CN104882931A - Aviation power supply battery management system and method - Google Patents

Abstract

An aviation power supply battery management system and a method are disclosed. The system comprises a main control unit, monitoring subunits and an upper computer. The main control unit comprises a main controller module, a charging and discharging voltage measurement module, a charging and discharging current measurement module, an over-voltage and over-current protection module, an A/D conversion module, a contactor module, an air pressure acquisition module and an isoSPI conversion module. There are many monitoring subunits. Each monitoring subunit comprises a daughter board control module and a temperature measurement module. The charging and discharging voltage measurement module collects a charging and discharging total voltage. The charging and discharging current measurement module collects a charging and discharging total current. The air pressure acquisition module collects an outside atmospheric pressure value in real time. Each temperature measurement module measures each temperature value of a single battery pack. Each daughter board control module collects a monomer battery voltage value of the corresponding single battery pack. The controller module realizes overvoltage and over-current protection according to a collected signal and estimates a SOC value and a SOH value of an aviation power supply battery. The daughter board control module carries out energy equalization control on the single battery.

Description

Airplane power source battery management system and method thereof

Technical field

The invention belongs to technical field of battery management, be specifically related to airplane power source battery management system and method thereof.

Background technology

Along with the development of aerospace industry, its airborne power consumption equipment is increasing, being designed in order to key of airplane power source battery management system.Airplane power source battery management system is not only function system, is also important safe-guard system.Due to the development of electric aircraft, the importance of airplane power source battery system also will rise to a new height.A good power-supply battery management system not only will detect the electric current and voltage of battery pack, and the estimation of battery charge state and health status, the charge and discharge balancing problem of battery also becomes the important and difficult issues of research.

At present, on market, the power-supply battery management system of main flow has had qualitative leap than analog electrical minor battery management system, but still have all deficiencies, such as: the accuracy of measurement and real-time need to improve, the data type measured is perfect not, need to be connected with host computer interface, realize battery management system visual.

Summary of the invention

For the deficiencies in the prior art, the present invention proposes airplane power source battery management system and method thereof.

Technical solution of the present invention is as follows:

Airplane power source battery management system, comprises main control unit, monitoring subelement and host computer;

Described main control unit, comprises main controller module, charging/discharging voltage measurement module, charging and discharging currents measurement module, over-voltage over-current protection module, A/D modular converter, contact modules, air pressure acquisition module and isoSPI modular converter;

Described monitoring subelement has multiple, and each monitoring subelement includes daughter board control module and temperature-measuring module;

The input of described charging/discharging voltage measurement module connects the integral battery door group two ends of airplane power source, the input of charging and discharging currents measurement module connects the load of the integral battery door group of airplane power source, the output of charging/discharging voltage measurement module is connected the input of A/D modular converter with the output of charging and discharging currents measurement module, the output of A/D modular converter connects the first input end of main controller module by iic bus; The output of described air pressure acquisition module connects the second input of main controller module by iic bus; First output of described main controller module connects the input of over-voltage over-current protection module, and the output of over-voltage over-current protection module connects the input of contact modules, and the output of contact modules connects the integral battery door group of airplane power source; Described main controller module connects host computer by CAN; The output of described each temperature-measuring module connects the first input end of corresponding daughter board control module respectively, and the second input of each daughter board control module connects corresponding monocell group two ends; Described each daughter board control module connects isoSPI modular converter by spi bus, and isoSPI modular converter connects main controller module by spi bus.

This system also comprises power subsystem, and the input of power subsystem connects the integral battery door group of airplane power source, and the output of power subsystem connects the power end of main controller module;

Described power subsystem, adopts voltage isolating converter, for being each module of main control unit and each module required voltage of monitoring subelement, is each module of main control unit and each module for power supply of monitoring subelement by the voltage transitions of airplane power source battery.

Main controller module, adopt single-chip microcomputer, carry out voltage, current detecting for the charging total current value of the electric discharge total voltage value of the charging total voltage value of integral battery door group according to the airplane power source gathered, integral battery door group, integral battery door group, the electric discharge total current value of integral battery door group and the monomer battery voltage value of monocell group, and send a control signal to over-voltage over-current protection module; Calculate the voltage deviation of the cell of monocell group according to the magnitude of voltage of the cell of monocell group, and send a control signal to daughter board control module; SOC value and the estimation of airplane power source battery SOH value of airplane power source battery is carried out according to the electric discharge total voltage of the charging total voltage of the integral battery door group of the airplane power source of Real-time Collection, integral battery door group, the charging total current of integral battery door group, the electric discharge total current of integral battery door group and integral battery door group temperature value; The magnitude of voltage of cell of the temperature value of the external atmosphere pressure force value of the electric discharge total current value of the charging total current value of the electric discharge total voltage value of the charging total voltage value of the integral battery door group of airplane power source, integral battery door group, integral battery door group, integral battery door group, integral battery door group, each monocell group, monocell group, the SOC value of airplane power source and airplane power source battery SOH value are sent to host computer;

Described charging/discharging voltage measurement module, for the electric discharge total voltage of the charging total voltage and integral battery door group that gather the integral battery door group of airplane power source, and is sent to A/D modular converter; Charging/discharging voltage measurement module, comprises discharge voltage measuring circuit and charging voltage measuring circuit;

Described discharge voltage measuring circuit comprises the first operational amplifier, the first isolator and the second operational amplifier; The input of the first described operational amplifier connects the integral battery door group two ends of airplane power source, the output of the first operational amplifier connects the input of the first isolator, the output of the first isolator connects the input of the second operational amplifier, and the output of the second operational amplifier connects the input of A/D modular converter;

Described charging voltage measuring circuit comprises the 3rd operational amplifier, the second isolator and four-operational amplifier; The input of the 3rd described operational amplifier connects the integral battery door group two ends of airplane power source, the output of the 3rd operational amplifier connects the input of the second isolator, the output of the second isolator connects the input of four-operational amplifier, and the output of four-operational amplifier connects the input of A/D modular converter.

Described charging and discharging currents measurement module, for the electric discharge total current of the charging total current and integral battery door group that gather the integral battery door group of airplane power source, and is sent to A/D modular converter; Charging and discharging currents measurement module, comprises discharge current measuring circuit and charging current measuring circuit;

Described discharge current measuring circuit comprises the 5th operational amplifier and the 6th operational amplifier; The input of the 5th described operational amplifier connects the integral battery door group load of airplane power source, and the output of the 5th operational amplifier connects the input of the 6th operational amplifier, and the output of the 6th operational amplifier connects the input of A/D modular converter;

Described charging current measuring circuit comprises the 7th operational amplifier and the 8th operational amplifier; The input of the 7th described operational amplifier connects the integral battery door group load of airplane power source, and the output of the 7th operational amplifier connects the input of the 8th operational amplifier, and the output of the 8th operational amplifier connects the input of A/D modular converter.

Described A/D modular converter, adopt A/D converter, carry out analog-to-digital conversion for the charging total voltage of the integral battery door group of the airplane power source by collection, total voltage of discharging, charging total current and electric discharge total current, and the charging total voltage value of the integral battery door group of the airplane power source of conversion, electric discharge total voltage value, charging total current value and total current value of discharging are sent to main controller module by iic bus;

Described over-voltage over-current protection module, for the control signal according to reception main controller module, when overvoltage, overcurrent appear in the integral battery door group of airplane power source or the cell of monocell group, the break-make of control contactor module, realizes over-voltage over-current protection; Over-voltage over-current protection module, comprises photoelectrical coupler, the first triode and the second triode;

The input of described photoelectrical coupler connects the first output of main controller module, and the first output of photoelectrical coupler connects the input of the first triode, and the second output of photoelectrical coupler connects the input of the second triode; The output of the first triode is connected the input of contact modules respectively with the output of the second triode.

Described air pressure acquisition module, adopting baroceptor, for gathering the external atmosphere pressure force value of the integral battery door group of airplane power source, and being sent to main controller module;

Described isoSPI modular converter, for the mutual conversion of the standard SPI of the standard SPI and two-wire system that realize four-wire system, realizes the communication between main controller module and multiple daughter board control module; IsoSPI modular converter, comprises the isolated communication interface of isoSPI and Ethernet isolating transformer;

The input of the isolated communication interface of described isoSPI connects main controller module by spi bus, the output of the isolated communication interface of isoSPI connects the input of isolating transformer, and the output of isolating transformer connects each daughter board control module by spi bus.

Described daughter board control module, adopt battery pack monitor, for gathering the monomer battery voltage value of the monocell group of airplane power source, the temperature value of the monomer battery voltage value of the monocell group of airplane power source and the monocell group of airplane power source is sent to main controller module; According to main controller module control signal, balancing energy control is carried out to the cell of monocell group;

Described temperature-measuring module, adopting thermistor, for gathering the temperature value of the monocell group of airplane power source, and being sent to daughter board control module;

Described contact modules, for the break-make of the break-make and airplane power source battery and load that control airplane power source battery and battery charger; Contact modules, comprises two D.C. contactors: charging D.C. contactor and electric discharge D.C. contactor;

The input of described charging D.C. contactor is connected the output of over-voltage over-current protection module with the input of electric discharge D.C. contactor; the output of charging D.C. contactor connects the battery charger of airplane power source battery, and the output of electric discharge D.C. contactor connects the load of airplane power source battery.

Described host computer, for showing the charging total voltage value of the integral battery door group of airplane power source, the electric discharge total voltage value of integral battery door group, the charging total current value of integral battery door group, the electric discharge total current value of integral battery door group, the external atmosphere pressure force value of integral battery door group, the temperature value of each monocell group, the magnitude of voltage of the cell of monocell group, the SOC value of airplane power source battery and airplane power source battery SOH value.

Adopt airplane power source battery management system to carry out the method for airplane power source battery management, comprise the following steps:

Step 1: in airplane power source cell operations, the charging total voltage of the integral battery door group of charging/discharging voltage measurement module Real-time Collection airplane power source and electric discharge total voltage, charging and discharging currents measurement module gathers charging total current and the electric discharge total current of the integral battery door group of airplane power source, A/D modular converter is by the charging total voltage of integral battery door group, electric discharge total voltage, charging total current and electric discharge total current carry out analog-to-digital conversion, and by the charging total voltage value of the integral battery door group of the airplane power source of conversion, electric discharge total voltage value, charging total current value and electric discharge total current value are sent to main controller module,

Step 2: the external atmosphere pressure force value of the integral battery door group of air pressure acquisition module Real-time Collection airplane power source, and be sent to main controller module;

Step 3: each temperature-measuring module gathers the temperature value of each monocell group of airplane power source, and is sent to daughter board control module;

Step 4: each daughter board control module gathers the monomer battery voltage value of the monocell group of corresponding airplane power source, and the temperature value of the monomer battery voltage value of the monocell group of airplane power source and the monocell group of airplane power source is sent to main controller module;

Step 5: main controller module carries out voltage, current detecting according to the charging total current value of the electric discharge total voltage value of the charging total voltage value of integral battery door group of the airplane power source gathered, integral battery door group, integral battery door group, the electric discharge total current value of integral battery door group and the monomer battery voltage value of monocell group, and send a control signal to the break-make of over-voltage over-current protection module controls contact modules, realize the over-voltage over-current protection of airplane power source battery;

Step 5.1: the upper voltage limit threshold value of cell of setting monocell group, the lower voltage limit threshold value of the cell of monocell group, integral battery door group discharge and recharge total voltage upper limit threshold, integral battery door group discharge and recharge total voltage lower threshold, integral battery door group discharge and recharge total current upper limit threshold and integral battery door group discharge and recharge total current lower threshold;

Step 5.2: when the charging total voltage value of upper voltage limit threshold value or integral battery door group that the monomer battery voltage value of monocell group is greater than the cell of monocell group is greater than integral battery door group discharge and recharge total voltage upper limit threshold, main controller module sends a control signal to over-voltage over-current protection module, and control contactor module disconnects the battery charger of airplane power source battery;

Step 5.3: when the electric discharge total voltage value of lower voltage limit threshold value or integral battery door group that the monomer battery voltage value of monocell group is less than the cell of monocell group is less than integral battery door group discharge and recharge total voltage lower threshold, main controller module sends a control signal to over-voltage over-current protection module, and control contactor module disconnects the load of airplane power source battery;

Step 5.4: when the charging total current value of integral battery door group is greater than integral battery door group discharge and recharge total current upper limit threshold, main controller module sends a control signal to over-voltage over-current protection module, control contactor module disconnects the battery charger of airplane power source battery;

Step 5.5: when the electric discharge total current value of integral battery door group is less than integral battery door group discharge and recharge total current lower threshold, main controller module sends a control signal to over-voltage over-current protection module, control contactor module disconnects the load of airplane power source battery;

Step 6: main controller module calculates the voltage deviation of the cell of monocell group according to the magnitude of voltage of the cell of monocell group, send and control signal to daughter board control module, daughter board control module carries out balancing energy control to the cell of monocell group;

Step 6.1: the cell upper deviation threshold value of setting monocell group;

Step 6.2: when the voltage deviation of the cell of monocell group is greater than the cell upper deviation threshold value of monocell group, main controller module sends a control signal to daughter board control module, and the cell of daughter board control module to the excessive monocell group of voltage discharges;

Step 7: main controller module carries out SOC value and the estimation of airplane power source battery SOH value of airplane power source battery according to the electric discharge total voltage of the charging total voltage of the integral battery door group of the airplane power source of Real-time Collection, integral battery door group, the charging total current of integral battery door group, the electric discharge total current of integral battery door group and integral battery door group temperature value;

Step 7.1: adopt randles model to carry out modeling to airplane power source battery, obtain airplane power source battery randles model;

Step 7.2: using gather integral battery door group charging total voltage or electric discharge total voltage as discharge and recharge total voltage, using the charging total current of integral battery door group or electric discharge total current as discharge and recharge total current, by the temperature value of the mean value of the cell temperature value of monocell group battery pack as a whole;

Step 7.3: according to the randles model of airplane power source battery, adopt the method for EKF, utilize the temperature value of the discharge and recharge total voltage of the integral battery door group of the airplane power source of Real-time Collection, the discharge and recharge total current of integral battery door group and integral battery door group to estimate the SOC value of airplane power source battery and the SOH value of airplane power source battery;

Step 8: the SOH value of the external atmosphere pressure force value of the charging total current value of the charging total voltage value of integral battery door group of host computer display airplane power source, the electric discharge total voltage value of integral battery door group, integral battery door group, the electric discharge total current value of integral battery door group, integral battery door group, the temperature value of each monocell group, the magnitude of voltage of the cell of monocell group, the SOC value of airplane power source battery and airplane power source battery.

Beneficial effect of the present invention:

The present invention proposes airplane power source battery management system and method thereof, the monomer battery voltage of each monocell group of Measurement accuracy, airplane power source discharge and recharge total voltage, airplane power source discharge and recharge total current, the information such as the temperature of airplane power source battery and the air pressure of airplane power source battery, there is balanced monomer battery voltage simultaneously, control battery charging and discharging, the function that battery overcurrent-overvoltage controls.And adopt the lithium battery charge state (SOC) based on EKF (EKF) and health status (SOH) method of estimation, this airplane power source battery management system can be made accurately to grasp the operating state of lithium battery group, constitute that integrated level is high, perfect in shape and function, function admirable utility system.

Accompanying drawing explanation

Fig. 1 is the airplane power source battery management system structural representation of the specific embodiment of the invention;

Fig. 2 is the circuit diagram of the discharge voltage measuring circuit of the charging/discharging voltage measurement module of the specific embodiment of the invention;

Fig. 3 is the circuit diagram of the charging voltage measuring circuit of the charging/discharging voltage measurement module of the specific embodiment of the invention;

Fig. 4 is the circuit diagram of the discharge current measuring circuit of the charging and discharging currents measurement module of the specific embodiment of the invention;

Fig. 5 is the circuit diagram of the charging current measuring circuit of the charging and discharging currents measurement module of the specific embodiment of the invention;

Fig. 6 is the circuit diagram of the A/D modular converter of the specific embodiment of the invention;

Fig. 7 is the circuit diagram of the over-voltage over-current protection module of the specific embodiment of the invention;

Fig. 8 is the circuit diagram of the CAN of the specific embodiment of the invention;

Fig. 9 is the circuit diagram of the isoSPI modular converter of the specific embodiment of the invention;

Figure 10 is the circuit diagram of the power subsystem of the specific embodiment of the invention;

Figure 11 is the flow chart of the airplane power source battery management method of the specific embodiment of the invention;

Figure 12 is the airplane power source battery randles model of the specific embodiment of the invention.

Embodiment

Below in conjunction with accompanying drawing to specific embodiment of the invention detailed description in addition.

In present embodiment, airplane power source battery has 8 monocell groups, and each monocell group has 12 joint cells.Airplane power source battery management system, as shown in Figure 1, comprises main control unit, monitoring subelement and host computer.

Main control unit, comprises main controller module, charging/discharging voltage measurement module, charging and discharging currents measurement module, over-voltage over-current protection module, A/D modular converter, contact modules, air pressure acquisition module and isoSPI modular converter.

Monitoring subelement has 8, and each monitoring subelement includes daughter board control module and temperature-measuring module.

The input of charging/discharging voltage measurement module connects the integral battery door group two ends of airplane power source, the input of charging and discharging currents measurement module connects the load of the integral battery door group of airplane power source, the output of charging/discharging voltage measurement module is connected the input of A/D modular converter with the output of charging and discharging currents measurement module, the output of A/D modular converter connects the first input end of main controller module by iic bus; The output of described air pressure acquisition module connects the second input of main controller module by iic bus; First output of described main controller module connects the input of over-voltage over-current protection module, and the output of over-voltage over-current protection module connects the input of contact modules, and the output of contact modules connects the integral battery door group of airplane power source; Described main controller module connects host computer by CAN; The output of described each temperature-measuring module connects the first input end of corresponding daughter board control module respectively, and the second input of each daughter board control module connects corresponding monocell group two ends; Described each daughter board control module connects isoSPI modular converter by spi bus, and isoSPI modular converter connects main controller module by spi bus.

In present embodiment, main controller module adopts model to be Freescale MC9S12XET256 single-chip microcomputer, carry out voltage, current detecting for the charging total current value of the electric discharge total voltage value of the charging total voltage value of integral battery door group according to the airplane power source gathered, integral battery door group, integral battery door group, the electric discharge total current value of integral battery door group and the monomer battery voltage value of monocell group, and send a control signal to over-voltage over-current protection module; Calculate the voltage deviation of the cell of monocell group according to the magnitude of voltage of the cell of monocell group, and send a control signal to daughter board control module; SOC value and the estimation of airplane power source battery SOH value of airplane power source battery is carried out according to the electric discharge total voltage of the charging total voltage of the integral battery door group of the airplane power source of Real-time Collection, integral battery door group, the charging total current of integral battery door group, the electric discharge total current of integral battery door group and integral battery door group temperature value; The magnitude of voltage of cell of the temperature value of the external atmosphere pressure force value of the electric discharge total current value of the charging total current value of the electric discharge total voltage value of the charging total voltage value of the integral battery door group of airplane power source, integral battery door group, integral battery door group, integral battery door group, integral battery door group, each monocell group, monocell group, the SOC value of airplane power source and airplane power source battery SOH value are sent to host computer.

Charging/discharging voltage measurement module, for the electric discharge total voltage of the charging total voltage and integral battery door group that gather the integral battery door group of airplane power source, and is sent to A/D modular converter.

Charging/discharging voltage measurement module, comprises discharge voltage measuring circuit and charging voltage measuring circuit.

In present embodiment, discharge voltage measuring circuit as shown in Figure 2, comprises the first operational amplifier U24B, the first isolator U23 and the second operational amplifier U24A.The positive input terminal of the first operational amplifier U24B connects the integral battery door group two ends of airplane power source by BAT+ pin, the output of the first operational amplifier U24B connects the FD_AI_1 pin of the first isolator U23, the FD_AI_2 pin of the first isolator U23 connects the positive input terminal of the second operational amplifier U24A, and the output of the second operational amplifier U24A connects the FD_V pin of AD conversion chip U25.

In present embodiment, charging voltage measuring circuit as shown in Figure 3, comprises the 3rd operational amplifier U14B, the second isolator U23 and four-operational amplifier U14A.The positive input terminal of the 3rd operational amplifier U14B connects the integral battery door group two ends of airplane power source by C+ pin, the output of the 3rd operational amplifier U14B connects the CD_AI_1 pin of the second isolator U23, the CD_AI_2 pin of the second isolator U23 connects the positive input terminal of four-operational amplifier U14A, and the output of four-operational amplifier U14A connects the CD_V pin of AD conversion chip U25.

In present embodiment, first isolator U23 and the second isolator U13 all adopts model to be ISO124 isolator, and it is OPA2340 operational amplifier that the first operational amplifier U24B, the second operational amplifier U24A, the 3rd operational amplifier U14B and four-operational amplifier U14A all adopt signal to be model.

Charging and discharging currents measurement module, for gathering charging total current and the electric discharge total current of the integral battery door group of airplane power source, and is sent to A/D modular converter.

Charging and discharging currents measurement module, comprises discharge current measuring circuit and charging current measuring circuit.

In present embodiment, discharge current measuring circuit as shown in Figure 4, comprises the 5th operational amplifier U15D and the 6th operational amplifier U15C.The positive input terminal of the 5th operational amplifier U15D connects the integral battery door group load of airplane power source by Hall element, the output of the 5th operational amplifier U15D connects the positive input terminal of the 6th operational amplifier U15C, and the output of the 6th operational amplifier U15C connects the FD_C pin of AD conversion chip U25.

In present embodiment, charging current measuring circuit as shown in Figure 5, comprises the 7th operational amplifier U15B and the 8th operational amplifier U15A.The positive input terminal of the 7th operational amplifier U15B connects the integral battery door group load of airplane power source by Hall element, the output of the 7th operational amplifier U15B connects the positive input terminal of the 8th operational amplifier U15A, and the output of the 8th operational amplifier U15A connects the CD_C pin of AD conversion chip U25.

In present embodiment, choose the Hall element that model is HTA2020, the model of the 5th operational amplifier U15D, the 6th operational amplifier U15C, the 7th operational amplifier U15B and the 8th operational amplifier U15A is OPA4227 operational amplifier.

A/D modular converter as shown in Figure 6, employing model is 16 high-precision AD conversion chip U25 of ADS1115, carry out analog-to-digital conversion for the charging total voltage of the integral battery door group of the airplane power source by collection, total voltage of discharging, charging total current and electric discharge total current, and the charging total voltage value of the integral battery door group of the airplane power source of conversion, electric discharge total voltage value, charging total current value and total current value of discharging are sent to main controller module by iic bus.

The FD_V pin of AD conversion chip ADS1115 connects the output of the second operational amplifier U24A of discharge voltage measuring circuit, the CD_V pin of AD conversion chip ADS1115 connects the output of the four-operational amplifier U14A of charging voltage measuring circuit, the FD_C pin of AD conversion chip ADS1115 connects the output of the 6th operational amplifier U15C of discharge current measuring circuit, the CD_V pin of AD conversion chip ADS1115 connects the output of the 8th operational amplifier U15A of charging current measuring circuit, the AD_SCL pin of AD conversion chip ADS1115, AD_SDA pin is connected the input of main controller module respectively with AD_STATE pin.

16 high-precision AD conversion chip ADS1115, perform switching rate, up to 860 samples per second, there is programmable gain amplifier (PGA) on a sheet, large-signal and small-signal can be measured with high-resolution, ADS1115 also has an input multiplexer (MUX), can provide 2 Differential Input or 4 single ended input.Present embodiment adopts single-ended input fashion to divide four tunnels to measure charging total voltage, electric discharge total voltage, charging total current and electric discharge total current respectively, and the accuracy of voltage and electric current is that the estimation of airplane power source battery pack SOC and SOH provides accuracy guarantee.Through experiment measuring, the certainty of measurement of battery pack total current reaches < 3%, and the certainty of measurement of assembled battery total voltage reaches < 2%.

As shown in Figure 7, for the control signal according to main controller module, when overvoltage, overcurrent appear in the integral battery door group of airplane power source or the cell of monocell group, the break-make of control contactor module, realizes over-voltage over-current protection to over-voltage over-current protection module.

Over-voltage over-current protection module, comprises photoelectrical coupler U22, the first triode Q5 and the second triode Q4, also comprises the first diode D9 and the second diode D4.

In present embodiment, the model of photoelectrical coupler U22 is TLP521_2, and the model of the first triode Q5 and the second triode Q4 is TIP41C, and the model of the first diode D9 and the second diode D4 is IN4148.

The FD_DO_1 pin of photoelectrical coupler U22 is connected main controller module with FD_DO-2 pin, the FD_1 pin of photoelectrical coupler U22 connects the base stage of the first triode Q5, the collector electrode of the first triode Q5 connects the positive pole of the first diode D9, the collector electrode of the first triode Q5 is connected the FD_JK1 pin of the electric discharge D.C. contactor of contact modules with the tie point of the positive pole of the first diode D9, the grounded emitter of the first triode Q5, the negative pole of the first diode D9 connects+24V input power, the CD_1 pin of photoelectrical coupler U22 connects the base stage of the second triode Q4, the collector electrode of the second triode Q4 connects the positive pole of the second diode D4, the collector electrode of the second triode Q4 is connected the CD_JK1 pin of the charging D.C. contactor of contact modules with the tie point of the positive pole of the second diode D4, the grounded emitter of the second triode Q4, the negative pole of the second diode D4 connects+24V input power.

As shown in Figure 8, employing model is the high-speed CAN isolation transceiver U2 of CTM1050T to CAN, for realizing the communication of main controller module and host computer.The CAN_T1 pin of high-speed CAN isolation transceiver U2 is connected main controller module with CAN_R pin, the CAN_GND pin ground connection of high-speed CAN isolation transceiver U2, CANH with the CANL pin of high-speed CAN isolation transceiver U2 is connected host computer by USB-CAN transceiver.

In present embodiment, select two pieces of high-speed CAN isolation transceiver CTM1050T, one piece for proper communication, another block is for subsequent use.

Air pressure acquisition module, adopting model to be the baroceptor of BMP085, for gathering the external atmosphere pressure force value of the integral battery door group of airplane power source, and being sent to main controller module.The precision of baroceptor BMP085 is high, it is low to consume energy, and is connected, directly sends the external atmospheric pressure of the integral battery door group of collection to main controller module and process by iic bus with main controller module.

IsoSPI modular converter as shown in Figure 9, for the mutual conversion of the standard SPI of the standard SPI and two-wire system that realize four-wire system, realizes the communication between main controller module and multiple daughter board control module.

IsoSPI modular converter, comprises the isolated communication interface U11 of isoSPI and Ethernet isolating transformer U12.

In present embodiment, the model of the isolated communication interface U11 of isoSPI is LTC6820FA, function is the standard SPI standard SPI of four-wire system being converted into two-wire system, the model of Ethernet isolating transformer U12 is HX1188, function improves transmission range for strengthening signal strength signal intensity, die terminals is isolated and prevents external interference and signal from harassing.

The iso_MOSI pin of the isolated communication interface U11 of isoSPI, iso_MISO pin, iso_SCK pin are connected main controller module with iso_/CS pin, IP pin and the IM pin of the isolated communication interface U11 of isoSPI are connected IP pin and the IM pin of Ethernet isolating transformer U12 respectively, iso_IP with the iso_IM pin of Ethernet isolating transformer U12 is connected with iso_IP with iso_IM of daughter board control module.

Daughter board control module, adopt the Linear6804-2 multiple batteries group monitor of Linear company, for gathering the monomer battery voltage value of the monocell group of airplane power source, the temperature value of the monocell group of the monomer battery voltage value of the monocell group of airplane power source and the airplane power source of reception is sent to main controller module; According to main controller module control signal, balancing energy control is carried out to the cell of monocell group.

Battery pack monitor Linear6804-2 can measure the voltage the overall measurement error had lower than 1.2mV that reach 12 Stringing cells, can the measurement of all batteries in completion system within 290 μ s, main controller module is connected with 8 pieces of daughter board control modules by the mode adopting a kind of multiaddress to configure, totally 96 joint monomer battery voltages can be gathered, and balancing energy control can be carried out to each cell.When main controller module detects that the monomer battery voltage that daughter board control module is passed back is too high, main controller module will send discharge signal to daughter board control module, daughter board control module drives discharge tube by driving chip, carries out electric discharge realize energy content of battery equilibrium to corresponding cell.

Temperature-measuring module, adopting model to be the thermistor of NTC-MF52AT, for gathering the temperature value of the monocell group of airplane power source, and being sent to daughter board control module.

Contact modules, for the break-make of the break-make and airplane power source battery and load that control airplane power source battery and battery charger.

Contact modules, comprises two D.C. contactors: charging D.C. contactor and electric discharge D.C. contactor, and charging D.C. contactor and electric discharge D.C. contactor are the D.C. contactor that model is SZJ100A.

The input of charging D.C. contactor is connected the output of over-voltage over-current protection module with the input of electric discharge D.C. contactor; the output of charging D.C. contactor connects the battery charger of airplane power source battery, and the output of electric discharge D.C. contactor connects the load of airplane power source battery.

Host computer, select computer, for showing the charging total voltage value of the integral battery door group of airplane power source, the electric discharge total voltage value of integral battery door group, the charging total current value of integral battery door group, the electric discharge total current value of integral battery door group, the external atmosphere pressure force value of integral battery door group, the temperature value of each monocell group, the magnitude of voltage of the cell of monocell group, the SOC value of airplane power source battery and airplane power source battery SOH value.

This system also comprises power subsystem as shown in Figure 10, employing model is the voltage isolating converter U16 of PV10-27B24, for being 24V voltage by the voltage transitions of airplane power source battery, being each module of main control unit and monitoring subelement each module required voltage by 24V voltage transitions again, is each module of main control unit and each module for power supply of monitoring subelement.+ VIN the pin of voltage isolating converter U16 is connected the integral battery door group of airplane power source with-VIN pin ,+VO the pin of voltage isolating converter U16 provides+24V voltage to be connected to the power end of main controller module.

Adopt airplane power source battery management system to carry out the method for airplane power source battery management, as shown in figure 11, comprise the following steps:

Step 1: in airplane power source cell operations, the charging total voltage of the integral battery door group of charging/discharging voltage measurement module Real-time Collection airplane power source and electric discharge total voltage, charging and discharging currents measurement module gathers charging total current and the electric discharge total current of the integral battery door group of airplane power source, A/D modular converter is by the charging total voltage of integral battery door group, electric discharge total voltage, charging total current and electric discharge total current carry out analog-to-digital conversion, and by the charging total voltage value of the integral battery door group of the airplane power source of conversion, electric discharge total voltage value, charging total current value and electric discharge total current value are sent to main controller module.

Step 2: the external atmosphere pressure force value of the integral battery door group of air pressure acquisition module Real-time Collection airplane power source, and be sent to main controller module.

Step 3: each temperature-measuring module gathers the temperature value of each monocell group of airplane power source, and is sent to daughter board control module.

Step 4: each daughter board control module gathers the monomer battery voltage value of the monocell group of corresponding airplane power source, and the temperature value of the monomer battery voltage value of the monocell group of airplane power source and the monocell group of airplane power source is sent to main controller module.

Step 5: main controller module carries out voltage, current detecting according to the charging total current value of the electric discharge total voltage value of the charging total voltage value of integral battery door group of the airplane power source gathered, integral battery door group, integral battery door group, the electric discharge total current value of integral battery door group and the monomer battery voltage value of monocell group; and send a control signal to the break-make of over-voltage over-current protection module controls contact modules, realize the over-voltage over-current protection of airplane power source battery.

Step 5.1: the upper voltage limit threshold value of cell of setting monocell group, the lower voltage limit threshold value of the cell of monocell group, integral battery door group discharge and recharge total voltage upper limit threshold, integral battery door group discharge and recharge total voltage lower threshold, integral battery door group discharge and recharge total current upper limit threshold and integral battery door group discharge and recharge total current lower threshold.

In present embodiment, the upper voltage limit threshold value of the cell of the monocell group of setting is 4.25V, the lower voltage limit threshold value of the cell of monocell group is 2.5V, integral battery door group discharge and recharge total voltage upper limit threshold is 411V, integral battery door group discharge and recharge total voltage lower threshold is 239V, integral battery door group discharge and recharge total current upper limit threshold is 125A, and integral battery door group discharge and recharge total current lower threshold is 12.5A.

Step 5.2: when the charging total voltage value of upper voltage limit threshold value or integral battery door group that the monomer battery voltage value of monocell group is greater than the cell of monocell group is greater than integral battery door group discharge and recharge total voltage upper limit threshold; main controller module sends a control signal to over-voltage over-current protection module, and control contactor module disconnects the battery charger of airplane power source battery.

Step 5.3: when the electric discharge total voltage value of lower voltage limit threshold value or integral battery door group that the monomer battery voltage value of monocell group is less than the cell of monocell group is less than integral battery door group discharge and recharge total voltage lower threshold; main controller module sends a control signal to over-voltage over-current protection module, and control contactor module disconnects the load of airplane power source battery.

Step 5.4: when the charging total current value of integral battery door group is greater than integral battery door group discharge and recharge total current upper limit threshold, main controller module sends a control signal to over-voltage over-current protection module, control contactor module disconnects the battery charger of airplane power source battery.

Step 5.5: when the electric discharge total current value of integral battery door group is less than integral battery door group discharge and recharge total current lower threshold, main controller module sends a control signal to over-voltage over-current protection module, control contactor module disconnects the load of airplane power source battery.

Step 6: main controller module calculates the voltage deviation of the cell of monocell group according to the magnitude of voltage of the cell of monocell group, send and control signal to daughter board control module, daughter board control module carries out balancing energy control to the cell of monocell group.

Step 6.1: the cell upper deviation threshold value of setting monocell group.

In present embodiment, the cell upper deviation threshold value of the monocell group of setting is 0.005V.

Step 6.2: when the voltage deviation of the cell of monocell group is greater than the cell upper deviation threshold value of monocell group, main controller module sends a control signal to daughter board control module, and the cell of daughter board control module to the excessive monocell group of voltage discharges.

Step 7: main controller module carries out SOC value and the estimation of airplane power source battery SOH value of airplane power source battery according to the electric discharge total voltage of the charging total voltage of the integral battery door group of the airplane power source of Real-time Collection, integral battery door group, the charging total current of integral battery door group, the electric discharge total current of integral battery door group and integral battery door group temperature value.

Step 7.1: adopt randles model to carry out modeling to airplane power source battery, as shown in figure 12, obtain airplane power source battery randles model.

In Figure 12, the open circuit voltage that Uocv (SOC) is airplane power source battery pack, R ₀for airplane power source battery pack ohmic internal resistance, R ₁for electric discharge link inertia resistance, R ₂for electric discharge link inertia resistance, C ₁for polarization capacity, C ₂for polarization capacity, R ₁c ₁, R ₂c ₂two RC links are in order to describe airplane power source battery pack polarity effect, R ₁voltage be U ₁, R ₂voltage be U ₂, discharge and recharge total current is I, definition time constant τ ₁=R ₁c ₁, τ ₂=R ₂c ₂, the function U of SOC can be obtained according to the circuit diagram of Figure 12 _oCV(SOC) formula is as follows such as formula (1), formula (2) and formula (3):

U _OCV(SOC)＝IR ₀+U ₁+U ₂(1)

$U_1=U_{1\left(0\right)}{e}^{-\frac{t}{{\mathrm{\&tau;}}_1}}+{\mathrm{IR}}_1(1-e^{-\frac{t}{{\mathrm{\&tau;}}_1}})---\left(2\right)$

$U_2=U_{2\left(0\right)}{e}^{-\frac{t}{{\mathrm{\&tau;}}_2}}+{\mathrm{IR}}_2(1-e^{-\frac{t}{{\mathrm{\&tau;}}_2}})---\left(3\right)$

Wherein, U _{1 (0)}for voltage U ₁initial value, U _{2 (0)}for voltage U ₂initial value, t is the time.

To the function U of SOC _oCV(SOC) formula carries out OCV-SOC matching, introduces natural exponential function and with 6 fitting of a polynomials, obtains the function U of the SOC of matching _oCV(SOC) formula is such as formula shown in (4):

$U_{\mathrm{OCV}}\left(\mathrm{SOC}\right)=a_0+a_1\mathrm{SOC}+...+a_6{\mathrm{SOC}}^6+b_0{e}^{b_1\mathrm{SOC}}---\left(4\right)$

Wherein, a ₀, a ₁, a ₂... a ₆, b ₀, b ₁for the parameter that airplane power source battery pack self character is relevant, according to contrived experiment: first, airplane power source battery pack trickle is full of, power-off; Secondly, sufficient standing about 3 hours, the open circuit voltage U of airplane power source battery pack during record SOC=100% _oCV(SOC); Subsequently, use the method for small area analysis stage discharge, steppingly the SOC of airplane power source battery pack be adjusted to 90%, 80%, 70%..., 20% etc., and after adjustment each time sufficient standing to obtain the open circuit voltage U of airplane power source battery pack accurately _oCV(SOC), thus obtain the OCV-SOC curve of airplane power source battery pack, then can estimate parameter a with least square fitting ₀, a ₁, a ₂... a ₆, b ₀, b ₁.

Ignore the impact of the factor such as temperature, cycle-index, carry out mixed pulses power test (HPPC), namely to airplane power source battery pack with constant-current discharge 10s, leave standstill 40s, constant current charge 10s, leave standstill 40s, record airplane power source battery pack current and terminal voltage, calculate the airplane power source battery pack internal resistance R in airplane power source battery randles model according to parameter identification ₀, electric discharge link inertia resistance R ₁, electric discharge link inertia resistance R ₂, polarization capacity C ₁, polarization capacity C ₂, R ₁voltage U ₁, R ₂voltage U ₂with discharge and recharge total current I.

Considering that airplane power source battery pack temperature and discharge-rate are on the impact of airplane power source battery model, to the function U of the SOC of matching _oCV(SOC) formula (4) is revised, and obtains the function U of the SOC revised _oCV(SOC) formula is such as formula shown in (5):

$U_{\mathrm{OCV}}\left(\mathrm{SOC}\right)=a_0+a_1\mathrm{SOC}+...+a_6{\mathrm{SOC}}^6+b_0{e}^{b_1\mathrm{SOC}}+c_{1}T+c_2{e}^{c_{3}T}+(d_{1}C+d_2{e}^{d_{3}C})---\left(5\right)$

Wherein, c ₁, c ₂, c ₃, d ₁, d ₂, d ₃for airplane power source battery pack empirical curve calibrating parameters, T is integral battery door group temperature value, and C is airplane power source battery pack present discharge multiplying power.

Step 7.2: using gather integral battery door group charging total voltage or electric discharge total voltage as discharge and recharge total voltage, using the charging total current of integral battery door group or electric discharge total current as discharge and recharge total current, by the temperature value of the mean value of the cell temperature value of monocell group battery pack as a whole.

In present embodiment, when airplane power source battery in charging process using the charging total current of integral battery door group as discharge and recharge total current, using the charging total voltage of integral battery door group as discharge and recharge total voltage, when airplane power source battery in discharge process using the electric discharge total current of integral battery door group as discharge and recharge total current, using the electric discharge total voltage of integral battery door group as discharge and recharge total voltage.

Step 7.3: according to the randles model of airplane power source battery, adopt the method for EKF, utilize the temperature value of the discharge and recharge total voltage of the integral battery door group of the airplane power source of Real-time Collection, the discharge and recharge total current of integral battery door group and integral battery door group to estimate the SOC value of airplane power source battery and the SOH value of airplane power source battery.

According to the randles model of airplane power source battery adopt the SOC value of the method for EKF estimation airplane power source battery and SOH value method as follows:

If the sampling time is Δ t, the total electricity of airplane power source battery pack is Q ₀, then the SOC of airplane power source battery and the relation between discharge and recharge total current I, airplane power source battery electric quantity Q are such as formula shown in (6):

$\mathrm{SOC}(k+1)=\frac{Q(k+1)}{Q_0}=\frac{Q\left(k\right)+\mathrm{I\&Delta;t}}{Q_0}=\mathrm{SOC}\left(k\right)+\frac{\mathrm{I\&Delta;t}}{Q_0}---\left(6\right)$

Wherein, k is the sequence number of sample sequence, sets up airplane power source battery state equation such as formula shown in (7) and formula (8):

$\left[\begin{array}{c}\mathrm{SOC}(k+1)\\ U_1(k+1)\\ U_2(k+1)\end{array}\right]=\left[\begin{array}{ccc}1& 0& 0\\ 0& e^{-\frac{t}{{\mathrm{\&tau;}}_1}}& 0\\ 0& 0& e^{-\frac{t}{{\mathrm{\&tau;}}_2}}\end{array}\right]\left[\begin{array}{c}\mathrm{SOC}\left(k\right)\\ U_1\left(k\right)\\ U_2\left(k\right)\end{array}\right]+\left[\begin{array}{c}\frac{\mathrm{I\&Delta;t}}{Q_0}\\ R_1(1-e^{-\frac{t}{{\mathrm{\&tau;}}_1}})\\ R_2(1-e^{-\frac{t}{{\mathrm{\&tau;}}_2}})\end{array}\right]I\left(k\right)+\mathrm{\&omega;}\left(k\right)---\left(7\right)$

U _L(k)＝U _OVC(SOC(k))+I(k)R ₀+U ₁(k)+U ₂(k)+υ(k) (8)

Wherein, U _lfor driving noise when discharge and recharge total voltage, ω (k) they are estimation SOC, measurement noise when υ (k) is estimation SOC.

Initialization system state variable is X (k)=[SOC (k), U ₁(k), U ₂(k)] ^t, input signal U (k)=I (k), measures and exports as Z (k)=U _l(k), matrix $A=\left[\begin{array}{ccc}1& 0& 0\\ 0& e^{-\mathrm{\&Delta;t}/{\mathrm{\&tau;}}_1}& 0\\ 0& 0& e^{-\mathrm{\&Delta;t}/{\mathrm{\&tau;}}_2}\end{array}\right],$ Matrix $B=\left[\begin{array}{c}\mathrm{\&eta;\&Delta;t}/Q_0\\ R_1(1-e^{-\mathrm{\&Delta;t}/{\mathrm{\&tau;}}_1})\\ R_2(1-e^{-\mathrm{\&Delta;t}/{\mathrm{\&tau;}}_2})\end{array}\right].$ Wherein, η is charge-discharge magnification.

Then the computational methods of system measurements-state transition matrix C (k) are such as formula shown in (9):

$C\left(k\right)=\frac{\&PartialD;g(X\left(k\right),U\left(k\right))}{\&PartialD;X\left(k\right)}=[\frac{{\mathrm{dU}}_{\mathrm{OCV}}\left(\mathrm{SOC}\left(k\right)\right)}{\mathrm{dSOC}\left(k\right)},1.1]---\left(9\right)$

Adopt above-mentioned parameter, carry out iteration according to the recurrence formula of EKF, can estimate the SOC value of airplane power source battery in real time.

By airplane power source battery pack internal resistance R ₀as system mode, obtain the state equation of airplane power source battery pack internal resistance such as formula shown in (10) and formula (11):

R ₀ ^k+1＝R ₀ ^k+r _k(10)

U _L(k)＝U _ocv(SOC(k))+I(k)R ₀+U ₁(k)+U ₂(k)+n(k) (11)

Wherein, r _kfor driving noise during estimation SOH, measurement noise when n (k) is estimation SOH.

According to airplane power source battery pack internal resistance R ₀estimate the SOH value of airplane power source battery, shown in (12):

$\mathrm{SOH}=\frac{R_{\mathrm{EOL}}-R_0}{R_{\mathrm{EOL}}-R_{\mathrm{new}}}---\left(12\right)$

Wherein, R _eOLfor internal resistance of cell when airplane power source battery life terminates, R _newfor initial internal resistance when airplane power source battery pack is dispatched from the factory.

Step 8: the SOH value of the external atmosphere pressure force value of the charging total current value of the charging total voltage value of integral battery door group of host computer display airplane power source, the electric discharge total voltage value of integral battery door group, integral battery door group, the electric discharge total current value of integral battery door group, integral battery door group, the temperature value of each monocell group, the magnitude of voltage of the cell of monocell group, the SOC value of airplane power source battery and airplane power source battery.

Claims (9)

1. an airplane power source battery management system, is characterized in that, comprises main control unit, monitoring subelement and host computer;

Described main control unit, comprises main controller module, charging/discharging voltage measurement module, charging and discharging currents measurement module, over-voltage over-current protection module, A/D modular converter, contact modules, air pressure acquisition module and isoSPI modular converter;

Described monitoring subelement has multiple, and each monitoring subelement includes daughter board control module and temperature-measuring module;

The input of described charging/discharging voltage measurement module connects the integral battery door group two ends of airplane power source, the input of charging and discharging currents measurement module connects the load of the integral battery door group of airplane power source, the output of charging/discharging voltage measurement module is connected the input of A/D modular converter with the output of charging and discharging currents measurement module, the output of A/D modular converter connects the first input end of main controller module by iic bus; The output of described air pressure acquisition module connects the second input of main controller module by iic bus; First output of described main controller module connects the input of over-voltage over-current protection module, and the output of over-voltage over-current protection module connects the input of contact modules, and the output of contact modules connects the integral battery door group of airplane power source; Described main controller module connects host computer by CAN; The output of described each temperature-measuring module connects the first input end of corresponding daughter board control module respectively, and the second input of each daughter board control module connects corresponding monocell group two ends; Described each daughter board control module connects isoSPI modular converter by spi bus, and isoSPI modular converter connects main controller module by spi bus.

2. airplane power source battery management system according to claim 1, is characterized in that, this system also comprises power subsystem, and the input of power subsystem connects the integral battery door group of airplane power source, and the output of power subsystem connects the power end of main controller module;

Described power subsystem, adopts voltage isolating converter, for being each module of main control unit and each module required voltage of monitoring subelement, is each module of main control unit and each module for power supply of monitoring subelement by the voltage transitions of airplane power source battery.

3. airplane power source battery management system according to claim 1, it is characterized in that, described main controller module, adopt single-chip microcomputer, carry out voltage, current detecting for the charging total current value of the electric discharge total voltage value of the charging total voltage value of integral battery door group according to the airplane power source gathered, integral battery door group, integral battery door group, the electric discharge total current value of integral battery door group and the monomer battery voltage value of monocell group, and send a control signal to over-voltage over-current protection module; Calculate the voltage deviation of the cell of monocell group according to the magnitude of voltage of the cell of monocell group, and send a control signal to daughter board control module; SOC value and the estimation of airplane power source battery SOH value of airplane power source battery is carried out according to the electric discharge total voltage of the charging total voltage of the integral battery door group of the airplane power source of Real-time Collection, integral battery door group, the charging total current of integral battery door group, the electric discharge total current of integral battery door group and integral battery door group temperature value; The magnitude of voltage of cell of the temperature value of the external atmosphere pressure force value of the electric discharge total current value of the charging total current value of the electric discharge total voltage value of the charging total voltage value of the integral battery door group of airplane power source, integral battery door group, integral battery door group, integral battery door group, integral battery door group, each monocell group, monocell group, the SOC value of airplane power source and airplane power source battery SOH value are sent to host computer;

Described charging/discharging voltage measurement module, for the electric discharge total voltage of the charging total voltage and integral battery door group that gather the integral battery door group of airplane power source, and is sent to A/D modular converter;

Described charging and discharging currents measurement module, for the electric discharge total current of the charging total current and integral battery door group that gather the integral battery door group of airplane power source, and is sent to A/D modular converter;

Described A/D modular converter, adopt A/D converter, carry out analog-to-digital conversion for the charging total voltage of the integral battery door group of the airplane power source by collection, total voltage of discharging, charging total current and electric discharge total current, and the charging total voltage value of the integral battery door group of the airplane power source of conversion, electric discharge total voltage value, charging total current value and total current value of discharging are sent to main controller module by iic bus;

Described over-voltage over-current protection module, for the control signal according to main controller module, when overvoltage, overcurrent appear in the integral battery door group of airplane power source or the cell of monocell group, the break-make of control contactor module, realizes over-voltage over-current protection;

Described air pressure acquisition module, adopting baroceptor, for gathering the external atmosphere pressure force value of the integral battery door group of airplane power source, and being sent to main controller module;

Described isoSPI modular converter, for the mutual conversion of the standard SPI of the standard SPI and two-wire system that realize four-wire system, realizes the communication between main controller module and multiple daughter board control module;

Described daughter board control module, adopt battery pack monitor, for gathering the monomer battery voltage value of the monocell group of airplane power source, the temperature value of the monomer battery voltage value of the monocell group of airplane power source and the monocell group of airplane power source is sent to main controller module; According to main controller module control signal, balancing energy control is carried out to the cell of monocell group;

Described temperature-measuring module, adopting thermistor, for gathering the temperature value of the monocell group of airplane power source, and being sent to daughter board control module;

Described contact modules, for the break-make of the break-make and airplane power source battery and load that control airplane power source battery and battery charger;

Described host computer, for showing the charging total voltage value of the integral battery door group of airplane power source, the electric discharge total voltage value of integral battery door group, the charging total current value of integral battery door group, the electric discharge total current value of integral battery door group, the external atmosphere pressure force value of integral battery door group, the temperature value of each monocell group, the magnitude of voltage of the cell of monocell group, the SOC value of airplane power source battery and airplane power source battery SOH value.

4. airplane power source battery management system according to claim 1, is characterized in that, described charging/discharging voltage measurement module, comprises discharge voltage measuring circuit and charging voltage measuring circuit;

Described discharge voltage measuring circuit comprises the first operational amplifier, the first isolator and the second operational amplifier; The input of the first described operational amplifier connects the integral battery door group two ends of airplane power source, the output of the first operational amplifier connects the input of the first isolator, the output of the first isolator connects the input of the second operational amplifier, and the output of the second operational amplifier connects the input of A/D modular converter;

Described charging voltage measuring circuit comprises the 3rd operational amplifier, the second isolator and four-operational amplifier; The input of the 3rd described operational amplifier connects the integral battery door group two ends of airplane power source, the output of the 3rd operational amplifier connects the input of the second isolator, the output of the second isolator connects the input of four-operational amplifier, and the output of four-operational amplifier connects the input of A/D modular converter.

5. airplane power source battery management system according to claim 1, is characterized in that, described charging and discharging currents measurement module, comprises discharge current measuring circuit and charging current measuring circuit;

Described discharge current measuring circuit comprises the 5th operational amplifier and the 6th operational amplifier; The input of the 5th described operational amplifier connects the integral battery door group load of airplane power source, and the output of the 5th operational amplifier connects the input of the 6th operational amplifier, and the output of the 6th operational amplifier connects the input of A/D modular converter;

Described charging current measuring circuit comprises the 7th operational amplifier and the 8th operational amplifier; The input of the 7th described operational amplifier connects the integral battery door group load of airplane power source, and the output of the 7th operational amplifier connects the input of the 8th operational amplifier, and the output of the 8th operational amplifier connects the input of A/D modular converter.

6. airplane power source battery management system according to claim 1, is characterized in that, described isoSPI modular converter, comprises the isolated communication interface of isoSPI and Ethernet isolating transformer;

The input of the isolated communication interface of described isoSPI connects main controller module by spi bus, the output of the isolated communication interface of isoSPI connects the input of isolating transformer, and the output of isolating transformer connects each daughter board control module by spi bus.

7. airplane power source battery management system according to claim 1, is characterized in that, described over-voltage over-current protection module, comprises photoelectrical coupler, the first triode and the second triode;

The input of described photoelectrical coupler connects the first output of main controller module, and the first output of photoelectrical coupler connects the input of the first triode, and the second output of photoelectrical coupler connects the input of the second triode; The output of the first triode is connected the input of contact modules respectively with the output of the second triode.

8. airplane power source battery management system according to claim 1, is characterized in that, described contact modules, comprises two D.C. contactors: charging D.C. contactor and electric discharge D.C. contactor;

The input of described charging D.C. contactor is connected the output of over-voltage over-current protection module with the input of electric discharge D.C. contactor; the output of charging D.C. contactor connects the battery charger of airplane power source battery, and the output of electric discharge D.C. contactor connects the load of airplane power source battery.

9. adopt airplane power source battery management system according to claim 1 to carry out the method for airplane power source battery management, it is characterized in that, comprise the following steps:

Step 1: in airplane power source cell operations, the charging total voltage of the integral battery door group of charging/discharging voltage measurement module Real-time Collection airplane power source and electric discharge total voltage, charging and discharging currents measurement module gathers charging total current and the electric discharge total current of the integral battery door group of airplane power source, A/D modular converter is by the charging total voltage of integral battery door group, electric discharge total voltage, charging total current and electric discharge total current carry out analog-to-digital conversion, and by the charging total voltage value of the integral battery door group of the airplane power source of conversion, electric discharge total voltage value, charging total current value and electric discharge total current value are sent to main controller module,

Step 2: the external atmosphere pressure force value of the integral battery door group of air pressure acquisition module Real-time Collection airplane power source, and be sent to main controller module;

Step 3: each temperature-measuring module gathers the temperature value of each monocell group of airplane power source, and is sent to daughter board control module;

Step 4: each daughter board control module gathers the monomer battery voltage value of the monocell group of corresponding airplane power source, and the temperature value of the monomer battery voltage value of the monocell group of airplane power source and the monocell group of airplane power source is sent to main controller module;

Step 5: main controller module carries out voltage, current detecting according to the charging total current value of the electric discharge total voltage value of the charging total voltage value of integral battery door group of the airplane power source gathered, integral battery door group, integral battery door group, the electric discharge total current value of integral battery door group and the monomer battery voltage value of monocell group, and send a control signal to the break-make of over-voltage over-current protection module controls contact modules, realize the over-voltage over-current protection of airplane power source battery;

Step 5.1: the upper voltage limit threshold value of cell of setting monocell group, the lower voltage limit threshold value of the cell of monocell group, integral battery door group discharge and recharge total voltage upper limit threshold, integral battery door group discharge and recharge total voltage lower threshold, integral battery door group discharge and recharge total current upper limit threshold and integral battery door group discharge and recharge total current lower threshold;

Step 5.2: when the charging total voltage value of upper voltage limit threshold value or integral battery door group that the monomer battery voltage value of monocell group is greater than the cell of monocell group is greater than integral battery door group discharge and recharge total voltage upper limit threshold, main controller module sends a control signal to over-voltage over-current protection module, and control contactor module disconnects the battery charger of airplane power source battery;

Step 5.3: when the electric discharge total voltage value of lower voltage limit threshold value or integral battery door group that the monomer battery voltage value of monocell group is less than the cell of monocell group is less than integral battery door group discharge and recharge total voltage lower threshold, main controller module sends a control signal to over-voltage over-current protection module, and control contactor module disconnects the load of airplane power source battery;

Step 5.4: when the charging total current value of integral battery door group is greater than integral battery door group discharge and recharge total current upper limit threshold, main controller module sends a control signal to over-voltage over-current protection module, control contactor module disconnects the battery charger of airplane power source battery;

Step 5.5: when the electric discharge total current value of integral battery door group is less than integral battery door group discharge and recharge total current lower threshold, main controller module sends a control signal to over-voltage over-current protection module, control contactor module disconnects the load of airplane power source battery;

Step 6: main controller module calculates the voltage deviation of the cell of monocell group according to the magnitude of voltage of the cell of monocell group, send and control signal to daughter board control module, daughter board control module carries out balancing energy control to the cell of monocell group;

Step 6.1: the cell upper deviation threshold value of setting monocell group;

Step 6.2: when the voltage deviation of the cell of monocell group is greater than the cell upper deviation threshold value of monocell group, main controller module sends a control signal to daughter board control module, and the cell of daughter board control module to the excessive monocell group of voltage discharges;

Step 7: main controller module carries out SOC value and the estimation of airplane power source battery SOH value of airplane power source battery according to the electric discharge total voltage of the charging total voltage of the integral battery door group of the airplane power source of Real-time Collection, integral battery door group, the charging total current of integral battery door group, the electric discharge total current of integral battery door group and integral battery door group temperature value;

Step 7.1: adopt randles model to carry out modeling to airplane power source battery, obtain airplane power source battery randles model;

Step 7.2: using gather integral battery door group charging total voltage or electric discharge total voltage as discharge and recharge total voltage, using the charging total current of integral battery door group or electric discharge total current as discharge and recharge total current, by the temperature value of the mean value of the cell temperature value of monocell group battery pack as a whole;

Step 7.3: according to the randles model of airplane power source battery, adopt the method for EKF, utilize the temperature value of the discharge and recharge total voltage of the integral battery door group of the airplane power source of Real-time Collection, the discharge and recharge total current of integral battery door group and integral battery door group to estimate the SOC value of airplane power source battery and the SOH value of airplane power source battery;

Step 8: the SOH value of the external atmosphere pressure force value of the charging total current value of the charging total voltage value of integral battery door group of host computer display airplane power source, the electric discharge total voltage value of integral battery door group, integral battery door group, the electric discharge total current value of integral battery door group, integral battery door group, the temperature value of each monocell group, the magnitude of voltage of the cell of monocell group, the SOC value of airplane power source battery and airplane power source battery.