CN201868712U - Main pipe for automatic aviation control lead - Google Patents
Main pipe for automatic aviation control lead Download PDFInfo
- Publication number
- CN201868712U CN201868712U CN2010205369630U CN201020536963U CN201868712U CN 201868712 U CN201868712 U CN 201868712U CN 2010205369630 U CN2010205369630 U CN 2010205369630U CN 201020536963 U CN201020536963 U CN 201020536963U CN 201868712 U CN201868712 U CN 201868712U
- Authority
- CN
- China
- Prior art keywords
- lead
- terminal box
- house steward
- automatic pilot
- main pipe
- 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.)
- Expired - Lifetime
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- Details Of Connecting Devices For Male And Female Coupling (AREA)
Abstract
The utility model relates to a main pipe for an automatic aviation control lead, which is characterized in that: the main pipe comprises a junction box, an installation harness, a lead, thirty-one cable plugs for connecting accessories, five cramp frames and thirty-one protecting jackets, wherein the five cramp frames are installed on the junction box, the lead is connected with a socket in the junction box by braze welding, and extends out of the junction box after penetrating through the five cramp frames, the protecting jackets are sleeved outside the lead, the cable plugs are connected to the tail end of the lead by braze welding, and the lead are divided into different harnesses through the installation harness. The main pipe for the automatic aviation control lead has the advantages that the structure is simple, the weight is light and is 72% of weight of the traditional product, and the cable is soft in texture and is more flexible to be assembled on the engine. The protective jackets are woven by non-metallic wires and metal wires, so that the requirements of the high and low temperature tests, the vibration and impact tests, the mould test, the salt spray test and other tests are met, and the electric property of the main pipe meets the operating requirements of the engine.
Description
Technical field
The utility model relates to Aviation cable, particularly the automatic pilot house steward of a kind of aviation.
Background technology
At present, aero-engine cable external structure in the past all is a complex structure basically, and weight is big, manufacturing process is loaded down with trivial details, and assembling and repairing lack flexibility, and the metallic shield flexible pipe weight that is especially adopted is big, decay resistance is bad, influences properties of product and useful life.
The utility model content
The purpose of this utility model is for weight reduction, enhances product performance, and the spy provides a kind of aviation automatic pilot house steward.
The utility model provides a kind of aviation automatic pilot house steward, it is characterized in that: the automatic pilot house steward of described aviation comprises a terminal box 1, installation wiring 2, and 5,31 couplings of lead overlap 6 with 3,5 cramp frame 4,31 root guards of cable plug;
Wherein: 5 cramp frames 4 are installed on the terminal box 1, socket 101 in lead 5 and the terminal box is connected by soldering, lead 5 passes 5 cramp frames 4 and stretches out terminal box 1, protective jacket 6 is enclosed within the outside of lead 5, cable plug 3 solderings are connected the end of lead 5, and lead 5 is told different wire harness by installation wiring 2.
Be connected by nut between described cramp frame 4 and the terminal box 1.
Described attaching nut is 5.
Described terminal box 1 interpolation block 101 numbers are 4.
Described protective jacket 6 is the software material-structure.
Described protective jacket 6 is that nonmetal wire becomes with metal wire knitted.
Advantage of the present utility model:
Automatic pilot house steward is simple in structure, in light weight in aviation described in the utility model, and weight is 72% of traditional product, and the cable quality is softer, and assembling has more flexibility on the engine.Protective jacket adopts nonmetal wire to become with metal wire knitted, has satisfied the high and low temperature test, the vibratory impulse test, and tests such as mould, salt fog, electric property satisfies the engine instructions for use.
Description of drawings
Below in conjunction with drawings and the embodiments the utility model is described in further detail:
Fig. 1 is the automatic pilot house steward of an aviation general illustration;
Fig. 2 is the cable plug structural representation;
Fig. 3 is the junction box structure schematic diagram;
Fig. 4 is lead and protective jacket assembling schematic cross-section;
Fig. 5 is the installation wiring schematic diagram.
Embodiment
Embodiment 1
Present embodiment provides a kind of aviation automatic pilot house steward, it is characterized in that: the automatic pilot house steward of described aviation comprises a terminal box 1, installation wiring 2, and 5,31 couplings of lead overlap 6 with 3,5 cramp frame 4,31 root guards of cable plug;
Wherein: 5 cramp frames 4 are installed on the terminal box 1, socket 101 in lead 5 and the terminal box is connected by soldering, lead 5 passes 5 cramp frames 4 and stretches out terminal box 1, protective jacket 6 is enclosed within the outside of lead 5, cable plug 3 solderings are connected the end of lead 5, and lead 5 is told different wire harness by installation wiring 2.
Be connected by nut between described cramp frame 4 and the terminal box 1.
Described attaching nut is 5.
Described terminal box 1 interpolation block 101 numbers are 4.
Described protective jacket 6 is the software material-structure.
Described protective jacket 6 is that nonmetal wire becomes with metal wire knitted.
Present embodiment provides a kind of aviation automatic pilot house steward, it is characterized in that: the automatic pilot house steward of described aviation comprises a terminal box 1, installation wiring 2, and 5,31 couplings of lead overlap 6 with 3,5 cramp frame 4,31 root guards of cable plug;
Wherein: 5 cramp frames 4 are installed on the terminal box 1, socket 101 in lead 5 and the terminal box is connected by soldering, lead 5 passes 5 cramp frames 4 and stretches out terminal box 1, protective jacket 6 is enclosed within the outside of lead 5, cable plug 3 solderings are connected the end of lead 5, and lead 5 is told different wire harness by installation wiring 2.
Be connected by nut between described cramp frame 4 and the terminal box 1.
Described protective jacket 6 is the software material-structure.
Claims (6)
1. automatic pilot house steward of aviation, it is characterized in that: the automatic pilot house steward of described aviation comprises a terminal box (1), installation wiring (2), lead (5), 31 coupling cable plugs (3), 5 cramp frames (4), 31 root guard covers (6);
Wherein: 5 cramp frames (4) are installed on the terminal box (1), socket (101) in lead (5) and the terminal box is connected by soldering, lead (5) passes 5 cramp frames (4) and stretches out terminal box (1), protective jacket (6) is enclosed within the outside of lead (5), cable plug (3) soldering is connected the end of lead (5), and lead (5) is told different wire harness by installation wiring (2).
2. according to the automatic pilot house steward of the described aviation of claim 1, it is characterized in that: be connected by nut between described cramp frame (4) and the terminal box (1).
3. according to the automatic pilot house steward of the described aviation of claim 2, it is characterized in that: described attaching nut is 5.
4. according to the automatic pilot house steward of the described aviation of claim 1, it is characterized in that: described terminal box (1) interpolation block (101) number is 4.
5. according to the automatic pilot house steward of the described aviation of claim 1, it is characterized in that: described protective jacket (6) is the software material-structure.
6. according to the automatic pilot house steward of the described aviation of claim 1, it is characterized in that: described protective jacket (6) becomes with metal wire knitted for nonmetal wire.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010205369630U CN201868712U (en) | 2010-09-21 | 2010-09-21 | Main pipe for automatic aviation control lead |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010205369630U CN201868712U (en) | 2010-09-21 | 2010-09-21 | Main pipe for automatic aviation control lead |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201868712U true CN201868712U (en) | 2011-06-15 |
Family
ID=44139855
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010205369630U Expired - Lifetime CN201868712U (en) | 2010-09-21 | 2010-09-21 | Main pipe for automatic aviation control lead |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201868712U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102412485A (en) * | 2010-09-21 | 2012-04-11 | 沈阳黎明航空发动机(集团)有限责任公司 | Aviation automatic control wire main tube |
-
2010
- 2010-09-21 CN CN2010205369630U patent/CN201868712U/en not_active Expired - Lifetime
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102412485A (en) * | 2010-09-21 | 2012-04-11 | 沈阳黎明航空发动机(集团)有限责任公司 | Aviation automatic control wire main tube |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee after: Chinese Hangfa Shenyang Liming Aero engine limited liability company Address before: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee before: Liming Aeroplane Engine (Group) Co., Ltd., Shenyang City |
|
| CP01 | Change in the name or title of a patent holder | ||
| CX01 | Expiry of patent term |
Granted publication date: 20110615 |
|
| CX01 | Expiry of patent term |