CN203838700U - Novel flight control computer cable connecting structure - Google Patents
Novel flight control computer cable connecting structure Download PDFInfo
- Publication number
- CN203838700U CN203838700U CN201420185163.7U CN201420185163U CN203838700U CN 203838700 U CN203838700 U CN 203838700U CN 201420185163 U CN201420185163 U CN 201420185163U CN 203838700 U CN203838700 U CN 203838700U
- Authority
- CN
- China
- Prior art keywords
- connector
- control computer
- flight control
- signal connector
- output signal
- 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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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 title claims abstract description 37
- 238000012423 maintenance Methods 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 4
- 230000000052 comparative effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Abstract
The utility model discloses a novel flight control computer cable connecting structure which is composed of a power line connector (1), a big-load output signal connector (2), a small-load output signal connector (3), a small-load input signal connector (4) and a flight control computer case (5). A connecting part for the flight control computer case (5) is fixed on an air plane; the power line connector (1), the big-load output signal connector (2), the small-load output signal connector (3) and the small-load input signal connector (4) are respectively arranged on a front panel of the flight control computer case (5). The novel flight control computer cable connecting structure is high in reliability, small in volume, good in resistance to the environment, and convenient to detach, and efficiently avoids the problems of poor contact and bad maintenance caused by a rapid plugging rectangular connector.
Description
Technical field
The utility model relates to structural design and the application of syndeton, and a kind of novel flight control computer cable connection structure is provided especially.
Background technology
In the use of the flight-control computer of certain series aircraft, occur causing system false-alarm report because connector contact is bad therefore, mode cannot enter even the serious consequences such as computing machine burns.The reason of searching to the bottom is that the type of attachment of flight control computer has adopted fast insert-pull rectangular connector, this kind of mode, rectangular connector socket is fixed on flight control computer support, rectangular connector plug is fixed on flight control computer casing rear portion, on support, there is register pin, on flight control computer casing, have pilot hole, when installation, pilot hole is aimed at register pin, pushed cabinet plug and socket and link together.The advantage of which is, dismounting computer operation step is few, but there are equally a lot of problems, because positioning requirements is high, high to the accuracy requirement of casing structure design and processing, but due to long-time use, positioning precision declines, often cause while maintenance and cause connector contact bad, occur that false-alarm system mode cannot connect, the phenomenon that even computing machine burns; Because of the technological problems of location, the plug after cabinet can not design multiple, conventionally designs one in addition, forms like this power supply and heavy load signal and little load signal and shares a plug, is unfavorable for maintenance.
This problem is repeatedly appearance on this series aircraft, and to aircraft, follow-up use has brought great potential safety hazard.
People urgently wish to obtain the good novel flight control computer cable connection structure of a kind of technique effect.
Utility model content
The purpose of this utility model is to provide a kind of novel flight control computer cable connection structure of high reliability.
Described novel flight control computer cable connection structure is constructed as follows: power interface connector 1, heavy load output signal connector 2, little load output signal connector 3, little load input signal connector 4 and flight control computer cabinet 5; Described flight control computer cabinet 5 web members are fixing aboard, described power interface connector 1, heavy load output signal connector 2, little load output signal connector 3 and little load input signal connector 4 are arranged on flight control computer cabinet 5 front panels, and described power interface connector 1, heavy load output signal connector 2, little load output signal connector 3, little load input signal connector 4 all adopt bayonet type cylindrical connector.
The model that the model of described power interface connector 1 is specially described power interface connector 1 is specially: JY27467T1B99SN.
The model of described heavy load output signal connector 2 is specially: Y27467T23B55SB; The model of little load out connector is specially: JY27467T23B55SA; The model of described little load input connector is specially: JY27467T23B55SN.
Described bayonet type cylindrical connector is the connector of comparative maturity, and its reliability is high, volume is little, resistance to environment is good, convenient disassembly.The poor problem of loose contact maintainability that adopts this connected mode effectively to avoid fast insert-pull rectangular connector to cause.
Described novel flight control computer cable connection structure adopts bayonet type cylindrical connector, and be arranged in front panel, and by arranged apart to power interface connector 1, heavy load output signal connector 2, little load output signal connector 3, little load input signal connector 4, the poor problem of loose contact maintainability of effectively avoiding fast insert-pull rectangular connector to cause.
Brief description of the drawings
Fig. 1 is bayonet type cylindrical connector structure schematic diagram;
Fig. 2 is novel flight control computer cable connection structure schematic diagram;
Fig. 3 is traditional flight control computer cable connection structure plug schematic diagram;
Fig. 4 is traditional flight control computer cable connection structure socket schematic diagram.
Wherein: 6 is that plug contact, 7 is that flight control computer cabinet, 8 is pilot hole; 9 is that register pin, 10 is that socket contact, 11 is flight control computer support.
Embodiment
Embodiment 1
Described novel flight control computer cable connection structure is constructed as follows: power interface connector 1, heavy load output signal connector 2, little load output signal connector 3, little load input signal connector 4 and flight control computer cabinet 5; Described flight control computer cabinet 5 web members are fixing aboard, described power interface connector 1, heavy load output signal connector 2, little load output signal connector 3 and little load input signal connector 4 are arranged on flight control computer cabinet 5 front panels, and described power interface connector 1, heavy load output signal connector 2, little load output signal connector 3, little load input signal connector 4 all adopt bayonet type cylindrical connector.
The model that the model of described power interface connector 1 is specially described power interface connector 1 is specially: JY27467T1B99SN.
The model of described heavy load output signal connector 2 is specially: Y27467T23B55SB; The model of little load out connector is specially: JY27467T23B55SA; The model of described little load input connector is specially: JY27467T23B55SN.
Described bayonet type cylindrical connector is the connector of comparative maturity, and its reliability is high, volume is little, resistance to environment is good, convenient disassembly.The poor problem of loose contact maintainability that adopts this connected mode effectively to avoid fast insert-pull rectangular connector to cause.
Described novel flight control computer cable connection structure adopts bayonet type cylindrical connector, and be arranged in front panel, and by arranged apart to power interface connector 1, heavy load output signal connector 2, little load output signal connector 3, little load input signal connector 4, the poor problem of loose contact maintainability of effectively avoiding fast insert-pull rectangular connector to cause.
Claims (3)
1. a novel flight control computer cable connection structure, is characterized in that: described novel flight control computer cable connection structure is constructed as follows: power interface connector (1), heavy load output signal connector (2), little load output signal connector (3), little load input signal connector (4) and flight control computer cabinet (5); Described flight control computer cabinet (5) web member is fixing aboard, described power interface connector (1), heavy load output signal connector (2), little load output signal connector (3) and little load input signal connector (4) are arranged on flight control computer cabinet (5) front panel, and described power interface connector (1), heavy load output signal connector (2), little load output signal connector (3), little load input signal connector (4) all adopt bayonet type cylindrical connector.
2. novel flight control computer cable connection structure as claimed in claim 1, is characterized in that: the model of described power interface connector (1) is specially: JY27467T1B99SN.
3. novel flight control computer cable connection structure as claimed in claim 2, is characterized in that: the model of described heavy load output signal connector (2) is specially: 27467T23B55SB; The model of little load out connector is specially: JY27467T23B55SA; The model of described little load input connector is specially: JY27467T23B55SN.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420185163.7U CN203838700U (en) | 2014-04-16 | 2014-04-16 | Novel flight control computer cable connecting structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420185163.7U CN203838700U (en) | 2014-04-16 | 2014-04-16 | Novel flight control computer cable connecting structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203838700U true CN203838700U (en) | 2014-09-17 |
Family
ID=51516515
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420185163.7U Expired - Lifetime CN203838700U (en) | 2014-04-16 | 2014-04-16 | Novel flight control computer cable connecting structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203838700U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104407191A (en) * | 2014-12-01 | 2015-03-11 | 江西洪都航空工业集团有限责任公司 | Conversion device of data acquisition system |
| CN106527401A (en) * | 2016-11-30 | 2017-03-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Flight control test automated testing system |
| CN114286556A (en) * | 2021-12-16 | 2022-04-05 | 贵州航天南海科技有限责任公司 | Quick plug multimachine frame |
-
2014
- 2014-04-16 CN CN201420185163.7U patent/CN203838700U/en not_active Expired - Lifetime
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104407191A (en) * | 2014-12-01 | 2015-03-11 | 江西洪都航空工业集团有限责任公司 | Conversion device of data acquisition system |
| CN104407191B (en) * | 2014-12-01 | 2017-05-17 | 江西洪都航空工业集团有限责任公司 | Conversion device of data acquisition system |
| CN106527401A (en) * | 2016-11-30 | 2017-03-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Flight control test automated testing system |
| CN106527401B (en) * | 2016-11-30 | 2023-09-05 | 中国航空工业集团公司沈阳飞机设计研究所 | Automatic test system for flight control test |
| CN114286556A (en) * | 2021-12-16 | 2022-04-05 | 贵州航天南海科技有限责任公司 | Quick plug multimachine frame |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |