Charging and discharging control instrument for airplane storage battery

Abstract

The utility model discloses a charging and discharging control instrument for an aircraft storage battery, which relates to the technical field of charging and discharging of the aircraft storage battery, integrates a plurality of charging and discharging control modules, realizes charging and discharging operation on the aircraft storage battery through a charging module, a mutual inductor, a main power supply connector and a discharging module, and can charge and discharge the aircraft storage battery in the charging and discharging process. Each single battery in the airplane storage battery is connected through the cell connector, the voltage data of each single battery is acquired by the voltage acquisition board card, and the relay module is provided with a group of pins corresponding to the pins of the cell connector so as to realize short circuit. Different pins of the total voltage acquisition module are used for cooperatively acquiring the total voltage of different airplane storage batteries, and different pins of the current acquisition module are used for cooperatively acquiring the current of different airplane storage batteries, so that the charging and discharging processes of a plurality of airplane storage batteries can be monitored at the same time. According to the utility model, charging and discharging monitoring of a plurality of airplane storage batteries can be realized at the same time, and the monitoring efficiency is high.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of airplane battery charging and discharging, especially to a charging and discharging control instrument for airplane battery. BACKGROUND

[0002] The nickel-chromium battery on the airplane is a rechargeable storage battery based on the nickel and cadmium electrochemical system, which has been long-term used as the core equipment of the key direct-current power supply system to guarantee the flight safety and normal operation due to its high reliability, wide temperature adaptability and strong rate discharge capability. The nickel-chromium battery is composed of multiple single batteries in series, which forms different total voltage levels according to the power supply demand of the airplane.

[0003] At present, when the nickel-chromium battery is monitored for charging and discharging, it needs to be monitored for charging and discharging separately according to different batteries, and each battery is composed of multiple single batteries, which needs to monitor each single battery of each battery and then collect all the monitoring data, resulting in that the existing charging and discharging monitoring of multiple nickel-chromium batteries is not only low in efficiency, but also consumes a lot of manpower and time. UTILITY MODEL CONTENT

[0004] Therefore, the application provides a charging and discharging control instrument for airplane battery to solve the problems in the prior art.

[0005] The first aspect of the application provides a charging and discharging control instrument for airplane battery, which comprises:

[0006] a plurality of charging and discharging control modules, each of which comprises a cell connector, a voltage acquisition board card, a relay module, a mutual inductor, a main power connector, a charging module and a discharging module, and all the charging and discharging control modules share a first direct-current power supply, a second direct-current power supply, a total voltage acquisition module and a current acquisition module;

[0007] One end of the cell connector is connected with each single battery in a single airplane battery, and the other end of the cell connector is connected with the relay module, which comprises multiple groups of short-circuit pins, each group of which realizes short-circuiting with each single battery in a single airplane battery; the voltage acquisition board card is connected with the other end of the cell connector and is used to acquire the voltage of each single battery in a single airplane battery;

[0008] One end of the charging module is connected with one end of the mutual inductor, and the other end of the mutual inductor is connected with one end of the main power connector, and the other end of the main power connector is used to connect the airplane battery, thereby realizing charging of the airplane battery;

[0009] The airplane battery is connected with the main power connector and then connected with the discharging module, thereby realizing discharging of the airplane battery.

[0010] The total voltage acquisition module comprises a plurality of groups of voltage acquisition pins, each group of voltage acquisition pins being used to acquire the total voltage of a single aircraft battery; the current acquisition module comprises a plurality of groups of current acquisition pins, each group of current acquisition pins being used to acquire the current of a single aircraft battery; the first DC power supply supplies power to the voltage acquisition board card, the relay module, the total voltage acquisition module, and the current acquisition module; and the second DC power supply supplies power to the mutual inductor.

[0011] In a possible implementation manner of the first aspect, the charging module comprises a charging power supply, a relay K1, and a diode D1, the charging power supply is connected with the positive electrode of the diode D1, the negative electrode of the diode D1 is connected with one end of the relay K1, the other end of the relay K1 is connected with one end of the mutual inductor, and the other end of the mutual inductor is connected with the No. 1 pin and the No. 3 pin of the main power connector.

[0012] In a possible implementation manner of the first aspect, the discharging module comprises an electronic load and a relay K2, the positive electrode of the electronic load is connected with one end of the mutual inductor through the relay K2, and the negative electrode of the electronic load is connected with the No. 2 pin and the No. 4 pin of the main power connector through the relay K2.

[0013] In a possible implementation manner of the first aspect, the relay K1 and the relay K2 are both double-pole single-throw relays.

[0014] In a possible implementation manner of the first aspect, the number of the charging and discharging control modules is six.

[0015] In a possible implementation manner of the first aspect, the first DC power supply is a 24V DC power supply, and the second DC power supply is a 12V DC power supply.

[0016] In a possible implementation manner of the first aspect, the charging power supply is a 30V charging power supply.

[0017] In a possible implementation manner of the first aspect, the model of the voltage acquisition board card is ZH-44241G-14F2, the model of the total voltage acquisition module is ZH-44081-14M2, and the model of the current acquisition module is ZH-44082-14M2.

[0018] Its beneficial effect lies in: the utility model discloses a kind of for aircraft battery's charge-discharge control instrument, integrates multiple charge-discharge control module, each charge-discharge control module includes cell connector, voltage acquisition board card, relay module, mutual inductor, main power connector, charging module and discharging module, and share first DC power supply, second DC power supply, total voltage acquisition module and current acquisition module;Through charging module, mutual inductor, main power connector and discharging module, realize charge-discharge operation to aircraft battery, in charge-discharge process, through cell connector connects each single battery in aircraft battery, utilizes voltage acquisition board card to gather the voltage data of each single battery, while the pins of relay module corresponding cell connector are all provided with a group of pins to realize short circuit, utilize the different pins of total voltage acquisition module to cooperate and gather the total voltage of different aircraft battery, and the different pins of current acquisition module cooperate and gather the current of different aircraft battery, finally realize the monitoring of the charge-discharge process of multiple aircraft battery simultaneously.The utility model can realize the charge-discharge monitoring of multiple aircraft battery simultaneously, and monitoring efficiency is higher. BRIEF DESCRIPTION OF DRAWINGS

[0019] In order to more clearly illustrate the technical solutions of the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiment or prior art description. Obviously, the drawings in the following description are only part of the embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor on the basis of the provided drawings.

[0020] Figure 1 It is a kind of charge-discharge control instrument circuit schematic diagram for aircraft battery provided by the embodiment of the present application;

[0021] Figure 2 It is a kind of charge-discharge control instrument circuit schematic diagram for aircraft battery provided by the embodiment of the present application;

[0022] Figure 3 It is a kind of charge-discharge control instrument circuit schematic diagram for aircraft battery provided by the embodiment of the present application; DETAILED DESCRIPTION

[0023] The technical solutions of the embodiments of the present application will be described clearly and completely in the following by combining with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor are within the scope of protection of the present application.

[0024] In this application, the terms such as first and second, etc. are merely used to distinguish one entity or operation from another, and do not necessarily require or imply there is any such actual relationship or order between these entities or operations. Also, the terms "include", "contain" or any other variants thereof are intended to cover non-exclusive inclusion, so that the process, method, article or equipment including a series of elements not only includes those elements, but also includes other elements not explicitly listed or inherent to such process, method, article or equipment. Without more limitations, the element defined by the statement "including a" does not exclude the presence of additional identical elements in the process, method, article or equipment including the element.

[0025] Embodiments

[0026] In the prior art, when monitoring the charging and discharging of nickel-chromium batteries, it is necessary to separately monitor the charging and discharging of different batteries, and each battery is composed of multiple single batteries, which requires monitoring each single battery of each battery, and then collecting all the monitoring data, resulting in that when monitoring the charging and discharging of multiple nickel-chromium batteries, the monitoring efficiency is low, and a lot of manpower and time is consumed.

[0027] Therefore, the present application provides a charging and discharging control instrument for aircraft batteries, as shown in Figure 1 、 Figure 2 and Figure 3 , comprising:

[0028] a plurality of charging and discharging control modules, each charging and discharging control module comprising a cell connector, a voltage acquisition board card, a relay module, a mutual inductor, a main power connector, a charging module and a discharging module, all charging and discharging control modules sharing a first DC power supply, a second DC power supply, a total voltage acquisition module and a current acquisition module;

[0029] One end of the cell connector is connected with each single battery in a single aircraft battery, and the other end of the cell connector is connected with the relay module, the relay module comprising a plurality of groups of short-circuit pins, each group of short-circuit pins achieving short-circuit with each single battery in a single aircraft battery; the voltage acquisition board card is connected with the other end of the cell connector, for acquiring the voltage of each single battery in a single aircraft battery;

[0030] One end of the charging module is connected with one end of the mutual inductor, the other end of the mutual inductor is connected with one end of the main power connector, and the other end of the main power connector is used for connecting the aircraft battery, achieving charging of the aircraft battery;

[0031] The aircraft battery is connected with the main power connector and then connected with the discharging module, so as to realize discharging of the aircraft battery.

[0032] The total voltage acquisition module comprises a plurality of groups of voltage acquisition pins, each group of voltage acquisition pins being used for acquiring the total voltage of a single aircraft battery; the current acquisition module comprises a plurality of groups of current acquisition pins, each group of current acquisition pins being used for acquiring the current of a single aircraft battery; the first direct current power supply is used for supplying power to the voltage acquisition board card, the relay module, the total voltage acquisition module and the current acquisition module; and the second direct current power supply is used for supplying power to the mutual inductor.

[0033] The charging module comprises a charging power supply, a relay K1 and a diode D1, the relay K1 is a double-pole single-throw relay, and the charging power supply is a 30V charging power supply; the charging module, the mutual inductor and the main power connector are cooperated to realize charging of the aircraft battery, the diode D1 is used for preventing damage to components caused by reverse current or reverse voltage, the mutual inductor is used for realizing conversion and isolation of electrical quantities, and the main power connector is used for establishing detachable electrical connection between different power units (the charging power supply and the aircraft battery) and ensuring safety, stability and speed of power transmission. Figure 1 The mutual inductor m point is a neutral point.

[0034] The discharging module comprises an electronic load and a relay K2, the relay K2 is a double-pole single-throw relay, and the electronic load can be a 6723 type load; the discharging module and the main power connector are cooperated to realize discharging of the aircraft battery, and the main power connector has the similar function as in the charging process, which will not be described in detail in the embodiment.

[0035] The voltage acquisition board card, the relay module, the total voltage acquisition module and the current acquisition module are supplied with power by the first direct current power supply, and the mutual inductor is supplied with power by the second direct current power supply; in the embodiment, the mutual inductor is an active electronic mutual inductor, so that an external power supply is needed for power supply.

[0036] The first direct current power supply and the second direct current power supply are shown in FIG. 4. Figure 2, the cell connector contains 22 pins (corresponding to 1~22), since the aircraft battery (nickel-chromium battery) is usually composed of 19 or 20 single batteries, therefore, the No. 1~20 pin is used to connect the 20 single batteries in a single aircraft battery, and the No. 21 pin is used for grounding; then the voltage acquisition board card contains 20 groups of voltage acquisition pins, respectively (01+, 01-)~(20+, 20-), each group of voltage acquisition pins is responsible for collecting the voltage data of a single battery, the model of the voltage acquisition board card is ZH-44241G-14F2, which also includes a positive (+) pin for connecting a power supply and a negative (-) pin for grounding; the relay module is connected with the cell connector to realize short circuit, which can realize signal path forced conduction, function verification or fault troubleshooting through short circuit, and ensure the accuracy and reliability of the voltage acquisition process. It should be noted that Figure 2 The relay module in the above formula contains pins (COM1, NC1, NO1)~pins (COM24, NC24, NO24), COM is the common end, NO is the normally open contact, NC is the normally closed contact, and it also includes pin 24V+ for connecting a power supply and pin 24V- for grounding, in addition, there are function standardization pins 1~9. In addition, it also contains resistors R1~R20, which are used to protect the circuit, and direct short circuit may cause overcurrent damage to the relay contact. It should be noted that the INT, G, A, B pins in the voltage acquisition board card are all function standardization pins, the INT pin is an interrupt request pin, the G pin is a ground reference pin, and the A / B pins form a differential analog input pin. While Figure 1 and Figure 2 The C point in the above formula is the connection between the NO23 pin of the relay module and the relay K1, and the D point is the connection between the NO21 pin of the relay module and the relay K2.

[0037] Among them, please refer to Figure 3 for the circuit diagram of the total voltage acquisition module and the current acquisition module, the total voltage acquisition module adopts the ZH-44081-14M2 model, and the current acquisition module adopts the ZH-44082-14M2 model. The total voltage acquisition module contains 8 groups of voltage acquisition pins, respectively (V1+, V1-)~(V8+, V8-), each group of voltage acquisition pins can realize the total voltage (i.e. 20 single battery voltages) acquisition of a single aircraft battery, and a total of 8 aircraft battery total voltage acquisition can be realized; the current acquisition module contains 8 groups of current acquisition pins, respectively (I1+, I1-)~(I8+, I8-), each group of current pins can realize the current acquisition of a single aircraft battery, and a total of 8 aircraft battery current acquisition can be realized. Since this example is for simultaneous charging and discharging monitoring of 6 aircraft batteries, the I1- to I6- pins are grounded, and then the I1+ to I6+ pins are connected with the mutual inductor.

[0038] In the embodiment, six channels are provided, each of which includes voltage data of 20 single batteries, total voltage data and total current data, the total voltage refers to the sum of the voltage data of the 20 single batteries, and during charging, the preset voltage, current, time range, trickle voltage, current and time range are set according to different types of batteries. Similarly, during discharging, the above data are also set according to different types of batteries. In addition, historical records are provided for querying historical data. It should be noted that the above collection data are displayed by the industrial computer and saved in history, which are well known to those skilled in the art and do not belong to the improvement of the embodiment. The improvement of the embodiment is to monitor the charging and discharging process of the multiple aircraft batteries at the same time, and the monitoring data is summarized and displayed by the industrial computer or other electronic devices with display function.

[0039] In the embodiment, six channels are provided, each of which includes voltage data of 20 single batteries, total voltage data and total current data, the total voltage refers to the sum of the voltage data of the 20 single batteries, and during charging, the preset voltage, current, time range, trickle voltage, current and time range are set according to different types of batteries. Similarly, during discharging, the above data are also set according to different types of batteries. In addition, historical records are provided for querying historical data. It should be noted that the above collection data are displayed by the industrial computer and saved in history, which are well known to those skilled in the art and do not belong to the improvement of the embodiment. The improvement of the embodiment is to monitor the charging and discharging process of the multiple aircraft batteries at the same time, and the monitoring data is summarized and displayed by the industrial computer or other electronic devices with display function.

[0040] In some embodiments, the charging module includes a charging power supply, a relay K1 and a diode D1, the charging power supply is connected with the positive electrode of the diode D1, the negative electrode of the diode D1 is connected with one end of the relay K1, the other end of the relay K1 is connected with one end of the mutual inductor, and the other end of the mutual inductor is connected with the No. 1 pin and the No. 3 pin of the main power connector.

[0041] In some embodiments, the discharging module includes an electronic load and a relay K2, the positive electrode of the electronic load is connected with one end of the mutual inductor through the relay K2, and the negative electrode of the electronic load is connected with the No. 2 pin and the No. 4 pin of the main power connector through the relay K2.

[0042] In some embodiments, the relay K1 and the relay K2 are double-pole single-throw relays.

[0043] In some embodiments, the number of the charging and discharging control modules is six.

[0044] In some embodiments, the first direct current power supply is a 24V direct current power supply, and the second direct current power supply is a 12V direct current power supply.

[0045] In some embodiments, the charging power supply is a 30V charging power supply.

[0046] In some embodiments, the model of the voltage acquisition board card is ZH-44241G-14F2, the model of the total voltage acquisition module is ZH-44081-14M2, and the model of the current acquisition module is ZH-44082-14M2.

[0047] While the preferred embodiments of the application have been described, it should be understood that various modifications can be made therein by those skilled in the art without departing from the spirit of the application. Accordingly, it is intended that all such alternatives, modifications and variations be included within the scope of the following claims and thereo equivalents.

[0048] Obviously, numerous modifications and variations of the present application are possible in light of the above teachings. It is therefore to be understood that within the scope of the appended claims and their equivalents, the application can be practiced otherwise than as specifically described.

Claims

1. A charge-discharge controller for an aircraft battery, characterized by comprising: The application relates to a battery charging and discharging control system for an airplane, which comprises the following: a plurality of charging and discharging control modules, each of which comprises a cell connector, a voltage acquisition board, a relay module, a mutual inductor, a main power supply connector, a charging module and a discharging module, all of which share a first direct current power supply, a second direct current power supply, a total voltage acquisition module and a current acquisition module; one end of the cell connector is connected with each single battery in a single airplane battery, and the other end of the cell connector is connected with the relay module; the relay module comprises a plurality of groups of short-circuit pins, each group of short-circuit pins realizes short-circuit connection with each single battery in a single airplane battery; the voltage acquisition board is connected with the other end of the cell connector and is used for acquiring the voltage of each single battery in a single airplane battery; one end of the charging module is connected with one end of the mutual inductor, the other end of the mutual inductor is connected with one end of the main power supply connector, and the other end of the main power supply connector is used for connecting the airplane battery, so as to realize charging of the airplane battery; after the airplane battery is connected with the main power supply connector, the airplane battery is connected with the discharging module, so as to realize discharging of the airplane battery; the total voltage acquisition module comprises a plurality of groups of voltage acquisition pins, each group of voltage acquisition pins is used for acquiring the total voltage of a single airplane battery; the current acquisition module comprises a plurality of groups of current acquisition pins, each group of current acquisition pins is used for acquiring the current of a single airplane battery; the first direct current power supply is used for supplying power to the voltage acquisition board, the relay module, the total voltage acquisition module and the current acquisition module; and the second direct current power supply is used for supplying power to the mutual inductor.

2. The charge-discharge controller for the aircraft battery according to claim 1, wherein The charging module comprises a charging power supply, a relay K1 and a diode D1; the charging power supply is connected with the positive electrode of the diode D1; the negative electrode of the diode D1 is connected with one end of the relay K1; the other end of the relay K1 is connected with one end of the mutual inductor; and the other end of the mutual inductor is connected with No.1 pin and No.3 pin of the main power supply connector.

3. The charge-discharge controller for an aircraft battery according to claim 2, wherein The discharging module comprises an electronic load and a relay K2; the positive electrode of the electronic load is connected with one end of the mutual inductor through the relay K2; and the negative electrode of the electronic load is connected with No.2 pin and No.4 pin of the main power supply connector through the relay K2.

4. The charge-discharge controller for an aircraft battery according to claim 3, wherein The relay K1 and the relay K2 are both double-pole single-throw relays.

5. The charge-discharge controller for an aircraft battery according to claim 1, wherein The number of the charging and discharging control modules is six.

6. The charge-discharge controller for aircraft storage battery according to claim 1, wherein The first direct current power supply is a 24V direct current power supply, and the second direct current power supply is a 12V direct current power supply.

7. The charge-discharge controller for an aircraft battery according to claim 2, wherein The charging power supply is a 30V charging power supply.

8. The charge-discharge controller for aircraft storage battery according to claim 1, characterized in that, The model of the voltage acquisition board is ZH-44241G-14F2, the model of the total voltage acquisition module is ZH-44081-14M2, and the model of the current acquisition module is ZH-44082-14M2.

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