CN216509192U - Multi-battery pack power supply management device of portable testing equipment of airplane - Google Patents

Abstract

The utility model discloses a multi-battery pack power supply management device of portable testing equipment of an airplane, belongs to the field of battery management, and aims to solve the problem that a power supply system is inconvenient in the testing process in the prior art. According to the utility model, the multi-battery pack unit and the charging circuit unit are connected to supply power to the multi-battery pack unit for charging and the power supply path selection function of the charger, the multi-battery pack unit is connected with the power supply control unit to realize the collection and analysis of the battery information of the multi-battery pack unit, the battery management circuit of the multi-battery pack unit collects the battery state and performs protection and management functions on the battery pack, the safety of a power supply system is ensured, meanwhile, the multi-battery pack unit is packaged into the battery pack through a PVC packaging film, the problem that the power supply system is not easy to carry is solved, and the realization device has a simple structure and is convenient to install; the 18650 lithium ion battery is adopted as the battery of the battery pack to supply power to equipment, and the service life can be prolonged due to high energy density of the battery.

Description

Multi-battery-pack power management device of portable testing equipment of airplane

Technical Field

The utility model belongs to the technical field of battery management, and particularly relates to a multi-battery pack power supply management device of portable testing equipment of an airplane.

Background

The aircraft puts forward higher requirements on the aspects of function inspection, system fault elimination, daily function maintenance and the like of an onboard system in an external environment in the production and maintenance processes, and in order to meet the convenience of daily test, the required matched test equipment is developed towards miniaturization and intellectualization, wherein the stability and the safety of a power supply system are a great problem which restricts the portability of the power supply system.

The traditional battery pack is only used for simply packaging batteries into a battery pack according to requirements, and then 2 groups of wires are led out from the positive and negative electrodes of the batteries to be used as charging and discharging wires. This method does not consider the problem of the balance of electric quantity between batteries and between battery packs, and is easy to cause the high-temperature fire phenomenon caused by the overcharge or the overdischarge of the batteries. Likewise, the dynamic charge characteristics of the battery are not monitored using a fuel gauge, basic information of the battery cannot be estimated, corresponding protective measures are lacked, and the service life of the battery is shortened.

SUMMERY OF THE UTILITY MODEL

In order to overcome the defects of the prior art, the utility model aims to provide a multi-battery-pack power management device for an aircraft portable testing device, and aims to solve the technical problems that a power supply system is not portable in the testing process and the electric quantity among battery packs is unbalanced in the prior art.

In order to achieve the purpose, the utility model adopts the following technical scheme to realize the purpose:

the utility model provides a multi-battery pack power management device of portable airplane test equipment, which comprises a charging circuit unit, a multi-battery pack unit and a power control unit, wherein a first output port of the charging circuit unit is connected with a first input port of the power control unit; the second output port of the charging circuit unit is connected with the input port of the multi-battery pack unit, and the output port of the multi-battery pack unit is connected with the second input port of the power supply control unit;

the multi-battery cell includes a battery pack and a battery management circuit including a fuel gauge and an ORing + FET circuit; a first port of the fuel gauge is connected with a second output port of the charging circuit unit, a second port of the fuel gauge is connected with the battery pack, a third port of the fuel gauge is connected with one end of the ORing + FET circuit, and the other end of the ORing + FET circuit is connected with the power supply control unit; and the multi-battery management unit is packaged into a battery pack through a PVC packaging film.

Preferably, the battery pack comprises 3 batteries, and each battery is connected in series.

Preferably, the battery is a 18650 lithium ion battery.

Preferably, the multi battery cells are 4 groups, and each group of multi battery cells are connected in parallel.

Preferably, the battery management circuits of each group of multi-battery cells are identical.

Preferably, the multi battery pack unit and the power control unit are connected through an SMBUS bus.

Preferably, the charging circuit unit, the multi-battery pack unit and the power control unit have independent circuits.

Preferably, the output ports of the power control unit are connected with a voltage stabilizing circuit.

Preferably, the multi-battery pack unit selects different numbers of series battery sections and parallel battery packs according to actual power utilization conditions.

Compared with the prior art, the utility model has the following beneficial effects:

according to the multi-battery pack power management device for the portable test equipment of the airplane, one end of the multi-battery pack unit is connected with the charging circuit unit, so that power supply charging and charger power supply path selection functions can be achieved for the multi-battery pack unit, the other end of the multi-battery pack unit is connected with the power control unit, gathering and analysis of battery information of the multi-battery pack unit can be achieved, a fuel gauge is arranged in a battery management circuit of the multi-battery pack unit, monitoring of basic information of batteries and protection in the using process are achieved, and the active balance problem among batteries connected in series is achieved; the problems of balance, reverse charge and the like among the parallel battery packs are solved by arranging the ORing + FET circuit in the battery management circuit. Meanwhile, the multiple battery units are packaged into the battery pack through the PVC packaging film, and the problem that a power supply system is not easy to carry is solved. Aiming at the implementation device of the portable test equipment of the airplane, the multi-battery unit is respectively connected with the charging circuit unit and the power supply control unit, so that the portable test equipment is simple in structure and convenient to install, and the portability of the equipment is ensured to a great extent.

Further, a plurality of groups of battery packs are adopted, and 3 batteries in the battery packs can meet the power supply duration of the equipment.

Furthermore, the characteristics of light weight, high energy, long service life and short charging time of the 18650 lithium ion battery are utilized to realize power supply of the equipment by matching with a corresponding management circuit and a corresponding control circuit.

Furthermore, the charging circuit unit, the multi-battery pack unit and the power supply control unit are provided with independent functional circuits, so that the quick module replacement and the replacement of a standby battery can be realized.

Furthermore, the battery pack unit automatically learns and draws a battery impedance curve according to the actual application condition, so that the battery pack can accurately reflect the power utilization condition.

Furthermore, the power supply control unit performs voltage stabilization treatment on the dynamic voltage output by the battery, and ensures that the power utilization unit works under normal voltage and large current.

Furthermore, the power control unit controls and indicates the power utilization state, so that the optimal power utilization of the system is ensured, and the power consumption loss is reduced.

Drawings

In order to more clearly explain the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention, and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.

FIG. 1 is a block diagram of a multi-battery power management apparatus for an aircraft-based portable test device according to the present invention;

FIG. 2 is a block diagram of the composition of a multi-battery cell of the present invention;

FIG. 3 is a functional block diagram of a multi-battery cell of the present invention;

fig. 4 is a schematic block diagram of a power control unit of the present invention.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.

Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the utility model, as claimed, but is merely representative of selected embodiments of the utility model. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.

In the description of the embodiments of the present invention, it should be noted that, if the terms "upper", "lower", "horizontal", "inner", etc. are used for indicating the orientation or positional relationship based on the orientation or positional relationship shown in the drawings or the orientation or positional relationship which is usually placed when the products of the present invention are used, the description is only for convenience and simplicity, but the indication or suggestion that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like are used merely to distinguish one description from another, and are not to be construed as indicating or implying relative importance.

Furthermore, the term "horizontal", if present, does not mean that the component is required to be absolutely horizontal, but may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.

In the description of the embodiments of the present invention, it should be further noted that unless otherwise explicitly stated or limited, the terms "disposed," "mounted," "connected," and "connected" should be interpreted broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

The utility model is described in further detail below with reference to the accompanying drawings:

the utility model provides a multi-battery pack power management device of portable test equipment of an airplane, as shown in figure 1, the implementation device comprises a charging circuit unit, a multi-battery pack unit and a power control unit, wherein a first output port of the charging circuit unit is connected with a first input port of the power control unit; the second output port of the charging circuit unit is connected with the input port of the multi-battery pack unit, and the output port of the multi-battery pack unit is connected with the second input port of the power supply control unit.

The multi-battery pack unit is connected with the power supply control unit through an SMBUS (system management bus), and comprises a lithium ion battery pack and a battery management circuit, wherein the battery management circuit comprises a fuel gauge and an ORing + FET (field effect transistor) circuit; the first port of the electricity meter is connected with the second output port of the charging circuit unit, the second port of the electricity meter is connected with the battery pack, the third port of the electricity meter is connected with one end of the ORing + FET circuit, and the other end of the ORing + FET circuit is connected with the power supply control unit; and the multi-battery management unit is packaged into a battery pack through a PVC packaging film.

The multi-battery cells are 4 groups, and each group of multi-battery cells are connected in parallel. The battery pack is divided into 4, each battery pack is connected with a battery management circuit, and each battery pack is formed by connecting 3 batteries in series. The battery management circuit is added with the fuel gauge in the design, so that the monitoring of basic information of the battery and the protection in the use process are realized, and the active balance problem among batteries connected in series is realized; and the problems of balance, reverse charge and the like among the parallel battery packs are also realized through the ORing + FET circuit. On the premise of meeting the requirement of power supply of equipment, the protection monitoring and function of the battery are achieved, and the service life of the battery is prolonged. The battery management circuit can realize the functions of collecting, protecting and managing the battery state; the power supply control unit realizes the summarization and analysis of multiple groups of battery information of the multiple battery pack units; the output ports of the power supply control unit are connected with voltage stabilizing circuits, and the power utilization unit is guaranteed to work under normal voltage and large current.

The power supply control unit realizes the functions of battery power supply information acquisition, power supply voltage stabilization, power-on and power-off control and the like. The charging circuit unit, the multi-battery pack unit and the power supply control unit are provided with independent functional circuits, so that the quick module replacement and the replacement of a standby battery can be realized.

Preferably, the charging circuit unit can realize the functions of supplying power to the multi-battery pack unit and selecting a power supply path of the charger.

Preferably, each group of the multi-battery pack units has the same management circuit, and the connection with the power supply control unit is realized through an SMBUS bus.

Preferably, the multi-battery pack unit selects different numbers of series-connected battery sections and parallel-connected battery packs according to actual power utilization conditions.

Preferably, the multi-battery pack unit automatically learns and draws a battery impedance curve according to the actual application condition, so that the battery pack can accurately reflect the power utilization condition.

Preferably, the power supply control unit controls and indicates the power utilization state of the multi-battery pack unit, so that the system power utilization is optimal, and the power utilization loss is reduced.

As shown in fig. 1, the charging circuit unit is implemented by a dedicated lithium ion battery charging chip, and the charging circuit unit can implement 4 cycles of charging by sampling current, thereby maximally extending the service life of the battery. The power supply path is determined by comparing the voltage difference between the input voltage of the battery pack and the input voltage of the charger, and when the charger is inserted, the charger can supply power to the electric equipment so as to reduce the discharge times of the battery. The circuit also has a charging state indicating function and realizes charging state reporting.

As shown in fig. 2, the battery is 18650 lithium ion battery, and the rated voltage of the battery is 3.7V, the maximum voltage is 4.2V, and the rated capacity is 3350 mAh. The battery pack has 4 groups of multi-battery pack units connected in parallel, and each group comprises 3 batteries connected in series and a battery management circuit. The device operating voltage adds the voltage potential of each cell through the series connection of the cells to obtain the total terminal voltage. The working voltage of the equipment is 12V, so that the series connection of 3 batteries is selected; the rated capacity of the electric quantity of the equipment is obtained by adding the rated capacity of each battery through the parallel connection of the batteries. The device needs to work continuously for 4 hours under the current of 3A, and 4 groups of parallel battery packs are selected to realize the purpose in consideration of energy loss and efficiency. The battery pack forms a 3-series-4-parallel mode through nickel bar spot welding, each group of series-connected batteries is connected with a management protection battery management circuit with a fuel gauge, and finally, the management protection battery management circuit is packaged through a PVC packaging film to form a battery pack. The battery pack is fixed in the battery box and the drawn-out cable is fitted to the connector of the battery box to constitute a battery module.

As shown in fig. 3, the multi-battery cell operating principle: the larger the battery, the longer the service life of the battery is not necessarily meant. Battery capacity is affected by a number of parameters, such as current, voltage, and temperature. The steady battery system must possess electric quantity monitoring meter and protector, so not only can improve test equipment's security, can also prolong the operating time and the life-span of group battery. The battery capacity monitoring meter of TI Impedance Track technology is adopted in the design of the series battery pack in the implementation device, and the influence of discharge multiplying power, temperature, aging and other factors on the battery can be directly measured by measuring the battery Impedance. The protector is used for protecting by setting relevant parameters in the electric quantity monitoring meter. The specific implementation of the fuel gauge design is as follows.

1) The circuit board with the electricity meter is tightly attached to the surface of the battery, so that the current, the voltage and the temperature of the battery can be more accurately collected.

2) And connecting the Battery pack with the electricity meter circuit to TI Battery Management Studio upper computer software, learning the Battery according to Battery learning circulation steps, and accessing the actual load in the learning charge-discharge process as much as possible, so that the impedance of the Battery is measured most accurately.

3) And setting battery parameters. The main parameters include parameters for judging the full Charge condition, such as full Charge Voltage (Charge Voltage), full Current (high Current), and full Voltage (high Voltage); battery Capacity information such as cell rated Capacity (Design Capacity), cell rated Energy (Design Energy), and cell rated Voltage (Design Voltage); the system information includes information such as a minimum operating Voltage (terminal Voltage), a discharge Current threshold (Dsg terminal Current), a charge Current threshold (Chg terminal Current), and a Quit Current value (Quit Current).

4) And recording calibration information. And (4) according to the use condition, writing the actual voltage, current and temperature information values of the measuring circuit into a calibration interface by using a multimeter for calibration.

5) And selecting the battery cell chemical ID. And selecting the selected cell CHEM-ID from the TI chemical ID library, if the cell CHEM-ID is not selected, recording data LOG according to corresponding charging and discharging steps and then sending the data LOG to a TI official party, wherein the TI can help to select the proper cell CHEM-ID.

6) And circularly learning. After the above work is finished, cyclic learning is performed according to the charging and discharging steps, the learning state bit is read, and when the Update Status is 0X06, the learning is successful.

7) And manufacturing mass production files. And exporting the learned data through software to generate a mass production file, and directly burning the mass production file in the subsequent batch manufacturing process of the battery fuel gauges, so that the accuracy of the battery impedance application can be ensured.

The parameter configuration before learning can realize the safe and reliable operation of group battery, and equipment can provide accurate battery monitoring, makes real-time adjustment to the voltage balance problem in every section battery, avoids electric core damage that voltage unbalance leads to between the series connection battery. And setting corresponding voltage and current thresholds, performing overcurrent protection in the charging and discharging processes, and providing protection when the battery is overcharged, the electric quantity is exhausted and the temperature is overhigh.

The successfully learned battery pack can be connected with a power supply control circuit through an SMBUS bus to provide a system with metering and displaying battery capacity, which generally comprises residual capacity (RM), Full Charge Capacity (FCC), percentage capacity (SOC), voltage, current, charge-discharge state, temperature, discharge residual time, charge full charge time, battery health (SOH) and the like. These parameters can improve the user experience, discharge as much battery power as possible, and prolong the battery life.

As shown in fig. 3, the ORing function is required when a plurality of series-connected battery packs must be connected together in order to provide a large capacity power source to the device. The device is connected with ORing + FET circuits in series behind each group of 3 series battery packs, and the ORing + FET circuits are mainly used for solving the problem of voltage imbalance among the parallel battery packs. Parasitic diode R using FET_DS(on) blocking the high voltage battery voltage from flowing into the low voltage battery due to the difference in voltage between the parallel battery packs, can effectively prevent reverse leakage current and contribute to prolonging the battery life.

As shown in fig. 4, the principle of the power supply control unit: dynamic 9V-12.6V voltage input by the battery is converted into stable 12V voltage by using a BUCK-BOOST circuit to supply power to a load. In order to meet the requirement of low power consumption, the voltage stabilizing circuit can be controlled by software to be switched on and off, and meanwhile, the working state of the voltage stabilizing circuit can be displayed. The main control chip can control the 2-way switch to control the power supply path, and can cut off the power supply in time when the load does not need power supply, thereby reducing the power loss. The main control chip can also use the battery information collected by the SMBUS bus as the upper computer display and power-on and power-off logic control, such as prompting that the electric quantity is too low when the electric quantity remains 10%, prompting that the human-computer interaction information such as automatic shutdown is about to be performed when the available time of the electric quantity is less than 5 minutes, and the like. The main control chip can also control a panel indicator light according to the collected battery information, and intuitively informs a user of the power utilization state.

The utility model provides a power supply management realizing device with low cost, ultra-long standby time and high intelligence, which is mainly used for the safety and the intelligence of a power supply system of portable equipment of an airplane. The power control unit realizes the extension of the service life of the battery and the management and control of application safety by the acquisition of charging and discharging management, battery voltage, current and temperature information of the battery through the integrated circuit. The phenomena of overcharge, overdischarge, overtemperature, overcurrent and the like of the battery are prevented from occurring, and the safe and long-time operation of the portable equipment is ensured.

The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (9)

1. The multi-battery pack power management device of the portable airplane test equipment is characterized by comprising a charging circuit unit, a multi-battery pack unit and a power control unit, wherein a first output port of the charging circuit unit is connected with a first input port of the power control unit; the second output port of the charging circuit unit is connected with the input port of the multi-battery pack unit, and the output port of the multi-battery pack unit is connected with the second input port of the power supply control unit;

the multi-battery cell includes a battery pack and a battery management circuit including a fuel gauge and an ORing + FET circuit; a first port of the electricity meter is connected with a second output port of the charging circuit unit, a second port of the electricity meter is connected with the battery pack, a third port of the electricity meter is connected with one end of the ORing + FET circuit, and the other end of the ORing + FET circuit is connected with the power supply control unit; and the multi-battery management unit is packaged into a battery pack through a PVC packaging film.

2. An aircraft portable test device multi-battery power management apparatus as in claim 1 wherein the battery pack comprises 3 cells, each cell being connected in series.

3. The aircraft portable test equipment multi-battery pack power management device of claim 2, wherein the battery is a 18650 lithium ion battery.

4. The aircraft portable test equipment multi-battery power management apparatus of claim 2, wherein the multi-battery cells are 4 groups, and each group of multi-battery cells are connected in parallel.

5. The aircraft portable test equipment multi-battery power management apparatus of claim 4, wherein the battery management circuits of each group of multi-battery cells are identical.

6. An aircraft portable test equipment multi-battery power management apparatus as claimed in claim 1, wherein the multi-battery cell and the power control unit are connected via an SMBUS bus.

7. The aircraft portable test equipment multi-battery power management device of claim 1, wherein the charging circuit unit, the multi-battery unit and the power control unit each have separate circuits.

8. The multi-battery-pack power management device for the aircraft portable test equipment of claim 1, wherein the output ports of the power control unit are connected with voltage stabilizing circuits.

9. The aircraft portable test equipment multi-battery power management apparatus of claim 1, wherein the multi-battery cell selects different numbers of series cells and parallel cells according to actual power usage.

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