CN110341982A - A kind of structure improving velocity sensor maintainability - Google Patents
A kind of structure improving velocity sensor maintainability Download PDFInfo
- Publication number
- CN110341982A CN110341982A CN201910548849.5A CN201910548849A CN110341982A CN 110341982 A CN110341982 A CN 110341982A CN 201910548849 A CN201910548849 A CN 201910548849A CN 110341982 A CN110341982 A CN 110341982A
- Authority
- CN
- China
- Prior art keywords
- plug
- cable
- socket
- velocity sensor
- connect
- 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.)
- Pending
Links
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 14
- 230000001939 inductive effect Effects 0.000 claims abstract description 14
- 230000006698 induction Effects 0.000 claims description 2
- 238000012423 maintenance Methods 0.000 abstract description 6
- 238000000034 method Methods 0.000 abstract description 5
- 238000009434 installation Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/40—Maintaining or repairing aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Regulating Braking Force (AREA)
Abstract
The invention discloses a kind of structures for improving velocity sensor maintainability, including inductive component, cable, plug, socket, flight control computer, inductive component is arranged in wheel, plug one end is connect with inductive component, the other end is connect with socket, cable one end is connect with socket, the other end is connect with flight control computer, the present invention is by the way that plug to be directly installed on inductive component, cable is passed through undercarriage axis inner hole to be connected on flight control computer, and it is connected and fixed by socket and product plug, when avoiding dismounting product, the clip that cable is fixed on undercarriage need to first be removed, the complicated processes for again extracting cable and plug from undercarriage axis inner hole out, improve Product maintenance.
Description
Technical field
The present invention relates to airplane brake system technical field more particularly to a kind of knots for improving velocity sensor maintainability
Structure.
Background technique
Currently, velocity sensor has been widely used for unmanned plane brake system, it is reliable to product with the needs of war preparedness
Property, maintainability, protection requirement be continuously improved, existing product structure has been unable to meet user demand.Make according to product is practical
With, installation, disassembly situation, design improved to product structure, improves Product maintenance, shortening maintenance time.
Summary of the invention
Goal of the invention: propose it is a kind of improve velocity sensor maintainability structure, can to avoid dismounting product when, need to first go
Except the clip for fixing cable on undercarriage, then the complicated processes that cable and plug are extracted out from undercarriage axis inner hole, improve product
Maintainability.
Technical solution:
A kind of structure improving velocity sensor maintainability, including inductive component, cable, plug, socket, winged control calculating
Machine, the inductive component are arranged in wheel, and described plug one end is connect with inductive component, and the other end is connect with socket,
Described cable one end is connect with socket, and the other end is connect with flight control computer.
Described cable one end is connect with socket, and the other end passes through undercarriage axis inner hole and connect with flight control computer.
The plug is detachably connected with socket.
The plug maximum outer dimension is 15mm, 5mm smaller than undercarriage axis inner hole.
The socket maximum outer dimension is 5mm smaller than undercarriage axis inner hole.
The cable length is 2500mm.
The utility model has the advantages that a kind of structure for improving velocity sensor maintainability is proposed, by the way that plug is directly installed on induction
On component, cable is passed through into undercarriage axis inner hole and is connected on flight control computer, and is connected and fixed by socket and product plug,
When avoiding dismounting product, the clip that cable is fixed on undercarriage need to be first removed, then cable and plug are taken out from undercarriage axis inner hole
Complicated processes out improve Product maintenance.
Detailed description of the invention
Fig. 1 is attachment structure schematic diagram of the present invention；
Wherein: 1, inductive component, 2, cable, 3, plug, 4, socket, 5, flight control computer, 6, wheel, 7, in undercarriage axis
Hole.
Specific embodiment
The present invention is further introduced with reference to the accompanying drawing, a kind of raising velocity sensor maintenance of the present invention
Property structure, including inductive component 1, cable 2, plug 3, socket 4, flight control computer 5, the inductive component 1 is arranged in machine
In wheel 6, described 3 one end of plug is connect with inductive component 1, and the other end is connect with socket 4, described 2 one end of cable and socket 4
Connection, the other end are connect with flight control computer 5.
Described 2 one end of cable is connect with socket 3, and the other end passes through undercarriage axis inner hole 7 and connect with flight control computer 5.
The plug 3 is detachably connected with socket 4, is easy for installation and removal.
The maximum outer dimension of the plug 3 is than the small 5mm of undercarriage axis inner hole 7, it is ensured that plug 3 can be passed through and be risen and fallen
Frame axis inner hole 7, in this patent, the full-size of plug 3 is 15mm, 7 internal diameter about 19-20mm of undercarriage axis inner hole, and band right angle turns
It is curved.
The maximum outer dimension of the socket 4 is than the small 5mm of undercarriage axis inner hole 7, it is ensured that socket can be passed through and be risen and fallen
Frame axis inner hole 7.
2 length of cable is 2500mm.
Cable 2 is passed through undercarriage axis inner hole 7 and is connected to by the present invention by the way that plug 3 to be directly installed on inductive component 1
It on flight control computer 5, and is connected and fixed by socket 4 with plug 3, when avoiding dismounting product, need to first be removed fixed on undercarriage
The clip of cable, then the complicated processes that cable 2 and plug 3 are extracted out from undercarriage axis inner hole 7 improve Product maintenance.
The above embodiments merely illustrate the technical concept and features of the present invention, and the purpose is to allow the skill for being familiar with the technical field
Art personnel can understand the content of the present invention and implement it accordingly, and can not be limited the scope of the invention with this, all bases
Equivalent changes or modifications made by spirit of that invention essence, should all cover in protection scope of the present invention.
Claims (8)
1. a kind of structure for improving velocity sensor maintainability, it is characterised in that: including inductive component (1), cable (2), plug
(3), socket (4), flight control computer (5), the plug (3) one end are connect with inductive component (1), the other end and socket (4)
Connection, the cable (2) one end are connect with socket (4), and the other end is connect with flight control computer (5).
2. a kind of structure for improving velocity sensor maintainability according to claim 1, it is characterised in that: the cable
The other end passes through undercarriage axis inner hole (7) and connect with flight control computer (5).
3. a kind of structure for improving velocity sensor maintainability according to claim 1, it is characterised in that: the plug
(3) it is detachably connected with socket (4).
4. a kind of structure for improving velocity sensor maintainability according to claim 1, it is characterised in that: the induction
Component (1) setting is in wheel (6).
5. a kind of structure for improving velocity sensor maintainability according to claim 1, it is characterised in that: the plug
(3) maximum outer dimension is 5mm smaller than undercarriage axis inner hole (7).
6. a kind of structure for improving velocity sensor maintainability according to claim 1, it is characterised in that: the socket
(4) maximum outer dimension is 5mm smaller than undercarriage axis inner hole (7).
7. a kind of structure for improving velocity sensor maintainability according to claim 1, it is characterised in that: the cable
(2) length is 2500mm.
8. a kind of structure for improving velocity sensor maintainability according to claim 1, it is characterised in that: the plug
(3) maximum outer dimension is 15mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910548849.5A CN110341982A (en) | 2019-06-24 | 2019-06-24 | A kind of structure improving velocity sensor maintainability |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910548849.5A CN110341982A (en) | 2019-06-24 | 2019-06-24 | A kind of structure improving velocity sensor maintainability |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110341982A true CN110341982A (en) | 2019-10-18 |
Family
ID=68182883
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910548849.5A Pending CN110341982A (en) | 2019-06-24 | 2019-06-24 | A kind of structure improving velocity sensor maintainability |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110341982A (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5139461A (en) * | 1990-10-17 | 1992-08-18 | Aircraft Braking Systems Corporation | Coupler for an aircraft wheel speed transducer |
| US20050281510A1 (en) * | 2004-06-17 | 2005-12-22 | Vo Chanh C | Fiber optic cable and plug assembly |
| US20110029183A1 (en) * | 2007-11-29 | 2011-02-03 | Daniel Gomiero | Testing device and method for checking the operability of a nose wheel steering control unit in an aircraft |
| CN103803098A (en) * | 2014-02-13 | 2014-05-21 | 西安航空制动科技有限公司 | Airplane wheel speed simulation device |
| CN104897922A (en) * | 2015-06-29 | 2015-09-09 | 贵州新安航空机械有限责任公司 | Non-contact Hall magnetic induction-type airplane wheel speed sensor |
| CN105431740A (en) * | 2013-03-13 | 2016-03-23 | 伍德沃德有限公司 | Aircraft wheel speed sensor |
| CN106081136A (en) * | 2016-06-03 | 2016-11-09 | 北方工业大学 | Unmanned aerial vehicle sliding lateral deviation detection method and device |
| US10040576B1 (en) * | 2017-09-14 | 2018-08-07 | Ilya Daniel Rosenberg | Tram system and methods for autonomous takeoff and landing of aircraft |
| CN210793680U (en) * | 2019-06-24 | 2020-06-19 | 贵州新安航空机械有限责任公司 | Structure for improving maintainability of speed sensor |
-
2019
- 2019-06-24 CN CN201910548849.5A patent/CN110341982A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5139461A (en) * | 1990-10-17 | 1992-08-18 | Aircraft Braking Systems Corporation | Coupler for an aircraft wheel speed transducer |
| US20050281510A1 (en) * | 2004-06-17 | 2005-12-22 | Vo Chanh C | Fiber optic cable and plug assembly |
| US20110029183A1 (en) * | 2007-11-29 | 2011-02-03 | Daniel Gomiero | Testing device and method for checking the operability of a nose wheel steering control unit in an aircraft |
| CN105431740A (en) * | 2013-03-13 | 2016-03-23 | 伍德沃德有限公司 | Aircraft wheel speed sensor |
| CN103803098A (en) * | 2014-02-13 | 2014-05-21 | 西安航空制动科技有限公司 | Airplane wheel speed simulation device |
| CN104897922A (en) * | 2015-06-29 | 2015-09-09 | 贵州新安航空机械有限责任公司 | Non-contact Hall magnetic induction-type airplane wheel speed sensor |
| CN106081136A (en) * | 2016-06-03 | 2016-11-09 | 北方工业大学 | Unmanned aerial vehicle sliding lateral deviation detection method and device |
| US10040576B1 (en) * | 2017-09-14 | 2018-08-07 | Ilya Daniel Rosenberg | Tram system and methods for autonomous takeoff and landing of aircraft |
| CN210793680U (en) * | 2019-06-24 | 2020-06-19 | 贵州新安航空机械有限责任公司 | Structure for improving maintainability of speed sensor |
Non-Patent Citations (1)
| Title |
|---|
| 陈艳华: "《城市轨道交通信号基础设备》", 30 September 2013, 重庆大学出版社, pages: 157 - 161 * |
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