CN108627775A - A kind of fault detection method suitable for 787 aircraft aviation lithium battery of Boeing - Google Patents
A kind of fault detection method suitable for 787 aircraft aviation lithium battery of Boeing Download PDFInfo
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- CN108627775A CN108627775A CN201810618731.0A CN201810618731A CN108627775A CN 108627775 A CN108627775 A CN 108627775A CN 201810618731 A CN201810618731 A CN 201810618731A CN 108627775 A CN108627775 A CN 108627775A
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Abstract
A kind of fault detection method suitable for 787 aircraft aviation lithium battery of Boeing.It includes：Build fault detection system；Primary fault detection is carried out to aviation lithium battery using fault detection system；Using fault detection system live part fault detect is first carried out before executing charging operations to aviation lithium battery；Discharge portion fault detect is first carried out before executing discharge operation；Real-time fault detection is carried out in carry out charge or discharge operating process.The present invention generates principle according to the principle features and aviation lithium battery interior fault-signal of lithium battery, the fault detect being in aviation lithium battery under static and charging and discharging state can be achieved, meet daily maintenance requirement, it can ensure that aviation lithium battery can be safe and reliable, extend its service life, ensures flight safety.The fault detection method has simple and practicable, detection high reliability.
Description
Technical field
The invention belongs to aviation power supply unit technical fields, being suitable for 787 aircraft aviation lithium of Boeing more particularly to one kind
The fault detection method of battery.
Background technology
Aviation battery belongs to a part for aircraft power system, can be used as the emergency power supply of aircraft.According to airworthiness requirement,
In emergency circumstances aviation battery should at least power 30 minutes to aircraft important equipment.Currently, in conventional airplane still with acid and
Based on alkaline storage battery.With the development of aviation new technology, the lithium battery with many advantages also begins to obtain on type aircraft
Application, compared to general alkali storage battery and acid storage battery, lithium battery is had excellent performance, and is enjoyed great popularity.But the safety of lithium battery
Sex chromosome mosaicism is always an important factor for influencing lithium battery steady operation, when lithium battery is overcharged or when over-discharge, all can
Irreversible damage is caused to the internal structure of lithium battery, or even is exploded.As 787 aircraft of Boeing occurs in use
A lot of accidents be all and to directly result in the grounding of 787 aircraft of Boeing in the world as caused by aviation lithium battery.
The main reason for aviation lithium battery Frequent Accidents, is the failure to effectively detect the various faults signal of lithium battery interior to fail
Necessary maintenance measure is taken to aviation lithium battery.Aviation lithium battery is expensive, to safeguarding that environmental requirement is higher, attended operation
Cumbersome and battery replacement is poor, and domestic operator all relies on import for the maintained equipment of aviation lithium battery.Currently, China
Possess 787 aircraft of multi rack Boeing, and can also introduce 787 aircraft of more Boeing later, with a large amount of uses of these types,
The proper use of and maintenance of aviation lithium battery just becomes more urgent.
Invention content
To solve the above-mentioned problems, the purpose of the present invention is to provide one kind being suitable for 787 aircraft aviation lithium battery of Boeing
Fault detection method.
In order to achieve the above object, the fault detect side provided by the invention suitable for 787 aircraft aviation lithium battery of Boeing
Method includes the following steps carried out in order：
1) fault detection system of aviation lithium battery is built, the aviation lithium battery is equipped with contactor and battery cell monitoring
Unit；The fault detection system includes SCM system, ambient temperature detection circuit, battery signal interface and fault detect
Circuit, battery voltage detection circuit, charging and discharging currents detection circuit and attention display；Wherein ambient temperature detection circuit is installed
At aviation lithium battery setting；Battery signal interface and fault detection circuit are connected with battery monitoring unit；Cell voltage is examined
Slowdown monitoring circuit is connected with the positive and negative anodes of aviation lithium battery；Charging and discharging currents detection circuit is connected with the positive and negative anodes of aviation lithium battery
It connects；SCM system is electric with ambient temperature detection circuit, battery signal interface and fault detection circuit, battery voltage detection simultaneously
Road, charging and discharging currents detection circuit are connected with attention display；
2) primary fault detection is carried out to the aviation lithium battery to remain static using above-mentioned fault detection system；
3) it in the case of not finding that aviation lithium battery breaks down in primary fault detection process, is examined using above-mentioned failure
Examining system first carries out live part fault detect before executing charging operations to aviation lithium battery；It is put to the execution of aviation lithium battery
Discharge portion fault detect is first carried out before electrically operated；It is carried out in carrying out charge or discharge operating process to aviation lithium battery real-time
Fault detect.
In step 2), the method for carrying out primary fault detection to the aviation lithium battery to remain static includes
The following steps carried out in order：
2.1) environment temperature is detected using ambient temperature detection circuit, is then transferred to SCM system, by list
Piece machine system judges environment temperature whether in the range of 18 DEG C -28 DEG C, if going beyond the scope, under the control of SCM system
Alarm and malfunction coefficient are carried out using attention display；Otherwise it enters step 2.2)；
2.2) inside for the aviation lithium battery for detecting above-mentioned environment temperature and battery signal interface and fault detection circuit
Temperature is compared, if the temperature difference of the two is more than 5 DEG C, is alarmed using attention display under the control of SCM system
And malfunction coefficient；Otherwise it enters step 2.3)；
2.3) the BMU discrete signals received to battery signal interface and fault detection circuit are detected, BMU discrete signals
Including：Charging forbids 1, electric discharge to forbid 1,1 verification, charging is forbidden to forbid 2, forbid 2 verifications, battery failure, low voltage failure and mistake
Stream failure is alarmed using attention display under the control of SCM system if detecting failure and shows generation of being out of order
Code；Otherwise it enters step 2.4)；
2.4) BMU enable signals are inputted；
2.5) above-mentioned BMU discrete signals are detected, if detecting failure, report is utilized under the control of SCM system
Alert display is alarmed and shows failure code；Otherwise it enters step 2.6)；
2.6) battery-charge signal is inputted；
2.7) whether the contactor detected on aviation lithium battery disconnects, if contactor is not turned off, in SCM system
Control is lower to carry out alarm and malfunction coefficient using attention display；Otherwise it enters step 2.8)；
2.8) above-mentioned BMU discrete signals are detected, if detecting failure, report is utilized under the control of SCM system
Alert display is alarmed and exports failure code；Otherwise it enters step 2.9)；
2.9) it cuts off battery-charge signal and detects whether contactor is closed, if contactor is not closed, in microcontroller system
Under the control of system alarm and malfunction coefficient are carried out using attention display；Otherwise it enters step 2.10)；
2.10) above-mentioned BMU discrete signals are detected, if detecting failure, are utilized under the control of SCM system
Attention display is alarmed and exports failure code；Otherwise it enters step 2.11)；
2.11) voltage value for detecting battery voltage value and the battery voltage detection circuit of battery monitoring unit output into
Row compares, if the difference of voltage value is more than 0.03V, alarm and event are carried out using attention display under the control of SCM system
Barrier display；Otherwise it enters step 2.12)；
2.12) by the current value of cell current value and charging and discharging currents the detection circuit detection of battery monitoring unit output into
Row compares, if the difference of current value is more than 3A, alarm and failure are carried out using attention display under the control of SCM system
Display；Otherwise primary fault detection is completed.
In step 3), the above-mentioned fault detection system of the utilization is advanced before executing charging operations to aviation lithium battery
The method of row live part fault detect includes the following steps carried out in order：
3.1) environment temperature is detected using ambient temperature detection circuit 7, is then transferred to SCM system, by list
Piece machine system judges environment temperature whether in the range of 0-40 DEG C, sharp under the control of SCM system if going beyond the scope
Alarm and malfunction coefficient are carried out with attention display；Otherwise it enters step 3.2)；
3.2) the BMU discrete signals received to battery signal interface and fault detection circuit are detected, BMU discrete signals
Including：Charging forbids 1, electric discharge to forbid 1,1 verification, charging is forbidden to forbid 2, forbid 2 verifications, battery failure, low voltage failure and mistake
Stream failure is alarmed using attention display under the control of SCM system if detecting failure and shows generation of being out of order
Code；Otherwise it enters step 3.3)；
3.3) BMU enable signals are inputted；
3.4) above-mentioned BMU discrete signals are detected, if detecting failure, report is utilized under the control of SCM system
Alert display is alarmed and shows failure code；Otherwise it enters step 3.5)；
3.5) battery-charge signal is inputted；
3.6) whether the contactor detected on aviation lithium battery disconnects, if contactor is not turned off, in SCM system
Control is lower to carry out alarm and malfunction coefficient using attention display；Otherwise it enters step 3.7)；
3.7) above-mentioned BMU discrete signals are detected, if detecting failure, report is utilized under the control of SCM system
Alert display is alarmed and exports failure code；Otherwise it enters step 3.8).
3.8) it cuts off battery-charge signal and detects whether contactor is closed, if contactor is not closed, in microcontroller system
Under the control of system alarm and malfunction coefficient are carried out using attention display；Otherwise it enters step 3.9).
3.9) above-mentioned BMU discrete signals are detected, if detecting failure, report is utilized under the control of SCM system
Alert display is alarmed and exports failure code；Otherwise it enters step 3.10).
3.10) battery voltage value of battery monitoring unit output and the voltage value of battery voltage detection circuit detection are carried out
Compare, if the difference of voltage value is more than 0.03V, alarm and failure are carried out using attention display under the control of SCM system
Display；Otherwise it enters step 3.11).
3.11) by the current value of cell current value and charging and discharging currents the detection circuit detection of battery monitoring unit output into
Row compares, if the difference of current value is more than 3A, alarm and failure are carried out using attention display under the control of SCM system
Display；Otherwise live part fault detect is completed, and can carry out charging operations.
In step 3), the above-mentioned fault detection system of the utilization is advanced before executing discharge operation to aviation lithium battery
The method of row discharge portion fault detect includes the following steps carried out in order：
4.1) the BMU discrete signals to battery signal interface and fault detection circuit reception are examined by SCM system
It surveys, BMU discrete signals include：Charging forbids 1, electric discharge to forbid 1,1 verification, charging is forbidden to forbid 2,2 verifications, battery is forbidden to lose
Effect, low voltage failure and over current fault are alarmed under the control of SCM system using attention display if detecting failure
And show failure code；Otherwise it enters step 4.2)；
4.2) BMU enable signals are inputted；
4.3) above-mentioned BMU discrete signals are detected, if detecting failure, report is utilized under the control of SCM system
Alert display is alarmed and shows failure code；Otherwise it enters step 4.4)；
4.4) battery voltage value of battery monitoring unit output and the voltage value of battery voltage detection circuit detection are carried out
Compare, if the difference of voltage value is more than 0.03V, alarm and failure are carried out using attention display under the control of SCM system
Display；Otherwise it enters step 4.5)；
4.5) by the current value of cell current value and charging and discharging currents the detection circuit detection of battery monitoring unit output into
Row compares, if the difference of current value is more than 3A, alarm and failure are carried out using attention display under the control of SCM system
Display；Otherwise it enters step 4.6)；
4.6) environment temperature is detected using ambient temperature detection circuit, is then transferred to SCM system, by list
Piece machine system judges environment temperature whether in the range of 0-40 DEG C, sharp under the control of SCM system if going beyond the scope
Alarm and malfunction coefficient are carried out with attention display；Otherwise it enters step 4.7)；
4.7) battery SOC is detected, if battery minimum SOC signals generate, is utilized under the control of SCM system
Attention display carries out alarm and malfunction coefficient；Otherwise it enters step 4.8)；
4.8) cell voltage is detected, if cell voltage is less than 31.75V, is utilized under the control of SCM system
Attention display carries out alarm and malfunction coefficient；Otherwise discharge portion fault detect is completed, and can carry out discharge operation.
It is described to carry out real time fail inspection in carrying out charge or discharge operating process to aviation lithium battery in step 3)
The method of survey includes the following steps carried out in order：
5.1) in aviation lithium battery carries out charge or discharge operating process, battery signal is connect in real time by SCM system
The BMU discrete signals that mouth and fault detection circuit receive are detected, and BMU discrete signals include：Charging forbids 1, electric discharge to forbid
1, forbid 1 verification, charging forbid 2, forbid 2 verifications, battery failure, low voltage failure and over current fault, if detecting failure, interrupt
The charge or discharge of aviation lithium battery operate, while being alarmed and being shown using attention display under the control of SCM system
Failure code is shown；Otherwise continue charge or discharge；
5.2) by the current value of cell current value and charging and discharging currents the detection circuit detection of battery monitoring unit output into
Row compares, if the difference of current value is more than 3A, interrupts the charge or discharge operation of aviation lithium battery, while in SCM system
Control is lower to carry out alarm and malfunction coefficient using attention display；Otherwise continue charge or discharge.
It is provided by the invention to be had the advantages that suitable for 787 aircraft aviation lithium battery fault detection method of Boeing：This
Invention generates principle, it can be achieved that aviation lithium battery according to the principle features and aviation lithium battery interior fault-signal of lithium battery
Fault detect under static and charging and discharging state meets daily maintenance requirement, can ensure that aviation lithium battery can be safe and reliable
Operation extends its service life, ensures flight safety.The fault detection method has simple and practicable, and detection reliability height etc. is excellent
Point.
Description of the drawings
Fig. 1 is the event provided by the invention used suitable for the fault detection method of 787 aircraft aviation lithium battery of Boeing
Hinder detecting system and constitutes schematic diagram.
Fig. 2 is provided by the invention suitable for 787 aircraft aviation lithium battery primary fault overhaul flow chart of Boeing.
Fig. 3 is provided by the invention suitable for 787 aircraft aviation lithium battery live part fault detect flow chart of Boeing.
Fig. 4 is provided by the invention suitable for 787 aircraft aviation lithium battery discharge portion fault detect flow chart of Boeing.
Fig. 5 is provided by the invention suitable for 787 aircraft aviation lithium battery real-time fault detection flow chart of Boeing.
Specific implementation mode
Below in conjunction with the accompanying drawings to the fault detection method provided by the invention suitable for 787 aircraft aviation lithium battery of Boeing into
Row is described in detail.
As shown in Figure 1, the fault detection method provided by the invention suitable for 787 aircraft aviation lithium battery of Boeing includes pressing
The following steps that sequence carries out：
1) fault detection system of structure aviation lithium battery 1, the aviation lithium battery 1 are equipped with contactor 2 and battery
Monitoring unit (BMU) 3；The fault detection system includes that SCM system 6, ambient temperature detection circuit 7, battery signal connect
Mouth and fault detection circuit 8, battery voltage detection circuit 9, charging and discharging currents detection circuit 10 and attention display 11；Its middle ring
Border temperature sensing circuit 7 is mounted at 1 setting of aviation lithium battery, is detected for the environment temperature to aviation lithium battery 1；Electricity
Pond signaling interface and fault detection circuit 8 are connected with battery monitoring unit 3, for following input/output signal transmission, connect
It receives and detects, including：Charging forbids 1, electric discharge to forbid 1,1 verification, charging is forbidden to forbid 2, forbid 2 verifications, battery failure, low pressure
Failure, over current fault totally 8 discrete fault-signals of BMU, cell voltage+signal, cell voltage-signal, current signal, in battery
Portion's temperature signal, battery minimum SOC signals, direct current+15V signals, GND signals, direct current -15V signals, battery-charge signal and
BMU enable signals；Battery voltage detection circuit 9 is connected with the positive and negative anodes of aviation lithium battery 1, for detecting aviation lithium battery 1
Voltage；Charging and discharging currents detection circuit 10 is connected with the positive and negative anodes of aviation lithium battery 1, is filled for detecting aviation lithium battery 1
Electric current when electric discharge；SCM system 6 simultaneously with ambient temperature detection circuit 7, battery signal interface and fault detection circuit 8,
Battery voltage detection circuit 9, charging and discharging currents detection circuit 10 are connected with attention display 11, for completing environment temperature inspection
In slowdown monitoring circuit 7, battery signal interface and fault detection circuit 8, battery voltage detection circuit 9 and charging and discharging currents detection circuit 10
The analysis and processing of the various detection signals passed, and when finding failure, control attention display 11 carries out alarm and failure is aobvious
Show.
2) primary fault detection is carried out to the aviation lithium battery 1 to remain static using above-mentioned fault detection system；
3) in the case of not finding that aviation lithium battery 1 breaks down in primary fault detection process, above-mentioned failure is utilized
Detecting system first carries out live part fault detect before executing charging operations to aviation lithium battery 1；It is held to aviation lithium battery 1
Discharge portion fault detect is first carried out before row discharge operation；To aviation lithium battery 1 carry out charge or discharge operating process in into
Row real-time fault detection.
As shown in Fig. 2, in step 2), it is described that primary fault inspection is carried out to the aviation lithium battery 1 to remain static
The method of survey includes the following steps carried out in order：
2.1) environment temperature is detected using ambient temperature detection circuit 7, is then transferred to SCM system 6, by
SCM system 6 judges environment temperature whether in the range of 18 DEG C -28 DEG C, if going beyond the scope, in the control of SCM system 6
System is lower to carry out alarm and malfunction coefficient using attention display 11；Otherwise it enters step 2.2)；
2.2) in the aviation lithium battery 1 for detecting above-mentioned environment temperature and battery signal interface and fault detection circuit 8
Portion's temperature is compared, if the temperature difference of the two is more than 5 DEG C, under the control of SCM system 6 using attention display 11 into
Row alarm and malfunction coefficient；Otherwise it enters step 2.3)；
2.3) the BMU discrete signals received to battery signal interface and fault detection circuit 8 are detected, the discrete letters of BMU
Number include：Charging forbids 1, electric discharge forbids 1, forbid 1 verification, charging to forbid 2, forbid 2 verifications, battery failure, low voltage failure and
Over current fault is alarmed using attention display 11 under the control of SCM system 6 if detecting failure and shows event
Hinder code；Otherwise it enters step 2.4)；
2.4) BMU enable signals are inputted；
2.5) above-mentioned BMU discrete signals are detected, if detecting failure, are utilized under the control of SCM system 6
Attention display 11 is alarmed and shows failure code；Otherwise it enters step 2.6)；
2.6) input battery-charge signal；
2.7) whether the contactor 2 on detection aviation lithium battery 1 disconnects, if contactor 2 is not turned off, in SCM system
Under 6 control alarm and malfunction coefficient are carried out using attention display 11；Otherwise it enters step 2.8)；
2.8) above-mentioned BMU discrete signals are detected, if detecting failure, are utilized under the control of SCM system 6
Attention display 11 is alarmed and exports failure code；Otherwise it enters step 2.9)；
2.9) it cuts off battery-charge signal and detects whether contactor 2 is closed, if contactor 2 is not closed, in microcontroller
Under the control of system 6 alarm and malfunction coefficient are carried out using attention display 11；Otherwise it enters step 2.10)；
2.10) above-mentioned BMU discrete signals are detected, if detecting failure, are utilized under the control of SCM system 6
Attention display 11 is alarmed and exports failure code；Otherwise it enters step 2.11)；
2.11) voltage value for detecting the battery voltage value that battery monitoring unit 3 exports with battery voltage detection circuit 9
It is compared, if the difference of voltage value is more than 0.03V, is reported using attention display 11 under the control of SCM system 6
Alert and malfunction coefficient；Otherwise it enters step 2.12)；
2.12) electric current for detecting the cell current value that battery monitoring unit 3 exports with charging and discharging currents detection circuit 10
Value is compared, if the difference of current value is more than 3A, is alarmed using attention display 11 under the control of SCM system 6
And malfunction coefficient；Otherwise primary fault detection is completed.
As shown in figure 3, in step 3), the above-mentioned fault detection system of the utilization is filled to the execution of aviation lithium battery 1
It includes the following steps carried out in order that the method for live part fault detect is first carried out before electrically operated：
3.1) environment temperature is detected using ambient temperature detection circuit 7, is then transferred to SCM system 6, by
SCM system 6 judges environment temperature whether in the range of 0-40 DEG C, if going beyond the scope, in the control of SCM system 6
It is lower to carry out alarm and malfunction coefficient using attention display 11；Otherwise it enters step 3.2)；
3.2) the BMU discrete signals received to battery signal interface and fault detection circuit 8 are detected, the discrete letters of BMU
Number include：Charging forbids 1, electric discharge forbids 1, forbid 1 verification, charging to forbid 2, forbid 2 verifications, battery failure, low voltage failure and
Over current fault is alarmed using attention display 11 under the control of SCM system 6 if detecting failure and shows event
Hinder code；Otherwise it enters step 3.3)；
3.3) BMU enable signals are inputted；
3.4) above-mentioned BMU discrete signals are detected, if detecting failure, are utilized under the control of SCM system 6
Attention display 11 is alarmed and shows failure code；Otherwise it enters step 3.5)；
3.5) battery-charge signal is inputted；
3.6) whether the contactor 2 on detection aviation lithium battery 1 disconnects, if contactor 2 is not turned off, in SCM system
Under 6 control alarm and malfunction coefficient are carried out using attention display 11；Otherwise it enters step 3.7)；
3.7) above-mentioned BMU discrete signals are detected, if detecting failure, are utilized under the control of SCM system 6
Attention display 11 is alarmed and exports failure code；Otherwise it enters step 3.8).
3.8) it cuts off battery-charge signal and detects whether contactor 2 is closed, if contactor 2 is not closed, in microcontroller
Under the control of system 6 alarm and malfunction coefficient are carried out using attention display 11；Otherwise it enters step 3.9).
3.9) above-mentioned BMU discrete signals are detected, if detecting failure, are utilized under the control of SCM system 6
Attention display 11 is alarmed and exports failure code；Otherwise it enters step 3.10).
3.10) voltage value for detecting battery voltage value that battery monitoring unit 3 exports with battery voltage detection circuit 9 into
Row compares, if the difference of voltage value is more than 0.03V, is alarmed using attention display 11 under the control of SCM system 6
And malfunction coefficient；Otherwise it enters step 3.11).
3.11) electric current for detecting the cell current value that battery monitoring unit 3 exports with charging and discharging currents detection circuit 10
Value is compared, if the difference of current value is more than 3A, is alarmed using attention display 11 under the control of SCM system 6
And malfunction coefficient；Otherwise live part fault detect is completed, and can carry out charging operations.
As shown in figure 4, in step 3), the above-mentioned fault detection system of the utilization is put to the execution of aviation lithium battery 1
It includes the following steps carried out in order that the method for discharge portion fault detect is first carried out before electrically operated：
4.1) the BMU discrete signals received to battery signal interface and fault detection circuit 8 are carried out by SCM system 6
Detection, BMU discrete signals include：Charging forbids 1, electric discharge to forbid 1,1 verification, charging is forbidden to forbid 2,2 verifications, battery is forbidden to lose
Effect, low voltage failure and over current fault are carried out under the control of SCM system 6 using attention display 11 if detecting failure
It alarms and shows failure code；Otherwise it enters step 4.2)；
4.2) BMU enable signals are inputted；
4.3) above-mentioned BMU discrete signals are detected, if detecting failure, are utilized under the control of SCM system 6
Attention display 11 is alarmed and shows failure code；Otherwise it enters step 4.4)；
4.4) voltage value for detecting battery voltage value that battery monitoring unit 3 exports with battery voltage detection circuit 9 into
Row compares, if the difference of voltage value is more than 0.03V, is alarmed using attention display 11 under the control of SCM system 6
And malfunction coefficient；Otherwise it enters step 4.5)；
4.5) current value for detecting the cell current value that battery monitoring unit 3 exports with charging and discharging currents detection circuit 10
Be compared, if the difference of current value be more than 3A, under the control of SCM system 6 using attention display 11 carry out alarm and
Malfunction coefficient；Otherwise it enters step 4.6)；
4.6) environment temperature is detected using ambient temperature detection circuit 7, is then transferred to SCM system 6, by
SCM system 6 judges environment temperature whether in the range of 0-40 DEG C, if going beyond the scope, in the control of SCM system 6
It is lower to carry out alarm and malfunction coefficient using attention display 11；Otherwise it enters step 4.7)；
4.7) battery SOC is detected, if battery minimum SOC signals generate, is utilized under the control of SCM system 6
Attention display 11 carries out alarm and malfunction coefficient；Otherwise it enters step 4.8)；
4.8) cell voltage is detected, if cell voltage is less than 31.75V, is utilized under the control of SCM system 6
Attention display 11 carries out alarm and malfunction coefficient；Otherwise discharge portion fault detect is completed, and can carry out discharge operation.
As shown in figure 5, in step 3), it is described in carrying out charge or discharge operating process to aviation lithium battery 1 into
The method of row real-time fault detection includes the following steps carried out in order：
5.1) in aviation lithium battery 1 carries out charge or discharge operating process, by SCM system 6 in real time to battery signal
The BMU discrete signals that interface and fault detection circuit 8 receive are detected, and BMU discrete signals include：Charging forbids 1, electric discharge to prohibit
Only 1,1 verification, charging is forbidden to forbid 2, forbid 2 verifications, battery failure, low voltage failure and over current fault, if detecting failure, in
It stops navigation the charge or discharge operation of sky lithium battery 1, while being reported using attention display 11 under the control of SCM system 6
It warns and shows failure code；Otherwise continue charge or discharge；
5.2) current value for detecting the cell current value that battery monitoring unit 3 exports with charging and discharging currents detection circuit 10
It is compared, if the difference of current value is more than 3A, interrupts the charge or discharge operation of aviation lithium battery 1, while in microcontroller system
Under the control of system 6 alarm and malfunction coefficient are carried out using attention display 11；Otherwise continue charge or discharge.
Claims (5)
1. a kind of fault detection method suitable for 787 aircraft aviation lithium battery of Boeing, it is characterised in that：The fault detect
Method includes the following steps carried out in order：
1) fault detection system of structure aviation lithium battery (1), the aviation lithium battery (1) are equipped with contactor (2) and electricity
Cell monitoring unit (3)；The fault detection system includes SCM system (6), ambient temperature detection circuit (7), battery letter
Number interface and fault detection circuit (8), battery voltage detection circuit (9), charging and discharging currents detection circuit (10) and alarm indication
Device (11)；Wherein ambient temperature detection circuit (7) is mounted at aviation lithium battery (1) setting；Battery signal interface and failure inspection
Slowdown monitoring circuit (8) is connected with battery monitoring unit (3)；The positive and negative anodes phase of battery voltage detection circuit (9) and aviation lithium battery (1)
Connection；Charging and discharging currents detection circuit (10) is connected with the positive and negative anodes of aviation lithium battery (1)；SCM system (6) at the same with
Ambient temperature detection circuit (7), battery signal interface and fault detection circuit (8), battery voltage detection circuit (9), charge and discharge
Current detection circuit (10) is connected with attention display (11)；
2) primary fault detection is carried out to the aviation lithium battery (1) to remain static using above-mentioned fault detection system；
3) it in the case of not finding that aviation lithium battery (1) breaks down in primary fault detection process, is examined using above-mentioned failure
Examining system first carries out live part fault detect before executing charging operations to aviation lithium battery (1)；To aviation lithium battery (1)
Discharge portion fault detect is first carried out before executing discharge operation；Charge or discharge operating process is being carried out to aviation lithium battery (1)
Middle carry out real-time fault detection.
2. the fault detection method according to claim 1 suitable for 787 aircraft aviation lithium battery of Boeing, feature exists
In：In step 2), the method for carrying out primary fault detection to the aviation lithium battery (1) to remain static includes pressing
The following steps that sequence carries out：
2.1) environment temperature is detected using ambient temperature detection circuit (7), is then transferred to SCM system (6), by
SCM system (6) judges environment temperature whether in the range of 18 DEG C -28 DEG C, if going beyond the scope, in SCM system (6)
Control under using attention display (11) carry out alarm and malfunction coefficient；Otherwise it enters step 2.2)；
2.2) the aviation lithium battery (1) for detecting above-mentioned environment temperature and battery signal interface and fault detection circuit (8) is interior
Portion's temperature is compared, if the temperature difference of the two is more than 5 DEG C, attention display is utilized under the control of SCM system (6)
(11) alarm and malfunction coefficient are carried out；Otherwise it enters step 2.3)；
2.3) the BMU discrete signals received to battery signal interface and fault detection circuit (8) are detected, BMU discrete signals
Including：Charging forbids 1, electric discharge to forbid 1,1 verification, charging is forbidden to forbid 2, forbid 2 verifications, battery failure, low voltage failure and mistake
Stream failure is alarmed and is shown using attention display (11) under the control of SCM system (6) if detecting failure
Failure code；Otherwise it enters step 2.4)；
2.4) BMU enable signals are inputted；
2.5) above-mentioned BMU discrete signals are detected, if detecting failure, report is utilized under the control of SCM system (6)
Alert display (11) is alarmed and shows failure code；Otherwise it enters step 2.6)；
2.6) battery-charge signal is inputted；
2.7) whether the contactor (2) on detection aviation lithium battery (1) disconnects, if contactor (2) is not turned off, in microcontroller system
Under the control of system (6) alarm and malfunction coefficient are carried out using attention display (11)；Otherwise it enters step 2.8)；
2.8) above-mentioned BMU discrete signals are detected, if detecting failure, report is utilized under the control of SCM system (6)
Alert display (11) is alarmed and exports failure code；Otherwise it enters step 2.9)；
2.9) it cuts off battery-charge signal and detects whether contactor (2) is closed, if contactor (2) is not closed, in microcontroller
Under the control of system (6) alarm and malfunction coefficient are carried out using attention display (11)；Otherwise it enters step 2.10)；
2.10) above-mentioned BMU discrete signals are detected, if detecting failure, report is utilized under the control of SCM system (6)
Alert display (11) is alarmed and exports failure code；Otherwise it enters step 2.11)；
2.11) voltage value for detecting the battery voltage value of battery monitoring unit (3) output with battery voltage detection circuit (9)
Be compared, if the difference of voltage value be more than 0.03V, under the control of SCM system (6) using attention display (11) into
Row alarm and malfunction coefficient；Otherwise it enters step 2.12)；
2.12) by the electric current of the cell current value of battery monitoring unit (3) output and charging and discharging currents detection circuit (10) detection
Value is compared, if the difference of current value is more than 3A, is carried out using attention display (11) under the control of SCM system (6)
Alarm and malfunction coefficient；Otherwise primary fault detection is completed.
3. the fault detection method according to claim 1 suitable for 787 aircraft aviation lithium battery of Boeing, feature exists
In：In step 3), described is first carried out using above-mentioned fault detection system before executing charging operations to aviation lithium battery (1)
The method of live part fault detect includes the following steps carried out in order：
3.1) environment temperature is detected using ambient temperature detection circuit (7), is then transferred to SCM system (6), by
SCM system (6) judges environment temperature whether in the range of 0-40 DEG C, if going beyond the scope, in SCM system (6)
Control is lower to carry out alarm and malfunction coefficient using attention display (11)；Otherwise it enters step 3.2)；
3.2) the BMU discrete signals received to battery signal interface and fault detection circuit (8) are detected, BMU discrete signals
Including：Charging forbids 1, electric discharge to forbid 1,1 verification, charging is forbidden to forbid 2, forbid 2 verifications, battery failure, low voltage failure and mistake
Stream failure is alarmed and is shown using attention display (11) under the control of SCM system (6) if detecting failure
Failure code；Otherwise it enters step 3.3)；
3.3) BMU enable signals are inputted；
3.4) above-mentioned BMU discrete signals are detected, if detecting failure, report is utilized under the control of SCM system (6)
Alert display (11) is alarmed and shows failure code；Otherwise it enters step 3.5)；
3.5) battery-charge signal is inputted；
3.6) whether the contactor (2) on detection aviation lithium battery (1) disconnects, if contactor (2) is not turned off, in microcontroller system
Under the control of system (6) alarm and malfunction coefficient are carried out using attention display (11)；Otherwise it enters step 3.7)；
3.7) above-mentioned BMU discrete signals are detected, if detecting failure, report is utilized under the control of SCM system (6)
Alert display (11) is alarmed and exports failure code；Otherwise it enters step 3.8).
3.8) it cuts off battery-charge signal and detects whether contactor (2) is closed, if contactor (2) is not closed, in microcontroller
Under the control of system (6) alarm and malfunction coefficient are carried out using attention display (11)；Otherwise it enters step 3.9).
3.9) above-mentioned BMU discrete signals are detected, if detecting failure, report is utilized under the control of SCM system (6)
Alert display (11) is alarmed and exports failure code；Otherwise it enters step 3.10).
3.10) by the voltage value of battery voltage value and battery voltage detection circuit (9) detection of battery monitoring unit (3) output into
Row compares, if the difference of voltage value is more than 0.03V, is carried out using attention display (11) under the control of SCM system (6)
Alarm and malfunction coefficient；Otherwise it enters step 3.11).
3.11) by the electric current of the cell current value of battery monitoring unit (3) output and charging and discharging currents detection circuit (10) detection
Value is compared, if the difference of current value is more than 3A, is carried out using attention display (11) under the control of SCM system (6)
Alarm and malfunction coefficient；Otherwise live part fault detect is completed, and can carry out charging operations.
4. the fault detection method according to claim 1 suitable for 787 aircraft aviation lithium battery of Boeing, feature exists
In：In step 3), described is first carried out using above-mentioned fault detection system before executing discharge operation to aviation lithium battery (1)
The method of discharge portion fault detect includes the following steps carried out in order：
4.1) the BMU discrete signals to battery signal interface and fault detection circuit (8) reception are carried out by SCM system (6)
Detection, BMU discrete signals include：Charging forbids 1, electric discharge to forbid 1,1 verification, charging is forbidden to forbid 2,2 verifications, battery is forbidden to lose
Effect, low voltage failure and over current fault utilize attention display (11) if detecting failure under the control of SCM system (6)
It is alarmed and shows failure code；Otherwise it enters step 4.2)；
4.2) BMU enable signals are inputted；
4.3) above-mentioned BMU discrete signals are detected, if detecting failure, report is utilized under the control of SCM system (6)
Alert display (11) is alarmed and shows failure code；Otherwise it enters step 4.4)；
4.4) by the voltage value of battery voltage value and battery voltage detection circuit (9) detection of battery monitoring unit (3) output into
Row compares, if the difference of voltage value is more than 0.03V, is carried out using attention display (11) under the control of SCM system (6)
Alarm and malfunction coefficient；Otherwise it enters step 4.5)；
4.5) by the current value of the cell current value of battery monitoring unit (3) output and charging and discharging currents detection circuit (10) detection
It is compared, if the difference of current value is more than 3A, is reported using attention display (11) under the control of SCM system (6)
Alert and malfunction coefficient；Otherwise it enters step 4.6)；
4.6) environment temperature is detected using ambient temperature detection circuit (7), is then transferred to SCM system (6), by
SCM system (6) judges environment temperature whether in the range of 0-40 DEG C, if going beyond the scope, in SCM system (6)
Control is lower to carry out alarm and malfunction coefficient using attention display (11)；Otherwise it enters step 4.7)；
4.7) battery SOC is detected, if battery minimum SOC signals generate, report is utilized under the control of SCM system (6)
Alert display (11) carries out alarm and malfunction coefficient；Otherwise it enters step 4.8)；
4.8) cell voltage is detected, if cell voltage is less than 31.75V, report is utilized under the control of SCM system (6)
Alert display (11) carries out alarm and malfunction coefficient；Otherwise discharge portion fault detect is completed, and can carry out discharge operation.
5. the fault detection method according to claim 1 suitable for 787 aircraft aviation lithium battery of Boeing, feature exists
In：It is described that aviation lithium battery (1) is being carried out to carry out real-time fault detection in charge or discharge operating process in step 3)
Method include the following steps carried out in order：
5.1) in aviation lithium battery (1) carries out charge or discharge operating process, by SCM system (6) in real time to battery signal
The BMU discrete signals that interface and fault detection circuit (8) receive are detected, and BMU discrete signals include：1, electric discharge is forbidden in charging
Forbid 1,1 verification, charging is forbidden to forbid 2, forbid 2 verifications, battery failure, low voltage failure and over current fault, if detecting failure,
The charge or discharge operation of aviation lithium battery (1) is interrupted, while utilizing attention display under the control of SCM system (6)
(11) it is alarmed and shows failure code；Otherwise continue charge or discharge；
5.2) by the current value of the cell current value of battery monitoring unit (3) output and charging and discharging currents detection circuit (10) detection
It is compared, if the difference of current value is more than 3A, interrupts the charge or discharge operation of aviation lithium battery (1), while in microcontroller
Under the control of system (6) alarm and malfunction coefficient are carried out using attention display (11)；Otherwise continue charge or discharge.
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