CN104967179A - Electric airplane energy management system - Google Patents
Electric airplane energy management system Download PDFInfo
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- CN104967179A CN104967179A CN201510408936.2A CN201510408936A CN104967179A CN 104967179 A CN104967179 A CN 104967179A CN 201510408936 A CN201510408936 A CN 201510408936A CN 104967179 A CN104967179 A CN 104967179A
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Abstract
The invention provides an electric airplane energy management system, belongs to the technical field of energy management, and particularly relates to the electric airplane energy management system. The invention provides the electric airplane energy management system through which safe flight time of an airplane can be pre-judged. The electric airplane energy management system comprises a battery unit current acquisition part, a temperature acquisition part, a battery monitoring part, a controller and battery unit balancing modules. The structural key points of the electric airplane energy management system are that the voltage signal acquisition port of the battery monitoring part is connected with batteries. The batteries are connected in series, and the battery unit balancing modules are connected between the positive and negative electrodes of each battery. The control signal input ports of the battery unit balancing modules are connected with the control signal output port of the battery monitoring part. The current signal output port of the battery unit current acquisition part is connected with the current signal input port of the battery monitoring part. The temperature signal output port of the temperature acquisition part is connected with the temperature signal input port of the battery monitoring part.
Description
Technical field
The invention belongs to energy management technical field, particularly relate to a kind of electric airplane EMS.
Background technology
Electric airplane battery pack is composed in series by multiple single-unit lithium ion battery.Because lithium battery has significantly non-linear, inconsistency and time-varying characteristics, make it in long-term charge and discharge process due to the impact of charge acceptance, self-discharge rate and capacity attenuation speed etc. between each cell, the discreteness between stack battery is easily caused to strengthen, performance degradation aggravates, in series battery, one piece of battery goes wrong and will whole battery pack be caused ineffective, so when battery charging and discharging, must note cell balancing management and monitoring, find that the bad battery unit of performance processes in time, guarantee electric airplane flight safety.
Electric airplane requires more important than automobile to the health status (State-of-Health, SOH) of battery.If battery goes wrong, be exactly great accident concerning aircraft, therefore electric airplane must be paid attention to SOH, and can the battery damaged be taken effective measures.Based on above reason, aircraft is can introduce battery management system to be absolutely necessary to improve safety.
For aircraft, the maximum difference of lithium battery and traditional fuel is exactly the unpredictability of lithium battery energy, it can cause aircraft can know mileage accurately unlike use aviation kerosine, and the consumption of aircraft energy under different state of flights has huge difference in addition; Thus when making aircraft flight, there is danger.
Summary of the invention
The present invention is exactly for the problems referred to above, and providing a kind of can carry out the pre-electric airplane EMS judged to the aircraft safety flight time.
For achieving the above object, the present invention adopts following technical scheme, the present invention includes battery unit current acquisition part, temperature acquisition part, battery cell monitoring part, controller and cell balancing module, the voltage signal acquisition port of its structural feature battery cell monitoring part is connected with battery, serial battery, be connected with described cell balancing module between the both positive and negative polarity of each battery, the control signal input port of cell balancing module is connected with the control signal output port of battery cell monitoring part; The current signal output end mouth of battery unit current acquisition part is connected with the current signal input port of battery cell monitoring part; The temperature signal output port of temperature acquisition part is connected with the temperature signal input mouth of battery cell monitoring part; The signal transmission port of battery cell monitoring part is connected with the signal transmission port of controller.
As a kind of preferred version, battery cell monitoring part of the present invention comprises LTC6804 chip, and temperature acquisition part comprises temperature sensor, LTC6255 chip and 74HC4051 chip, the DRIVE pin of LTC6804 chip is connected with the base stage of NPN triode Q13, the emitter of Q13 is connected with 16 pins of the Vreg pin of LTC6804 chip, electric capacity C28 one end, LTC6255 chip power end, 74HC4051 chip respectively, the C28 other end respectively with the V-of ground wire, electric capacity C27 one end, electric capacity C26 one end, LTC6804 chip
*the ISOMD pin of the V-pin of pin, LTC6804 chip, the SWTEN pin of LTC6804 chip, LTC6804 chip is connected, and the collector electrode of Q13 is connected with the V+ pin of LTC6804 chip by resistance R50, 1 pin of LTC6255 chip respectively with 100 resistance one end, Europe, 4 pins of LTC6255 chip are connected, the 100 Europe resistance other ends respectively with 100nF electric capacity one end, the GPIO1 pin of LTC6804 chip is connected, the 100nF electric capacity other end respectively with ground wire, 2 pins of LTC6255 chip are connected, 3 pins of LTC6255 chip are connected with 3 pins of 74HC4051 chip, 9 of 74HC4051 chip, 10, 11 pins respectively with the GPIO4 of LTC6804 chip, GPIO3, GPIO2 pin correspondence is connected, Y0 ~ Y7 pin of LTC6804 chip is connected with the signal output port of each temperature sensor respectively, described temperature sensor is arranged on battery surface.
As another kind of preferred version, battery unit current acquisition part of the present invention adopts LEM-dhab Hall current sensor, and CH1, CH2 pin of LEM-dhab Hall current sensor is corresponding with GPIO1, GPIO2 pin of LTC6804 chip to be respectively connected.
As another kind of preferred version, cell balancing module of the present invention comprises PMOS, the grid of PMOS is connected with S (n) pin of LTC6804 chip by 3.3K Europe resistance, the source electrode of PMOS is connected with C (n) pin of anode, LTC6804 chip, 10nF electric capacity one end respectively, the 10nF electric capacity other end is connected with C (n-1) pin of 100 resistance one end, Europe, LTC6804 chip respectively, the 100 Europe resistance other ends are connected with 33 resistance one end, Europe, battery cathode respectively, and the 33 Europe resistance other ends are connected with the drain electrode of PMOS.
As another kind of preferred version, the drain electrode of PMOS of the present invention is connected with light-emitting diodes tube anode, light-emitting diodes tube cathode is connected with battery cathode by 475 Europe resistance, C (n) pin of LTC6804 chip is by the first capacity earth, and C (n-1) pin of LTC6804 chip is by the second capacity earth.
As another kind of preferred version, controller of the present invention adopts ATmega16 single-chip microcomputer U1, the display output port of U1 is connected with the display input port of LCD12864 display, 5 pins of U1 are connected with resistance R54 one end, a 1M resistance one end respectively, and the resistance R54 other end is connected with the CSB pin of LTC6804 chip; 6 pins of U1 are connected with resistance R51 one end, and the R51 other end is connected with the SDO pin of LTC6804 chip; 7 pins of U1 are connected with resistance R52 one end, the 2nd 1M resistance one end respectively, and the R52 other end is connected with the SDI pin of LTC6804 chip; 8 pins of U1 are connected with resistance R53 one end, the 3rd 1M resistance one end respectively, and the R53 other end is connected with the SCK pin of LTC6804 chip; A described 1M resistance other end, the 2nd 1M resistance other end, the 3rd 1M resistance other end are connected ground connection.
As another kind of preferred version, 12 pins of U1 of the present invention are connected with a 30pF electric capacity one end, 8M crystal oscillator one end respectively, the one 30pF electric capacity other end is connected with ground wire, the 2nd 30pF electric capacity one end respectively, and the 2nd 30pF electric capacity other end is connected with 13 pins of the 8M crystal oscillator other end, U1 respectively.
As another kind of preferred version, cell voltage when controller survey aircraft of the present invention will start, draws the SOC of battery according to battery open circuit voltage
0, when aircraft travels, integration is carried out to the energy of battery loss, calculates battery electric quantity during flight,
in formula, C
nfor battery rated capacity; V (τ) is cell voltage during τ; I (τ) is charging and discharging currents during τ, is just during electric discharge, is negative during charging; η is coulombic efficiency;
Adopt following discrete state equations and observational equation: X
k+1=A
kx
k+ B
ku
k+ ω
k, Y
k+1=C
kx
k+ D
ku
k+ υ
kin formula, X
kand X
k+1represent T respectively
kand T
kcertain moment quantity of state after moment; u
kfor input variable; A
k, B
k, C
k, D
kbe respectively state matrix, gating matrix, calculation matrix and input/output relation matrix; ω
kand υ
kbe respectively excitation white noise and observation white noise; Y
kand Y
k+1represent T respectively
kand T
kcertain moment observed quantity after moment;
By charge-discharge magnification, battery temperature, self discharge loss and circulating battery number of times because usually revising error: X
k+1=X
k-(η Δ t/CN) I
ky
k, Y
k=Y
0-RI
k-K
1/ X
k-K
2x
k+ K
3lnX
k+ K
4ln (1-X
k), K in formula
ifor the polarization resistance of battery, R is the internal resistance of cell, and X is battery SOC, and Y is cell voltage; Calculation process is as follows: 1) initial value assignment is
2) state variable, mean square deviation error prediction are estimated as
wherein, D
wfor process noise error;
3) gain is
wherein, D
vfor observation noise error;
4) optimal estimation value calculates
Secondly, coulombic efficiency of the present invention comprises charge-discharge magnification, circulating battery number of times, self discharge loss and Temperature affection factor; The flight time is obtained divided by the energy of aircraft attrition by total electricity; Described controller is communicated by CAN with battery cell monitoring part.
In addition, controller of the present invention detects cell voltage, if pressure reduction exceedes the pressure difference of setting between battery, control cell balancing module carries out battery discharge makes electric voltage equalization, until battery pressure reduction is less than the pressure difference of setting; The pressure difference of described setting is 0.01V ~ 0.05V.
Beneficial effect of the present invention.
The present invention by battery unit current acquisition part, temperature acquisition part, battery cell monitoring part, controller and cell balancing module with the use of, Charge Management can be carried out to electric airplane Li-ion batteries piles, extend battery; To battery dump energy estimate, the aircraft safety flight time is judged in advance, be convenient under different flight state give pilot with prompting.
Accompanying drawing explanation
Below in conjunction with the drawings and specific embodiments, the present invention will be further described.Scope is not only confined to the statement of following content.
The integrated circuit figure of Fig. 1 battery cell monitoring chip of the present invention.
The method circuit diagram of electric voltage equalization between Fig. 2 monomer battery voltage collection of the present invention and battery.
Fig. 3 battery temperature measuring circuit figure of the present invention.
Fig. 4 battery current measuring circuit figure of the present invention.
Fig. 5 controller portion parallel circuit of the present invention figure.
Fig. 6 the present invention is at normal temperatures to the voltage-SOC curve that one piece of new lithium battery being full of electricity carries out drawing with a stable current discharge.
Fig. 7 a is the comparison diagram that battery discharges-20 DEG C time and battery discharges under ecotopia.
Fig. 7 b is battery standing about 60 days after the being full of electricity comparison diagrams discharged under ecotopia with battery that discharge afterwards.
Fig. 7 c be battery when discharge and recharge with the comparison diagram of different charge-discharge magnification.
Fig. 7 d is that battery is at the comparison diagram of capacity that repeatedly charges repeatedly.
The general flow chart of Fig. 8 battery electric quantity state pre-estimation of the present invention.
Embodiment
As shown in the figure, the present invention includes battery unit current acquisition part, temperature acquisition part, battery cell monitoring part, controller and cell balancing module, the voltage signal acquisition port of its structural feature battery cell monitoring part is connected with battery, serial battery, be connected with described cell balancing module between the both positive and negative polarity of each battery, the control signal input port of cell balancing module is connected with the control signal output port of battery cell monitoring part; The current signal output end mouth of battery unit current acquisition part is connected with the current signal input port of battery cell monitoring part; The temperature signal output port of temperature acquisition part is connected with the temperature signal input mouth of battery cell monitoring part; The signal transmission port of battery cell monitoring part is connected with the signal transmission port of controller.
Described battery cell monitoring part comprises LTC6804 chip, and temperature acquisition part comprises temperature sensor, LTC6255 chip and 74HC4051 chip, the DRIVE pin of LTC6804 chip is connected with the base stage of NPN triode Q13, the emitter of Q13 is connected with 16 pins of the Vreg pin of LTC6804 chip, electric capacity C28 one end, LTC6255 chip power end, 74HC4051 chip respectively, the C28 other end respectively with the V-of ground wire, electric capacity C27 one end, electric capacity C26 one end, LTC6804 chip
*the ISOMD pin of the V-pin of pin, LTC6804 chip, the SWTEN pin of LTC6804 chip, LTC6804 chip is connected, and the collector electrode of Q13 is connected with the V+ pin of LTC6804 chip by resistance R50, 1 pin of LTC6255 chip respectively with 100 resistance one end, Europe, 4 pins of LTC6255 chip are connected, the 100 Europe resistance other ends respectively with 100nF electric capacity one end, the GPIO1 pin of LTC6804 chip is connected, the 100nF electric capacity other end respectively with ground wire, 2 pins of LTC6255 chip are connected, 3 pins of LTC6255 chip are connected with 3 pins of 74HC4051 chip, 9 of 74HC4051 chip, 10, 11 pins respectively with the GPIO4 of LTC6804 chip, GPIO3, GPIO2 pin correspondence is connected, Y0 ~ Y7 pin of LTC6804 chip is connected with the signal output port of each temperature sensor respectively, described temperature sensor is arranged on battery surface.Temperature has no small impact for the capacity of battery, and in general 25 DEG C of-30 DEG C of battery capacities are maximum, so in order to solve the impact that temperature is estimated SOC, battery context temperature is a very important factor; And battery is when overcharging and cross and putting, temperature may have more violent fluctuation, so battery management system must be monitored the real time temperature of battery.Adopt temperature sensor to carry out temperature acquisition, LTC6804 has temperature acquisition function, sets up multiplex electronics to support more signal number.Temperature sensor is arranged on battery surface, like this can the temperature of each block battery of Measurement accuracy.
LTC6804 is sent to upper process the voltage measured, electric current and battery temperature by SDI, SDO.
Temperature sensor the data measured by a selector, LTC6804 by GPIO3,4, the configuration of 5 chooses required battery temperature, reads temperature by GPIO1.
Described battery unit current acquisition part adopts LEM-dhab Hall current sensor, and CH1, CH2 pin of LEM-dhab Hall current sensor is corresponding with GPIO1, GPIO2 pin of LTC6804 chip to be respectively connected.LEM-dhab Hall current sensor is adopted to carry out current acquisition, this transducer adopts a 5V Power supply, then the magnetic field that the magnetic field that primary current produces at magnetism gathering rings place is produced by a secondary current compensates, its secondary current reflects primary current accurately, and LEM-dhab transducer is converted into secondary current and inputs identical conversion sequence with battery and carry out identical digitized processing by GPIO1 and GPIO2 inputted as ADC.Measure battery charging and discharging electric current by Hall element, export and be sent to LTC6804 by GPIO2, finally all transfer of data to microprocessor.
Described cell balancing module comprises PMOS, the grid of PMOS is connected with S (n) pin of LTC6804 chip by 3.3K Europe resistance, the source electrode of PMOS is connected with C (n) pin of anode, LTC6804 chip, 10nF electric capacity one end respectively, the 10nF electric capacity other end is connected with C (n-1) pin of 100 resistance one end, Europe, LTC6804 chip respectively, the 100 Europe resistance other ends are connected with 33 resistance one end, Europe, battery cathode respectively, and the 33 Europe resistance other ends are connected with the drain electrode of PMOS.Adopt the battery pack monitor chip LTC6804 of single battery, the voltage the overall measurement error had lower than 1.2mV that reach 12 Stringing cells can be measured, single battery voltage measurement scope 0V to 5V.The voltage of all 12 batteries can complete measurement within 290 μ s, and lower data acquisition rate can be selected to suppress to realize strong noise.Bottom battery cathode is connected to C0, and positive pole is connected to C1.By that analogy, top negative pole C11, positive pole C12.The ADC of monitor chip can measure cell voltage accurately.
Balance module: integrated chip takes the method controlling outside MOSFET to carry out equilibrium to battery pack, can obtain larger discharging current, improves discharging efficiency.As shown in Figure 1: integrated chip utilizes the pull-up resistor of S pin inside to drive the grid of the P road ditch MOSFET of external circuit, thus makes electricity transfer to low-voltage battery from high-voltage battery, reaches balanced object.
The drain electrode of described PMOS is connected with light-emitting diodes tube anode, light-emitting diodes tube cathode is connected with battery cathode by 475 Europe resistance, C (n) pin of LTC6804 chip is by the first capacity earth, and C (n-1) pin of LTC6804 chip is by the second capacity earth.
Described controller adopts ATmega16 single-chip microcomputer U1, the display output port of U1 is connected with the display input port of LCD12864 display, 5 pins of U1 are connected with resistance R54 one end, a 1M resistance one end respectively, and the resistance R54 other end is connected with the CSB pin of LTC6804 chip; 6 pins of U1 are connected with resistance R51 one end, and the R51 other end is connected with the SDO pin of LTC6804 chip; 7 pins of U1 are connected with resistance R52 one end, the 2nd 1M resistance one end respectively, and the R52 other end is connected with the SDI pin of LTC6804 chip; 8 pins of U1 are connected with resistance R53 one end, the 3rd 1M resistance one end respectively, and the R53 other end is connected with the SCK pin of LTC6804 chip; A described 1M resistance other end, the 2nd 1M resistance other end, the 3rd 1M resistance other end are connected ground connection.ATmega16 is 8 single-chip microcomputers based on AVRRISC structure of a employing Low-Power CMOS explained hereafter.The core of AVR single chip is bound up at 32 work registers and abundant instruction set, all work registers are all directly connected with ALU (ALU), achieve the operation that (read-write) two independent register are accessed in the instruction performed within a clock cycle simultaneously.Such a construction increases code efficiency, make the time of implementation of most of instruction be only a clock cycle.Therefore, ATmega16 can reach the performance close to 1MIPS/MHz, and the speed of service exceeds 10 times than common CISC single-chip microcomputer.Transfer of data, to ATmega16, after treatment, demonstrates the result of process at LCD12864.
12 pins of described U1 are connected with a 30pF electric capacity one end, 8M crystal oscillator one end respectively, and a 30pF electric capacity other end is connected with ground wire, the 2nd 30pF electric capacity one end respectively, and the 2nd 30pF electric capacity other end is connected with 13 pins of the 8M crystal oscillator other end, U1 respectively.
Cell voltage when described controller survey aircraft will start, draws the SOC0 of battery according to battery open circuit voltage, carry out integration when aircraft travels to the energy of battery loss, calculates battery electric quantity during flight,
in formula, C
nfor battery rated capacity; V (τ) is cell voltage during τ; I (τ) is charging and discharging currents during τ, is just during electric discharge, is negative during charging; η is coulombic efficiency; Because the SOC value of battery, with the voltage in proportion relation of battery, can obtain battery accurate voltage-SOC curve by experiment.
Adopt following discrete state equations and observational equation: X
k+1=A
kx
k+ B
ku
k+ ω
k, Y
k+1=C
kx
k+ D
ku
k+ υ
kin formula, X
kand X
k+1represent T respectively
kand T
kcertain moment quantity of state after moment; u
kfor input variable; A
k, B
k, C
k, D
kbe respectively state matrix, gating matrix, calculation matrix and input/output relation matrix; ω
kand υ
kbe respectively excitation white noise and observation white noise; Y
kand Y
k+1represent T respectively
kand T
kcertain moment observed quantity after moment; Real-time renewal and process can be carried out to the data of collection in worksite.
By charge-discharge magnification, battery temperature, self discharge loss and circulating battery number of times because usually revising error: X
k+1=X
k-(η Δ t/CN) I
ky
k, Y
k=Y
0-RI
k-K
1/ X
k-K
2x
k+ K
3lnX
k+ K
4ln (1-X
k), K in formula
ifor the polarization resistance of battery, R is the internal resistance of cell, and X is battery SOC, and Y is cell voltage; Calculation process is as follows: 1) initial value assignment is
2) state variable, mean square deviation error prediction are estimated as
wherein, D
wfor process noise error;
3) gain is
wherein, D
vfor observation noise error;
4) optimal estimation value calculates
Described coulombic efficiency comprises charge-discharge magnification, circulating battery number of times, self discharge loss and Temperature affection factor; The flight time is obtained divided by the energy of aircraft attrition by total electricity; Described controller is communicated by CAN with battery cell monitoring part.In advance by aircraft flight speed, highly, the measurement of the data such as engine speed, analyzing aircraft should the energy of loss at normal flight; Then by the loss of aircraft state of flight energy now, the total electricity of battery is processed.
CAN communications applications is in battery pack, kernel control chip needs communication in order to the operating state of each battery unit of perception, adopt CAN to make the data communication between cell group real-time, and easily form redundancy structure, improve the reliability of system and the flexibility of system.
Described controller detects cell voltage, if pressure reduction exceedes the pressure difference of setting between battery, control cell balancing module carries out battery discharge makes electric voltage equalization, until battery pressure reduction is less than the pressure difference of setting; The pressure difference of described setting is 0.01V ~ 0.05V.
4 groups of battery pack be made up of 72 pieces of batteries respectively can be adopted to test, and battery pack adopts ferric phosphate lithium cell, and battery voltage is about 300V, and capacity is 35Ah.In order to obtain accurate Fig. 6, with the current discharge of constant 3A at room temperature 25 DEG C.Often release 1% of capacity, after stopping electric discharge, battery standing discharges, until dead battery for 1 hour again.During battery discharge, the voltage of the battery of monitoring battery group monomer, after battery ceiling voltage and minimum voltage have had the gap of 0.05V, has started battery balanced module, until the little 0.01V of battery maximum differential pressure.
In order to solve other the impact of factor of battery.After battery pack is full of electricity, as shown in Figure 7a, other conditions and Fig. 6 constant when, be-20 DEG C of electric discharges in temperature.During battery discharge, the voltage of the battery of monitoring battery group monomer, after battery ceiling voltage and minimum voltage have had the gap of 0.05V, has started battery balanced module, until the little 0.01V of battery maximum differential pressure.Obtain the relation of battery capacity and ambient temperature.
As shown in Figure 7b, leave standstill 60 days after battery is full of electricity after, again battery is discharged.During battery discharge, the voltage of the battery of monitoring battery group monomer, after battery ceiling voltage and minimum voltage have had the gap of 0.05V, has started battery balanced module, until the little 0.01V of battery maximum differential pressure.Obtain battery capacity and the battery relation from loss.
As shown in Figure 7 c, when other conditions and Fig. 6 constant, discharge with the discharge-rate of 0.5C, 1C, 2C, 3C, 5C respectively.During battery discharge, the voltage of the battery of monitoring battery group monomer, after battery ceiling voltage and minimum voltage have had the gap of 0.05V, has started battery balanced module, until the little 0.01V of battery maximum differential pressure.Obtain the relation of battery capacity and charge-discharge magnification.
As shown in figure 7d, under the condition of Fig. 6, to battery fast, endless discharge and recharge.During battery discharge, the voltage of the battery of monitoring battery group monomer, after battery ceiling voltage and minimum voltage have had the gap of 0.05V, has started battery balanced module, until the little 0.01V of battery maximum differential pressure.Obtain the relation of battery capacity and circulating battery number of times.
After obtaining above-mentioned result, the SOC that when aircraft starts, the voltage that obtains of measurements can obtain when aircraft starts according to Fig. 6, then according to voltage, the electric current of measurement during flight, can obtain SOC during aircraft flight.According to the impact of factor each in Fig. 7, to obtaining SOC process, obtain accurate SOC.
In aircraft running test, the height of aircraft, speed, weather, the series data such as wind speed and engine speed are gathered.According to state during aircraft flight, draw an accurate flight energy loss; The loss of the energy content of battery under this kind of state of flight can be learnt by flight energy loss, thus draw the cruising time under this state of aircraft.Finally the aircraft safety flight time is judged in advance, and give pilot with prompting.
Experimental data of the present invention is not limited to above-described embodiment, and the model of such as electric airplane is different, the kind of battery, and model is different etc.In addition, battery balanced pressure reduction also can change along with electronic and demand that is battery.
Be understandable that, above about specific descriptions of the present invention, the technical scheme described by the embodiment of the present invention is only not limited to for illustration of the present invention, those of ordinary skill in the art is to be understood that, still can modify to the present invention or equivalent replacement, to reach identical technique effect; Needs are used, all within protection scope of the present invention as long as meet.
Claims (10)
1. electric airplane EMS, comprise battery unit current acquisition part, temperature acquisition part, battery cell monitoring part, controller and cell balancing module, it is characterized in that the voltage signal acquisition port of battery cell monitoring part is connected with battery, serial battery, be connected with described cell balancing module between the both positive and negative polarity of each battery, the control signal input port of cell balancing module is connected with the control signal output port of battery cell monitoring part; The current signal output end mouth of battery unit current acquisition part is connected with the current signal input port of battery cell monitoring part; The temperature signal output port of temperature acquisition part is connected with the temperature signal input mouth of battery cell monitoring part; The signal transmission port of battery cell monitoring part is connected with the signal transmission port of controller.
2. electric airplane EMS according to claim 1, it is characterized in that described battery cell monitoring part comprises LTC6804 chip, temperature acquisition part comprises temperature sensor, LTC6255 chip and 74HC4051 chip, the DRIVE pin of LTC6804 chip is connected with the base stage of NPN triode Q13, the emitter of Q13 is connected with 16 pins of the Vreg pin of LTC6804 chip, electric capacity C28 one end, LTC6255 chip power end, 74HC4051 chip respectively, the C28 other end respectively with the V-of ground wire, electric capacity C27 one end, electric capacity C26 one end, LTC6804 chip
*the ISOMD pin of the V-pin of pin, LTC6804 chip, the SWTEN pin of LTC6804 chip, LTC6804 chip is connected, and the collector electrode of Q13 is connected with the V+ pin of LTC6804 chip by resistance R50, 1 pin of LTC6255 chip respectively with 100 resistance one end, Europe, 4 pins of LTC6255 chip are connected, the 100 Europe resistance other ends respectively with 100nF electric capacity one end, the GPIO1 pin of LTC6804 chip is connected, the 100nF electric capacity other end respectively with ground wire, 2 pins of LTC6255 chip are connected, 3 pins of LTC6255 chip are connected with 3 pins of 74HC4051 chip, 9 of 74HC4051 chip, 10, 11 pins respectively with the GPIO4 of LTC6804 chip, GPIO3, GPIO2 pin correspondence is connected, Y0 ~ Y7 pin of LTC6804 chip is connected with the signal output port of each temperature sensor respectively, described temperature sensor is arranged on battery surface.
3. electric airplane EMS according to claim 2, it is characterized in that described battery unit current acquisition part adopts LEM-dhab Hall current sensor, CH1, CH2 pin of LEM-dhab Hall current sensor is corresponding with GPIO1, GPIO2 pin of LTC6804 chip to be respectively connected.
4. electric airplane EMS according to claim 2, it is characterized in that described cell balancing module comprises PMOS, the grid of PMOS is connected with S (n) pin of LTC6804 chip by 3.3K Europe resistance, the source electrode of PMOS respectively with anode, C (n) pin of LTC6804 chip, 10nF electric capacity one end is connected, the 10nF electric capacity other end respectively with 100 resistance one end, Europe, C (n-1) pin of LTC6804 chip is connected, the 100 Europe resistance other ends respectively with 33 resistance one end, Europe, battery cathode is connected, the 33 Europe resistance other ends are connected with the drain electrode of PMOS.
5. electric airplane EMS according to claim 4, it is characterized in that the drain electrode of described PMOS is connected with light-emitting diodes tube anode, light-emitting diodes tube cathode is connected with battery cathode by 475 Europe resistance, C (n) pin of LTC6804 chip is by the first capacity earth, and C (n-1) pin of LTC6804 chip is by the second capacity earth.
6. electric airplane EMS according to claim 2, it is characterized in that described controller adopts ATmega16 single-chip microcomputer U1, the display output port of U1 is connected with the display input port of LCD12864 display, 5 pins of U1 are connected with resistance R54 one end, a 1M resistance one end respectively, and the resistance R54 other end is connected with the CSB pin of LTC6804 chip; 6 pins of U1 are connected with resistance R51 one end, and the R51 other end is connected with the SDO pin of LTC6804 chip; 7 pins of U1 are connected with resistance R52 one end, the 2nd 1M resistance one end respectively, and the R52 other end is connected with the SDI pin of LTC6804 chip; 8 pins of U1 are connected with resistance R53 one end, the 3rd 1M resistance one end respectively, and the R53 other end is connected with the SCK pin of LTC6804 chip; A described 1M resistance other end, the 2nd 1M resistance other end, the 3rd 1M resistance other end are connected ground connection.
7. electric airplane EMS according to claim 6, it is characterized in that 12 pins of described U1 are connected with a 30pF electric capacity one end, 8M crystal oscillator one end respectively, the one 30pF electric capacity other end is connected with ground wire, the 2nd 30pF electric capacity one end respectively, and the 2nd 30pF electric capacity other end is connected with 13 pins of the 8M crystal oscillator other end, U1 respectively.
8. electric airplane EMS according to claim 1, is characterized in that cell voltage when described controller survey aircraft will start, draws the SOC of battery according to battery open circuit voltage
0, when aircraft travels, integration is carried out to the energy of battery loss, calculates battery electric quantity during flight,
in formula, C
nfor battery rated capacity; V (τ) is cell voltage during τ; I (τ) is charging and discharging currents during τ, is just during electric discharge, is negative during charging; η is coulombic efficiency;
Adopt following discrete state equations and observational equation: X
k+1=A
kx
k+ B
ku
k+ ω
k, Y
k+1=C
kx
k+ D
ku
k+ υ
kin formula, X
kand X
k+1represent T respectively
kand T
kcertain moment quantity of state after moment; u
kfor input variable; A
k, B
k, C
k, D
kbe respectively state matrix, gating matrix, calculation matrix and input/output relation matrix; ω
kand υ
kbe respectively excitation white noise and observation white noise; Y
kand Y
k+1represent T respectively
kand T
kcertain moment observed quantity after moment;
By charge-discharge magnification, battery temperature, self discharge loss and circulating battery number of times because usually revising error: X
k+1=X
k-(η Δ t/C
n) I
ky
k, Y
k=Y
0-RI
k-K
1/ X
k-K
2x
k+ K
3lnX
k+ K
4ln (1-X
k), K in formula
ifor the polarization resistance of battery, R is the internal resistance of cell, and X is battery SOC, and Y is cell voltage; Calculation process is as follows: 1) initial value assignment is
2) state variable, mean square deviation error prediction are estimated as
wherein, D
wfor process noise error;
3) gain is
Wherein, D
vfor observation noise error;
4) optimal estimation value calculates
9. electric airplane EMS according to claim 8, is characterized in that described coulombic efficiency comprises charge-discharge magnification, circulating battery number of times, self discharge loss and Temperature affection factor; The flight time is obtained divided by the energy of aircraft attrition by total electricity; Described controller is communicated by CAN with battery cell monitoring part.
10. electric airplane EMS according to claim 1, it is characterized in that described controller detects cell voltage, if pressure reduction exceedes the pressure difference of setting between battery, control cell balancing module carries out battery discharge makes electric voltage equalization, until battery pressure reduction is less than the pressure difference of setting; The pressure difference of described setting is 0.01V ~ 0.05V.
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| CN107219469A (en) * | 2016-11-17 | 2017-09-29 | 深圳市海盈科技股份有限公司 | Suitable for the continuation of the journey power predicating method of unmanned machine battery |
| TWI711832B (en) * | 2020-02-25 | 2020-12-01 | 龍華科技大學 | A battery charging method based on model predictive control |
| CN112874378A (en) * | 2021-01-27 | 2021-06-01 | 一汽解放汽车有限公司 | Method, device and equipment for processing battery sampling temperature and vehicle |
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| CN204947627U (en) * | 2015-07-13 | 2016-01-06 | 沈阳航空航天大学 | A kind of electric airplane EMS |
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