinct device.
Undercarriage line protection method as shown in Figure 1 comprises the steps: many cables on each undercarriage to carry out line protection separately, carrying out separately line protection and be specially following steps: step 1: carrying out boundling by needing the cable arranging the common plug be connected in multiple cable, thus form many wire harness, the corresponding plug of every bar wire harness; Step 2: each wire harness after step 2 is wound around respectively by bandage 1; Step 3: each wire harness after step 3 processes is inserted in bellows 2 respectively; Step 4: each wire harness after step 4 processes is inserted in respectively anti-ripple cover 3; Step 5: make multiple shielding deconcentrator 5, each shielding deconcentrator has an input, and the wire harness after step 4 processes is shunted after entering the input of each shielding deconcentrator, thus stretches out from each output of shielding deconcentrator; Step 6: each wire harness after step 5 processes is inserted in heat-shrinkable T bush 4; Step 7: the end of each wire harness after described step 6 processes is connected with plug respectively.
For example, an aircraft has 3 undercarriages, then the wire harness on each undercarriage all adopts the step of carrying out separately in line protection as above.
The trend of the wire harness that the shape of above-mentioned shielding deconcentrator can be shunted required for it and determining.Can be that there is an output, two outputs or more output.
In the present embodiment, bandage is wound around three layers, protection wire harness, thus can increase resistance to wear.
In the present embodiment, undercarriage line protection method comprises further: step 8: pin tail annex is carried out bonding.
In the present embodiment, the bellows in step 3 is polytetrafluoroethylbellows bellows.Adopt in this way, can improve Total Product tensile strength, bending stress when release is installed, ensures water proofing property simultaneously;
In the present embodiment, the anti-ripple cover in described step 4 is the anti-ripple cover of high density.Adopt in this way, while can mechanical protection being increased, ensure that product shielding is good.
In the present embodiment, the shielding deconcentrator in described step 5 adopts metal structure.Shielding conductor deconcentrator adopts metal structure, ensures shielding properties and anti-shake performance, and shielding deconcentrator and conductive cable contacts interface energy realize 360 ° and shield and be connected.
In the present embodiment, the end of the wire harness in step 7 and plug junction are provided with buttock line and press from both sides, and the end of described wire harness and described plug junction outer setting have mould to contract overlaps.The wire harness of undercarriage is exposed outside aircraft cabin, and wire harness and plug junction have employed mould contracting cover and achieve water-tight protection.
In the present embodiment, pin tail annex is carried out bonding concrete grammar be in described step 8: all adopt to be tied up by memory ring and reach 360 ° of EMI/RFI bondings protections, adopts mould contracting cover to realize water-tight protection simultaneously.
Undercarriage line protection method of the present invention can realize electromagnetic protection simultaneously, and mechanical protection and water-tight protection, solve following problem:
1) wire harness in landing gear compartment region is positioned at because affecting larger by electromagnetic environment and lightning effects, require that the electromagnetic interference of landing gear compartment wire harness, HIRF protection and lightning protection should meet the requirements, and the shielding of circuit junction must not be interrupted and guarantee the normal work of system under installation state, like this, the Combination Design of landing gear compartment wire harness and protection are one of design key technology;
2) aircraft is in the process of take-off and landing, and the wire harness in landing gear compartment region is exposed outside aircraft cabin, and wire harness will have very strong lightning protection function and the explosion function of preventing rotor; When aircraft is parked in ground simultaneously, may have ponding and splash, like this, the Combination Design of landing gear compartment wire harness and waterproof protective etc. are also one of design key technology;
3) the different wire harness of landing gear compartment is arranged on different undercarriage wheel position respectively, there are many wire harness again in each wheel simultaneously, the cable equipment that whereabouts is different again in every root wire harness, so requirement will have shielding conductor to divide device to the trend of wire harness and installation.Shielding deconcentrator will realize 360 ° with conductive cable contacts interface energy and shield and be connected.The simultaneously vibrations of aircraft when landing and impact comparatively strong, landing gear compartment harness wiring deconcentrator used will have stronger shockproof properties;
4) designing requirement of landing gear compartment wire harness can realize 360 ° of full-shields and extraordinary shielding continuity, be required to meet again seaworthiness (seaworthiness clause the 25.1701st article definition EWIS) requirement, this has many key technologies to belong at home at manufacture view to break through first.
Finally it is to be noted: above embodiment only in order to technical scheme of the present invention to be described, is not intended to limit.Although with reference to previous embodiment to invention has been detailed description, those of ordinary skill in the art is to be understood that: it still can be modified to the technical scheme described in foregoing embodiments, or carries out equivalent replacement to wherein portion of techniques feature; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of various embodiments of the present invention technical scheme.
Claims (7)
1. a undercarriage line protection method, described aircraft comprises multiple undercarriage, each undercarriage is provided with the many cables be communicated on aircraft distinct device, it is characterized in that, described undercarriage line protection method comprises the steps:
Many cables on each described undercarriage are carried out line protection separately, and the described line protection that carries out separately is specially following steps:
Step 1: will the cable that the common plug be connected is set be needed in multiple cable to carry out boundling, thus form many wire harness, the corresponding plug of every bar wire harness;
Step 2: each wire harness after described step 2 is wound around respectively by bandage (1);
Step 3: each wire harness after described step 3 processes is inserted in bellows (2) respectively;
Step 4: each wire harness after described step 4 processes is inserted in anti-ripple cover (3) respectively;
Step 5: make multiple shielding deconcentrator (5), each described shielding deconcentrator has an input, shunt after wire harness after described step 4 processes enters the input shielding deconcentrator described in each, thus stretch out from each output of shielding deconcentrator;
Step 6: each wire harness after described step 5 processes is inserted in heat-shrinkable T bush (4);
Step 7: the end of each wire harness after described step 6 processes is connected with plug respectively.
2. undercarriage line protection method as claimed in claim 1, it is characterized in that, described undercarriage line protection method comprises further:
Step 8: pin tail annex is carried out bonding.
3. undercarriage line protection method as claimed in claim 2, it is characterized in that, the bellows in described step 3 is polytetrafluoroethylbellows bellows.
4. undercarriage line protection method as claimed in claim 3, is characterized in that, the anti-ripple cover in described step 4 is the anti-ripple cover of high density.
5. undercarriage line protection method as claimed in claim 4, is characterized in that, the shielding deconcentrator in described step 5 adopts metal structure, and the output of described shielding deconcentrator is one or more.
6. undercarriage line protection method as claimed in claim 5, it is characterized in that, the end of the wire harness in described step 7 and plug junction are provided with buttock line and press from both sides, and the end of described wire harness and described plug junction outer setting have mould to contract overlaps.
7. undercarriage line protection method as claimed in claim 2, is characterized in that, pin tail annex is carried out bonding concrete grammar be in described step 8:
Whole employing is tied up by memory ring and is reached 360 ° of EMI/RFI bonding protections, adopts mould contracting cover to realize water-tight protection simultaneously.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510932910.8A CN105576573B (en) | 2015-12-13 | 2015-12-13 | A kind of undercarriage line protection method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510932910.8A CN105576573B (en) | 2015-12-13 | 2015-12-13 | A kind of undercarriage line protection method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105576573A true CN105576573A (en) | 2016-05-11 |
| CN105576573B CN105576573B (en) | 2018-06-29 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510932910.8A Active CN105576573B (en) | 2015-12-13 | 2015-12-13 | A kind of undercarriage line protection method |
Country Status (1)
| Country | Link |
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| CN (1) | CN105576573B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111030424A (en) * | 2019-12-17 | 2020-04-17 | 中航贵州飞机有限责任公司 | Method for installing direct-current power supply for suppressing interference emission of multipurpose airplane |
| CN115535277A (en) * | 2022-12-06 | 2022-12-30 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft splash protection system |
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| CN115535277A (en) * | 2022-12-06 | 2022-12-30 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft splash protection system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105576573B (en) | 2018-06-29 |
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