CN102270869B - Automatic control equipment for charging and discharging of aviation storage battery - Google Patents
Automatic control equipment for charging and discharging of aviation storage battery Download PDFInfo
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- CN102270869B CN102270869B CN201110210515.0A CN201110210515A CN102270869B CN 102270869 B CN102270869 B CN 102270869B CN 201110210515 A CN201110210515 A CN 201110210515A CN 102270869 B CN102270869 B CN 102270869B
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Abstract
The invention discloses automatic control equipment for the charging and discharging of an aviation storage battery and belongs to the field of automatic control equipment. The automatic control equipment disclosed by the invention is composed of a charging device, a constant current controller, a device, a displayer and a wiring rack, wherein a discharging controller controls a pulse width adjuster to output pulse signals with variable duty ratio and is used for adjusting a high-power dual-gate transistor to maintain the constant discharging current. The discharging voltage, the discharging time and a voltage-time curve are monitored by a computer in real time by inputting the acquisition data of an acquisition card into the computer through an RS485 bus. The automatic control equipment disclosed by the invention can automatically record the voltage and discharging time of the storage battery and is provided with a window for displaying the voltage-time curve. After the discharging is completed, the curve can be printed out. The automatic control equipment disclosed by the invention can be used for realizing the automatic control of the constant-current discharging, automatically stopping the discharging and warning when reaching discharging completion conditions, and is safe and reliable.
Description
Technical field
The invention belongs to the control appliance scope of accumulator cell charging and discharging, particularly a kind of automatic control equipment discharging and recharging for aircraft battery.
Background technology
Battery charging and discharging is in the highly developed current era of modern electronic technology, incorporated in everyone life, the large storage battery to Aeronautics and Astronautics equipment, little and personal mobile phone battery, battery quality quality or life-span length with discharge and recharge control technology and have direct relation, usually because overcharge, excessively put, battery can not normally be used, the most simply electric discharge is with a fixing load discharge at present; Or by manual monitoring, carrying out constant-current discharge with tunable load, this just requires necessary Attended mode when storage battery is carried out to capacity check, adjusts at any time load and could keep discharging current constant.
Summary of the invention
The object of the invention is to propose a kind of automatic control equipment discharging and recharging for aircraft battery, it is characterized in that, the automatic control equipment that aircraft battery discharges and recharges consists of charging device 1, constant-current controller 2, discharge control device 3, display 4 and patch bay 5; Charging device 1 is connected with the C2 interface of the discharge controller of discharge control device 3 by discharging and recharging change over switch, and the charging output cathode of charging device 1 and the electric discharge of constant-current controller 2 input negative pole link together; The C3 interface of the discharge controller of discharge control device 3 is connected with display 4 with the grid of constant-current controller 2, high-power double-gated transistor M respectively; The joint that inputs or outputs of each part mentioned above is connected with address bus 6 by patch bay 5; Then through RS485 bus, be communicated with computer, discharge voltage, discharge time and volt-time curve are inputted computer by capture card image data through RS485 bus, by real-time monitoring of computer.
24V power supply in described charging device 1 connects respectively start button, starting relay J1, timer and discharge and recharge change over switch; Timer is connected with charger output switch by electrotimer J15, discharging and recharging change over switch is connected with alarm relay J13 by starting relay J1 respectively, alarm relay J13 connects signal alarm bell and alarm reset button, when stopping discharging, alarm is triggered, stand by lamp is bright, alarm bell ring, at this moment by manual reset.
The input of described charger connects separately the 220V AC power supplies of 10A.
Described timer and 24V power supply are connected to the 220V AC power supplies of 2A jointly, and before 2A fuse F1 and connect red led, after 2A fuse F1 and connect electric discharge fan swicth, on electric discharge fan swicth and connect green indicating lamp, fan, 12V voltage changer and ac joint.
Described starting relay J1 connects respectively start button and indicator light and stop button and indicator light.
In described discharge control device 3, the C2 interface of discharge controller is connected to and discharges and recharges change over switch discharge end and electric discharge cooling fan relay J12; The C3 interface of discharge controller is connected to normally opened contact one end of respectively shift gears in the grid, constant-current controller 2 of high-power double-gated transistor M relay J 3, J5, J7J9, J11 and regulating relay J14; The source electrode of high-power double-gated transistor M; The C4 interface of discharge controller is connected to address bus 6 by D/O reference address 1; The C1 interface of discharge controller meets discharging current adjusting knob WR1; The C5 interface of discharge controller meets alarm relay J13.
The drain electrode of described high-power double-gated transistor M is connected with normally opened contact one end of the relay J of gearshift 2, relay J 4, relay J 6, relay J 8 and relay J 10; Normally opened contact one end of relay J 3, relay J 5, relay J 7, relay J 9, relay J 11 and the regulating relay J14 of gearshift is connected with the source electrode of high-power double-gated transistor M; The normally opened contact other end of the relay J 2-J11 of gearshift connects corresponding gear load resistance; Another termination constant flow regulation load resistance of the normally opened contact of regulating relay J14 WR2; And relay J 2, relay J 3, relay J 4, relay J 5, normally-closed contact one end of relay J 6, relay J 7, relay J 8, relay J 9, relay J 10, relay J 11 and regulating relay J14 connects rear ground connection; The normally-closed contact other end of regulating relay J14 connects constant current indicator light; Relay J 2 also connects respectively a gearshift indicator light after being connected separately with relay J 9, relay J 10 and the other end of the normally-closed contact of relay J 11 with relay J 7, relay J 8 with relay J 3, relay J 6; The relay J 4 normally-closed contact other ends connect shift gears indicator light and diode D1 positive pole, and diode D1 negative pole connects the normally-closed contact other end of diode D2 negative pole and relay J 5; Diode D2 positive pole is connected to the relay J 2 normally-closed contact other ends.
Described display 4 comprises liquid crystal voltage table and liquid crystal ammeter, and liquid crystal voltage table connects respectively electric discharge and inputs on the common port of anodal and each gear load resistance, ground connection and power supply termination electric discharge fan swicth and connect green indicating lamp and ac power connection; Liquid crystal ammeter connects respectively on the C3 interface, ground connection of discharge controller and power supply termination electric discharge fan swicth and connects green indicating lamp and ac power connection.
Described patch bay 5 one end are connected with common port and the constant-current controller 2 electric discharge input positive poles of each gear load resistance, the other end is connected with charger output negative pole through the 220V AC power supplies of the 220V of RS485 bus, 2A AC power supplies, 10A, and is connected with A/D1 reference address 1, A/D2 reference address 2 and A/D3 reference address 3; A/D1 reference address 1, A/D2 reference address 2 and A/D3 reference address 3 are connected to address bus.
The invention has the beneficial effects as follows that the constant current charge-discharge equipment that provides is realized controls constant-current discharge automatically, reach while discharge condition and automatically stop discharging and reporting to the police, and when discharging, record discharge curve, discharge time, battery voltage while stopping discharging; Realized the automatic control of implementing electric discharge, do not needed manual monitoring, improved work efficiency: guarantee not can because of personnel leave or other reason by storage battery over-discharge can, safe and reliable.
Accompanying drawing explanation
Fig. 1 is accumulator cell charging and discharging automatic control equipment circuit theory diagrams.
Fig. 2 is discharge controller circuit theory diagrams.
Embodiment
The present invention proposes a kind of automatic control equipment discharging and recharging for aircraft battery.Below in conjunction with accompanying drawing, the present invention is explained.
In Fig. 1, shown in accumulator cell charging and discharging automatic control equipment by charging device 1, constant-current controller 2, discharge control device 3, display 4 and patch bay 5, formed; Charging device 1 is connected with the C2 interface of the discharge controller of discharge control device 3 by discharging and recharging change over switch, and the charging output cathode of charging device 1 and the electric discharge of constant-current controller 2 input negative pole link together; The C3 interface of the discharge controller of discharge control device 3 is connected with display 4 with the grid of constant-current controller 2, high-power double-gated transistor M respectively; The drain electrode of described high-power double-gated transistor M is connected with normally opened contact one end of the relay J of gearshift 2, relay J 4, relay J 6, relay J 8 and relay J 10; Normally opened contact one end of relay J 3, relay J 5, relay J 7, relay J 9, relay J 11 and the regulating relay J14 of gearshift is connected with the source electrode of high-power double-gated transistor M; The normally opened contact other end of the relay J 2-J11 of gearshift connects corresponding gear load resistance; Another termination constant flow regulation load resistance of the normally opened contact of regulating relay J14 WR2; And relay J 2, relay J 3, relay J 4, relay J 5, normally-closed contact one end of relay J 6, relay J 7, relay J 8, relay J 9, relay J 10, relay J 11 and regulating relay J14 connects rear ground connection; The normally-closed contact other end of regulating relay J14 connects constant current indicator light; Relay J 2 also connects respectively a gearshift indicator light after being connected separately with relay J 9, relay J 10 and the other end of the normally-closed contact of relay J 11 with relay J 7, relay J 8 with relay J 3, relay J 6; The relay J 4 normally-closed contact other ends connect shift gears indicator light and diode D1 positive pole, and diode D1 negative pole connects the normally-closed contact other end of diode D2 negative pole and relay J 5; Diode D2 positive pole is connected to the relay J 2 normally-closed contact other ends.
The joint that inputs or outputs of each part mentioned above is connected with address bus 6 by patch bay 5 one end.Described patch bay 5 one end are connected with common port and the constant-current controller 2 electric discharge input positive poles of each gear load resistance, the other end is connected with charger output negative pole through the 220V AC power supplies of the 220V of RS485 bus, 2A AC power supplies, 10A, and is connected with A/D1 reference address 1, A/D2 reference address 2 and A/D3 reference address 3; A/D1 reference address 1, A/D2 reference address 2 and A/D3 reference address 3 are connected to address bus.
Described charger adopts bridge rectifier charging (model KCG2-30A/E40V), by the 0-24h Timer Controlling charging interval, prevents from overcharging.
In described constant-current controller 2 with one group of resistance wire as dead load, when implementing electric discharge, each gear load resistance is as dead load, respectively shift gears in the constant-current controller 2 normally opened contact access of relay J 2-J11, normally opened contact by regulating relay J14 accesses one group of resistance wire as variable load, by the discharging current adjusting knob WR1 tune of discharge controller (as shown in Figure 2) in discharge control device 3
Joint discharging current, regulate discharging current signal to be gathered by proportional amplifier (being formed by two OP07 in Fig. 2), through proportional amplifier, be input to pulse-width modulator (TL494 module in Fig. 2), control the variable pulse signal of pulse-width modulator output duty cycle, through the C3 interface of discharge controller, input to the grid of high-power double-gated transistor M, be used for regulating high-power double-gated transistor M to keep discharging current constant.The C4 interface of the pulse signal process discharge controller that pulse-width modulator output duty cycle is variable is connected to address bus 6 by D/O reference address 1, through inputting computer through RS485 bus, after machine system stability to be calculated (approximately 5 minutes), double-click " battery discharging curve " icon, selection is discharged the piece number of battery, enters the test page of this piece number.Click " start/stop " button, enter discharge condition, corresponding indicator light should ignite (corresponding with the discharging current of this piece number).When discharge voltage is during at 24V, write down current value, discharging current adjusting knob WR1 regulates discharging current to stop when electric current also starts to increase not the position of increase through proportional amplifier in Fig. 2; When cell voltage is less than 24V, discharging current starts to decline.At this moment, constant-current controller 2 auto-compensations, when not reaching best constant current, can mend constant current value by manual adjustment discharging current adjusting knob WR1 or WR2.When stopping discharging, alarm is triggered, and stand by lamp is bright, alarm bell ring.At this moment can be by manual reset.
Above-mentioned discharge voltage, electric current, discharge time etc., discharge voltage, discharge time and volt-time curve were also by real-time monitoring of computer and demonstration except the display 4 by comprising liquid crystal voltage table and liquid crystal ammeter shows; Automatically record battery voltage and discharge time, and have the window that shows volt-time curve, also can be by curve printing out after having discharged.
Claims (9)
1. the automatic control equipment discharging and recharging for aircraft battery, is characterized in that, battery charging and discharging automatic control equipment consists of charging device (1), constant-current controller (2), discharge control device (3), display (4) and patch bay (5); Charging device (1) is connected with the C2 interface of the discharge controller of discharge control device (3) by discharging and recharging change over switch, and the electric discharge input negative pole of the charging output cathode of charging device (1) and constant-current controller (2) links together; The C3 interface of the discharge controller of discharge control device (3) is connected with display (4) with the grid of constant-current controller (2), high-power double-gated transistor M respectively; The joint that inputs or outputs of each part mentioned above is connected with address bus (6) by patch bay (5); Then through RS485 bus, be communicated with computer, discharge voltage, discharge time and volt-time curve are inputted computer by capture card image data through RS485 bus, by real-time monitoring of computer.
2. the automatic control equipment discharging and recharging for aircraft battery according to claim 1, is characterized in that, the 24V power supply in described charging device (1) connects respectively start button, starting relay J1, timer and discharge and recharge change over switch; Timer is connected with charger output switch by electrotimer J15, discharging and recharging change over switch is connected with alarm relay J13 by starting relay J1 respectively, alarm relay J13 connects signal alarm bell and alarm reset button, when stopping discharging, alarm is triggered, stand by lamp is bright, alarm bell ring, at this moment by manual reset.
3. the automatic control equipment discharging and recharging for aircraft battery according to claim 2, is characterized in that, the input of described charger connects separately the 220V AC power supplies of 10A.
4. the automatic control equipment discharging and recharging for aircraft battery according to claim 1, it is characterized in that, described display (4) comprises liquid crystal voltage table and liquid crystal ammeter, and liquid crystal voltage table connects respectively electric discharge input positive pole, the common port of each gear load resistance, ground connection; On its power supply termination electric discharge fan swicth and the green indicating lamp and the ac power connection that connect; Liquid crystal ammeter connects respectively C3 interface, the ground connection of discharge controller, and on power supply termination electric discharge fan swicth and the green indicating lamp and the ac power connection that connect.
5. the automatic control equipment discharging and recharging for aircraft battery according to claim 2, it is characterized in that, described timer and 24V power supply are connected to the 220V AC power supplies of 2A jointly, and before 2A fuse F1 and connect red led, after 2A fuse F1 and connect electric discharge fan swicth, on electric discharge fan swicth and connect green indicating lamp, fan and 12V voltage changer.
6. the automatic control equipment discharging and recharging for aircraft battery according to claim 2, is characterized in that, described starting relay J1 connects respectively start button and indicator light and stop button and indicator light.
7. the automatic control equipment discharging and recharging for aircraft battery according to claim 1, is characterized in that, in described discharge control device (3), the C2 interface of discharge controller is connected to and discharges and recharges change over switch discharge end and electric discharge cooling fan relay J12; The C3 interface of discharge controller is connected to normally opened contact one end of respectively shift gears in the grid, constant-current controller (2) of high-power double-gated transistor M relay J 3, J5, J7, J9, J11 and regulating relay J14; The source electrode of high-power double-gated transistor M; The C4 interface of discharge controller is connected to address bus (6) by D/O reference address 1; The C1 interface of discharge controller meets discharging current adjusting knob WR1; The C5 interface of discharge controller meets alarm relay J13.
8. the automatic control equipment discharging and recharging for aircraft battery according to claim 7, it is characterized in that, the drain electrode of described high-power double-gated transistor M is connected with normally opened contact one end of the relay J of gearshift 2, relay J 4, relay J 6, relay J 8 and relay J 10; Normally opened contact one end of relay J 3, relay J 5, relay J 7, relay J 9, relay J 11 and the regulating relay J14 of gearshift is connected with the source electrode of high-power double-gated transistor M, and the normally opened contact other end of the relay J 2-J11 of gearshift connects corresponding gear load resistance; Another termination constant flow regulation load resistance of the normally opened contact of regulating relay J14 WR2; And relay J 2, relay J 3, relay J 4, relay J 5, normally-closed contact one end of relay J 6, relay J 7, relay J 8, relay J 9, relay J 10, relay J 11 and regulating relay J14 connects rear ground connection; The normally-closed contact other end of regulating relay J14 connects constant current indicator light; Relay J 2 also connects respectively a gearshift indicator light after being connected separately with relay J 9, relay J 10 and the other end of the normally-closed contact of relay J 11 with relay J 7, relay J 8 with relay J 3, relay J 6; The relay J 4 normally-closed contact other ends connect shift gears indicator light and diode D1 positive pole, and diode D1 negative pole connects the normally-closed contact other end of diode D2 negative pole and relay J 5; Diode D2 positive pole is connected to the relay J 2 normally-closed contact other ends.
9. the automatic control equipment discharging and recharging for aircraft battery according to claim 4, it is characterized in that, described patch bay (5) one end is connected with common port and constant-current controller (2) the electric discharge input positive pole of each gear load resistance, the other end is connected with charger output negative pole through the 220V AC power supplies of the 220V of RS485 bus, 2A AC power supplies, 10A, and is connected with A/D1 reference address 1, A/D2 reference address 2 and A/D3 reference address 3; A/D1 reference address 1, A/D2 reference address 2 and A/D3 reference address 3 are connected to address bus.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110210515.0A CN102270869B (en) | 2011-07-26 | 2011-07-26 | Automatic control equipment for charging and discharging of aviation storage battery |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110210515.0A CN102270869B (en) | 2011-07-26 | 2011-07-26 | Automatic control equipment for charging and discharging of aviation storage battery |
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| Publication Number | Publication Date |
|---|---|
| CN102270869A CN102270869A (en) | 2011-12-07 |
| CN102270869B true CN102270869B (en) | 2014-05-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201110210515.0A Expired - Fee Related CN102270869B (en) | 2011-07-26 | 2011-07-26 | Automatic control equipment for charging and discharging of aviation storage battery |
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| CN109382498A (en) * | 2017-08-07 | 2019-02-26 | 科华控股股份有限公司 | Suction pouring inhales the pneumatic and electric control loop of casting room |
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2011
- 2011-07-26 CN CN201110210515.0A patent/CN102270869B/en not_active Expired - Fee Related
Patent Citations (6)
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| JP3683753B2 (en) * | 1999-10-01 | 2005-08-17 | 日本電信電話株式会社 | Secondary battery automatic test method |
| CN101697376A (en) * | 2009-09-30 | 2010-04-21 | 徐玉凤 | Method and special device for comprehensive control of storage battery pack |
| CN201754511U (en) * | 2010-01-26 | 2011-03-02 | 苏州市职业大学 | Solar photovoltaic storage battery charging and discharging protective controller |
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| CN102270869A (en) | 2011-12-07 |
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Owner name: BEIJING FENGRONG AVIATION TECHNOLOGY CO., LTD. Free format text: FORMER NAME: FENGRONG AVIATION SCIENCE TECHNOLOGY (BEIJING) CO., LTD. |
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| CP01 | Change in the name or title of a patent holder |
Address after: 101300 Shunyi District Shunyi color Garden Industrial Zone Beijing Beijing Rong Rong Aviation Technology Co., Ltd. Patentee after: BEIJING FENGRONG AVIATION TECHNOLOGY CO., LTD. Address before: 101300 Shunyi District Shunyi color Garden Industrial Zone Beijing Beijing Rong Rong Aviation Technology Co., Ltd. Patentee before: Fengrong Aviation Science Technology (Beijing) Co., Ltd. |
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Granted publication date: 20140507 Termination date: 20200726 |