CN102060104B - Micro-switch assembly - Google Patents
Micro-switch assembly Download PDFInfo
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- CN102060104B CN102060104B CN 201010550559 CN201010550559A CN102060104B CN 102060104 B CN102060104 B CN 102060104B CN 201010550559 CN201010550559 CN 201010550559 CN 201010550559 A CN201010550559 A CN 201010550559A CN 102060104 B CN102060104 B CN 102060104B
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Abstract
The invention discloses a device on crosslinking of an engine control system with an airplane flap control system and an airplane undercarriage control system. The engine control system completes switching over of a cable wire of a frame section and a cable wire of a wing section through pulleys on upper and lower ends of a center shaft of the micro-switch assembly. By changing the angle of an engine throttle, the pulleys on the upper and lower ends of the center shaft of the micro-switch assembly drive the shaft to rotate, and the shaft drives a cam assembly to rotate synchronously with the shaft. When the rotating shaft rotates to a certain angle, the cam assembly props against a specific switch, so signals are output to a flap warning system and a undercarriage control warning system to achieve the aims of safety and reliability of a certain type of an airplane. The device has the characteristics of simple structure and low cost, and is easy for production.
Description
Technical field
The invention belongs to aero-engine maneuvering system field, relate to a kind of engine throttle Angular measures aircraft flap maneuvering system and the mutually crosslinked device of undercarriage extension and retraction system.
Background technology
For reliability and the safety that guarantees aircraft, aero-engine maneuvering system, aircraft flap maneuvering system and undercarriage extension and retraction system need certain concertedness, therefore need a crosslinking apparatus that is used for collaborative aero-engine maneuvering system, aircraft flap maneuvering system and the work of undercarriage extension and retraction system.
At present, the crosslinking apparatus of domestic certain type transport plane engine control system, aircraft flap maneuvering system and undercarriage extension and retraction system need be finished 4 power managements simultaneously, 8 transit workings that cable wire extends to both wings.Inner cable wire switching pillar integrates, so that this crosslinking apparatus complex structure, reliability is low, and the part manufacture difficulty is large.
Summary of the invention
The objective of the invention is: provide a kind of simple in structure, be easy to produce, reliability is high, can realize the aero-engine maneuvering system, flap control system and the crosslinked micro-switch assembly of landing-gear system.
Technical scheme of the present invention is: a kind of micro-switch assembly, it comprises main casing, axle, bearing, top sheave, cable wire, lower sheave, lower cover, roll wheel assembly, cam pack and micro-switch switch, wherein, the column that has two hollows on the main casing, described axle is arranged in the column by bearing, the up and down two ends of described axle are fixed with respectively top sheave and lower sheave, lower cover and main casing are fastenedly connected, axle is provided with cam pack after passing lower cover, roll wheel assembly and cam pack are oppositely arranged, and the corresponding roll wheel assembly setting of micro-switch switch, and link to each other with the crosslinked system of needs, be connected with cable wire on pulley and the pulley, cable wire on the pulley links to each other with the throttle operation bar of center pedestal, cable wire on the pulley is connected on the engine fuel regulating control, and described cam pack is comprised of two cams with edge protuberance that superpose up and down, has up and down 60 ° to 70 ° differential seat angle between the projection of two cams.Projection thickness on the cam only is 5mm, wherein, the roll wheel assembly corresponding with overhead cam is provided with the micro-switch switch with flap control ALM circuit communication, and the roll wheel assembly corresponding with lower cam is provided with the micro-switch switch that is communicated with the landing-gear system warning circuit.
Be provided with the lining that seals between axle and the main casing for realizing in the main casing inner chamber.
Described cam pack is arranged on the axle by spline.
The invention has the beneficial effects as follows: the present invention at first finishes the engine control system cable wire and passes the signaling transfer point of airtight cabin to central wing and break-in to the room of setting out along spanwise from fuselage interior, while is to the alarm system output signal of aircraft flap maneuvering system and undercarriage extension and retraction system, thus the safety and reliability of raising aircraft.And micro-switch unit construction of the present invention is simple, has simplified the design of part form, has reduced production and assembly difficulty, has shortened the part production cycle, has improved part and has criticized production efficiency.
Description of drawings
Fig. 1 is micro-switch assembly outside drawing, among the figure: top sheave 1, bearing 2, lining 3, axle 4, body shell 5, tie bolt 6, cable wire 7, lower sheave 8, lower cover 9.
Fig. 2 is cam mechanism, roll wheel assembly and the micro-switch figure in the micro-switch assembly, among the figure: lower cover 9, roll wheel assembly 10, micro-switch 11, cam pack 12, mount pad 13.
Fig. 3 is cam pack figure.
The specific embodiment
Below in conjunction with accompanying drawing and the specific embodiment the present invention is described in further detail:
See also Fig. 1 and Fig. 2, wherein, Fig. 1 is the front view of micro-switch assembly of the present invention, and Fig. 2 is that the A of Fig. 1 is to view.In the present embodiment, the micro-switch assembly comprises main casing 5, axle 4, lining 3, bearing 2, top sheave 1, cable wire 7, tie bolt 6, lower sheave 8, lower cover 9, roll wheel assembly 10, cam pack 12, micro-switch switch 11 and mount pad 13.Wherein, the column that has two hollows on the main casing 5.Two ends are crossed to win bearing 2 are installed about each column, and axle 4 passes bearing 2 and is arranged in the column.Lining 3 arranges in main casing 5 inner chambers, realizes the sealing between axle 4 and the main casing 5.Top sheave 1 and lower sheave 8 are fixedly connected on respectively axle, and about in the of 4 two ends, rotate synchronously with axle 4, and be connected with cable wire on lower sheave 8 and the top sheave 1, cable wire on the lower sheave 8 links to each other with the throttle lever of center pedestal, cable wire on the top sheave 1 prolongs spanwise and lays, and is connected on the engine fuel regulating control.
Lower cover 9 is fastenedly connected by four tie bolts 6 and main casing 5.Axle 4 is provided with cam pack 12 by spline after passing lower cover 9, and described cam pack 12 rotates synchronously with axle 4, so the pulley 1 at axle two ends about in the of 4 can be realized servo-actuated with cam pack 12.
See also Fig. 3, it is the structural representation of cam pack.Described cam pack 12 is comprised of two cams with edge protuberance that superpose up and down, the differential seat angle that has up and down 60 ° to 70 ° between the projection of two cams, its concrete angular dimension is relevant with protruding radian, and the projection thickness on the cam only is 5mm, when therefore micro-switch is worked, roll wheel assembly 10 assembly strokes are little, can realize fine motion control.The bilevel cam lobe of lower cover 9 corresponding cam packs 12 is respectively arranged with two roll wheel assemblies 10, wherein, the roll wheel assembly 10 corresponding with overhead cam is provided with the micro-switch switch with flap control ALM circuit communication, and the roll wheel assembly 10 corresponding with lower cam is provided with the micro-switch switch that is communicated with the landing-gear system warning circuit.Can squeezing roller assembly 10 after cam pack 12 turns to certain angle with pulley 1, and after roll wheel assembly 10 is squeezed, can presses micro-switch switch 11, thereby connect the warning circuit of flap control system or landing-gear system.Described mount pad 13 links to each other with main casing 5 by four bolts in addition, and micro-switch assembly of the present invention is assemblied on the aircraft central wing front-axle beam realization installation aboard by this mount pad 13.
During micro-switch assembly work of the present invention, engine control system is finished the switching of frame sections cable wire and wing section cable wire by the pulley of micro-switch assembly axis 4 upper/lower terminals.Promote the throttle operation bar on the center pedestal, by cable wire the lower sheave 8 of micro-switch assembly is rotated, band moving axis 4, thus so that top sheave 1 rotates, change engine throttle angle (namely changing engine power).Simultaneously, axle 4 drive cam packs 12 rotate synchronously.When gasoline throttle angle from 0 ° increase to 55 °～more than 69 ° the time, overhead cam squeezing roller assembly, roll wheel assembly is pressed micro-switch connects the micro-switch of the acoustic signal device of wing flap warning circuit, if wing flap is not put into take-off angle, the alarm bell sound equipment that namely gives a warning, " wing flap is not put well " red eye is bright, notes to remind the aircrew.Before the aircraft landing, when gasoline throttle angle receive to 31 °～below 34 ° the time, lower cam squeezing roller assembly, roll wheel assembly is pressed micro-switch connects the micro-switch of the acoustic signal device of alighting gear warning circuit, if an alighting gear is arranged not to be put well, the alarm bell sound equipment that namely gives a warning, " alighting gear is not put well " red eye is bright, notes to remind the aircrew.
The present invention at first finishes motivation maneuvering system cable wire and passes the signaling transfer point of airtight cabin to central wing and break-in to the room of setting out along spanwise from fuselage interior, while is to the warning output signal of aircraft flap maneuvering system and undercarriage extension and retraction system, thus the safety and reliability of raising aircraft.And simple in structure, simplified the design of part form, reduced production and assembly difficulty, shortened the part production cycle, improved part and criticized production efficiency.
In addition, although in the above-mentioned embodiment, micro-switch assembly of the present invention only links to each other with the undercarriage extension and retraction system with the aircraft flap maneuvering system, crosslinked to realize with the airplane operation system, yet, micro-switch assembly of the present invention also can be with other needs crosslinked system to link to each other in the aircraft, thereby can enlarge the range of use of micro-switch assembly.
Claims (3)
1. micro-switch assembly, it is characterized in that: comprise main casing (5), axle (4), bearing (2), lining (3), top sheave (1), cable wire (7), lower sheave (8), lower cover (9), roll wheel assembly (10), cam pack (12) and micro-switch switch (11), wherein, the column that has two hollows on the main casing (5), described axle (4) is arranged in the column by bearing (2), the up and down two ends of described axle are fixed with respectively top sheave (1) and lower sheave (8), lower cover (9) is fastenedly connected with main casing (5), axle (4) is provided with cam pack (12) after passing lower cover (9), roll wheel assembly (10) is oppositely arranged with cam pack (12), and the corresponding roll wheel assembly of micro-switch switch (11) (10) arranges, and link to each other with the crosslinked system of needs, be connected with cable wire on lower sheave (8) and the top sheave (1), cable wire on the lower sheave (8) links to each other with the throttle operation bar of center pedestal, cable wire on the top sheave (1) is connected on the engine fuel regulating control, described cam pack (12) is comprised of two cams with edge protuberance that superpose up and down, the differential seat angle that has up and down 60 ° to 70 ° between the projection of two cams, projection thickness on the cam is 5mm, wherein, the roll wheel assembly corresponding with overhead cam (10) is provided with the micro-switch switch with flap control ALM circuit communication, and the roll wheel assembly (10) corresponding with lower cam is provided with the micro-switch switch that is communicated with the landing-gear system warning circuit.
2. micro-switch assembly according to claim 1 is characterized in that: be provided with in main casing (5) inner chamber for the lining (3) of realizing sealing between axle (4) and the main casing (5).
3. micro-switch assembly according to claim 2, it is characterized in that: described cam pack (12) is arranged on the axle (4) by spline.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010550559 CN102060104B (en) | 2010-11-19 | 2010-11-19 | Micro-switch assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010550559 CN102060104B (en) | 2010-11-19 | 2010-11-19 | Micro-switch assembly |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102060104A CN102060104A (en) | 2011-05-18 |
| CN102060104B true CN102060104B (en) | 2013-03-06 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201010550559 Active CN102060104B (en) | 2010-11-19 | 2010-11-19 | Micro-switch assembly |
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| CN (1) | CN102060104B (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103723270B (en) * | 2013-12-24 | 2017-06-30 | 中国人民解放军海军航空工程学院青岛校区 | A kind of Signal collection device of flap down final position of airplane |
| CN105523173A (en) * | 2014-09-28 | 2016-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Flap control system for utility aircraft |
| CN108054033B (en) * | 2017-12-14 | 2019-10-18 | 中国航空工业集团公司成都飞机设计研究所 | A kind of fixed front-wheel load switch trigger mechanism |
| CN109250129B (en) * | 2018-09-25 | 2021-09-14 | 陕西飞机工业（集团）有限公司 | Adjustable limiting device for aircraft engine in-air medium-small throttle |
| CN111114822A (en) * | 2019-12-25 | 2020-05-08 | 国营芜湖机械厂 | Repairing method for loosening of electric door rotating shaft at aircraft landing gear position end point and riveting tool thereof |
| CN113815844B (en) * | 2021-09-24 | 2023-09-08 | 中国航空工业集团公司西安飞机设计研究所 | Electric control type tail boom retraction system of airplane and control method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2507780Y (en) * | 2001-11-02 | 2002-08-28 | 熊伟 | Small tilting rotor commercial aircraft |
| CN2749784Y (en) * | 2004-09-30 | 2006-01-04 | 李威 | Automatic false-retracting resistant device for airplane landing gear |
| CN2841502Y (en) * | 2005-10-28 | 2006-11-29 | 南京轻型飞机股份有限公司 | Light aircraft |
| JP4094786B2 (en) * | 1999-10-05 | 2008-06-04 | 株式会社共立 | Hand lever device |
-
2010
- 2010-11-19 CN CN 201010550559 patent/CN102060104B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4094786B2 (en) * | 1999-10-05 | 2008-06-04 | 株式会社共立 | Hand lever device |
| CN2507780Y (en) * | 2001-11-02 | 2002-08-28 | 熊伟 | Small tilting rotor commercial aircraft |
| CN2749784Y (en) * | 2004-09-30 | 2006-01-04 | 李威 | Automatic false-retracting resistant device for airplane landing gear |
| CN2841502Y (en) * | 2005-10-28 | 2006-11-29 | 南京轻型飞机股份有限公司 | Light aircraft |
Non-Patent Citations (1)
| Title |
|---|
| JP特许第4094786号B2 2008.06.04 |
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| CN102060104A (en) | 2011-05-18 |
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Address after: 723213 Liulin Town, Chenggu County, Hanzhong City, Shaanxi Province Patentee after: Shaanxi Aircraft Industry Co.,Ltd. Address before: 723213 box 34, Shaanxi, Hanzhoung Patentee before: Shaanxi Aircraft INDUSTRY(GROUP) Co.,Ltd. |
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