CN107526042A - High-power lithium battery performance evaluation instrument - Google Patents
High-power lithium battery performance evaluation instrument Download PDFInfo
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- CN107526042A CN107526042A CN201710763466.0A CN201710763466A CN107526042A CN 107526042 A CN107526042 A CN 107526042A CN 201710763466 A CN201710763466 A CN 201710763466A CN 107526042 A CN107526042 A CN 107526042A
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- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 title claims abstract description 25
- 229910052744 lithium Inorganic materials 0.000 title claims abstract description 25
- 238000011156 evaluation Methods 0.000 title claims abstract description 7
- 238000010438 heat treatment Methods 0.000 claims abstract description 10
- 238000005057 refrigeration Methods 0.000 claims abstract description 8
- 210000004027 cell Anatomy 0.000 claims description 68
- 238000001514 detection method Methods 0.000 claims description 36
- 238000012544 monitoring process Methods 0.000 claims description 10
- 239000003990 capacitor Substances 0.000 claims description 9
- 238000012360 testing method Methods 0.000 claims description 7
- 108010001267 Protein Subunits Proteins 0.000 claims description 6
- BASFCYQUMIYNBI-UHFFFAOYSA-N platinum Chemical compound [Pt] BASFCYQUMIYNBI-UHFFFAOYSA-N 0.000 claims description 6
- 230000005611 electricity Effects 0.000 claims description 3
- 238000000034 method Methods 0.000 claims description 3
- 239000000178 monomer Substances 0.000 claims description 3
- 229910052697 platinum Inorganic materials 0.000 claims description 3
- 230000008450 motivation Effects 0.000 claims 1
- 238000004891 communication Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 238000002955 isolation Methods 0.000 description 2
- 230000035945 sensitivity Effects 0.000 description 2
- 240000007594 Oryza sativa Species 0.000 description 1
- 235000007164 Oryza sativa Nutrition 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000003111 delayed effect Effects 0.000 description 1
- 238000013021 overheating Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 235000009566 rice Nutrition 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/36—Arrangements for testing, measuring or monitoring the electrical condition of accumulators or electric batteries, e.g. capacity or state of charge [SoC]
- G01R31/396—Acquisition or processing of data for testing or for monitoring individual cells or groups of cells within a battery
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/36—Arrangements for testing, measuring or monitoring the electrical condition of accumulators or electric batteries, e.g. capacity or state of charge [SoC]
- G01R31/378—Arrangements for testing, measuring or monitoring the electrical condition of accumulators or electric batteries, e.g. capacity or state of charge [SoC] specially adapted for the type of battery or accumulator
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/36—Arrangements for testing, measuring or monitoring the electrical condition of accumulators or electric batteries, e.g. capacity or state of charge [SoC]
- G01R31/382—Arrangements for monitoring battery or accumulator variables, e.g. SoC
- G01R31/3842—Arrangements for monitoring battery or accumulator variables, e.g. SoC combining voltage and current measurements
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Secondary Cells (AREA)
Abstract
The stability and quality of electric unit and module for power supply are needed to other to stablize the operating temperature of unmanned machine battery and then lifting it, the invention provides a kind of high-power lithium battery performance evaluation instrument, thermostatic control for the high-power lithium battery of unmanned plane, the lithium battery includes multiple battery cells, the unmanned plane includes the first constant temperature unit, second constant temperature unit and the 3rd constant temperature unit, first constant temperature unit, second constant temperature unit and the 3rd constant temperature unit can be used in heating mode of operation or refrigeration work pattern and be set in turn in outside batteries from inside to outside, the analytical instrument includes：Sensing unit, for sensing the electrically and physically parameter of lithium battery and unmanned plane；Analytic unit, for carrying out thermostatic control to lithium battery according to the result that sensing unit senses.
Description
Technical field
The present invention relates to flying vehicles control technical field, more particularly, to a kind of high-power lithium battery performance evaluation instrument
Device.
Background technology
Unmanned plane has much compared with the advantages of traditional approach, as portability is strong, manipulation is simple, cost is cheap, transmitting and recovery
Occupied ground is small etc..The occasion applied with unmanned plane gradually increases, and its contingency question also gradually emerges：For example it is less than
Subzero 10 DEG C of environment can cause dynamic lithium battery hydraulic performance decline more than 50%, but current most of unmanned planes are not for dynamic
The universal practical solution that power lithium battery works at low ambient temperatures.In addition, unmanned plane is more frequent in variation of ambient temperature
Region when, the operating ambient temperature of its high power battery may also change frequently, and this had both been unfavorable for battery and brought into normal play in itself
Performance, also it is unfavorable for its supply engine and communication equipment with stable electric power.
Moreover, unmanned plane battery management unit of the prior art or device are typically only capable to monitor battery temperature and residue electricity
Amount, it can not meet that unmanned plane flies control demand.
The content of the invention
Stability of electric unit and module for power supply is needed to other to stablize the operating temperature of unmanned machine battery and then lifting it
And quality, the invention provides a kind of high-power lithium battery performance evaluation instrument, the perseverance for the high-power lithium battery of unmanned plane
Temperature control system, the lithium battery include multiple battery cells, and the unmanned plane includes the first constant temperature unit, the second constant temperature unit and the
Three constant temperature units, first constant temperature unit, the second constant temperature unit and the 3rd constant temperature unit can be used in heating mode of operation
Or refrigeration work pattern and outside batteries are set in turn in from inside to outside, the analytical instrument includes：
Sensing unit, for sensing the electrically and physically parameter of lithium battery and unmanned plane；
Analytic unit, for carrying out thermostatic control to lithium battery according to the result that sensing unit senses.
Further, the sensing unit includes：
Battery cell detection unit, for detecting the temperature information and electric parameter information of battery cell；
Unmanned electrical-mechanical detection unit, for detecting unmanned plane electric parameter information；
Unmanned plane during flying Condition Monitoring Unit, for monitoring unmanned plane during flying state parameter information；
And the analytic unit includes：
Battery temperature control unit, for the temperature information according to battery cell and electric parameter information, unmanned electrical-mechanical
Parameter information and unmanned plane during flying state parameter information determine the first constant temperature unit, the second constant temperature unit and the 3rd constant temperature unit
Mode of operation, wherein the first constant temperature unit is opposite with the mode of operation of the 3rd constant temperature unit.
Further, the battery cell detection unit includes：
Battery cell current detecting subelement, for detecting the charging current and discharge current of each battery cell；
Battery cell voltage detecting subelement, for detecting the charging voltage and discharge voltage of each battery cell；
Battery cell temperature detection subelement, for detecting each battery cell surface temperature；
Interface temperature detection sub-unit, for detecting the electric power output interface temperature of battery.
Further, the unmanned electrical-mechanical detection unit includes：
Power determination subelement, the input voltage and input current of unmanned vehicle engine are input to for detecting；
Revolution detection sub-unit, for detecting the revolution of unmanned vehicle engine.
Further, the unmanned plane during flying Condition Monitoring Unit includes：
GPS subelements, for obtaining altitude data and obtaining flying speed data；
The sub- detection unit of unmanned plane environment temperature, for detecting the environment temperature of unmanned plane local environment.
Further, the battery temperature control unit includes：
Motion state detection subelement, for according to altitude data and flying speed data, whether determining unmanned plane
Moving, and if whether be in state of flight in motion；
First test subelement, for when in state of flight, if the first constant temperature unit works in heating mode of operation
And thermostat temperature is arranged at T1, then at the first moment, nothing is determined according to the input voltage of unmanned vehicle engine and input current
The input power P of man-machine engineInput 1And determine therefrom that input power PInput 1With the ratio L of this moment engine revolution1；According to
The charging current and discharge current and charging voltage and discharge voltage of each battery cell, determine the discharge capacity of each battery cell
Difference between amount and charging capacitor amount, by each difference divided by the temperature of corresponding battery cell, and determines therefrom that to obtain
Ratio between root-mean-square value E1And the ratio R of this moment environment temperature and the mean-square value1；At the second moment, according to nobody
The input voltage and input current of machine engine determine the input power P of unmanned vehicle engineInput 2And determine therefrom that input power
PInput 2With the ratio L of this moment engine revolution2；According to the charging current of each battery cell and discharge current and charging voltage
And discharge voltage, the difference between the discharge capacity of each battery cell and charging capacitor amount is determined, by each difference divided by therewith
The temperature of corresponding battery cell, and determine therefrom that the root-mean-square value E between obtained ratio2And this moment environment temperature with
The ratio R of the mean-square value2, second moment is after the first moment, when altitude data and flying speed data
Rate of change exceedes a certain moment after presetting the first rate of change and in the second moment unmanned plane still in state of flight respectively；
Second test subelement, for being preset greatly when the rate of change of altitude data and flying speed data exceedes respectively
In the 3rd moment after the second rate of change of the first rate of change and when the 3rd moment unmanned plane is still in state of flight, according to
The input voltage and input current of unmanned vehicle engine determine the input power P of unmanned vehicle engineInput 3And determine therefrom that input
Power PInput 3With the ratio L of this moment engine revolution3；According to the charging current of each battery cell and discharge current and charging
Voltage and discharge voltage, determine the difference between the discharge capacity of each battery cell and charging capacitor amount, by each difference divided by
The temperature of corresponding battery cell, and determine therefrom that the root-mean-square value E between obtained ratio3And this moment environment temperature
Degree and the ratio R of the mean-square value3；
Difference determination subelement, for determining temperature of second constant temperature unit at the first moment, the second moment and the 3rd moment
Degree；It is determined that ((L1/R1)+(L2/R2))/(2×(L3/R3)) this ratio and | (electric power output interface temperature/environment temperature
)First moment- (electric power output interface temperature/environment temperature)Second moment| whether ratio D between this difference is higher than first threshold and small
In Second Threshold, wherein " | | " represent signed magnitude arithmetic(al)；
Second constant temperature unit sets subelement, for when difference D is higher than first threshold and when being less than Second Threshold, holding the
The thermostat temperature T1 of one constant temperature unit simultaneously sets the mode of operation of the second constant temperature unit to heat mode of operation, wherein when | D |>1
When the thermostat temperature T2=T1/ of the second constant temperature unit is set | D | and work as | D |<The thermostat temperature T2 of second constant temperature unit is set when 1
=T1 × | D |；When difference D is more than Second Threshold, then change the mode of operation of the first constant temperature unit as refrigeration work pattern and
Thermostat temperature is T1；When | D |>Set when 1 the thermostat temperature T2=environment temperatures of second constant temperature unit/| D | and work as | D |<Set when 1
Put the thermostat temperature T2=environment temperatures of the second constant temperature unit × | D |.
Further, the detection to the temperature of each battery cell is by bridge-type balancing method and discharge circuit, using external temperature
Spend collection of the sensor realization to temperature.
Further, the detection to the temperature of the electric power output interface of battery is realized by platinum resistance temperature sensor
's.
Further, the charge and discharge electric current of each battery cell is calculated by high-precision current integral way.
Further, first moment is at the time of electric power output interface temperature reaches temperature value T1 and at the moment
Unmanned plane is still in state of flight.
The beneficial effects of the invention are as follows：
(1) present invention using to multiple battery cells monitoring by the way of can improve battery surface temperature accuracy of detection,
The degree of accuracy and sensitivity, so as to as far as possible reduce heating retardation effect cell operating conditions temperature adjustment is brought inaccuracy and
The property delayed influences；
(2) present invention is not only based on prior art and improves accuracy of detection and the degree of accuracy for general cell operating status
And sensitivity, and factor and nothing in terms of also contemplating the flying power of unmanned plane when considering thermostatic control entry condition
Itself man-machine electric parameter, being generated heat when drastically increasing simple detection battery (even multiple monomers of battery) temperature has
Delay effect causes not overheating battery or be subcooled to produce anticipation, so as to greatly extend the service life of battery, protection
The performance of battery；
(3) chosen by lot of experiments and parameter, applicants have discovered that the ratio and difference that are as above referred in technical scheme
Between for protection battery during unmanned plane during flying how for because itself flight accelerate, slow down, adjustment posture, communication with
And many principal elements for influenceing the change of battery-heating amount such as external environment make the rule of response as early as possible, and summarize
As above judgement and calculation, through experiment, seen in the result of Digi XTend series unmanned plane test, it can be ensured that it is in height above sea level
Ensure that battery temperature is in 25 ° or so all the time in the range of 500-2000 rice；
(4) present invention is creatively improved existing constant temperature technology, and formation is triple to be nested in cell peripheral successively
Constant temperature unit, wherein first and the 3rd constant temperature unit refrigeration or heating mode of operation on the contrary, and middle constant temperature unit can change
Become the thermostat temperature of its own, so as to drastically increase the autgmentability that battery is adapted to varying environment and scene：When first or
3rd constant temperature unit itself can not isolate to ambient temperature and (that is, make inside the unmanned plane residing for battery temperature and battery
The temperature isolation in other spaces) when can actively by the second constant temperature unit change thermostatic characteristics, helped on one's own initiative as transition zone
The reliable isolation of first constant temperature unit or the 3rd the constant temperature unit complete battery pair local environment in terms of temperature, compared with prior art
For there is originality.
Brief description of the drawings
Fig. 1 shows the structured flowchart of the analytical instrument according to the present invention.
Embodiment
As shown in figure 1, according to a preferred embodiment of the invention, the invention provides a kind of high-power lithium battery performance evaluation
Instrument, for the thermostatic control of the high-power lithium battery of unmanned plane, the lithium battery includes multiple battery cells, the unmanned plane
Including the first constant temperature unit, the second constant temperature unit and the 3rd constant temperature unit, first constant temperature unit, the second constant temperature unit and
Three constant temperature units can be used in heating mode of operation or refrigeration work pattern and be set in turn in outside batteries from inside to outside, should
Analytical instrument includes：
Sensing unit, for sensing the electrically and physically parameter of lithium battery and unmanned plane；
Analytic unit, for carrying out thermostatic control to lithium battery according to the result that sensing unit senses.
Preferably, the sensing unit includes：
Battery cell detection unit, for detecting the temperature information and electric parameter information of battery cell；
Unmanned electrical-mechanical detection unit, for detecting unmanned plane electric parameter information；
Unmanned plane during flying Condition Monitoring Unit, for monitoring unmanned plane during flying state parameter information；
And the analytic unit includes：
Battery temperature control unit, for the temperature information according to battery cell and electric parameter information, unmanned electrical-mechanical
Parameter information and unmanned plane during flying state parameter information determine the first constant temperature unit, the second constant temperature unit and the 3rd constant temperature unit
Mode of operation, wherein the first constant temperature unit is opposite with the mode of operation of the 3rd constant temperature unit.
Preferably, the battery cell detection unit includes：
Battery cell current detecting subelement, for detecting the charging current and discharge current of each battery cell；
Battery cell voltage detecting subelement, for detecting the charging voltage and discharge voltage of each battery cell；
Battery cell temperature detection subelement, for detecting each battery cell surface temperature；
Interface temperature detection sub-unit, for detecting the electric power output interface temperature of battery.
Preferably, the unmanned electrical-mechanical detection unit includes：
Power determination subelement, the input voltage and input current of unmanned vehicle engine are input to for detecting；
Revolution detection sub-unit, for detecting the revolution of unmanned vehicle engine.
Preferably, the unmanned plane during flying Condition Monitoring Unit includes：
GPS subelements, for obtaining altitude data and obtaining flying speed data；
The sub- detection unit of unmanned plane environment temperature, for detecting the environment temperature of unmanned plane local environment.
Preferably, the battery temperature control unit includes：
Motion state detection subelement, for according to altitude data and flying speed data, whether determining unmanned plane
Moving, and if whether be in state of flight in motion；
First test subelement, for when in state of flight, if the first constant temperature unit works in heating mode of operation
And thermostat temperature is arranged at T1, then at the first moment, nothing is determined according to the input voltage of unmanned vehicle engine and input current
The input power P of man-machine engineInput 1And determine therefrom that input power PInput 1With the ratio L of this moment engine revolution1；According to
The charging current and discharge current and charging voltage and discharge voltage of each battery cell, determine the discharge capacity of each battery cell
Difference between amount and charging capacitor amount, by each difference divided by the temperature of corresponding battery cell, and determines therefrom that to obtain
Ratio between root-mean-square value E1And the ratio R of this moment environment temperature and the mean-square value1；At the second moment, according to nobody
The input voltage and input current of machine engine determine the input power P of unmanned vehicle engineInput 2And determine therefrom that input power
PInput 2With the ratio L of this moment engine revolution2；According to the charging current of each battery cell and discharge current and charging voltage
And discharge voltage, the difference between the discharge capacity of each battery cell and charging capacitor amount is determined, by each difference divided by therewith
The temperature of corresponding battery cell, and determine therefrom that the root-mean-square value E between obtained ratio2And this moment environment temperature with
The ratio R of the mean-square value2, second moment is after the first moment, when altitude data and flying speed data
Rate of change exceedes a certain moment after presetting the first rate of change and in the second moment unmanned plane still in state of flight respectively；
Second test subelement, for being preset greatly when the rate of change of altitude data and flying speed data exceedes respectively
In the 3rd moment after the second rate of change of the first rate of change and when the 3rd moment unmanned plane is still in state of flight, according to
The input voltage and input current of unmanned vehicle engine determine the input power P of unmanned vehicle engineInput 3And determine therefrom that input
Power PInput 3With the ratio L of this moment engine revolution3；According to the charging current of each battery cell and discharge current and charging
Voltage and discharge voltage, determine the difference between the discharge capacity of each battery cell and charging capacitor amount, by each difference divided by
The temperature of corresponding battery cell, and determine therefrom that the root-mean-square value E between obtained ratio3And this moment environment temperature
Degree and the ratio R of the mean-square value3；
Difference determination subelement, for determining temperature of second constant temperature unit at the first moment, the second moment and the 3rd moment
Degree；It is determined that ((L1/R1)+(L2/R2))/(2×(L3/R3)) this ratio and | (electric power output interface temperature/environment temperature
)First moment- (electric power output interface temperature/environment temperature)Second moment| whether ratio D between this difference is higher than first threshold and small
In Second Threshold, wherein " | | " represent signed magnitude arithmetic(al)；
Second constant temperature unit sets subelement, for when difference D is higher than first threshold and when being less than Second Threshold, holding the
The thermostat temperature T1 of one constant temperature unit simultaneously sets the mode of operation of the second constant temperature unit to heat mode of operation, wherein when | D |>1
When the thermostat temperature T2=T1/ of the second constant temperature unit is set | D | and work as | D |<The thermostat temperature T2 of second constant temperature unit is set when 1
=T1 × | D |；When difference D is more than Second Threshold, then change the mode of operation of the first constant temperature unit as refrigeration work pattern and
Thermostat temperature is T1；When | D |>Set when 1 the thermostat temperature T2=environment temperatures of second constant temperature unit/| D | and work as | D |<Set when 1
Put the thermostat temperature T2=environment temperatures of the second constant temperature unit × | D |.
Preferably, the detection to the temperature of each battery cell is by bridge-type balancing method and discharge circuit, using external temp
Sensor realizes the collection to temperature.
Preferably, the detection to the temperature of the electric power output interface of battery is realized by platinum resistance temperature sensor.
Preferably, the charge and discharge electric current of each battery cell is calculated by high-precision current integral way.
Preferably, first moment be at the time of electric power output interface temperature reaches temperature value T1 and the moment without
It is man-machine still in state of flight.
The narration made above for presently preferred embodiments of the present invention is the purpose to illustrate, and is not intended to limit essence of the invention
It is really disclosed form, based on teaching above or learns from embodiments of the invention and make an amendment or change to be possible
, embodiment is to explain the principle of the present invention and allowing those skilled in the art to exist with various embodiments using the present invention
Selected in practical application and narration, technological thought of the invention attempt to be determined by claim and its equalization.
Claims (10)
1. a kind of high-power lithium battery performance evaluation instrument, for the thermostatic control of the high-power lithium battery of unmanned plane, the lithium
Battery includes multiple battery cells, and the unmanned plane includes the first constant temperature unit, the second constant temperature unit and the 3rd constant temperature unit, institute
The first constant temperature unit, the second constant temperature unit and the 3rd constant temperature unit is stated to can be used in heating mode of operation or refrigeration work pattern
And outside batteries are set in turn in from inside to outside, the analytical instrument includes：
Sensing unit, for sensing the electrically and physically parameter of lithium battery and unmanned plane；
Analytic unit, for carrying out thermostatic control to lithium battery according to the result that sensing unit senses.
2. analytical instrument according to claim 1, it is characterised in that the sensing unit includes：
Battery cell detection unit, for detecting the temperature information and electric parameter information of battery cell；
Unmanned electrical-mechanical detection unit, for detecting unmanned plane electric parameter information；
Unmanned plane during flying Condition Monitoring Unit, for monitoring unmanned plane during flying state parameter information；
And the analytic unit includes：
Battery temperature control unit, for the temperature information according to battery cell and electric parameter information, unmanned plane electric parameter
Information and unmanned plane during flying state parameter information determine the work of the first constant temperature unit, the second constant temperature unit and the 3rd constant temperature unit
Pattern, wherein the first constant temperature unit is opposite with the mode of operation of the 3rd constant temperature unit.
3. analytical instrument according to claim 2, it is characterised in that the battery cell detection unit includes：
Battery cell current detecting subelement, for detecting the charging current and discharge current of each battery cell；
Battery cell voltage detecting subelement, for detecting the charging voltage and discharge voltage of each battery cell；
Battery cell temperature detection subelement, for detecting each battery cell surface temperature；
Interface temperature detection sub-unit, for detecting the electric power output interface temperature of battery.
4. the analytical instrument according to Claims 2 or 3, it is characterised in that the unmanned electrical-mechanical detection unit includes：
Power determination subelement, the input voltage and input current of unmanned vehicle engine are input to for detecting；
Revolution detection sub-unit, for detecting the revolution of unmanned vehicle engine.
5. analytical instrument according to claim 4, it is characterised in that the unmanned plane during flying Condition Monitoring Unit includes：
GPS subelements, for obtaining altitude data and obtaining flying speed data；
The sub- detection unit of unmanned plane environment temperature, for detecting the environment temperature of unmanned plane local environment.
6. analytical instrument according to claim 5, it is characterised in that the battery temperature control unit includes：
Motion state detection subelement, for according to altitude data and flying speed data, determining whether unmanned plane is being transported
It is dynamic, and if whether it is in state of flight in motion；
First test subelement, for when in state of flight, if the first constant temperature unit works in heating mode of operation and perseverance
Temperature is arranged at T1, then at the first moment, unmanned plane is determined according to the input voltage of unmanned vehicle engine and input current
The input power P of engineInput 1And determine therefrom that input power PInput 1With the ratio L of this moment engine revolution1；According to each electricity
The charging current and discharge current and charging voltage and discharge voltage of pond monomer, determine the discharge capacity of each battery cell with
Difference between charging capacitor amount, by each difference divided by the temperature of corresponding battery cell, and determine therefrom that obtained ratio
Root-mean-square value E between value1And the ratio R of this moment environment temperature and the mean-square value1；At the second moment, sent out according to unmanned plane
The input voltage and input current of motivation determine the input power P of unmanned vehicle engineInput 2And determine therefrom that input power PInput 2With
The ratio L of this moment engine revolution2；According to the charging current of each battery cell and discharge current and charging voltage and electric discharge
Voltage, the difference between the discharge capacity of each battery cell and charging capacitor amount is determined, by each difference divided by corresponding
The temperature of battery cell, and determine therefrom that the root-mean-square value E between obtained ratio2And this moment environment temperature is square with this
The ratio R of value2, second moment is after the first moment, when the rate of change of altitude data and flying speed data
Exceed a certain moment after default first rate of change respectively and in the second moment unmanned plane still in state of flight；
Second test subelement, for default being more than the when the rate of change of altitude data and flying speed data exceedes respectively
The 3rd moment after second rate of change of one rate of change and when the 3rd moment unmanned plane is still in state of flight, according to nobody
The input voltage and input current of machine engine determine the input power P of unmanned vehicle engineInput 3And determine therefrom that input power
PInput 3With the ratio L of this moment engine revolution3；According to the charging current of each battery cell and discharge current and charging voltage
And discharge voltage, the difference between the discharge capacity of each battery cell and charging capacitor amount is determined, by each difference divided by therewith
The temperature of corresponding battery cell, and determine therefrom that the root-mean-square value E between obtained ratio3And this moment environment temperature with
The ratio R of the mean-square value3；
Difference determination subelement, for determining temperature of second constant temperature unit at the first moment, the second moment and the 3rd moment；Really
Fixed ((L1/R1)+(L2/R2))/(2×(L3/R3)) this ratio with | (electric power output interface temperature/environment temperature)First moment- (electricity
Power output interface temperature/environment temperature)Second moment| whether the ratio D between this difference is higher than first threshold and is less than the second threshold
Value, wherein " | | " represent signed magnitude arithmetic(al)；
Second constant temperature unit sets subelement, for when difference D is higher than first threshold and is less than Second Threshold, keeping the first perseverance
The thermostat temperature T1 of warm unit simultaneously sets the mode of operation of the second constant temperature unit to heat mode of operation, wherein when | D |>Set when 1
Put the thermostat temperature T2=T1/ of the second constant temperature unit | D | and work as | D |<The thermostat temperature T2=T1 of second constant temperature unit is set when 1
×|D|；When difference D is more than Second Threshold, then the mode of operation for changing the first constant temperature unit is refrigeration work pattern and constant temperature
Temperature is T1；When | D |>Set when 1 the thermostat temperature T2=environment temperatures of second constant temperature unit/| D | and work as | D |<Is set when 1
The thermostat temperature T2=environment temperatures of two constant temperature units × | D |.
7. analytical instrument according to claim 4, it is characterised in that the detection to the temperature of each battery cell passes through bridge-type
Balancing method and discharge circuit, the collection to temperature is realized using external temp sensor.
8. analytical instrument according to claim 4, it is characterised in that the detection to the temperature of the electric power output interface of battery
It is to be realized by platinum resistance temperature sensor.
9. analytical instrument according to claim 4, it is characterised in that each battery is calculated by high-precision current integral way
The charge and discharge electric current of monomer.
10. analytical instrument according to claim 6, it is characterised in that first moment is to work as electric power output interface temperature
Spend at the time of reaching temperature value T1 and in the moment unmanned plane still in state of flight.
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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