CN104882931B - 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 its method

Technical field

The invention belongs to technical field of battery management is and in particular to airplane power source battery management system and its method.

Background technology

With the continuous development of aerospace industry, its airborne electrical equipment is increasing, airplane power source battery management system It is designed to for key.Airplane power source battery management system is not only function system, is also important safe-guard system.Due to The continuous development of electric aircraft, the importance of airplane power source battery system also will rise to a new height.One good electricity Source battery management system not only will detect to the voltage x current of set of cells, the estimation of battery charge state and health status, The charge and discharge balancing problem of battery also becomes emphasis and the difficult point of research.

At present, on market, the power-supply battery management system of main flow has flying of matter than simulation electronic formula battery management system Jump, but still have a variety of deficiencies, such as: the degree of accuracy of measurement and real-time need to be improved, and the data type of measurement is not perfect, Need to be connected with host computer interface, realize battery management system visualization.

Content of the invention

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

Technical solution of the present invention is as follows:

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

Described main control unit, including main controller module, charging/discharging voltage measurement module, charging and discharging currents measurement mould Block, 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 all 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, discharge and recharge electricity The input of flow measurement module connects the load of the integral battery door group of airplane power source, the outfan of charging/discharging voltage measurement module and The outfan of charging and discharging currents measurement module connects the input of a/d modular converter, and the outfan of a/d modular converter passes through iic Bus connects the first input end of main controller module；The outfan of described air pressure acquisition module passes through iic bus and connects master Second input of controller module；First outfan of described main controller module connects the defeated of over-voltage over-current protection module Enter end, the outfan of over-voltage over-current protection module connects the input of contact modules, the outfan of contact modules connects boat The integral battery door group of empty power supply；Described main controller module connects host computer by can bus；Each temperature-measuring module defeated Go out the first input end that end connects corresponding daughter board control module respectively, the second input of each daughter board control module connects correspondence Single battery group two ends；Described each daughter board control module connects isospi modular converter, isospi modulus of conversion by spi bus Block connects main controller module by spi bus.

This system also includes power subsystem, and the input of power subsystem connects the integral battery door group of airplane power source, power supply list The outfan of unit connects the power end of main controller module；

Described power subsystem, using voltage isolating converter, for being master control by the voltage conversion of airplane power source battery The each module of unit processed and monitoring subelement each module required voltage, are each module of main control unit and the monitoring each module of subelement supplies Electricity.

Main controller module, using single-chip microcomputer, the charging for the integral battery door group of the airplane power source according to collection is always electric Pressure value, 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 of integral battery door group The monomer battery voltage value of value and single battery group carries out voltage, current detecting, and sends a control signal to over-voltage over-current protection mould Block；The magnitude of voltage of the cell according to single battery group calculates the voltage deviation of the cell of single battery group, and sends control Signal is to daughter board control module；The charging total voltage of the integral battery door group of the airplane power source according to Real-time Collection, integral battery door group Electric discharge total voltage, 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 Carry out soc value and the estimation of airplane power source battery soh value of airplane power source battery；Will be total for the charging of the integral battery door group of airplane power source Magnitude of voltage, the electric discharge total voltage value of integral battery door group, the charging total current value of integral battery door group, integral battery door group electric discharge always electric Flow valuve, the external atmosphere pressure force value of integral battery door group, the temperature value of each single battery group, the voltage of the cell of single battery group Value, the soc value of airplane power source and airplane power source battery soh value send to host computer；

Described charging/discharging voltage measurement module, for gathering the charging total voltage of integral battery door group of airplane power source and whole The electric discharge total voltage of body set of cells, and it is sent to a/d modular converter；Charging/discharging voltage measurement module, including discharge voltage measurement Circuit and charging voltage measuring circuit；

Described discharge voltage measuring circuit includes 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 End connects the input of the first isolator, and the outfan of the first isolator connects the input of the second operational amplifier, the second fortune The outfan calculating amplifier connects the input of a/d modular converter；

Described charging voltage measuring circuit includes 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 End connects the input of the second isolator, and the outfan of the second isolator connects the input of four-operational amplifier, the 4th fortune The outfan calculating amplifier connects the input of a/d modular converter.

Described charging and discharging currents measurement module, for gathering the charging total current of integral battery door group of airplane power source and whole The electric discharge total current of body set of cells, and it is sent to a/d modular converter；Charging and discharging currents measurement module, including discharge current measurement Circuit and charging current measuring circuit；

Described discharge current measuring circuit includes the 5th operational amplifier and the 6th operational amplifier；The 5th described fortune The input calculating amplifier connects the integral battery door group load of airplane power source, and the outfan of the 5th operational amplifier connects the 6th fortune Calculate the input of amplifier, the outfan of the 6th operational amplifier connects the input of a/d modular converter；

Described charging current measuring circuit includes the 7th operational amplifier and the 8th operational amplifier；The 7th described fortune The input calculating amplifier connects the integral battery door group load of airplane power source, and the outfan of the 7th operational amplifier connects the 8th fortune Calculate the input of amplifier, the outfan of the 8th operational amplifier connects the input of a/d modular converter.

Described a/d modular converter, using a/d transducer, for filling the integral battery door group of the airplane power source of collection Electric total voltage, electric discharge total voltage, charging total current and electric discharge total current carry out analog digital conversion, and the airplane power source of conversion is whole The charging total voltage value of body set of cells, electric discharge total voltage value, charging total current value and electric discharge total current value are transmitted by iic bus To main controller module；

Described over-voltage over-current protection module, for according to the control signal receiving main controller module, in airplane power source Integral battery door group or single battery group cell occur overvoltage, excessively stream when, the break-make of control contactor module, realize overvoltage Overcurrent protection；Over-voltage over-current protection module, including photoelectrical coupler, the first audion and the second audion；

First outfan of described photoelectrical coupler connects the base stage of the first audion, the second output of photoelectrical coupler End connects the base stage of the second triode, and the colelctor electrode of the colelctor electrode of the first audion and the second audion connects catalyst mould respectively The input of block.

Described air pressure acquisition module, using baroceptor, for gathering the external world of the integral battery door group of airplane power source Atmospheric pressure value, and it is sent to main controller module；

Described isospi modular converter, turns for realizing standard spi of four-wire system and the mutual of standard spi of two-wire system Change, realize the communication between main controller module and multiple daughter board control module；Isospi modular converter, including isospi isolation Formula communication interface and isolating transformer；

The input of the isolated communication interface of described isospi connects main controller module, isospi by spi bus The outfan of isolated communication interface connects the input of isolating transformer, and the outfan of isolating transformer passes through spi bus even Connect each daughter board control module.

Described daughter board control module, using set of cells monitor, for gathering the monomer of the single battery group of airplane power source Battery voltage value, the temperature value of the monomer battery voltage value of the single battery group of airplane power source and the single battery group of airplane power source is passed Deliver to main controller module；Balancing energy control is carried out to the cell of single battery group according to main controller module control signal System；

Described temperature-measuring module, using critesistor, for gathering the temperature value of the single battery group of airplane power source, and It is sent to daughter board control module；

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

The input of the described input of charging D.C. contactor and electric discharge D.C. contactor connects over-voltage over-current protection The outfan of module, the outfan of charging D.C. contactor connects the battery charger of airplane power source battery, electric discharge direct current contact The outfan of device 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, integral battery door group Electric discharge total voltage value, the charging total current value of integral battery door group, the electric discharge total current value of integral battery door group, integral battery door group outward Boundary's atmospheric pressure value, the temperature value of each single battery group, the magnitude of voltage of the cell of single battery group, the soc of airplane power source battery Value and airplane power source battery soh value.

The method carrying out airplane power source battery management using airplane power source battery management system, comprises the following steps:

Step 1: in airplane power source cell operations, charging/discharging voltage measurement module Real-time Collection airplane power source whole The charging total voltage of body set of cells and electric discharge total voltage, charging and discharging currents measurement module gathers the integral battery door group of airplane power source Charging total current and electric discharge total current, a/d modular converter will be total to the charging total voltage of integral battery door group, electric discharge total voltage, charging Electric current and electric discharge total current carry out analog digital conversion, and by the charging total voltage value of the integral battery door group of the airplane power source of conversion, put Electric 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 transmit To main controller module；

Step 3: each temperature-measuring module gathers the temperature value of each single battery 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 single battery group of corresponding airplane power source, will navigate The temperature value of the single battery group of the monomer battery voltage value of the single battery group of empty power supply and airplane power source is sent to master controller mould Block；

Step 5: the charging total voltage value of integral battery door group of the airplane power source according to collection for the main controller module, overall electricity The electric discharge total voltage value of pond group, the charging total current value of integral battery door group, the electric discharge total current value of integral battery door group and monocell The monomer battery voltage value of group carries out voltage, current detecting, and sends a control signal to the control contact of over-voltage over-current protection module The break-make of device module, realizes the over-voltage over-current protection of airplane power source battery；

Step 5.1: set the upper voltage limit threshold value of cell, the voltage of the cell of single battery group of single battery group Lower threshold, integral battery door group discharge and recharge total voltage upper limit threshold, integral battery door group discharge and recharge total voltage lower threshold, overall electricity Pond 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 monomer battery voltage value of single battery group is more than the upper voltage limit threshold of the cell of single battery group When the charging total voltage value of value or integral battery door group is more than integral battery door group discharge and recharge total voltage upper limit threshold, main controller module Send a control signal to over-voltage over-current protection module, control contactor module disconnects the battery charger of airplane power source battery；

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

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 When, main controller module sends a control signal to over-voltage over-current protection module, and control contactor module disconnects airplane power source battery Load；

Step 6: main controller module calculates the monomer electricity of single battery group according to the magnitude of voltage of the cell of single battery group The voltage deviation in pond, send control signal to daughter board control module, daughter board control module carries out energy to the cell of single battery group Amount Balance route；

Step 6.1: set the cell upper deviation threshold value of single battery group；

Step 6.2: when the voltage deviation of the cell of single battery group is more than the cell upper deviation of single battery group During threshold value, main controller module sends a control signal to daughter board control module, the daughter board control module monocell excessive to voltage The cell of group is discharged；

Step 7: main controller module is according to the charging total voltage of the integral battery door group of the airplane power source of Real-time Collection, entirety The electric discharge total voltage of set of cells, 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 carries out soc value and the estimation of airplane power source battery soh value of airplane power source battery；

Step 7.1: using randles model, airplane power source battery is modeled, obtains airplane power source battery randles Model；

Step 7.2: using the charging total voltage of the integral battery door group of collection or electric discharge total voltage as discharge and recharge total voltage, will The charging total current of integral battery door group or electric discharge total current as discharge and recharge total current, by the cell temperature value of single battery group Meansigma methodss as integral battery door group temperature value；

Step 7.3: according to the randles model of airplane power source battery, using the method for EKF, using reality When the discharge and recharge total voltage of the integral battery door group of airplane power source, the discharge and recharge total current of integral battery door group and the integral battery door that gather The temperature value of group estimates the soc value of airplane power source battery and the soh value of airplane power source battery；

Step 8: the charging total voltage value of integral battery door group of host computer display airplane power source, the electric discharge of integral battery door group are total Magnitude of voltage, the charging total current value of integral battery door group, the electric discharge total current value of integral battery door group, the ambient atmosphere of integral battery door group Pressure value, the temperature value of each single battery group, the magnitude of voltage of the cell of single battery group, the soc value of airplane power source battery and boat The soh value of empty power-supply battery.

Beneficial effects of the present invention:

The present invention proposes airplane power source battery management system and its method, accurately measures the cell electricity of each single battery group Pressure, airplane power source discharge and recharge total voltage, airplane power source discharge and recharge total current, the temperature of airplane power source battery and airplane power source battery The information such as air pressure, there is equilibrium monomer battery voltage simultaneously, control battery charging and discharging, the function that battery overcurrent-overvoltage controls. And using 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 working condition of lithium battery group, constitute integrated level height, a function Perfect, function admirable utility system.

Brief description

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

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

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

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

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

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 bus 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.

Specific embodiment

Below in conjunction with the accompanying drawings the specific embodiment of the invention is described in detail.

In present embodiment, airplane power source battery has 8 single battery groups, and each single battery group has 12 section cells.Aviation Power-supply battery management system, as shown in figure 1, include main control unit, monitoring subelement and host computer.

Main control unit, including main controller module, charging/discharging voltage measurement module, charging and discharging currents measurement module, mistake Pressure overcurrent protection module, a/d modular converter, contact modules, air pressure acquisition module and isospi modular converter.

Monitoring subelement has 8, and each monitoring subelement all 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, and charging and discharging currents measure The input of module connects load, the outfan of charging/discharging voltage measurement module and the discharge and recharge of the integral battery door group of airplane power source The outfan of current measurement module connects the input of a/d modular converter, and the outfan of a/d modular converter passes through iic bus even Connect the first input end of main controller module；The outfan of described air pressure acquisition module connects master controller by iic bus Second input of module；First outfan of described main controller module connects the input of over-voltage over-current protection module, The outfan of over-voltage over-current protection module connects the input of contact modules, and the outfan of contact modules connects airplane power source Integral battery door group；Described main controller module connects host computer by can bus；Described each temperature-measuring module defeated Go out the first input end that end connects corresponding daughter board control module respectively, the second input of each daughter board control module connects correspondence Single battery group two ends；Described each daughter board control module connects isospi modular converter, isospi modulus of conversion by spi bus Block connects main controller module by spi bus.

In present embodiment, main controller module adopts model Freescale mc9s12xet256 single-chip microcomputer, for root According to the charging total voltage value of the integral battery door group of the airplane power source of collection, the electric discharge total voltage value of integral battery door group, integral battery door The charging total current value of group, the electric discharge total current value of integral battery door group and the monomer battery voltage value of single battery group carry out voltage, Current detecting, and send a control signal to over-voltage over-current protection module；The magnitude of voltage of the cell according to single battery group calculates The voltage deviation of the cell of single battery group, and send a control signal to daughter board control module；Aviation according to Real-time Collection The charging total voltage of the integral battery door group of power supply, the electric discharge total voltage of integral battery door group, the charging total current of integral battery door group, whole The electric discharge total current of body set of cells and integral battery door group temperature value carry out soc value and the airplane power source battery of airplane power source battery Soh value is estimated；By 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, entirety The charging total current value of set of cells, the electric discharge total current value of integral battery door group, the external atmosphere pressure force value of integral battery door group, each list The temperature value of set of cells, the magnitude of voltage of the cell of single battery group, the soc value of airplane power source and airplane power source battery soh value Send to host computer.

Charging/discharging voltage measurement module, for gathering the charging total voltage of integral battery door group and the integral battery door of airplane power source The electric discharge total voltage of group, and it is sent to a/d modular converter.

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

In present embodiment, discharge voltage measuring circuit as shown in Fig. 2 include the first operational amplifier u24b, first every From device u23 and the second operational amplifier u24a.The positive input terminal of the first operational amplifier u24b connects aviation by bat+ pin The integral battery door group two ends of power supply, the fd_ai_1 of the outfan connection first isolator u23 of the first operational amplifier u24b draws Foot, the fd_ai_2 pin of the first isolator u23 connects the positive input terminal of the second operational amplifier u24a, the second operational amplifier The outfan of u24a connects the fd_v pin of ad conversion chip u25.

In present embodiment, charging voltage measuring circuit as shown in figure 3, include the 3rd operational amplifier u14b, second every From device u23 and four-operational amplifier u14a.The positive input terminal of the 3rd operational amplifier u14b connects aviation electricity by c+ pin The integral battery door group two ends in source, the outfan 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, four-operational amplifier u14a Outfan connect ad conversion chip u25 cd_v pin.

In present embodiment, the first isolator u23 and the second isolator u13 all using model iso124 isolator, One operational amplifier u24b, the second operational amplifier u24a, the 3rd operational amplifier u14b and four-operational amplifier u14a are equal It is model opa2340 operational amplifier using signal.

Charging and discharging currents measurement module, the charging total current for gathering the integral battery door group of airplane power source is always electric with electric discharge Stream, and it is sent to a/d modular converter.

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

In present embodiment, discharge current measuring circuit is as shown in figure 4, include the 5th operational amplifier u15d and the 6th fortune Calculate amplifier u15c.The positive input terminal of the 5th operational amplifier u15d connects the integral battery door of airplane power source by Hall element Group load, the outfan of the 5th operational amplifier u15d connects the positive input terminal of the 6th operational amplifier u15c, and the 6th computing is put The outfan of big device u15c connects the fd_c pin of ad conversion chip u25.

In present embodiment, charging current measuring circuit is as shown in figure 5, include the 7th operational amplifier u15b and the 8th fortune Calculate amplifier u15a.The positive input terminal of the 7th operational amplifier u15b connects the integral battery door of airplane power source by Hall element Group load, the outfan of the 7th operational amplifier u15b connects the positive input terminal of the 8th operational amplifier u15a, and the 8th computing is put The outfan of big device u15a connects the cd_c pin of ad conversion chip u25.

In present embodiment, choose the Hall element of model hta2020, the 5th operational amplifier u15d, the 6th fortune Calculate amplifier u15c, the model of the 7th operational amplifier u15b and the 8th operational amplifier u15a is opa4227 operation amplifier Device.

A/d modular converter, as shown in fig. 6, adopting 16 high accuracy ad conversion chip u25 of model ads1115, is used for The charging total voltage of the integral battery door group of the airplane power source of collection, electric discharge total voltage, charging total current and electric discharge total current are entered Row analog digital conversion, and will be always electric to the charging total voltage value of the integral battery door group of the airplane power source of conversion, electric discharge total voltage value, charging Flow valuve and electric discharge total current value are sent to main controller module by iic bus.

The fd_v pin of ad conversion chip ads1115 connects the second operational amplifier u24a's of discharge voltage measuring circuit Outfan, the cd_v pin of ad conversion chip ads1115 connects the four-operational amplifier u14a's of charging voltage measuring circuit Outfan, the fd_c pin of ad conversion chip ads1115 connects the 6th operational amplifier u15c's of discharge current measuring circuit Outfan, the cd_v pin of ad conversion chip ads1115 connects the 8th operational amplifier u15a's of charging current measuring circuit Outfan, the ad_scl pin of ad conversion chip ads1115, ad_sda pin and ad_state pin connect master controller respectively The input of module.

16 high accuracy ad conversion chip ads1115, execution switching rate is up to 860 samples per second to be had on a piece Programmable gain amplifier (pga), can measure big signal and small-signal with high-resolution, ads1115 also have one defeated Enter multiplexer (mux), it is possible to provide 2 Differential Input or 4 single ended input.Present embodiment is divided using single-ended input fashion Four tunnels measure charging total voltage, electric discharge total voltage, charging total current and electric discharge total current respectively, and voltage with the accuracy of electric current is The estimation of airplane power source set of cells soc and soh provides accuracy guarantee.Through experiment measurement, the measurement essence of set of cells total current Degree reaches ＜ 3%, and the certainty of measurement of assembled battery total voltage reaches ＜ 2%.

Over-voltage over-current protection module is as shown in fig. 7, be used for the control signal according to main controller module, in airplane power source When overvoltage, excessively stream in the cell of integral battery door group or single battery group, the break-make of control contactor module, realized pressing through Stream protection.

Over-voltage over-current protection module, including photoelectrical coupler u22, the first audion q5 and the second audion q4, also includes First diode d9 and the second diode d4.

In present embodiment, model tlp521_2 of photoelectrical coupler u22, the first audion q5 and the second audion q4 Model be tip41c, model in4148 of the first diode d9 and the second diode d4.

The fd_do_1 pin of photoelectrical coupler u22 and fd_do_2 pin connect main controller module, photoelectrical coupler u22 Fd_1 pin connect the base stage of the first audion q5, the colelctor electrode of the first audion q5 connects the positive pole of the first diode d9, The electric discharge direct current that the colelctor electrode of the first audion q5 connects contact modules with the junction point of the positive pole of the first diode d9 contacts The fd_jk1 pin of device, the grounded emitter of the first audion q5, the negative pole of the first diode d9 connects+24v input power, photoelectricity The cd_1 pin of bonder u22 connects the base stage of the second audion q4, and the colelctor electrode of the second audion q4 connects the second diode The positive pole of d4, the colelctor electrode of the second audion q4 is connected the charging of contact modules with the junction point of the positive pole of the second diode d4 The cd_jk1 pin of D.C. contactor, the grounded emitter of the second audion q4, the negative pole of the second diode d4 connects+24v input Power supply.

Can bus, as shown in figure 8, adopting high speed can isolated transceiver u2 of model ctm1050t, is used for realizing master control Device module processed and the communication of host computer.The can_t1 pin of high speed can isolated transceiver u2 and can_r pin connect master controller Module, the can_gnd pin ground connection of high speed can isolated transceiver u2, canh the and canl pin of high speed can isolated transceiver u2 Host computer is connected by usb-can transceiver.

In present embodiment, from two pieces of high speed can isolated transceivers ctm1050t, one piece is used for proper communication, another Block is standby.

Air pressure acquisition module, using the baroceptor of model bmp085, for gathering the integral battery door of airplane power source The external atmosphere pressure force value of group, and it is sent to main controller module.The high precision of baroceptor bmp085, power consumption are low, pass through Iic bus is connected with main controller module, and the external atmospheric pressure of the integral battery door group of collection is transmitted directly to master controller Module is processed.

Isospi modular converter is as shown in figure 9, be used for realizing the phase of standard spi of standard spi of four-wire system and two-wire system Mutually convert, realize the communication between main controller module and multiple daughter board control module.

Isospi modular converter, including isolated communication interface u11 of isospi and isolating transformer u12.

In present embodiment, model ltc6820fa of isolated communication interface u11 of isospi, function is by four-wire system Standard spi be converted into standard spi of two-wire system, model hx1188 of isolating transformer u12, function is enhancing signal intensity Improve transmission range, so that die terminals is isolated prevents external interference from harassing with signal.

The iso_mosi pin of isolated communication interface u11 of isospi, iso_miso pin, iso_sck pin and iso_/ Cs pin connects main controller module, and the ip pin of isolated communication interface u11 of isospi and im pin connect isolation respectively and become The ip pin of depressor u12 and im pin, iso_ip the and iso_im pin of isolating transformer u12 and the iso_ of daughter board control module Ip with iso_im is connected.

Daughter board control module, using the linear6804-2 multiple batteries group monitor of linear company, for collection boat The monomer battery voltage value of the single battery group of empty power supply, by the monomer battery voltage value of the single battery group of airplane power source and reception The temperature value of the single battery group of airplane power source is sent to main controller module；According to main controller module control signal to monocell The cell of group carries out balancing energy control.

Set of cells monitor linear6804-2 can measure the up to voltage of 12 Stringing cells having less than 1.2mv's Overall measurement error, can in completion system within 290 μ s all batteries measurement, using a kind of multiaddress configuration by the way of will lead Controller module is connected with 8 pieces of daughter board control modules, can gather totally 96 section monomer battery voltage, and each cell can be entered Row balancing energy controls.When main controller module too high, the main control that the monomer battery voltage that daughter board control module passes back is detected Device module will send discharge signal to daughter board control module, and daughter board control module drives discharge tube by driving chip, to phase The cell answered carries out electric discharge and realizes energy content of battery equilibrium.

Temperature-measuring module, using the critesistor of model ntc-mf52at, for gathering the monocell of airplane power source The temperature value of group, and it is sent to daughter board control module.

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

Contact modules, including two D.C. contactors: charging D.C. contactor and electric discharge D.C. contactor, charging direct current Catalyst is the D.C. contactor of model szj100a with electric discharge D.C. contactor.

The input of the input of charging D.C. contactor and electric discharge D.C. contactor connects over-voltage over-current protection module Outfan, the outfan of charging D.C. contactor connects the battery charger of airplane power source battery, and discharge the defeated of D.C. contactor Go out the load that end connects airplane power source battery.

Host computer, from computer, for showing charging total voltage value, the integral battery door of the integral battery door group of airplane power source The electric discharge total voltage value of group, the charging total current value of integral battery door group, the electric discharge total current value of integral battery door group, integral battery door group External atmosphere pressure force value, the temperature value of each single battery group, the magnitude of voltage of the cell of single battery group, airplane power source battery Soc value and airplane power source battery soh value.

This system also includes power subsystem as shown in Figure 10, using the voltage isolating converter of model pv10-27b24 U16, for by the voltage conversion of airplane power source battery be 24v voltage, then by 24v voltage conversion be each module of main control unit and Monitoring subelement each module required voltage, is each module of main control unit and the monitoring each module for power supply of subelement.Voltage isolation turns + vin the pin of parallel operation u16 and the integral battery door group of-vin pin connection airplane power source ,+the vo of voltage isolating converter u16 draws Foot provides+24v voltage to connect to the power end of main controller module.

The method that airplane power source battery management is carried out using airplane power source battery management system, as shown in figure 11, including with Lower step:

Step 1: in airplane power source cell operations, charging/discharging voltage measurement module Real-time Collection airplane power source whole The charging total voltage of body set of cells and electric discharge total voltage, charging and discharging currents measurement module gathers the integral battery door group of airplane power source Charging total current and electric discharge total current, a/d modular converter will be total to the charging total voltage of integral battery door group, electric discharge total voltage, charging Electric current and electric discharge total current carry out analog digital conversion, and by the charging total voltage value of the integral battery door group of the airplane power source of conversion, put Electric 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 transmit To main controller module.

Step 3: each temperature-measuring module gathers the temperature value of each single battery 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 single battery group of corresponding airplane power source, will navigate The temperature value of the single battery group of the monomer battery voltage value of the single battery group of empty power supply and airplane power source is sent to master controller mould Block.

Step 5: the charging total voltage value of integral battery door group of the airplane power source according to collection for the main controller module, overall electricity The electric discharge total voltage value of pond group, the charging total current value of integral battery door group, the electric discharge total current value of integral battery door group and monocell The monomer battery voltage value of group carries out voltage, current detecting, and sends a control signal to the control contact of over-voltage over-current protection module The break-make of device module, realizes the over-voltage over-current protection of airplane power source battery.

Step 5.1: set the upper voltage limit threshold value of cell, the voltage of the cell of single battery group of single battery group Lower threshold, integral battery door group discharge and recharge total voltage upper limit threshold, integral battery door group discharge and recharge total voltage lower threshold, overall electricity Pond 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 single battery group setting as 4.25v, single battery group The lower voltage limit threshold value of cell is 2.5v, and 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, and integral battery door group discharge and recharge total current upper limit threshold is 125a, and integral battery door group is filled Electric discharge total current lower threshold is 12.5a.

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

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

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 When, main controller module sends a control signal to over-voltage over-current protection module, and control contactor module disconnects airplane power source battery Load.

Step 6: main controller module calculates the monomer electricity of single battery group according to the magnitude of voltage of the cell of single battery group The voltage deviation in pond, send control signal to daughter board control module, daughter board control module carries out energy to the cell of single battery group Amount Balance route.

Step 6.1: set the cell upper deviation threshold value of single battery group.

In present embodiment, the cell upper deviation threshold value of the single battery group setting is as 0.005v.

Step 6.2: when the voltage deviation of the cell of single battery group is more than the cell upper deviation of single battery group During threshold value, main controller module sends a control signal to daughter board control module, the daughter board control module monocell excessive to voltage The cell of group is discharged.

Step 7: main controller module is according to the charging total voltage of the integral battery door group of the airplane power source of Real-time Collection, entirety The electric discharge total voltage of set of cells, 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 carries out soc value and the estimation of airplane power source battery soh value of airplane power source battery.

Step 7.1: using randles model, airplane power source battery is modeled, as shown in figure 12, obtains airplane power source Battery randles model.

In Figure 12, uocv (soc) is the open-circuit voltage of airplane power source set of cells, r₀For in airplane power source set of cells ohm Resistance, r₁For the link inertia resistance that discharges, r₂For the link inertia resistance that discharges, c₁For polarization capacity, c₂For polarization capacity, r₁c₁、r₂c₂ Two rc links are in order to describe airplane power source set of cells polarity effect, r₁Voltage be u₁, r₂Voltage be u₂, discharge and recharge is always electric Flow for i, definition timeconstantτ₁=r₁c₁, cloth=r₂c₂, the circuit diagram according to Figure 12 can obtain the function u of soc_ocv(soc) formula is such as Formula (1), formula (2) and formula (3) are as follows:

u_ocv(soc)=ir₀+u₁+u₂(1)

$u_1=u_{1\left(0\right)}{e}^{-\frac{t}{{\mathrm{\τ}}_1}}+{\mathrm{ir}}_1(1-e^{-\frac{t}{{\mathrm{\τ}}_1}})---\left(2\right)$

$u_2=u_{2\left(0\right)}{e}^{-\frac{t}{{\mathrm{\τ}}_2}}+{\mathrm{ir}}_2(1-e^{-\frac{t}{{\mathrm{\τ}}_2}})---\left(3\right)$

Wherein, u₁₍₀₎For voltage u₁Initial value, u₂₍₀₎For voltage u₂Initial value, t be the time.

Function u to soc_ocv(soc) formula carries out ocv-soc matching, introduces natural exponential function and with 6 multinomials Matching, obtains the function u of the soc of matching_ocv(soc) shown in formula such as formula (4):

$u_{ocv}\left(soc\right)=a_0+a_{1}soc+...+a_6{\mathrm{soc}}^6+b_0{e}^{b_{1}soc}---\left(4\right)$

Wherein, α₀、a₁、a₂...a₆、b₀、b₁For the related parameter of airplane power source set of cells self character, real according to design Test: first, airplane power source set of cells trickle is full of, power-off；Secondly, sufficient standing about 3 hours, boat during record soc=100% The open-circuit voltage u of empty power-supply battery group_ocv(soc)；Subsequently, using the method for small current stage discharge, steppingly by aviation electricity The soc of source battery group adjusts to 90%, 80%, 70%..., 20% etc., and after adjustment finishes each time sufficient standing to obtain Take the open-circuit voltage u of accurate airplane power source set of cells_ocv(soc), thus obtaining the ocv-soc of airplane power source set of cells

Curve, then can estimate parameter alpha with least square fitting₀、a₁、a₂...a₆、b₀、b₁.

Ignore the impact of the factors such as temperature, cycle-index, carry out mixed pulses power test (hppc), that is, to airplane power source Set of cells, with constant-current discharge 10s, stands 40s, constant-current charge 10s, stands 40s, record airplane power source battery pack current and end electricity Pressure, is calculated the airplane power source set of cells internal resistance r in airplane power source battery randles model according to parameter identification₀, electric discharge ring Section inertia resistance r₁, electric discharge link inertia resistance r₂, polarization capacity c₁, polarization capacity c₂、r₁Voltage u₁、r₂Voltage u₂With fill Electric discharge total current i.

Considering the impact to airplane power source battery model of airplane power source battery pack temperature and discharge-rate, to matching The function u of soc_ocv(soc) formula (4) is modified, and obtains the function u of the soc of correction_ocv(soc) shown in formula such as formula (5):

$u_{ocv}\left(soc\right)=a_0+a_{1}soc+...+a_6{\mathrm{soc}}^6+b_0{e}^{b_{1}soc}+c_{1}t+c_2{e}^{c_{3}t}+(d_{1}c+d_2{e}^{d_{3}c})---\left(5\right)$

Wherein, c₁、c₂、c₃、d₁、d₂、d₃For airplane power source set of cells empirical curve calibrating parameters, t is integral battery door group temperature Angle value, c is airplane power source set of cells present discharge multiplying power.

Step 7.2: using the charging total voltage of the integral battery door group of collection or electric discharge total voltage as discharge and recharge total voltage, will The charging total current of integral battery door group or electric discharge total current as discharge and recharge total current, by the cell temperature value of single battery group Meansigma methodss as integral battery door group temperature value.

In present embodiment, when airplane power source battery in charging process using the charging total current of integral battery door group as filling Electric discharge total current, using the charging total voltage of integral battery door group as discharge and recharge total voltage, when airplane power source battery is in discharge process The middle electric discharge total current using 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, using the method for EKF, using reality When the discharge and recharge total voltage of the integral battery door group of airplane power source, the discharge and recharge total current of integral battery door group and the integral battery door that gather The temperature value of group estimates the soc value of airplane power source battery and the soh value of airplane power source battery.

Randles model according to airplane power source battery adopts the method for EKF to estimate airplane power source battery Soc value and soh value method as follows:

If the sampling time is δ t, airplane power source set of cells total electricity is q₀, then the soc of airplane power source battery and discharge and recharge Shown in relation between total current i, airplane power source battery electric quantity q such as formula (6):

$soc(k+1)=\frac{q(k+1)}{q_0}=\frac{q\left(k\right)+i\mathrm{\δ}t}{q_0}=soc\left(k\right)+\frac{i\mathrm{\δ}t}{q_0}---\left(6\right)$

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

$\left[\begin{array}{c}soc(k+1)\\ u_1(k+1)\\ u_2(k+1)\end{array}\right]=\left[\begin{array}{ccc}1& 0& 0\\ 0& e^{-\frac{t}{{\mathrm{\τ}}_1}}& 0\\ 0& 0& e^{-\frac{t}{{\mathrm{\τ}}_2}}\end{array}\right]\left[\begin{array}{c}soc\left(k\right)\\ u_1\left(k\right)\\ u_2\left(k\right)\end{array}\right]+\left[\begin{array}{c}\frac{i\mathrm{\δ}t}{q_0}\\ r_1(1-e^{-\frac{t}{{\mathrm{\τ}}_1}})\\ r_2(1-e^{-\frac{t}{{\mathrm{\τ}}_2}})\end{array}\right]i\left(k\right)+\mathrm{\ω}\left(k\right)---\left(7\right)$

u_l(k)=u_ovc(soc(k))+i(k)r₀+u₁(k)+u₂(k)+v(k) (8)

Wherein, u_lIt is driving noise during estimation soc for discharge and recharge total voltage, ω (k), v (k) is amount during estimation soc Survey noise.

Initialization system state variable is x (k)=[soc (k), u₁(k), u₂(k)]^t, input signal u (k)=i (k), measure It is output as z (k)=u_l(k), matrixMatrixWherein, η is discharge and recharge Multiplying power.

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

$c\left(k\right)=\frac{\∂g\left(x\right(k),u(k\left)\right)}{\∂x\left(k\right)}=\[\frac{{\mathrm{du}}_{ocv}\left(soc\right(k\left)\right)}{dsoc\left(k\right)},1,1\]---\left(9\right)$

Using above-mentioned parameter, the recurrence formula according to ekf is iterated, you can the soc value to airplane power source battery in real time Estimated.

By airplane power source set of cells internal resistance r₀As system mode, obtain the state equation of airplane power source set of cells internal resistance such as Shown in formula (10) and formula (11):

r₀ ^k+1=r₀ ^k+r_k(10)

u_l(k)=u_ocv(soc(k))+i(k)r₀+u₁(k)+u₂(k)+n(k) (11)

Wherein, r_kFor driving noise during estimation soh, n (k) is measurement noise during estimation soh.

According to airplane power source set of cells internal resistance r₀Estimate the soh value of airplane power source battery, as shown in formula (12):

$soh=\frac{r_{eol}-r_0}{r_{eol}-r_{new}}---\left(12\right)$

Wherein, r_eolInternal resistance of cell when terminating for airplane power source battery life, r_newDispatch from the factory for airplane power source set of cells When initial internal resistance.

Step 8: the charging total voltage value of integral battery door group of host computer display airplane power source, the electric discharge of integral battery door group are total Magnitude of voltage, the charging total current value of integral battery door group, the electric discharge total current value of integral battery door group, the ambient atmosphere of integral battery door group Pressure value, the temperature value of each single battery group, the magnitude of voltage of the cell of single battery group, the soc value of airplane power source battery and boat The soh value of empty power-supply battery.

Claims (5)

1. a kind of airplane power source battery management system is it is characterised in that include main control unit, monitoring subelement and host computer；

Described main control unit, including 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 all 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, and charging and discharging currents are surveyed The input of amount module connects load, the outfan of charging/discharging voltage measurement module and the charge and discharge of the integral battery door group of airplane power source The outfan of electric current measurement module connects the input of a/d modular converter, and the outfan of a/d modular converter passes through iic bus Connect the first input end of main controller module；The outfan of described air pressure acquisition module connects main control by iic bus Second input of device module；First outfan of described main controller module connects the input of over-voltage over-current protection module End, the outfan of over-voltage over-current protection module connects the input of contact modules, and the outfan of contact modules connects aviation The integral battery door group of power supply；Described main controller module connects host computer by can bus；The output of each temperature-measuring module End connects the first input end of corresponding daughter board control module respectively, and the second input connection of each daughter board control module is corresponding Single battery group two ends；Described each daughter board control module connects isospi modular converter, isospi modular converter by spi bus Main controller module is connected by spi bus；

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

Described power subsystem, using voltage isolating converter, for being main control list by the voltage conversion of airplane power source battery The each module of unit and monitoring subelement each module required voltage, are each module of main control unit and the monitoring each module for power supply of subelement；

Described main controller module, using single-chip microcomputer, the charging for the integral battery door group of the airplane power source according to collection is total Magnitude of voltage, the electric discharge total voltage value of integral battery door group, the charging total current value of integral battery door group, integral battery door group electric discharge always electric The monomer battery voltage value of flow valuve and single battery group carries out voltage, current detecting, and sends a control signal to over-voltage over-current protection Module；The magnitude of voltage of the cell according to single battery group calculates the voltage deviation of the cell of single battery group, and sends control Signal processed is to daughter board control module；The charging total voltage of the integral battery door group of the airplane power source according to Real-time Collection, integral battery door The electric discharge total voltage of 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 carries out soc value and the estimation of airplane power source battery soh value of airplane power source battery；Charging by the integral battery door group of airplane power source Total voltage value, the electric discharge total voltage value of integral battery door group, the charging total current value of integral battery door group, integral battery door group electric discharge total Current value, the external atmosphere pressure force value of integral battery door group, the temperature value of each single battery group, the voltage of the cell of single battery group Value, the soc value of airplane power source and airplane power source battery soh value send to host computer；

Described charging/discharging voltage measurement module, the charging total voltage for gathering the integral battery door group of airplane power source is electric with overall The electric discharge total voltage of pond group, and it is sent to a/d modular converter；

Described charging and discharging currents measurement module, the charging total current for gathering the integral battery door group of airplane power source is electric with overall The electric discharge total current of pond group, and it is sent to a/d modular converter；

Described a/d modular converter, using a/d transducer, the charging for the integral battery door group of the airplane power source that will gather is total Voltage, electric discharge total voltage, charging total current and electric discharge total current carry out analog digital conversion, and the overall electricity by the airplane power source of conversion The charging total voltage value of pond group, electric discharge total voltage value, charging total current value and electric discharge total current value are sent to master by iic bus Controller module；

Described over-voltage over-current protection module, for the control signal according to main controller module, in the overall electricity of airplane power source When overvoltage, excessively stream in the cell of pond group or single battery group, the break-make of control contactor module, realize over-voltage and over-current and protect Shield；

Described air pressure acquisition module, using baroceptor, for gathering the ambient atmosphere of the integral battery door group of airplane power source Pressure value, and it is sent to main controller module；

Described isospi modular converter, for realizing the mutual conversion of standard spi of four-wire system and standard spi of two-wire system, Realize the communication between main controller module and multiple daughter board control module；Described isospi modular converter, including isospi Isolated communication interface and isolating transformer；The input of the isolated communication interface of described isospi is connected by spi bus Main controller module, the outfan of the isolated communication interface of isospi connects the input of isolating transformer, isolating transformer Outfan connects each daughter board control module by spi bus；

Described daughter board control module, using set of cells monitor, for gathering the cell of the single battery group of airplane power source Magnitude of voltage, the temperature value of the monomer battery voltage value of the single battery group of airplane power source and the single battery group of airplane power source is sent to Main controller module；Balancing energy control is carried out to the cell of single battery group according to main controller module control signal；

Described temperature-measuring module, using critesistor, for gathering the temperature value of the single battery group of airplane power source, and transmits To daughter board control module；

Described contact modules, for control the break-make of airplane power source battery and battery charger and airplane power source battery with negative The break-make carrying；

Described host computer, for showing the charging total voltage value of the integral battery door group of airplane power source, the electric discharge of integral battery door group Total voltage value, the charging total current value of integral battery door group, the electric discharge total current value of integral battery door group, integral battery door group extraneous big Air pressure force value, the temperature value of each single battery group, the magnitude of voltage of the cell of single battery group, the soc value of airplane power source battery and Airplane power source battery soh value.

2. airplane power source battery management system according to claim 1 is it is characterised in that described charging/discharging voltage measures Module, including discharge voltage measuring circuit and charging voltage measuring circuit；

Described discharge voltage measuring circuit includes the first operational amplifier, the first isolator and the second operational amplifier；Described The input of the first operational amplifier connect the integral battery door group two ends of airplane power source, the outfan of the first operational amplifier is even Connect the input of the first isolator, the outfan of the first isolator connects the input of the second operational amplifier, the second computing is put The outfan of big device connects the input of a/d modular converter；

Described charging voltage measuring circuit includes the 3rd operational amplifier, the second isolator and four-operational amplifier；Described The input of the 3rd operational amplifier connect the integral battery door group two ends of airplane power source, the outfan of the 3rd operational amplifier is even Connect the input of the second isolator, the outfan of the second isolator connects the input of four-operational amplifier, the 4th computing is put The outfan of big device connects the input of a/d modular converter.

3. airplane power source battery management system according to claim 1 is it is characterised in that described charging and discharging currents measure Module, including discharge current measuring circuit and charging current measuring circuit；

Described discharge current measuring circuit includes the 5th operational amplifier and the 6th operational amplifier；The 5th described computing is put The input of big device connects the integral battery door group load of airplane power source, and the outfan of the 5th operational amplifier connects the 6th computing and puts The input of big device, the outfan of the 6th operational amplifier connects the input of a/d modular converter；

Described charging current measuring circuit includes the 7th operational amplifier and the 8th operational amplifier；The 7th described computing is put The input of big device connects the integral battery door group load of airplane power source, and the outfan of the 7th operational amplifier connects the 8th computing and puts The input of big device, the outfan of the 8th operational amplifier connects the input of a/d modular converter.

4. airplane power source battery management system according to claim 1 is it is characterised in that described over-voltage over-current protection mould Block, including photoelectrical coupler, the first audion and the second audion；

First outfan of described photoelectrical coupler connects the base stage of the first audion, and the second outfan of photoelectrical coupler is even Connect the base stage of the second triode, the colelctor electrode of the colelctor electrode of the first audion and the second audion connects contact modules respectively Input, the emitter stage of described first audion and the grounded emitter of the second audion.

5. the method carrying out airplane power source battery management using the airplane power source battery management system described in claim 1, it is special Levy and be, comprise the following steps:

Step 1: in airplane power source cell operations, the overall electricity of charging/discharging voltage measurement module Real-time Collection airplane power source The charging total voltage of pond group and electric discharge total voltage, charging and discharging currents measurement module gathers the charging of the integral battery door group of airplane power source Total current and electric discharge total current, a/d modular converter by the charging total voltage of integral battery door group, electric discharge total voltage, charging total current Carry out analog digital conversion with electric discharge total current, and will be total to the charging total voltage value of the integral battery door group of the airplane power source of conversion, electric discharge Magnitude of voltage, 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 it is sent to master Controller module；

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

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

Step 5: the charging total voltage value of integral battery door group of the airplane power source according to collection for the main controller module, integral battery door group Electric discharge total voltage value, the charging total current value of integral battery door group, the electric discharge total current value of integral battery door group and single battery group Monomer battery voltage value carries out voltage, current detecting, and sends a control signal to over-voltage over-current protection module control contactor mould The break-make of block, realizes the over-voltage over-current protection of airplane power source battery；

Step 5.1: set the upper voltage limit threshold value of cell, the lower voltage limit of the cell of single battery group of single battery group Threshold value, 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 single battery group monomer battery voltage value be more than single battery group cell upper voltage limit threshold value or When the charging total voltage value of integral battery door group is more than integral battery door group discharge and recharge total voltage upper limit threshold, main controller module sends Control signal disconnects the battery charger of airplane power source battery to over-voltage over-current protection module, control contactor module；

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

Step 5.4: when the charging total current value of integral battery door group is more 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, and control contactor module disconnects the battery of airplane power source battery Charger；

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, and control contactor module disconnects the negative of airplane power source battery Carry；

Step 6: main controller module calculates the cell of single battery group according to the magnitude of voltage of the cell of single battery group Voltage deviation, send control signal to daughter board control module, it is equal that daughter board control module carries out energy to the cell of single battery group Weighing apparatus controls；

Step 6.1: set the cell upper deviation threshold value of single battery group；

Step 6.2: when the voltage deviation of the cell of single battery group is more than the cell upper deviation threshold value of single battery group When, main controller module sends a control signal to daughter board control module, the daughter board control module single battery group excessive to voltage Cell is discharged；

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

Step 7.1: using randles model, airplane power source battery is modeled, obtains airplane power source battery randles mould Type；

Step 7.2: using the charging total voltage of the integral battery door group of collection or electric discharge total voltage as discharge and recharge total voltage, will be overall The charging total current of set of cells or electric discharge total current are as discharge and recharge total current, flat by the cell temperature value of single battery group Average is as the temperature value of integral battery door group；

Step 7.3: according to the randles model of airplane power source battery, using the method for EKF, using adopting in real time The discharge and recharge total voltage of the integral battery door group of airplane power source of collection, the discharge and recharge total current of integral battery door group and integral battery door group Temperature value estimates the soc value of airplane power source battery and the soh value of airplane power source battery；

Step 8: host computer shows the charging total voltage value of integral battery door group of airplane power source, the electric discharge total voltage of integral battery door group Value, the charging total current value of integral battery door group, the electric discharge total current value of integral battery door group, the external atmospheric pressure of integral battery door group Value, the soc value of the temperature value of each single battery group, the magnitude of voltage of the cell of single battery group, airplane power source battery and aviation electricity The soh value of source battery.