CN102095570B - Automatic channel switching device for PDP (plasma display panel) vacuum ultraviolet fluorescent powder testing system - Google Patents
Automatic channel switching device for PDP (plasma display panel) vacuum ultraviolet fluorescent powder testing system Download PDFInfo
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- CN102095570B CN102095570B CN201010560925A CN201010560925A CN102095570B CN 102095570 B CN102095570 B CN 102095570B CN 201010560925 A CN201010560925 A CN 201010560925A CN 201010560925 A CN201010560925 A CN 201010560925A CN 102095570 B CN102095570 B CN 102095570B
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Abstract
An automatic channel switching device for a PDP (plasma display panel) vacuum ultraviolet fluorescent powder testing system is characterized in that the device comprises a casing, an operation panel, a window discrimination sensor, a DC power supply module, a main control circuit board, and corresponding aviation sockets, plugs and cables. The DC power supply module, the main control circuit board and the corresponding aviation sockets are arranged in the casing, and are connected with other instruments through the plugs and the cables. The automatic channel switching device has the advantages that the device has a plug-and-play function without changing the original testing system, and has stable, safe and reliable performance by adopting double-mode switching; the device is convenient in operation, and has high automaton degree and a direct result display function; and the device has short consumed time, can achieve the switching in one second, and can improve the sample detection efficiency and lower the labor intensity of operators.
Description
Technical field
[0001] the present invention relates to a kind of channel automatic switching control equipment, particularly relate to a kind of channel automatic switching control equipment of the PDP of being used for vacuum uv phosphor test macro.
Background technology
[0002] PDP (plasma display apparatus) vacuum uv phosphor test macro can be simulated the PDP duty, under high vacuum, measures the optical property parameters such as fluorescence spectrum, luminosity, fluorescence sunset glow time, luminescence spectrum peak wavelength, bandwidth, chromaticity coordinates, colour purity and predominant wavelength after fluorescent powder receives 147nm, 172nm excited by vacuum ultraviolet.Mainly partly form by vacuum ultraviolet-excited source, fluorescent powder vacuum test chamber, vacuum pump, compound vacuum gauge, controller, luminance test appearance, phosphorescence afterglow tester, spectral radiance analyser, computer system, AC frequency conversion power supply etc.It is the special inspecting equipment of development and exploitation PDP phosphor material powder.
The defective that this system exists is; When each sample of test; Fluorescent probe is behind brightness measurement window and afterglow measurement window transform, and the operator must arrive the switch board back side, with two channel cable plugs of drawing in the fluorescent probe; Plug conversion between luminance test appearance and twilight sunset tester, each about 50 ~ 60 seconds consuming time.If sample tray is once piled 10 samples, plug is 40 times back and forth.This channel switching method causes the sample detection inefficiency, and labor intensity of operating staff is big.
In addition, there are many cable connections at the switch board back side, except that light current, also has forceful electric power, often comes in and goes out, and operating personnel are also had potential safety hazard.And plug continually, cause the lead of joint to produce short circuit or open circuit easily, surveying work is interrupted suddenly, the data of surveying are scrapped, and must wait for after the maintenance personal repairs remeasuring, and have interrupted the continuity of test, and work is made troubles to teaching and scientific research.
Summary of the invention
The purpose of this invention is to provide a kind of low cost, automaticity high, easy and simple to handle, switch rapid and reliable and be used for PDP vacuum uv phosphor test macro channel switching method and device thereof.
The technical scheme that realizes the object of the invention is:
Comprise housing, guidance panel, window examination sensor, DC power supplier, main control board, and corresponding aviation socket, plug and cable.
DC power supplier, main control board, and corresponding aviation socket is arranged in the housing, and be connected with other instruments with plug, cable.
In the main control board, the program-controlled electronic switch that comprises main control unit that C51 series monolithic and MAX232 interface chip form, forms with DC12V relay and ULN2004 chip, with switch power module form+12V/+5V direct supply, the one 3 core aviation socket, the 23 core aviation socket, the 33 core aviation socket, the one 5 core aviation socket, the 25 core aviation socket, the 35 core aviation socket, the one 2 core aviation socket, the 22 core aviation socket, 4 core aviation sockets, 6 core aviation sockets, three group of two throw switch, two group of three throw switch, first magnetic induction switch, second magnetic induction switch, first light emitting diode, second light emitting diode, the 3rd light emitting diode, the 4th light emitting diode, the 5th light emitting diode.Two group of three throw switch, first light emitting diode, second light emitting diode, the 3rd light emitting diode, the 4th light emitting diode, the 5th light emitting diode, three group of two throw switch are welded on the main control board front, and all aviation sockets all are welded on the main control board reverse side.First group of three group of two throw switch connects direct supply, and second group connects the one 5 core aviation socket, and the 3rd group connects the one 3 core aviation socket; The common port of two group of three throw switch is connected with the output terminal of three group of two throw switch, and the output terminal of two group of three throw switch is connected with the 25 core aviation aviation socket, the 35 core aviation aviation socket, the 23 core aviation socket, the 33 core aviation socket port respectively.
Ten interfaces of drawing from housing 1 comprise: 4 core aviation sockets, 6 core aviation sockets, the one 2 core aviation socket, the 22 core aviation socket, the 25 core aviation socket, the 23 core aviation socket, the 35 core aviation socket, the 33 core aviation socket, the one 5 core aviation socket, the one 3 core aviation socket.4 core aviation sockets, 6 core aviation sockets are connected with computing machine through cable; The 25 core aviation socket, the 23 core aviation socket are connected with brightness detection instrument through cable; The 35 core aviation socket, the 33 core aviation socket are connected with the twilight sunset detector through cable, and the one 5 core aviation socket, the one 3 core aviation socket are connected with fluorescent probe with second probe lead wire through first probe lead wire respectively.
Window is screened sensor and is comprised first magnetic induction switch, second magnetic induction switch, magnet ring and plug stainless-steel pipe.First magnetic induction switch, second magnetic induction switch are packaged in respectively in the plug stainless-steel pipe, respectively draw a signal wire and are connected with the 22 core aviation socket with the one 2 core aviation socket respectively.Magnet ring sticks on the outer surface of tube wall of fluorescent probe, and first magnetic induction switch is installed in the dog screw part of brightness detection window, and second magnetic induction switch is installed in the dog screw part of twilight sunset detection window.Insert brightness detection window or twilight sunset detection window when fluorescent probe, magnet ring will encourage the magnetic force induction switch, screen the residing different measuring window of fluorescent probe with this.The first magnetic induction switch closure shows that fluorescent probe inserted the brightness measurement window; The second magnetic induction switch closure shows that fluorescent probe inserted the sunset glow measurement window; The window discriminator signal is input to main control unit through the one 2 core aviation socket and the 22 core aviation jack interface; After the control circuit processing, send corresponding relay steering order, thereby realize that channel switches fast.
Be furnished with two group of three throw switch, first light emitting diode, second light emitting diode, the 3rd light emitting diode, the 4th light emitting diode, the 5th light emitting diode, three group of two throw switch on the guidance panel.
First light emitting diode, second light emitting diode, the 3rd light emitting diode, the 4th light emitting diode, the 5th light emitting diode be display brightness window, vacant, sunset glow window, automatic, manual state respectively.Wherein, the 4th light emitting diode is bright, is expressed as automatic switching mode; The bright channel of then representing of first light emitting diode is " vacant " state; The bright channel of then representing of second light emitting diode is " brightness " state; The bright channel of then representing of the 3rd light emitting diode is " twilight sunset " state; , all the other light emitting diodes bright at next the 5th light emitting diode of manual switchover mode extinguish entirely.
Three group of two throw switch is used for being provided with switch mode, and when three group of two throw switch thrown in 1 retaining, then logical, the one 5 core aviation socket of direct supply and program-controlled electronic Switching Power Supply termination and the one 3 core aviation socket are communicated with the entering automatic switchover mode with the relay common; Throw in 2 retainings when three group of two throw switch, then direct supply and program-controlled electronic Switching Power Supply end break off, and the one 5 core aviation socket and the one 3 core aviation socket are communicated with two group of three throw switch common, get into the manual switchover pattern.
Two group of three throw switch is used for manual switchover, throws 1 retaining, and then the one 5 core aviation socket and the one 3 core aviation socket are communicated with the 25 core aviation socket and the 23 core aviation socket, carry out brightness measurement; Throw 2 retainings, then the one 5 core aviation socket and the one 3 core aviation socket are unsettled, do not measure; Throw 3 retainings, then the one 5 core aviation socket and the one 3 core aviation socket are communicated with the 35 core aviation socket and the 33 core aviation socket, carry out afterglow measurement.
Automatically, the benefit of manual dual-mode is, when automatic mode breaks down, still switching channels does not quickly interrupt test job.
The present invention has following advantage: to former test macro without any change, and plug and play.Double mode switching, stable performance, safe and reliable.Easy and simple to handle, automaticity is high, directly show switching result.Weak point consuming time can be accomplished switching in 1 second.Improve sample detection efficient, reduce labor intensity of operating staff.
Description of drawings
Fig. 1 is a schematic block circuit diagram of the present invention.
Fig. 2 connects for cable of the present invention and window is screened the sensor construction synoptic diagram.
Fig. 3 is an interface distribution schematic diagram of the present invention.
Fig. 4 arranges synoptic diagram in the guidance panel of the present invention.
U1. main control unit wherein, U2. program-controlled electronic switch, U3. direct supply, Y1. computing machine, Y2. brightness detection window; Y3. sunset glow measurement window, Y4. fluorescent probe, Y5. brightness detection instrument, Y6. twilight sunset detector, SI. first probe lead wire; HV. second probe lead wire, HV0. the one 3 core aviation socket, HV1. the 23 core aviation socket, HV2. the 33 core aviation socket, SI0. the one 5 core aviation socket; SI1. the 25 core aviation socket, SI2. the 35 core aviation socket, WS1. the one 2 core aviation socket, WS2. the 22 core aviation socket, AC220CZ.4 core aviation socket; RS232CZ.6 core aviation socket, three group of two throw switch of SW1., two group of three throw switch of SW2., K1. first magnetic induction switch, K2. second magnetic induction switch; LED1. first light emitting diode, LED2. second light emitting diode, LED3. the 3rd light emitting diode, LED4. the 4th light emitting diode; LED5. the 5th light emitting diode, 1. housing, 2. guidance panel, 3. magnet ring.
Embodiment
Below in conjunction with accompanying drawing the present invention is further specified.
DC power supplier, main control board, and corresponding aviation socket is arranged in the housing 1, and be connected with other instruments with plug, cable.
In the main control board, the program-controlled electronic switch U2 that comprises main control unit U1 that C51 series monolithic and MAX232 interface chip form, forms with DC12V relay and ULN2004 chip, with switch power module form+12V/+5V direct supply U3, the one 3 core aviation socket HV0, the 23 core aviation socket HV1, the 33 core aviation socket HV2, the one 5 core aviation socket SI0, the 25 core aviation socket SI1, the 35 core aviation socket SI2, the one 2 core aviation socket WS1, the 22 core aviation socket WS2,4 core aviation socket AC220CZ, 6 core aviation socket RS232CZ, three group of two throw switch SW1, two group of three throw switch SW2, the first magnetic induction switch K1, the second magnetic induction switch K2, first LED 1, second LED 2, the 3rd LED 3, the 4th LED 4, the 5th LED 5.Two group of three throw switch SW2, first LED 1, second LED 2, the 3rd LED 3, the 4th LED 4, the 5th LED 5, three group of two throw switch SW1 are welded on the main control board front, and all aviation sockets all are welded on the main control board reverse side.First group of three group of two throw switch SW1 connects direct supply U3, and second group connects the one 5 core aviation socket SI0, and the 3rd group connects the one 3 core aviation socket HV0; The common port of two group of three throw switch SW2 is connected with the output terminal of three group of two throw switch SW1, and the output terminal of two group of three throw switch SW2 is connected with the 25 core aviation socket SI1, the 35 core aviation socket SI2, the 23 core aviation socket HV1, the 33 core aviation socket HV2 port respectively.
Window is screened sensor and is comprised the first magnetic induction switch K1, the second magnetic induction switch K2, magnet ring 3 and plug stainless-steel pipe.The first magnetic induction switch K1, is packaged in the plug stainless-steel pipe respectively at the second magnetic induction switch K2, respectively draw a signal wire respectively with the one 2 core aviation socket WS1 and the 22 core aviation socket WS2 welding.Magnet ring 3 sticks on the reducing light extracting tube wall outside surface of fluorescent probe Y4, and the first magnetic induction switch K1 is installed in the dog screw part of brightness detection window Y2, and the second magnetic induction switch K2 is installed in the dog screw part of twilight sunset detection window Y3.
Ten interfaces of from housing 1, drawing comprise: 4 core aviation socket AC220CZ, 6 core aviation socket RS232CZ, the one 2 core aviation socket WS1, the 22 core aviation socket WS2, the 25 core aviation socket, the 23 core aviation socket, the 35 core aviation socket, the 33 core aviation socket, the one 5 core aviation socket SI0, the one 3 core aviation socket HV0.4 core aviation socket AC220CZ, 6 core aviation socket RS232CZ are connected with computing machine Y1 through cable; The 25 core aviation socket SI1, the 23 core aviation socket HV1 are connected with brightness detection instrument Y5 through cable; The 35 core aviation socket SI2, the 33 core aviation socket HV2 are connected with twilight sunset detector Y6 through cable, and the one 5 core aviation socket SI0, the one 3 core aviation socket HV0 are connected with fluorescent probe Y4 with the second probe lead wire HV through the first probe lead wire SI respectively.
Be furnished with two group of three throw switch SW2, first LED 1, second LED 2, the 3rd LED 3, the 4th LED 4, the 5th LED 5, three group of two throw switch SW1, guidance panel 2 on the guidance panel 2.
Three group of two throw switch SW1 is used for being provided with switch mode; First group of connection+12V direct supply wherein; Second group connects the one 5 core aviation socket SI0, and the 3rd group connects the one 3 core aviation socket HV0, when three group of two throw switch SW1 throws in 1 retaining; Then direct supply is communicated with the relay common with the connection of program-controlled electronic switch U2 power end, the one 5 core aviation socket SI0 and the one 3 core aviation socket HV0, gets into automatic switchover mode; When three group of two throw switch SW1 throws in 2 retainings, then direct supply and program-controlled electronic switch U2 power end break off, and the one 5 core aviation socket SI0 and the one 3 core aviation socket HV0 are communicated with two group of three throw switch SW2 common, entering manual switchover pattern.
Two group of three throw switch SW2 is used for manual switchover, throws 1 retaining, and then the one 5 core aviation socket SI0 and the one 3 core aviation socket HV0 are communicated with the 25 core aviation socket SI1 and the 23 core aviation socket HV1, carry out brightness measurement; Throw 2 retainings, then the one 5 core aviation socket SI0 and the one 3 core aviation socket HV0 are unsettled, do not measure; Throw 3 retainings, then the one 5 core aviation socket SI0 and the one 3 core aviation socket HV0 are communicated with the 35 core aviation socket SI2 and the 33 core aviation socket HV2, carry out afterglow measurement.
The selection of automatic mode, manual mode: it then is automatic mode that three group of two throw switch SW1 upwards dials, and the 4th LED 4 is bright; Three group of two throw switch SW1 then is manual mode to setting aside, and the 5th LED 5 is bright.
After using the present invention, the operating process that test macro switches under " automatically " pattern is following:
The 1st step, fluorescent probe Y4 is taken out from sunset glow measurement window Y3, first LED, 1 pilot lamp is bright, represent vacantly, inserts brightness measurement window Y2, and then second LED, 2 pilot lamp are bright, represent sensed luminance.
The 2nd step started the luminance test program, gathered brightness data,
The 3rd step, fluorescent probe Y4 is taken out from brightness measurement window Y2, first LED, 1 pilot lamp is bright, represent vacantly, inserts sunset glow measurement window Y3, and then the 3rd LED 3 pilot lamp are bright, expression detection sunset glow.
The 4th step, startup sunset glow test procedure are gathered the sunset glow data
Turned back to for the 1st step, measure next sample.
After using the present invention, the operating process that test macro switches under " manually " pattern is following:
The 1st goes on foot, fluorescent probe Y4 is taken out from sunset glow measurement window Y3, inserts brightness measurement window Y2, change-over switch SW2 is pushed " vacant " from " sunset glow " push " brightness " retaining again.
The 2nd step started the luminance test program, gathered brightness data,
The 3rd goes on foot, fluorescent probe Y4 is taken out from brightness measurement window Y2, inserts sunset glow measurement window Y3, change-over switch is pushed " vacant " from " brightness " push " sunset glow " retaining again.
The 4th step, startup sunset glow test procedure are gathered the sunset glow data
Turned back to for the 1st step, measure next sample.
Claims (4)
1. channel automatic switching control equipment that is used for PDP vacuum uv phosphor test macro; It is characterized in that: comprise housing (1), guidance panel (2), window examination sensor, DC power supplier, main control board, and corresponding aviation socket, plug and cable; DC power supplier, main control board, and corresponding aviation socket is arranged in the housing (1), and be connected with other instruments with plug, cable; Described window is screened sensor and is comprised first magnetic induction switch (K1), second magnetic induction switch (K2), magnet ring (3) and plug stainless-steel pipe; First magnetic induction switch (K1), second magnetic induction switch (K2) is packaged in respectively in the plug stainless-steel pipe, respectively draws a signal wire and is connected with the 22 core aviation socket (WS2) with the one 2 core aviation socket (WS1) respectively; Magnet ring (3) sticks on the reducing light extracting tube wall outside surface of fluorescent probe (Y4); First magnetic induction switch (K1) is installed in the dog screw part of brightness detection window (Y2), and second magnetic induction switch (K2) is installed in the dog screw part of twilight sunset detection window (Y3).
2. a kind of channel automatic switching control equipment that is used for PDP vacuum uv phosphor test macro according to claim 1; It is characterized in that: in the described main control board, the program-controlled electronic switch (U2) that comprises main control unit (U1) that C51 series monolithic and MAX232 interface chip form, forms with DC12V relay and ULN2004 chip, with switch power module form+12V/+5V direct supply (U3), the one 3 core aviation socket (HV0), the 23 core aviation socket (HV1), the 33 core aviation socket (HV2), the one 5 core aviation socket (SI0), the 25 core aviation socket (SI1), the 35 core aviation socket (SI2), the one 2 core aviation socket (WS1), the 22 core aviation socket (WS2), 4 core aviation sockets (AC220CZ), 6 core aviation sockets (RS232CZ), three group of two throw switch (SW1), two group of three throw switch (SW2), first magnetic induction switch (K1), second magnetic induction switch (K2), first light emitting diode (LED1), second light emitting diode (LED2), the 3rd light emitting diode (LED3), the 4th light emitting diode (LED4), the 5th light emitting diode (LED5); Two group of three throw switch (SW2), first light emitting diode (LED1), second light emitting diode (LED2), the 3rd light emitting diode (LED3), the 4th light emitting diode (LED4), the 5th light emitting diode (LED5), three group of two throw switch (SW1) are welded on the main control board front, and all aviation sockets all are welded on the main control board reverse side; First group of three group of two throw switch (SW1) connects direct supply (U3), and second group connects the one 5 core aviation socket (SI0), and the 3rd group connects the one 3 core aviation socket (HV0); The common port of two group of three throw switch (SW2) is connected with the output terminal of three group of two throw switch (SW1), and the output terminal of two group of three throw switch (SW2) is connected with the 25 core aviation socket (SI1), the 35 core aviation socket (SI2), the 23 core aviation socket (HV1), the 33 core aviation socket (HV2) port respectively.
3. a kind of channel automatic switching control equipment that is used for PDP vacuum uv phosphor test macro according to claim 1 and 2 is characterized in that: ten interfaces of drawing in the described housing (1) comprise: 4 core aviation sockets (AC220CZ), 6 core aviation sockets (RS232CZ), the one 2 core aviation socket (WS1), the 22 core aviation socket (WS2), the 25 core aviation socket (SI1), the 23 core aviation socket (HV1), the 35 core aviation socket (SI2), the 33 core aviation socket (HV2), the one 5 core aviation socket (SI0), the one 3 core aviation socket (HV0); 4 core aviation sockets (AC220CZ), 6 core aviation sockets (RS232CZ) are connected with computing machine (Y1) through cable; The 25 core aviation socket (SI1), the 23 core aviation socket (HV1) are connected with brightness detection instrument (Y5) through cable; The 35 core aviation socket (SI2), the 33 core aviation socket (HV2) are connected with twilight sunset detector (Y6) through cable, and the one 5 core aviation socket (SI0), the one 3 core aviation socket (HV0) are connected with fluorescent probe (Y4) with second probe lead wire (HV) through first probe lead wire (SI) respectively.
4. a kind of channel automatic switching control equipment that is used for PDP vacuum uv phosphor test macro according to claim 3 is characterized in that: be furnished with two group of three throw switch (SW2), first light emitting diode (LED1), second light emitting diode (LED2), the 3rd light emitting diode (LED3), the 4th light emitting diode (LED4), the 5th light emitting diode (LED5), three group of two throw switch (SW1) on the described guidance panel (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010560925A CN102095570B (en) | 2010-11-25 | 2010-11-25 | Automatic channel switching device for PDP (plasma display panel) vacuum ultraviolet fluorescent powder testing system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010560925A CN102095570B (en) | 2010-11-25 | 2010-11-25 | Automatic channel switching device for PDP (plasma display panel) vacuum ultraviolet fluorescent powder testing system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102095570A CN102095570A (en) | 2011-06-15 |
| CN102095570B true CN102095570B (en) | 2012-09-05 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201010560925A Expired - Fee Related CN102095570B (en) | 2010-11-25 | 2010-11-25 | Automatic channel switching device for PDP (plasma display panel) vacuum ultraviolet fluorescent powder testing system |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| JP5284454B2 (en) * | 2011-12-27 | 2013-09-11 | 株式会社東芝 | Transmission device, reception device, and communication path switching method |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1812535A (en) * | 2005-12-28 | 2006-08-02 | 海信集团有限公司 | Automatic switching method for signal source channel of video frequency display equipment |
| CN101309354A (en) * | 2008-06-24 | 2008-11-19 | 四川长虹电器股份有限公司 | Channel automatic switch system and method of display equipment signal source |
| CN101500286A (en) * | 2008-01-28 | 2009-08-05 | 华为技术有限公司 | Switching method, mobile terminal and network appliance |
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- 2010-11-25 CN CN201010560925A patent/CN102095570B/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1812535A (en) * | 2005-12-28 | 2006-08-02 | 海信集团有限公司 | Automatic switching method for signal source channel of video frequency display equipment |
| CN101500286A (en) * | 2008-01-28 | 2009-08-05 | 华为技术有限公司 | Switching method, mobile terminal and network appliance |
| CN101309354A (en) * | 2008-06-24 | 2008-11-19 | 四川长虹电器股份有限公司 | Channel automatic switch system and method of display equipment signal source |
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