CN108627775B - Fault detection method suitable for boeing 787 aircraft aviation lithium battery - Google Patents
Fault detection method suitable for boeing 787 aircraft aviation lithium battery Download PDFInfo
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Abstract
A fault detection method suitable for a Boeing 787 aircraft aviation lithium battery. It includes: constructing a fault detection system; carrying out initial fault detection on the aviation lithium battery by using a fault detection system; the method comprises the steps that a fault detection system is utilized to carry out fault detection on a charging part before charging operation is carried out on the aviation lithium battery; performing discharge portion fault detection before performing a discharge operation; and performing real-time fault detection and the like in the process of performing charging or discharging operation. According to the principle characteristic of the lithium battery and the principle of generating the fault signal in the aviation lithium battery, the fault detection of the aviation lithium battery in the static state and the charging and discharging state can be realized, the daily maintenance requirement is met, the safe and reliable operation of the aviation lithium battery can be guaranteed, the service life of the aviation lithium battery is prolonged, and the flight safety is guaranteed. The fault detection method has the advantages of simplicity, easiness, high detection reliability and the like.
Description
Technical Field
The invention belongs to the technical field of aviation power supply equipment, and particularly relates to a fault detection method suitable for a boeing 787 aircraft aviation lithium battery.
Background
The aviation storage battery belongs to a part of an airplane power supply system and can be used as an emergency power supply of an airplane. According to airworthiness requirements, the aviation battery can supply power for at least 30 minutes to important equipment of the airplane in an emergency. At present, acidic and alkaline storage batteries are mainly used on the traditional airplane. With the development of new aviation technologies, lithium batteries with a plurality of advantages are also applied to novel airplanes, and compared with common alkaline storage batteries and acid storage batteries, the lithium batteries are excellent in performance and popular. However, the safety problem of the lithium battery has been an important factor affecting the stable operation of the lithium battery, and when the lithium battery is overcharged or overdischarged, irreversible damage or even explosion may be caused to the internal structure of the lithium battery. Many accidents such as the boeing 787 aircraft occur during use are caused by aviation lithium batteries, and directly result in the world-wide stopping and flying of the boeing 787 aircraft. The main reason why the accidents of the aviation lithium battery are frequent is that various fault signals inside the lithium battery cannot be effectively detected, so that necessary maintenance measures cannot be taken on the aviation lithium battery. The aviation lithium battery is expensive, has high requirements on maintenance environment, is complex to maintain and operate, has poor battery replaceability, and is imported by domestic airlines aiming at maintenance equipment of the aviation lithium battery. At present, China has a plurality of boeing 787 airplanes, and more boeing 787 airplanes are introduced later, and with the use of a large number of the airplanes, the correct use and maintenance of the aviation lithium battery become more urgent.
Disclosure of Invention
In order to solve the problems, the invention aims to provide a fault detection method suitable for a boeing 787 aircraft aviation lithium battery.
In order to achieve the purpose, the fault detection method suitable for the boeing 787 aircraft aviation lithium battery provided by the invention comprises the following steps in sequence:
1) constructing a fault detection system of an aviation lithium battery, wherein a contactor and a battery monitoring unit are arranged on the aviation lithium battery; the fault detection system comprises a single chip microcomputer system, an ambient temperature detection circuit, a battery signal interface, a fault detection circuit, a battery voltage detection circuit, a charging and discharging current detection circuit and an alarm display; the environment temperature detection circuit is arranged at the position where the aviation lithium battery is arranged; the battery signal interface and the fault detection circuit are connected with the battery monitoring unit; the battery voltage detection circuit is connected with the anode and the cathode of the aviation lithium battery; the charge and discharge current detection circuit is connected with the anode and the cathode of the aviation lithium battery; the single chip microcomputer system is simultaneously connected with the environment temperature detection circuit, the battery signal interface, the fault detection circuit, the battery voltage detection circuit, the charging and discharging current detection circuit and the alarm display;
2) carrying out initial fault detection on the aviation lithium battery in a static state by using the fault detection system;
3) under the condition that the fault of the aviation lithium battery is not found in the initial fault detection process, the fault detection system is utilized to carry out fault detection on a charging part before the aviation lithium battery is charged; the method comprises the steps of firstly carrying out discharge part fault detection before carrying out discharge operation on the aviation lithium battery; and carrying out real-time fault detection in the charging or discharging operation process of the aviation lithium battery.
In step 2), the method for detecting the initial fault of the aviation lithium battery in the static state comprises the following steps in sequence:
2.1) detecting the ambient temperature by using an ambient temperature detection circuit, then transmitting the ambient temperature to a singlechip system, judging whether the ambient temperature is in the range of 18-28 ℃ by the singlechip system, and if the ambient temperature is out of the range, alarming and displaying faults by using an alarm display under the control of the singlechip system; otherwise, entering step 2.2);
2.2) comparing the environmental temperature with the internal temperature of the aviation lithium battery detected by a battery signal interface and a fault detection circuit, and if the temperature difference between the environmental temperature and the internal temperature exceeds 5 ℃, alarming and fault displaying are carried out by utilizing an alarm display under the control of a single chip microcomputer system; otherwise, entering step 2.3);
2.3) detecting the BMU discrete signals received by the battery signal interface and the fault detection circuit, wherein the BMU discrete signals comprise: the method comprises the following steps of charging forbidding 1, discharging forbidding 1, checking forbidding 1, charging forbidding 2, checking forbidding 2, battery failure, low-voltage fault and overcurrent fault, and if the faults are detected, alarming and displaying fault codes by using an alarm display under the control of a single chip microcomputer system; otherwise, entering step 2.4);
2.4) inputting a BMU enabling signal;
2.5) detecting the BMU discrete signals, and if a fault is detected, alarming by using an alarm display under the control of the single chip microcomputer system and displaying a fault code; otherwise, entering step 2.6);
2.6) inputting a battery charging signal;
2.7) detecting whether a contactor on the aviation lithium battery is disconnected or not, and if the contactor is not disconnected, alarming and fault displaying are carried out by utilizing an alarm display under the control of the single chip microcomputer system; otherwise, entering step 2.8);
2.8) detecting the BMU discrete signals, and if a fault is detected, alarming by using an alarm display under the control of a single chip microcomputer system and outputting a fault code; otherwise, entering step 2.9);
2.9) cutting off a battery charging signal and detecting whether the contactor is closed, if the contactor is not closed, alarming and displaying faults by using an alarm display under the control of the single chip microcomputer system; otherwise, entering step 2.10);
2.10) detecting the BMU discrete signals, and if a fault is detected, alarming by using an alarm display under the control of a single chip microcomputer system and outputting a fault code; otherwise, entering step 2.11);
2.11) comparing the battery voltage value output by the battery monitoring unit with the voltage value detected by the battery voltage detection circuit, and if the difference value of the voltage values is more than 0.03V, alarming and fault displaying by using an alarm display under the control of the singlechip system; otherwise, entering step 2.12);
2.12) comparing the battery current value output by the battery monitoring unit with the current value detected by the charging and discharging current detection circuit, and if the difference value of the current values is more than 3A, alarming and fault displaying are carried out by utilizing an alarm display under the control of the singlechip system; otherwise, the initial fault detection is completed.
In step 3), the method for detecting the fault of the charging part before the charging operation is performed on the aviation lithium battery by using the fault detection system comprises the following steps in sequence:
3.1) detecting the ambient temperature by using an ambient temperature detection circuit 7, then transmitting the ambient temperature to a single chip microcomputer system, judging whether the ambient temperature is in the range of 0-40 ℃ by the single chip microcomputer system, and if the ambient temperature is out of the range, alarming and displaying faults by using an alarm display under the control of the single chip microcomputer system; otherwise, entering step 3.2);
3.2) detecting the BMU discrete signals received by the battery signal interface and the fault detection circuit, wherein the BMU discrete signals comprise: the method comprises the following steps of charging forbidding 1, discharging forbidding 1, checking forbidding 1, charging forbidding 2, checking forbidding 2, battery failure, low-voltage fault and overcurrent fault, and if the faults are detected, alarming and displaying fault codes by using an alarm display under the control of a single chip microcomputer system; otherwise, entering step 3.3);
3.3) inputting a BMU enabling signal;
3.4) detecting the BMU discrete signals, and if a fault is detected, alarming by using an alarm display under the control of the single chip microcomputer system and displaying a fault code; otherwise, entering step 3.5);
3.5) inputting a battery charging signal;
3.6) detecting whether a contactor on the aviation lithium battery is disconnected or not, and if the contactor is not disconnected, alarming and fault displaying are carried out by utilizing an alarm display under the control of the single chip microcomputer system; otherwise, entering step 3.7);
3.7) detecting the BMU discrete signals, and if a fault is detected, alarming by using an alarm display under the control of the single chip microcomputer system and outputting a fault code; otherwise step 3.8) is entered.
3.8) cutting off a battery charging signal and detecting whether the contactor is closed, if the contactor is not closed, alarming and displaying faults by using an alarm display under the control of the single chip microcomputer system; otherwise step 3.9) is entered.
3.9) detecting the BMU discrete signals, and if a fault is detected, alarming by using an alarm display under the control of the single chip microcomputer system and outputting a fault code; otherwise step 3.10) is entered.
3.10) comparing the battery voltage value output by the battery monitoring unit with the voltage value detected by the battery voltage detection circuit, and if the difference value of the voltage values is more than 0.03V, alarming and fault displaying by using an alarm display under the control of the singlechip system; otherwise step 3.11) is entered.
3.11) comparing the battery current value output by the battery monitoring unit with the current value detected by the charging and discharging current detection circuit, and if the difference value of the current values is more than 3A, alarming and fault displaying are carried out by utilizing an alarm display under the control of the singlechip system; otherwise, the charging part fault detection is completed, and the charging operation can be carried out.
In step 3), the method for detecting the fault of the discharge part by using the fault detection system before performing the discharge operation on the aviation lithium battery comprises the following steps in sequence:
4.1) detecting the BMU discrete signals received by the battery signal interface and the fault detection circuit by the singlechip system, wherein the BMU discrete signals comprise: the method comprises the following steps of charging forbidding 1, discharging forbidding 1, checking forbidding 1, charging forbidding 2, checking forbidding 2, battery failure, low-voltage fault and overcurrent fault, and if the faults are detected, alarming and displaying fault codes by using an alarm display under the control of a single chip microcomputer system; otherwise, entering step 4.2);
4.2) inputting a BMU enabling signal;
4.3) detecting the BMU discrete signals, and if a fault is detected, alarming by using an alarm display under the control of the single chip microcomputer system and displaying a fault code; otherwise, entering step 4.4);
4.4) comparing the battery voltage value output by the battery monitoring unit with the voltage value detected by the battery voltage detection circuit, and if the difference value of the voltage values is more than 0.03V, alarming and fault displaying are carried out by utilizing an alarm display under the control of the single chip microcomputer system; otherwise, entering step 4.5);
4.5) comparing the battery current value output by the battery monitoring unit with the current value detected by the charging and discharging current detection circuit, and if the difference value of the current values is more than 3A, alarming and fault displaying are carried out by utilizing an alarm display under the control of the singlechip system; otherwise, entering step 4.6);
4.6) detecting the ambient temperature by using an ambient temperature detection circuit, then transmitting the ambient temperature to the singlechip system, judging whether the ambient temperature is in the range of 0-40 ℃ by the singlechip system, and if the ambient temperature is out of the range, alarming and displaying faults by using an alarm display under the control of the singlechip system; otherwise, entering step 4.7);
4.7) detecting the SOC of the battery, and if the minimum SOC signal of the battery is generated, alarming and displaying faults by using an alarm display under the control of the single chip microcomputer system; otherwise, entering step 4.8);
4.8) detecting the voltage of the battery, and if the voltage of the battery is lower than 31.75V, alarming and displaying faults by using an alarm display under the control of the single chip microcomputer system; otherwise, the discharge part fault detection is completed, and the discharge operation can be performed.
In step 3), the method for real-time fault detection during the charging or discharging operation of the aviation lithium battery comprises the following steps in sequence:
5.1) in the process of charging or discharging the aviation lithium battery, the BMU discrete signal received by the battery signal interface and the fault detection circuit is detected by the single chip microcomputer system in real time, and the BMU discrete signal comprises: the method comprises the following steps of charging forbidding 1, discharging forbidding 1, forbidding 1 verification, charging forbidding 2, forbidding 2 verification, battery failure, low-voltage fault and overcurrent fault, interrupting the charging or discharging operation of the aviation lithium battery if the faults are detected, and simultaneously alarming and displaying fault codes by using an alarm display under the control of a single chip microcomputer system; otherwise, continuing to charge or discharge;
5.2) comparing the battery current value output by the battery monitoring unit with the current value detected by the charging and discharging current detection circuit, if the difference value of the current values is more than 3A, interrupting the charging or discharging operation of the aviation lithium battery, and simultaneously utilizing an alarm display to alarm and display faults under the control of the single chip microcomputer system; otherwise, the charging or discharging is continued.
The method for detecting the faults of the aircraft aviation lithium battery suitable for the Boeing 787 provided by the invention has the following beneficial effects: according to the principle characteristic of the lithium battery and the principle of generating the fault signal in the aviation lithium battery, the fault detection of the aviation lithium battery in the static state and the charging and discharging state can be realized, the daily maintenance requirement is met, the safe and reliable operation of the aviation lithium battery can be guaranteed, the service life of the aviation lithium battery is prolonged, and the flight safety is guaranteed. The fault detection method has the advantages of simplicity, easiness, high detection reliability and the like.
Drawings
Fig. 1 is a schematic view of a fault detection system adopted in the fault detection method for a boeing 787 aircraft lithium battery provided in the invention.
Fig. 2 is a flow chart of initial fault detection of a boeing 787 aircraft lithium battery provided by the invention.
Fig. 3 is a flow chart of fault detection of a charging part of a lithium battery applicable to boeing 787 aircraft aviation provided by the invention.
Fig. 4 is a flow chart of fault detection of the discharging part of the aircraft lithium battery suitable for the boeing 787 provided by the invention.
Fig. 5 is a flow chart of real-time fault detection of a boeing 787 aircraft lithium battery provided by the invention.
Detailed Description
The fault detection method suitable for the boeing 787 aircraft aviation lithium battery provided by the invention is described in detail below with reference to the accompanying drawings.
As shown in fig. 1, the fault detection method for the boeing 787 aircraft lithium battery provided by the invention comprises the following steps in sequence:
1) constructing a fault detection system of an aviation lithium battery 1, wherein a contactor 2 and a Battery Monitoring Unit (BMU)3 are arranged on the aviation lithium battery 1; the fault detection system comprises a singlechip system 6, an ambient temperature detection circuit 7, a battery signal interface and fault detection circuit 8, a battery voltage detection circuit 9, a charging and discharging current detection circuit 10 and an alarm display 11; the environment temperature detection circuit 7 is installed at the setting position of the aviation lithium battery 1 and is used for detecting the environment temperature of the aviation lithium battery 1; the battery signal interface and fault detection circuit 8 is connected to the battery monitoring unit 3 for the transmission, reception and detection of the following input and output signals, including: 8 BMU discrete fault signals including charge forbidding 1, discharge forbidding 1, forbidding 1 verification, charge forbidding 2, forbidding 2 verification, battery failure, low-voltage fault and overcurrent fault, battery voltage + signal, battery voltage-signal, current signal, battery internal temperature signal, battery minimum SOC signal, direct current +15V signal, GND signal, direct current-15V signal, battery charging signal and BMU enabling signal; the battery voltage detection circuit 9 is connected with the anode and the cathode of the aviation lithium battery 1 and is used for detecting the voltage of the aviation lithium battery 1; the charging and discharging current detection circuit 10 is connected with the anode and the cathode of the aviation lithium battery 1 and is used for detecting the current of the aviation lithium battery 1 during charging and discharging; the single chip microcomputer system 6 is simultaneously connected with the ambient temperature detection circuit 7, the battery signal interface and fault detection circuit 8, the battery voltage detection circuit 9, the charging and discharging current detection circuit 10 and the alarm display 11, and is used for completing analysis and processing of various detection signals uploaded by the ambient temperature detection circuit 7, the battery signal interface and fault detection circuit 8, the battery voltage detection circuit 9 and the charging and discharging current detection circuit 10, and controlling the alarm display 11 to give an alarm and display faults when faults are found.
2) Carrying out initial fault detection on the aviation lithium battery 1 in a static state by using the fault detection system;
3) under the condition that the failure of the aviation lithium battery 1 is not found in the initial failure detection process, the failure detection system is utilized to carry out the failure detection of a charging part before the aviation lithium battery 1 is charged; the method comprises the following steps of firstly carrying out discharge part fault detection before carrying out discharge operation on the aviation lithium battery 1; and carrying out real-time fault detection in the charging or discharging operation process of the aviation lithium battery 1.
As shown in fig. 2, in step 2), the method for detecting the initial fault of the lithium aviation battery 1 in the static state includes the following steps in sequence:
2.1) detecting the ambient temperature by using an ambient temperature detection circuit 7, then transmitting the ambient temperature to a singlechip system 6, judging whether the ambient temperature is in the range of 18-28 ℃ by the singlechip system 6, and if the ambient temperature is out of the range, alarming and displaying faults by using an alarm display 11 under the control of the singlechip system 6; otherwise, entering step 2.2);
2.2) comparing the environmental temperature with the internal temperature of the aviation lithium battery 1 detected by the battery signal interface and the fault detection circuit 8, and if the temperature difference between the environmental temperature and the internal temperature exceeds 5 ℃, alarming and fault displaying are carried out by using an alarm display 11 under the control of the singlechip system 6; otherwise, entering step 2.3);
2.3) detecting the BMU discrete signal received by the battery signal interface and fault detection circuit 8, wherein the BMU discrete signal comprises: the method comprises the following steps of charging forbidding 1, discharging forbidding 1, checking forbidding 1, charging forbidding 2, checking forbidding 2, battery failure, low-voltage fault and overcurrent fault, and if the faults are detected, alarming and displaying fault codes by using an alarm display 11 under the control of a single chip microcomputer system 6; otherwise, entering step 2.4);
2.4) inputting a BMU enabling signal;
2.5) detecting the BMU discrete signals, if a fault is detected, alarming by using an alarm display 11 under the control of the singlechip system 6 and displaying a fault code; otherwise, entering step 2.6);
2.6) inputting a battery charging signal;
2.7) detecting whether the contactor 2 on the aviation lithium battery 1 is disconnected or not, and if the contactor 2 is not disconnected, alarming and fault displaying are carried out by utilizing the alarm display 11 under the control of the singlechip system 6; otherwise, entering step 2.8);
2.8) detecting the BMU discrete signals, and if a fault is detected, alarming by using an alarm display 11 under the control of the singlechip system 6 and outputting a fault code; otherwise, entering step 2.9);
2.9) cutting off a battery charging signal and detecting whether the contactor 2 is closed, if the contactor 2 is not closed, alarming and fault displaying are carried out by utilizing the alarm display 11 under the control of the singlechip system 6; otherwise, entering step 2.10);
2.10) detecting the BMU discrete signals, if a fault is detected, alarming by using an alarm display 11 under the control of the singlechip system 6 and outputting a fault code; otherwise, entering step 2.11);
2.11) comparing the battery voltage value output by the battery monitoring unit 3 with the voltage value detected by the battery voltage detection circuit 9, and if the difference value of the voltage values is more than 0.03V, alarming and fault displaying are carried out by utilizing the alarm display 11 under the control of the singlechip system 6; otherwise, entering step 2.12);
2.12) comparing the battery current value output by the battery monitoring unit 3 with the current value detected by the charging and discharging current detection circuit 10, if the difference value of the current values is more than 3A, alarming and fault displaying are carried out by utilizing the alarm display 11 under the control of the singlechip system 6; otherwise, the initial fault detection is completed.
As shown in fig. 3, in step 3), the method for detecting the fault of the charging part before the charging operation is performed on the lithium aviation battery 1 by using the fault detection system comprises the following steps in sequence:
3.1) detecting the ambient temperature by using an ambient temperature detection circuit 7, then transmitting the ambient temperature to a singlechip system 6, judging whether the ambient temperature is in the range of 0-40 ℃ by the singlechip system 6, and if the ambient temperature is out of the range, alarming and displaying faults by using an alarm display 11 under the control of the singlechip system 6; otherwise, entering step 3.2);
3.2) detecting the BMU discrete signal received by the battery signal interface and fault detection circuit 8, wherein the BMU discrete signal comprises: the method comprises the following steps of charging forbidding 1, discharging forbidding 1, checking forbidding 1, charging forbidding 2, checking forbidding 2, battery failure, low-voltage fault and overcurrent fault, and if the faults are detected, alarming and displaying fault codes by using an alarm display 11 under the control of a single chip microcomputer system 6; otherwise, entering step 3.3);
3.3) inputting a BMU enabling signal;
3.4) detecting the BMU discrete signals, and if a fault is detected, alarming by using an alarm display 11 under the control of the singlechip system 6 and displaying a fault code; otherwise, entering step 3.5);
3.5) inputting a battery charging signal;
3.6) detecting whether the contactor 2 on the aviation lithium battery 1 is disconnected, and if the contactor 2 is not disconnected, alarming and fault displaying are carried out by utilizing the alarm display 11 under the control of the singlechip system 6; otherwise, entering step 3.7);
3.7) detecting the BMU discrete signals, if a fault is detected, alarming by using an alarm display 11 under the control of the singlechip system 6 and outputting a fault code; otherwise step 3.8) is entered.
3.8) cutting off a battery charging signal and detecting whether the contactor 2 is closed, if the contactor 2 is not closed, alarming and fault displaying are carried out by utilizing the alarm display 11 under the control of the singlechip system 6; otherwise step 3.9) is entered.
3.9) detecting the BMU discrete signals, and if a fault is detected, alarming by using an alarm display 11 under the control of the singlechip system 6 and outputting a fault code; otherwise step 3.10) is entered.
3.10) comparing the battery voltage value output by the battery monitoring unit 3 with the voltage value detected by the battery voltage detection circuit 9, and if the difference value of the voltage values is more than 0.03V, alarming and fault displaying are carried out by utilizing the alarm display 11 under the control of the singlechip system 6; otherwise step 3.11) is entered.
3.11) comparing the battery current value output by the battery monitoring unit 3 with the current value detected by the charging and discharging current detection circuit 10, and if the difference value of the current values is more than 3A, alarming and fault displaying are carried out by utilizing the alarm display 11 under the control of the singlechip system 6; otherwise, the charging part fault detection is completed, and the charging operation can be carried out.
As shown in fig. 4, in step 3), the method for detecting the fault of the discharge part before the discharging operation is performed on the lithium aviation battery 1 by using the fault detection system comprises the following steps in sequence:
4.1) the single chip microcomputer system 6 detects the BMU discrete signals received by the battery signal interface and the fault detection circuit 8, and the BMU discrete signals comprise: the method comprises the following steps of charging forbidding 1, discharging forbidding 1, checking forbidding 1, charging forbidding 2, checking forbidding 2, battery failure, low-voltage fault and overcurrent fault, and if the faults are detected, alarming and displaying fault codes by using an alarm display 11 under the control of a single chip microcomputer system 6; otherwise, entering step 4.2);
4.2) inputting a BMU enabling signal;
4.3) detecting the BMU discrete signals, if a fault is detected, alarming by using an alarm display 11 under the control of the singlechip system 6 and displaying a fault code; otherwise, entering step 4.4);
4.4) comparing the battery voltage value output by the battery monitoring unit 3 with the voltage value detected by the battery voltage detection circuit 9, and if the difference value of the voltage values is more than 0.03V, alarming and fault displaying are carried out by utilizing the alarm display 11 under the control of the singlechip system 6; otherwise, entering step 4.5);
4.5) comparing the battery current value output by the battery monitoring unit 3 with the current value detected by the charging and discharging current detection circuit 10, and if the difference value of the current values is more than 3A, alarming and fault displaying are carried out by utilizing the alarm display 11 under the control of the singlechip system 6; otherwise, entering step 4.6);
4.6) detecting the ambient temperature by using the ambient temperature detection circuit 7, then transmitting the ambient temperature to the singlechip system 6, judging whether the ambient temperature is in the range of 0-40 ℃ by the singlechip system 6, and if the ambient temperature is out of the range, alarming and displaying faults by using the alarm display 11 under the control of the singlechip system 6; otherwise, entering step 4.7);
4.7) detecting the SOC of the battery, and if the minimum SOC signal of the battery is generated, alarming and displaying faults by using an alarm display 11 under the control of the single chip microcomputer system 6; otherwise, entering step 4.8);
4.8) detecting the battery voltage, and if the battery voltage is lower than 31.75V, alarming and displaying faults by using the alarm display 11 under the control of the singlechip system 6; otherwise, the discharge part fault detection is completed, and the discharge operation can be performed.
As shown in fig. 5, in step 3), the method for real-time fault detection during the charging or discharging operation of the lithium aviation battery 1 includes the following steps in sequence:
5.1) in the process of charging or discharging operation of the aviation lithium battery 1, the BMU discrete signal received by the battery signal interface and the fault detection circuit 8 is detected by the singlechip system 6 in real time, and the BMU discrete signal comprises: the method comprises the following steps of charging forbidding 1, discharging forbidding 1, forbidding 1 verification, charging forbidding 2, forbidding 2 verification, battery failure, low-voltage fault and overcurrent fault, if the faults are detected, interrupting the charging or discharging operation of the aviation lithium battery 1, and simultaneously utilizing an alarm display 11 to give an alarm and display fault codes under the control of a single chip microcomputer system 6; otherwise, continuing to charge or discharge;
5.2) comparing the battery current value output by the battery monitoring unit 3 with the current value detected by the charging and discharging current detection circuit 10, if the difference value of the current values is more than 3A, interrupting the charging or discharging operation of the aviation lithium battery 1, and simultaneously performing alarm and fault display by using the alarm display 11 under the control of the singlechip microcomputer system 6; otherwise, the charging or discharging is continued.
Claims (2)
1. The utility model provides a fault detection method suitable for boeing 787 aircraft aviation lithium cell which characterized in that: the fault detection method comprises the following steps which are carried out in sequence:
1) constructing a fault detection system of an aviation lithium battery (1), wherein a contactor (2) and a battery monitoring unit (3) are arranged on the aviation lithium battery (1); the fault detection system comprises a single chip microcomputer system (6), an ambient temperature detection circuit (7), a battery signal interface, a fault detection circuit (8), a battery voltage detection circuit (9), a charging and discharging current detection circuit (10) and an alarm display (11); wherein the ambient temperature detection circuit (7) is arranged at the position where the aviation lithium battery (1) is arranged; the battery signal interface and the fault detection circuit (8) are connected with the battery monitoring unit (3); the battery voltage detection circuit (9) is connected with the anode and the cathode of the aviation lithium battery (1); the charging and discharging current detection circuit (10) is connected with the anode and the cathode of the aviation lithium battery (1); the single chip microcomputer system (6) is simultaneously connected with an ambient temperature detection circuit (7), a battery signal interface and fault detection circuit (8), a battery voltage detection circuit (9), a charging and discharging current detection circuit (10) and an alarm display (11);
2) the fault detection system is used for carrying out initial fault detection on the aviation lithium battery (1) in a static state;
3) under the condition that the fault of the aviation lithium battery (1) is not found in the initial fault detection process, the fault detection system is utilized to carry out fault detection on a charging part before the aviation lithium battery (1) is charged; the method comprises the steps of firstly carrying out discharge part fault detection before carrying out discharge operation on the aviation lithium battery (1); real-time fault detection is carried out in the process of charging or discharging the aviation lithium battery (1);
in the step 2), the method for detecting the initial fault of the aviation lithium battery (1) in the static state comprises the following steps in sequence:
2.1) detecting the ambient temperature by using an ambient temperature detection circuit (7), then transmitting the ambient temperature to a singlechip system (6), judging whether the ambient temperature is in the range of 18-28 ℃ by the singlechip system (6), and if the ambient temperature is out of the range, alarming and displaying faults by using an alarm display (11) under the control of the singlechip system (6); otherwise, entering step 2.2);
2.2) comparing the environmental temperature with the internal temperature of the aviation lithium battery (1) detected by a battery signal interface and a fault detection circuit (8), and if the temperature difference between the environmental temperature and the internal temperature exceeds 5 ℃, alarming and fault displaying are carried out by using an alarm display (11) under the control of a singlechip system (6); otherwise, entering step 2.3);
2.3) detecting the BMU discrete signal received by the battery signal interface and fault detection circuit (8), wherein the BMU discrete signal comprises: the method comprises the following steps of charging forbidding 1, discharging forbidding 1, forbidding 1 verification, charging forbidding 2, forbidding 2 verification, battery failure, low-voltage fault and overcurrent fault, and if the faults are detected, alarming and displaying fault codes by using an alarm display (11) under the control of a single chip microcomputer system (6); otherwise, entering step 2.4);
2.4) inputting a BMU enabling signal;
2.5) detecting the BMU discrete signals, and if a fault is detected, alarming and displaying a fault code by using an alarm display (11) under the control of a single chip microcomputer system (6); otherwise, entering step 2.6);
2.6) inputting a battery charging signal;
2.7) detecting whether the contactor (2) on the aviation lithium battery (1) is disconnected, and if the contactor (2) is not disconnected, alarming and fault displaying are carried out by using the alarm display (11) under the control of the singlechip system (6); otherwise, entering step 2.8);
2.8) detecting the BMU discrete signals, and if a fault is detected, alarming by using an alarm display (11) under the control of a single chip microcomputer system (6) and outputting a fault code; otherwise, entering step 2.9);
2.9) cutting off a battery charging signal and detecting whether the contactor (2) is closed, if the contactor (2) is not closed, alarming and fault displaying are carried out by utilizing the alarm display (11) under the control of the singlechip system (6); otherwise, entering step 2.10);
2.10) detecting the BMU discrete signals, if a fault is detected, alarming by using an alarm display (11) under the control of a singlechip system (6) and outputting a fault code; otherwise, entering step 2.11);
2.11) comparing the battery voltage value output by the battery monitoring unit (3) with the voltage value detected by the battery voltage detection circuit (9), and if the difference value of the voltage values is more than 0.03V, alarming and fault displaying are carried out by using the alarm display (11) under the control of the singlechip system (6); otherwise, entering step 2.12);
2.12) comparing the battery current value output by the battery monitoring unit (3) with the current value detected by the charging and discharging current detection circuit (10), and if the difference value of the current values is more than 3A, alarming and fault displaying are carried out by using an alarm display (11) under the control of the singlechip system (6); otherwise, the initial fault detection is finished;
in step 3), the method for detecting the fault of the charging part before the charging operation is performed on the aviation lithium battery (1) by using the fault detection system comprises the following steps in sequence:
3.1) detecting the ambient temperature by using an ambient temperature detection circuit (7), then transmitting the ambient temperature to a singlechip system (6), judging whether the ambient temperature is in the range of 0-40 ℃ by the singlechip system (6), and if the ambient temperature is out of the range, alarming and displaying faults by using an alarm display (11) under the control of the singlechip system (6); otherwise, entering step 3.2);
3.2) detecting the BMU discrete signal received by the battery signal interface and fault detection circuit (8), wherein the BMU discrete signal comprises: the method comprises the following steps of charging forbidding 1, discharging forbidding 1, forbidding 1 verification, charging forbidding 2, forbidding 2 verification, battery failure, low-voltage fault and overcurrent fault, and if the faults are detected, alarming and displaying fault codes by using an alarm display (11) under the control of a single chip microcomputer system (6); otherwise, entering step 3.3);
3.3) inputting a BMU enabling signal;
3.4) detecting the BMU discrete signals, and if a fault is detected, alarming and displaying a fault code by using an alarm display (11) under the control of a single chip microcomputer system (6); otherwise, entering step 3.5);
3.5) inputting a battery charging signal;
3.6) detecting whether the contactor (2) on the aviation lithium battery (1) is disconnected, and if the contactor (2) is not disconnected, alarming and fault displaying are carried out by using the alarm display (11) under the control of the singlechip system (6); otherwise, entering step 3.7);
3.7) detecting the BMU discrete signals, if a fault is detected, alarming by using an alarm display (11) under the control of a singlechip system (6) and outputting a fault code; otherwise, entering step 3.8);
3.8) cutting off a battery charging signal and detecting whether the contactor (2) is closed, if the contactor (2) is not closed, alarming and fault displaying are carried out by utilizing the alarm display (11) under the control of the singlechip system (6); otherwise, entering step 3.9);
3.9) detecting the BMU discrete signals, and if a fault is detected, alarming by using an alarm display (11) under the control of a singlechip system (6) and outputting a fault code; otherwise, entering step 3.10);
3.10) comparing the battery voltage value output by the battery monitoring unit (3) with the voltage value detected by the battery voltage detection circuit (9), and if the difference value of the voltage values is more than 0.03V, alarming and fault displaying are carried out by using an alarm display (11) under the control of the singlechip system (6); otherwise, entering step 3.11);
3.11) comparing the battery current value output by the battery monitoring unit (3) with the current value detected by the charging and discharging current detection circuit (10), and if the difference value of the current values is more than 3A, alarming and fault displaying are carried out by using the alarm display (11) under the control of the singlechip system (6); otherwise, the fault detection of the charging part is finished, and the charging operation can be carried out;
in step 3), the method for detecting the fault of the discharge part before the discharge operation is performed on the aviation lithium battery (1) by using the fault detection system comprises the following steps in sequence:
4.1) detecting the BMU discrete signals received by the battery signal interface and the fault detection circuit (8) by the singlechip system (6), wherein the BMU discrete signals comprise: the method comprises the following steps of charging forbidding 1, discharging forbidding 1, forbidding 1 verification, charging forbidding 2, forbidding 2 verification, battery failure, low-voltage fault and overcurrent fault, and if the faults are detected, alarming and displaying fault codes by using an alarm display (11) under the control of a single chip microcomputer system (6); otherwise, entering step 4.2);
4.2) inputting a BMU enabling signal;
4.3) detecting the BMU discrete signals, and if a fault is detected, alarming and displaying a fault code by using an alarm display (11) under the control of a single chip microcomputer system (6); otherwise, entering step 4.4);
4.4) comparing the battery voltage value output by the battery monitoring unit (3) with the voltage value detected by the battery voltage detection circuit (9), and if the difference value of the voltage values is more than 0.03V, alarming and fault displaying are carried out by using the alarm display (11) under the control of the singlechip system (6); otherwise, entering step 4.5);
4.5) comparing the battery current value output by the battery monitoring unit (3) with the current value detected by the charging and discharging current detection circuit (10), and if the difference value of the current values is more than 3A, alarming and fault displaying are carried out by using an alarm display (11) under the control of the singlechip system (6); otherwise, entering step 4.6);
4.6) detecting the ambient temperature by using an ambient temperature detection circuit (7), then transmitting the ambient temperature to a singlechip system (6), judging whether the ambient temperature is in the range of 0-40 ℃ by the singlechip system (6), and if the ambient temperature is out of the range, alarming and displaying faults by using an alarm display (11) under the control of the singlechip system (6); otherwise, entering step 4.7);
4.7) detecting the SOC of the battery, and if the minimum SOC signal of the battery is generated, alarming and fault displaying are carried out by utilizing an alarm display (11) under the control of the single chip microcomputer system (6); otherwise, entering step 4.8);
4.8) detecting the battery voltage, and if the battery voltage is lower than 31.75V, alarming and displaying faults by using the alarm display (11) under the control of the singlechip system (6); otherwise, the discharge part fault detection is completed, and the discharge operation can be performed.
2. The fault detection method suitable for the boeing 787 aircraft lithium battery of claim 1, wherein: in step 3), the method for real-time fault detection during the charging or discharging operation of the aviation lithium battery (1) comprises the following steps in sequence:
5.1) in the process of charging or discharging the aviation lithium battery (1), the BMU discrete signal received by the battery signal interface and the fault detection circuit (8) is detected in real time by the singlechip system (6), and the BMU discrete signal comprises: the method comprises the following steps of charging forbidding 1, discharging forbidding 1, forbidding 1 verification, charging forbidding 2, forbidding 2 verification, battery failure, low-voltage fault and overcurrent fault, interrupting the charging or discharging operation of the aviation lithium battery (1) if the faults are detected, and simultaneously alarming and displaying fault codes by using an alarm display (11) under the control of a single chip microcomputer system (6); otherwise, continuing to charge or discharge;
5.2) comparing the battery current value output by the battery monitoring unit (3) with the current value detected by the charging and discharging current detection circuit (10), if the difference value of the current values is more than 3A, interrupting the charging or discharging operation of the aviation lithium battery (1), and simultaneously utilizing an alarm display (11) to alarm and display faults under the control of the singlechip system (6); otherwise, the charging or discharging is continued.
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