A method and a tester for testing the capacity of a helicopter emergency battery

Abstract

The present invention relates to the technical field of aviation emergency power supply equipment, and discloses a method and a tester for testing the capacity of a helicopter emergency battery, including capacity testing and capacity recovery processing. The capacity testing includes rapid discharging, standing still, rapid charging, standing still, rapid discharging, standing still, and rapid charging in sequence. During the capacity testing, if the tested emergency battery fails, the capacity testing is aborted and the battery is switched to capacity recovery processing. The capacity recovery processing includes slow charging and slow discharging of the emergency battery. According to the inherent characteristics of the helicopter emergency battery, this method can complete the battery capacity detection, conventional charging and discharging, and capacity recovery of the emergency battery in various states in accordance with the requirements of the emergency battery maintenance manual, thereby prolonging the service life of the emergency battery and ensuring flight safety. At the same time, it has a reasonable structural design, convenient testing, and can independently complete capacity testing and capacity recovery, saving a large amount of manpower and material resources.

Description

Technical Field

[0001] The present invention relates to the technical field of aviation emergency power supply equipment, and particularly relates to a method and a tester for testing the capacity of a helicopter emergency battery. Background Art

[0002] The helicopter emergency battery is mainly used for emergency power supply of the standby attitude indicator of the helicopter. When the normal power supply of the helicopter fails, the emergency battery supplies power to maintain the flight of the helicopter to land at the nearest airport. Therefore, whether the emergency battery works reliably and whether its capacity is sufficient directly affect flight safety.

[0003] Due to the increasing requirements for the power supply of the helicopter emergency battery, the negative voltage increment needs to be tested during the capacity test, and whether the battery characteristics meet the requirements needs to be detected during the capacity test process. The ordinary charge and discharge method can no longer meet the test requirements and cannot well test and restore the battery capacity. Summary of the Invention

[0004] Aiming at the deficiencies of the existing technology, the purpose of the present invention is to provide a method and a tester for testing the capacity of a helicopter emergency battery.

[0005] In order to achieve the above purpose, the present invention provides the following technical solutions:

[0006] A method for testing the capacity of a helicopter emergency battery includes capacity testing and capacity recovery processing. The capacity testing includes rapid discharge, standing still, rapid charging, standing still, rapid discharge, standing still, and rapid charging in sequence. During the capacity testing, if the tested emergency battery fails, the capacity testing is aborted and the battery is switched to capacity recovery processing. The capacity recovery processing includes slow charging and slow discharging of the emergency battery.

[0007] Preferably, in the present invention, the capacity testing specifically includes the following steps:

[0008] S1: Rapidly discharge the emergency battery until the battery voltage is not greater than 18V, and stand still for 30 - 60 minutes;

[0009] S2: Rapidly charge the emergency battery for 60 minutes, and at the same time conduct a negative voltage increment test. When the negative voltage increment is greater than or equal to 2V, or the battery voltage reaches 32V but the charging time is less than 40 minutes, the battery is unqualified, the capacity testing ends, and capacity recovery processing is carried out. Otherwise, continue to the next step;

[0010] S3: Stand still for 30 - 60 minutes;

[0011] S4: Rapidly discharge the emergency battery until the battery voltage is not greater than 18V, and at the same time conduct a capacity detection. When the capacity is less than 75%, the battery is unqualified, the capacity testing ends, and capacity recovery processing is carried out. Otherwise, proceed to the next step;

[0012] S5: Stand still for 30 - 60 minutes;

[0013] S6: Quick charge the emergency battery for 60 minutes, and simultaneously conduct a negative voltage increment test. When the negative voltage increment is greater than or equal to 2V, or the battery voltage is greater than or equal to 32V but the charging time is less than 40 minutes, the battery is unqualified, the capacity test ends, and capacity recovery processing is carried out. Otherwise, the battery is qualified, the capacity test ends, and the measurement results are automatically printed.

[0014] In the present invention, preferably, the capacity recovery processing includes 3 times of slow charging and slow discharging. The specific steps of slow charging include:

[0015] S01: Set the charging current, limiting voltage, and charging time, and conduct slow charging. The slow charging current is 0.45A, and the charging time is 600 minutes;

[0016] S02: Start charging and simultaneously time. Collect the voltage and current of the emergency battery, calculate the negative voltage increment value, and judge it. If it is greater than or equal to 2V, the charging characteristics of the emergency battery are poor, the emergency battery is unqualified, print the recorded data, and end the charging. Otherwise, continue charging;

[0017] S03: Judge whether the battery voltage value is greater than or equal to 32V. When the battery voltage is greater than or equal to 32V and the charging time is less than or equal to 400 minutes, the emergency battery is unqualified, print the recorded data, and end the charging. Otherwise, continue charging;

[0018] S04: When the timing time is up, end the charging.

[0019] In the present invention, preferably, the specific steps of slow discharging include:

[0020] S11: Set the discharging current, rated capacity, and discharging termination voltage, and conduct slow discharging. The discharging current is 0.90A, and the termination voltage is 18V;

[0021] S12: Start discharging and simultaneously time. Collect the voltage and current of the emergency battery, and calculate the percentage of the discharged capacity;

[0022] S13: Judge whether the termination voltage is reached. If the termination voltage is reached but the capacity is less than or equal to 75%, the battery is unqualified, otherwise it is qualified. Print the recorded data, and the capacity recovery processing ends.

[0023] A helicopter emergency battery capacity tester, comprising a constant current charging circuit, a load discharging circuit, a signal amplifying circuit, a signal acquisition circuit, a reverse connection protection circuit and a main control module; the constant current charging circuit and the load discharging circuit are connected to the emergency battery through the reverse connection protection circuit, and are respectively used for charging and discharging the emergency battery, and the reverse connection protection circuit is used for protecting the emergency battery against reverse connection to prevent damage to the emergency battery; the signal acquisition circuit includes a Hall sensor U112, and the Hall sensor U112 is connected to the emergency battery; the signal amplifying circuit receives the signal of the signal acquisition circuit, processes it and transmits it to the main control module, and the main control module sends a charging control signal to the constant current charging circuit through a charging control circuit, and the main control module is directly connected to the load discharging circuit and sends a discharging control signal.

[0024] In the present invention, preferably, the reverse connection protection circuit includes a control relay K1, a protection relay K12 and a switching tube Q3. The coil of the control relay K1 is connected in series with the switching tube Q3. The first contact of the control relay K1 is connected to the third contact of the protection relay K12. One end of the coil of the protection relay K12 is connected to the battery, and the other end is grounded through a diode D60.

[0025] In the present invention, preferably, the signal amplifying circuit includes a follower U114. A resistor R116 is connected in series at the output end of the follower U114, and is grounded through a parallel circuit of a resistor R210 and a capacitor C211, and is connected to a protection circuit composed of diodes D114 and D116. The signal amplifying circuit is used for amplifying the current sampling signal.

[0026] In the present invention, preferably, the charging control circuit includes a voltage amplifying circuit and a current amplifying circuit. The voltage amplifying circuit includes an operational amplifier U200, and the operational amplifier U200 is used for amplifying the voltage control signal. The current amplifying circuit includes an operational amplifier U201, and the operational amplifier U201 is used for amplifying the current control signal.

[0027] In the present invention, preferably, the main control module is further connected with a USB module, a touch display screen and a micro printer. The USB module is used for saving electronic version measurement data; the touch display screen is used for realizing human-computer interaction; the micro printer is used for printing the measurement data.

[0028] Compared with the prior art, the beneficial effects of the present invention are:

[0029] According to the inherent characteristics of the helicopter emergency battery, the method of the present invention can complete the battery capacity detection, conventional charge and discharge, and capacity recovery of the emergency battery in various states according to the requirements of the emergency battery maintenance manual, thereby extending the service life of the emergency battery and ensuring flight safety. At the same time, it has a reasonable structural design, convenient testing, and can independently complete capacity testing and capacity recovery, saving a large amount of manpower and material resources. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 It is a capacity test flow chart of a method for testing the capacity of a helicopter emergency battery according to the present invention.

[0031] Figure 2 It is a charging flow chart of a method for testing the capacity of a helicopter emergency battery according to the present invention.

[0032] Figure 3 It is a discharge flow chart of a method for testing the capacity of a helicopter emergency battery according to the present invention.

[0033] Figure 4 It is a structural block diagram of a capacity tester for a helicopter emergency battery according to the present invention.

[0034] Figure 5 It is an anti-reverse protection circuit diagram of a capacity tester for a helicopter emergency battery according to the present invention.

[0035] Figure 6 It is a signal acquisition circuit diagram of a capacity tester for a helicopter emergency battery according to the present invention.

[0036] Figure 7 It is a signal amplification circuit diagram of a capacity tester for a helicopter emergency battery according to the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0037] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0038] It should be noted that when a component is referred to as "fixed to" another component, it can be directly on the other component or there can also be an intermediate component. When a component is considered to be "connected to" another component, it can be directly connected to the other component or there may be an intermediate component at the same time. When a component is considered to be "disposed on" another component, it can be directly disposed on the other component or there may be an intermediate component at the same time. The terms "vertical", "horizontal", "left", "right" and similar expressions used herein are for illustrative purposes only.

[0039] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by those of ordinary skill in the technical field to which this invention belongs. The terms used in the description of the present invention herein are for the purpose of describing specific embodiments only and are not intended to limit the present invention. The term "and / or" used herein includes any and all combinations of one or more of the related listed items.

[0040] Please also refer to Figures 1 to 3 , a preferred embodiment of the present invention provides a method for testing the capacity of a helicopter emergency battery. Through input research on the SB of the emergency battery and the relevant CMM manual, the optimal capacity testing and capacity recovery methods are proposed, including 7 steps of 2 chargings, 2 dischargings and 3 static waits. During the charging and discharging processes, the state detection of the battery is automatically completed, and qualified evaluation is carried out based on voltage negative increment (Negative Voltage slope - ΔU), charge and discharge voltage, current and time data, including capacity testing and capacity recovery processing. The capacity testing includes sequential rapid discharging, static waiting, rapid charging, static waiting, rapid discharging, static waiting, and rapid charging. In the capacity testing, the emergency battery with unqualified testing stops the capacity testing and turns to capacity recovery processing. The capacity recovery processing includes slow charging and slow discharging of the emergency battery.

[0041] Specifically, the capacity testing specifically includes the following steps:

[0042] S1: Rapidly discharge the emergency battery until the battery voltage is not greater than 18V, and statically wait for 30 - 60 minutes to wait for the internal chemical reaction of the battery to be completed thoroughly and reduce the battery temperature;

[0043] S2: Rapidly charge the emergency battery for 60 minutes, with a rapid charging current of 4.5A, and at the same time conduct a voltage negative increment test. When the voltage negative increment is greater than or equal to 2V, or the battery voltage reaches 32V but the charging time is less than 40 minutes, the battery is unqualified, the capacity testing ends, and capacity recovery processing is carried out. Otherwise, continue to the next step;

[0044] S3: Statically wait for 30 - 60 minutes to wait for the internal chemical reaction of the battery to be completed thoroughly and reduce the battery temperature;

[0045] S4: Rapidly discharge the emergency battery until the battery voltage is not greater than 18V, with a rapid discharge current of 4A. At the same time, conduct a capacity test. When the capacity is less than 75%, the battery is unqualified, the capacity test ends, and capacity recovery processing is performed. Otherwise, proceed to the next step;

[0046] S5: Let it stand for 30 - 60 minutes to wait for the internal chemical reaction of the battery to be completed thoroughly and reduce the battery temperature;

[0047] S6: Rapidly charge the emergency battery for 60 minutes, with a rapid charge current of 4.5A. At the same time, conduct a voltage negative increment test. When the voltage negative increment is greater than or equal to 2V, or the battery voltage is greater than or equal to 32V but the charging time is less than 40 minutes, the battery is unqualified, the capacity test ends, and capacity recovery processing is performed. Otherwise, the battery is qualified, the capacity test ends, and the measurement results are printed automatically.

[0048] In this embodiment, the capacity recovery processing includes 3 times of slow charging and slow discharging. The specific steps of slow charging include:

[0049] S01: Set the charging current, limit voltage, and charging time, and conduct slow charging. The slow charging current is 0.45A, and the charging time is 600 minutes;

[0050] S02: Start charging and time simultaneously. Collect the voltage and current of the emergency battery, calculate the voltage negative increment value, and judge it. If it is greater than or equal to 2V, the charging characteristic of the emergency battery is poor, the emergency battery is unqualified, print the recorded data, and end the charging. Otherwise, continue charging;

[0051] S03: Judge whether the battery voltage value is greater than or equal to 32V. When the battery voltage is greater than or equal to 32V and the charging time is less than or equal to 400 minutes, the emergency battery is unqualified, print the recorded data, and end the charging. Otherwise, continue charging;

[0052] S04: When the timing time is up, end the charging.

[0053] Furthermore, the specific steps of slow discharging include:

[0054] S11: Set the discharge current, rated capacity, and discharge termination voltage, and conduct slow discharging. The discharge current is 0.90A, and the termination voltage is 18V;

[0055] S12: Start discharging and time simultaneously. Collect the voltage and current of the emergency battery, and calculate the percentage of the discharged capacity;

[0056] S13: Judge whether the termination voltage is reached. If the termination voltage is reached but the capacity is less than or equal to 75%, the battery is unqualified. Otherwise, it is qualified, print the recorded data, and the capacity recovery processing ends.

[0057] Please refer to Figure 4 , another preferred embodiment of the present invention provides a helicopter emergency battery capacity tester, which includes a constant current charging circuit, a load discharging circuit, a signal amplification circuit, a signal acquisition circuit, a reverse connection protection circuit, and a main control module; the constant current charging circuit and the load discharging circuit are connected to the emergency battery through the reverse connection protection circuit, and are respectively used for charging and discharging the emergency battery. The reverse connection protection circuit is used for reverse connection protection of the emergency battery to prevent damage to the emergency battery; the signal acquisition circuit includes a Hall sensor U112, and the Hall sensor U112 is connected to the emergency battery for collecting the voltage and current signals of the emergency battery; the signal amplification circuit receives the signals of the signal acquisition circuit, processes them and transmits them to the main control module, and the main control module sends a charging control signal to the constant current charging circuit through the charging control circuit, and the main control module is directly connected to the load discharging circuit and sends a discharging control signal; the main control module is used for sampling and calculating the transmitted signals, and judging the capacity of the emergency battery during the charging and discharging process.

[0058] Specifically, the main control module adopts a single-chip microcomputer system. The main control module sends a charging instruction to the constant current charging circuit through the charging control circuit, and the constant current charging circuit charges the emergency battery. The main control module sends a discharging instruction to the load discharging circuit, and the load discharging circuit discharges the emergency battery. During the charging or discharging process of the emergency battery, the Hall sensor U112 connected to the emergency battery collects the current signal and transmits it to the signal amplification circuit. The signal amplification circuit processes the signal and then transmits it to the main control module. The main control module calculates according to the input signal, calculates the charging time and the voltage negative increment -ΔU, and determines whether the capacity of the emergency battery is qualified by comparison. The whole process automatically completes the constant current and constant voltage charging, discharging and capacity testing of the emergency battery, with reasonable design, convenient testing, and saving a lot of manpower and material resources.

[0059] Please refer to Figure 5 , in this embodiment, the reverse connection protection circuit includes a control relay K1, a protection relay K12, and a switching transistor Q3. The coil of the control relay K1 is connected in series with the switching transistor Q3. The first contact of the control relay K1 is connected to the third contact of the protection relay K12. One end of the coil of the protection relay K12 is connected to the battery, and the other end is grounded through a diode D60.

[0060] Specifically, one end of the coil of control relay K1 is connected to the 5V power supply, and the other end is grounded through switching transistor Q3. The base of switching transistor Q3 is connected to the main control module through resistor R31. A capacitor C65 is also grounded between resistor R31 and switching transistor Q3. A freewheeling diode D5 is connected in parallel with the coil of control relay K1. The common contact of control relay K1 is connected to the 15V power supply. The first contact of control relay K1 is connected to the third contact of protection relay K12 and is grounded after being reversely connected with diode D6. One end of the coil of protection relay K12 is connected to the battery, and the other end is grounded through diode D60. A freewheeling diode D61 is connected in parallel at both ends. The common contact of protection relay K12 is connected to the charge and discharge control contactor through socket P6. When the battery is not reversely connected, no current passes through protection relay K12, and the third contact is in the closed state. When it is necessary to charge and discharge the battery, the main control module sends a signal to switching transistor Q3, causing switching transistor Q3 to conduct, and the coil of control relay K1 is energized, causing the first contact to close. The current passes through the third contact to the charge and discharge control contactor, making the charge and discharge control contactor energized. When the battery is reversely connected, the coil of protection relay K12 is energized, the fourth contact of protection relay K12 closes, and the third contact opens. Even if the coil of control relay K1 is energized, the charge and discharge control contactor is not energized, thus protecting the battery.

[0061] Please refer to Figure 6 , in this embodiment, the Hall sensor U112 outputs a current feedback value. The current feedback value is filtered by capacitors C618 and C619 and then input to the signal amplification circuit. The signal amplification circuit includes a follower U114. The inverting input terminal of follower U114 is connected to the output terminal. One end of the protection circuits of diodes D114 and D116 is connected to the 3.3V power supply and the other end is grounded. The signal amplification circuit amplifies the signal according to the current feedback value and inputs it to the main control module.

[0062] Please refer to Figure 7 , in this embodiment, the charging control circuit includes a voltage amplification circuit and a current amplification circuit. The voltage amplification circuit includes an operational amplifier U200, and operational amplifier U200 is used to amplify the voltage control signal. The current amplification circuit includes an operational amplifier U201, and operational amplifier U201 is used to amplify the current control signal.

[0063] Specifically, the voltage amplification circuit includes an operational amplifier U200, which is used to amplify the charging voltage signal. The current amplification circuit includes an operational amplifier U201, which is used to amplify the charging current signal. Both the voltage amplification circuit and the current amplification circuit adopt negative feedback amplification circuits. The inverting input terminal of the operational amplifier U200 is connected to the output terminal through a resistor R204, and the output terminal is grounded through a parallel circuit composed of a capacitor C202, a resistor R201, and a diode D201. The inverting input terminal of the operational amplifier U201 is connected to the output terminal through a resistor R208, and the output terminal is grounded through a parallel circuit composed of a capacitor C205, a resistor R202, and a diode D202.

[0064] In this embodiment, the main control module is further connected to a USB module, which is an external memory for storing electronic measurement data. The main control module is also connected to a touch display screen, which is used to achieve human-computer interaction and control the charging and discharging of the aviation battery. The main control module is also connected to a micro printer, which is used to print the measurement data for analysis.

[0065] Working principle:

[0066] Capacity test process: First, select capacity test on the touch display screen, and then select the specific battery model. The tester automatically extracts the battery parameters and charge and discharge parameters in the database and executes steps S1 to S6 in sequence. If the capacity does not meet the requirements or the charging characteristics are poor, capacity recovery is performed through slow charging and slow discharging. Generally, 3 cycles are required for capacity recovery. If the requirements are not met after 3 cycles, the battery is scrapped.

[0067] Capacity recovery process: During slow charging, parameters such as the model of the battery under test, charging current, limiting voltage, and charging time are input through the touch display screen. Through the operation of the main control module, an instruction is output to the contactor K11. The first contact of the contactor K11 is closed, and the constant current charging circuit charges the emergency battery. The Hall sensor U112 collects the current signal of the emergency battery and transmits it to the signal amplification circuit. After signal processing by the signal amplification circuit, it is transmitted to the main control module for operation, and the charging time and voltage negative increment -ΔU are calculated. Finally, it is displayed through the touch display screen. The main control module controls the constant current charging circuit to perform constant current charging through the charging control circuit. When the charging end time condition is met, the charging ends. When the voltage negative increment -ΔU exceeds the standard or the charging time is insufficient during charging, the main control module will alarm through the touch display screen. Finally, the measurement data is saved to the memory through the USB module and can be printed through the micro printer for analysis. When the battery polarity is reversed, protection is achieved by the reverse connection protection circuit to prevent damage to the battery and the tester.

[0068] During discharging, parameters such as the model, discharging current, termination voltage, and rated capacity of the emergency battery to be charged are first input through the touch display screen. After being calculated by the main control module, instructions are output to the electronic load discharging circuit to discharge the emergency battery. The Hall sensor U112 collects the current signal of the emergency battery and transmits it to the signal amplification circuit. After passing through the signal amplification circuit, it is then transmitted to the main control module for calculation, and the percentage of the battery's discharged capacity is calculated. Finally, it is displayed through the touch display screen. The main control module controls the electronic load discharging circuit to perform constant current charging and discharging. When the discharging termination voltage end condition is met, the discharging ends. When charging with an unqualified capacity, the main control module will alarm through the touch display screen. Finally, the measured data is saved to the memory through the USB interface and can be printed through the micro printer for analysis.

[0069] The above description is a detailed description of the preferred feasible embodiment of the present invention. However, the embodiment is not intended to limit the scope of the patent application of the present invention. Any equivalent changes or modifications completed under the technical spirit disclosed by the present invention should fall within the scope of the patent covered by the present invention.

Claims

1. A method for testing the capacity of an emergency battery of a helicopter, characterized in that, Including capacity testing and capacity recovery processing, where the capacity testing includes sequential rapid discharging, standing still, rapid charging, standing still, rapid discharging, standing still, and rapid charging. During the capacity testing, if the emergency battery fails the test, the capacity testing is aborted and the capacity recovery processing is initiated. The capacity recovery processing includes slow charging and slow discharging of the emergency battery; The capacity recovery processing includes 3 times of slow charging and slow discharging. The specific steps of slow charging include: S01: Set the charging current, limiting voltage, and charging time, and perform slow charging. The slow charging current is 0.45 A and the charging time is 600 minutes; S02: Start charging and start timing simultaneously. Collect the voltage and current of the emergency battery, calculate the negative voltage increment value, and judge it. If it is greater than or equal to 2 V, the charging characteristic of the emergency battery is poor and the emergency battery is unqualified. Print the recorded data and end the charging. Otherwise, continue charging; S03: Judge whether the battery voltage value is greater than or equal to 32 V. When the battery voltage is greater than or equal to 32 V and the charging time is less than or equal to 400 minutes, the emergency battery is unqualified. Print the recorded data and end the charging. Otherwise, continue charging; S04: When the timing time is up, end the charging; The specific steps of the slow discharging include: S11: Set the discharging current, rated capacity, and discharging termination voltage, and perform slow discharging. The discharging current is 0.90 A and the termination voltage is 18 V; S12: Start timing while starting to discharge. Collect the voltage and current of the emergency battery and calculate the discharged capacity percentage; S13: Judge whether the termination voltage is reached. If the termination voltage is reached but the capacity is less than or equal to 75%, the battery is unqualified. Otherwise, it is qualified. Print the recorded data and the capacity recovery processing ends.

2. The method for testing the capacity of the emergency battery of a helicopter according to claim 1, characterized in that, The specific steps of the capacity testing include the following: S1: Rapidly discharge the emergency battery until the battery voltage is not greater than 18 V, and stand still for 30 - 60 minutes; S2: Rapidly charge the emergency battery for 60 minutes while performing the negative voltage increment test. When the negative voltage increment is greater than or equal to 2 V, or the battery voltage reaches 32 V but the charging time is less than 40 minutes, the battery is unqualified and the capacity testing ends. The capacity recovery processing is initiated. Otherwise, continue to the next step; S3: Stand still for 30 - 60 minutes; S4: Rapidly discharge the emergency battery until the battery voltage is not greater than 18 V while performing capacity detection. When the capacity is less than 75%, the battery is unqualified and the capacity testing ends. The capacity recovery processing is initiated. Otherwise, proceed to the next step; S5: Stand still for 30 - 60 minutes; S6: Rapidly charge the emergency battery for 60 minutes while performing the negative voltage increment test. When the negative voltage increment is greater than or equal to 2 V, or the battery voltage is greater than or equal to 32 V but the charging time is less than 40 minutes, the battery is unqualified and the capacity testing ends. The capacity recovery processing is initiated. Otherwise, the battery is qualified and the capacity testing ends. Automatically print the measurement results.

3. A helicopter emergency battery capacity tester, based on the helicopter emergency battery capacity testing method described in claim 2, characterized in that, It includes a constant current charging circuit, a load discharging circuit, a signal amplification circuit, a signal acquisition circuit, a reverse connection protection circuit and a main control module; the constant current charging circuit and the load discharging circuit are connected to the emergency battery through the reverse connection protection circuit, and are respectively used for charging and discharging the emergency battery. The reverse connection protection circuit is used for reverse connection protection of the emergency battery to prevent damage to the emergency battery; the signal acquisition circuit includes a Hall sensor U112, and the Hall sensor U112 is connected to the emergency battery; the signal amplification circuit receives the signal of the signal acquisition circuit, processes it and transmits it to the main control module, and the main control module sends a charging control signal to the constant current charging circuit through the charging control circuit, and the main control module is directly connected to the load discharging circuit and sends a discharging control signal.

4. The helicopter emergency battery capacity tester according to claim 3, wherein, The reverse connection protection circuit includes a control relay K1, a protection relay K12 and a switching tube Q3. The coil of the control relay K1 is connected in series with the switching tube Q3. The first contact of the control relay K1 is connected to the third contact of the protection relay K12. One end of the coil of the protection relay K12 is connected to the battery, and the other end is grounded through a diode D60.

5. The helicopter emergency battery capacity tester according to claim 4, wherein The signal amplification circuit includes a follower U114. A resistor R116 is connected in series at the output end of the follower U114, and is grounded through a parallel circuit of a resistor R210 and a capacitor C211, and is connected with a protection circuit composed of diodes D114 and D116. The signal amplification circuit is used for amplifying the current sampling signal.

6. The helicopter emergency battery capacity tester according to claim 5, characterized in that, The charging control circuit includes a voltage amplification circuit and a current amplification circuit. The voltage amplification circuit includes an operational amplifier U200, and the operational amplifier U200 is used for amplifying the voltage control signal. The current amplification circuit includes an operational amplifier U201, and the operational amplifier U201 is used for amplifying the current control signal.

7. The helicopter emergency battery capacity tester according to claim 3, wherein The main control module is also connected with a USB module, a touch display screen and a micro printer. The USB module is used for saving electronic measurement data; the touch display screen is used for realizing human-computer interaction; the micro printer is used for printing the measurement data.

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