CN113595160B - Simulation method and simulation device for aircraft battery - Google Patents
Simulation method and simulation device for aircraft battery Download PDFInfo
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- CN113595160B CN113595160B CN202010362339.1A CN202010362339A CN113595160B CN 113595160 B CN113595160 B CN 113595160B CN 202010362339 A CN202010362339 A CN 202010362339A CN 113595160 B CN113595160 B CN 113595160B
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/0063—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with circuits adapted for supplying loads from the battery
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/10—Energy storage using batteries
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- Engineering & Computer Science (AREA)
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- Charge And Discharge Circuits For Batteries Or The Like (AREA)
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Abstract
The invention discloses a simulation method and a simulation device of an aircraft storage battery, wherein the simulation method of the aircraft storage battery comprises the steps of determining the resistance value of a thermistor at any working temperature in a normal working temperature range under the normal power-on state of the storage battery; the method includes providing a first resistor having a fixed resistance value identical to a resistance value of the thermistor, determining a resistance of an internal load of a battery, providing a second resistor having a fixed resistance value identical to a resistance value of the resistance of the internal load, providing a ground power supply and a connector, electrically connecting the first resistor between two interfaces of the connector, and connecting the second resistor in series between the ground power supply and the connector. According to the technical scheme provided by the embodiment of the invention, the power supply signal of the storage battery can be simulated to realize the function of simulating the storage battery, and the power supply to the direct current system of the aircraft is realized in the state that the storage battery of the aircraft is not installed, so that the loss caused by repeated charge and discharge of the storage battery is avoided.
Description
Technical Field
The embodiment of the invention relates to the technical field of electrical systems, in particular to a simulation method and a simulation device of an aircraft storage battery.
Background
The main purpose of the storage battery on the aircraft is that the main power supply of the aircraft is used as an auxiliary power supply or an emergency power supply to supply power to important electric equipment when the main power supply of the aircraft does not work or fails, is used as a starting power supply of an engine of the aircraft, and can be used as a power supply for checking the small-power electric equipment of the aircraft before flying under certain special conditions (such as the field without power supply). When the aircraft accumulator is used as an emergency power supply, the aircraft accumulator is often used in parallel with a direct-current generator (main power supply).
Currently, when the direct current power supply is powered on, a connector on the aircraft is required to be connected with an interface on the storage battery. So that the battery outputs a temperature signal and a voltage signal to the data concentration device and the battery control device. According to the received signals, the storage battery control device judges the working state of the storage battery, such as charging, discharging or isolating. The data centralizing device sends signals to the display to display parameter values on the profile page. However, there is no method capable of simulating the storage battery, which causes that the storage battery is charged and discharged repeatedly after being installed, and thus the loss of the storage battery is larger.
Disclosure of Invention
The embodiment of the invention provides a simulation method and a simulation device for an aircraft storage battery, which are used for realizing the function of simulating the storage battery, and supplying power to an aircraft direct current system in a state that the aircraft storage battery is not installed, so that the loss caused by repeated charge and discharge of the storage battery is avoided.
The embodiment of the invention provides a simulation method of an aircraft storage battery, which comprises the following steps:
Determining the resistance value of the thermistor at any working temperature in a normal working temperature range under the normal power-on state of the storage battery;
providing a first resistor with a fixed resistance value which is the same as the resistance value of the thermistor;
determining the resistance of the internal load of the battery;
providing a second resistor of a fixed resistance value identical to the resistance value of the resistor of the internal load;
Providing a ground power supply and a connector;
the first resistor is electrically connected between two interfaces of the connector, and the second resistor is connected in series between the ground power supply and the connector.
In one embodiment, determining the resistance of the thermistor at any operating temperature within the normal operating temperature range under normal power-up conditions of the battery includes:
Providing a storage battery;
Normally powering up the storage battery and recording the temperature T of the storage battery when the storage battery works normally;
placing the battery in an environment at a temperature T for at least one hour;
And detecting the resistance value of the thermistor of the storage battery.
In one embodiment, determining the resistance of the internal load of the battery includes:
Connecting a test resistor with a resistance value of R0 in series and electrically between the positive electrode and the negative electrode of the storage battery;
testing the voltage at two ends of the test resistor, and recording the voltage as UR0;
calculating to obtain the resistance of the internal load of the storage battery;
wherein, the calculation formula is R1=R2= [ UP/(UR 0/R0) -R0]/2;
where UP is the voltage between the positive and negative electrodes of the battery, and R1 and R2 are the resistances of the internal loads at the positive and negative electrodes, respectively.
In one embodiment, the connector comprises a first connector and a second connector;
The positive electrode interface and the negative electrode interface of the first connector are respectively and electrically connected with the positive electrode and the negative electrode of the ground power supply;
The positive electrode interface of the second connector is electrically connected with the positive electrode of the ground power supply through a second first resistor, the negative electrode interface of the second connector is electrically connected with the negative electrode of the ground power supply through a second resistor, and the resistance values of the second first resistor and the second resistor are respectively equal to the resistance values of the resistors of the internal loads of the positive electrode end and the negative electrode end.
In one embodiment, the second connector includes a plurality of sets of interfaces connected to the first resistor;
The resistance of each first resistor is equal to the resistance of the thermistor of different storage batteries.
In one embodiment, providing a ground power supply and connector includes:
Providing a ground power supply meeting the requirements of an aircraft direct current system;
a connector of the same type as the battery is provided.
The embodiment of the invention also provides a simulation device of the airplane storage battery, which is formed by the simulation method of any one of the airplane storage batteries and comprises a ground power supply, a connector, a first resistor and a second resistor;
Wherein the first resistor is electrically connected between two interfaces of the connector, and the second resistor is connected in series between the ground power supply and the connector.
In one embodiment, the connector comprises a first connector and a second connector;
The positive electrode interface and the negative electrode interface of the first connector are respectively and electrically connected with the positive electrode and the negative electrode of the ground power supply;
The positive electrode interface of the second connector is electrically connected with the positive electrode of the ground power supply through a second first resistor, the negative electrode interface of the second connector is electrically connected with the negative electrode of the ground power supply through a second resistor, and the resistance values of the second first resistor and the second resistor are respectively equal to the resistance values of the resistors of the internal loads of the positive electrode end and the negative electrode end of the storage battery.
The simulation method of the aircraft storage battery comprises the steps of determining the resistance value of a thermistor at any working temperature in a normal working temperature range of the storage battery in a normal power-on state, providing a first resistor with a fixed resistance value which is the same as the resistance value of the thermistor, determining the resistance of an internal load of the storage battery, providing a second resistor with a fixed resistance value which is the same as the resistance value of the resistance of the internal load, providing a ground power supply and a connector, electrically connecting the first resistor between two interfaces of the connector, and connecting the second resistor in series between the ground power supply and the connector. Therefore, through cooperative electric connection among the ground power supply, the connector, the first resistor and the second resistor, the power supply signal of the storage battery can be simulated, so that the function of simulating the storage battery is realized, the power supply to the aircraft direct current system is realized under the state that the aircraft storage battery is not installed, and the loss caused by repeated charging and discharging of the storage battery is avoided.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, a brief description will be given below of the drawings required for the embodiments or the prior art descriptions, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1 is a schematic structural view of an aircraft battery according to an embodiment of the present invention;
fig. 2 is a schematic flow chart of a simulation method of an aircraft battery according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of an analog signal interface in the analog method of FIG. 2;
Fig. 4 is a schematic structural diagram of an analog device for an aircraft battery according to an embodiment of the present invention.
Detailed Description
The invention is described in further detail below with reference to the drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting thereof. It should be further noted that, for convenience of description, only some, but not all of the structures related to the present invention are shown in the drawings.
The improved point of the simulation method and the simulation device for the airplane storage battery (hereinafter also referred to as a storage battery) provided by the embodiment of the invention at least comprises the steps of providing a method for simulating power supply of the storage battery, and utilizing a ground power supply, a connector, a first resistor and a second resistor to be cooperatively and electrically connected to simulate an output signal of the storage battery so as to realize a direct current power supply function of the simulation storage battery, thereby realizing power supply to a direct current system of the airplane in a state that the airplane storage battery is not installed, and avoiding loss caused by repeated charge and discharge of the storage battery.
An exemplary method and an exemplary apparatus for simulating an aircraft battery according to an embodiment of the present invention are described below with reference to fig. 1 to 4.
Referring to fig. 1, the aircraft battery 01 comprises a battery main body, a first output port 011 and a second output port 012, wherein the first output port 011 is used for supplying power to an aircraft direct current system, and the second output port 012 is used for outputting a temperature signal and a voltage signal so as to realize power supply to an aircraft after the battery is installed, and meanwhile, realize monitoring of a power supply state.
In the related art, after the storage battery is installed, part of system equipment is powered by the storage battery, the storage battery is in a discharging state at the moment, and when the airplane detects that the electric quantity of the storage battery is insufficient, the storage battery enters a charging state. Therefore, once the battery is assembled, the battery enters a state of cyclic charge and discharge, and the battery loss is serious.
According to the embodiment of the invention, the functions of the storage battery are simulated by using the ground power supply, the connector, the first resistor and the second resistor according to the normal power supply state of the storage battery, and the power supply to the direct current system of the aircraft can be realized under the state that the storage battery is not installed, so that the loss caused by repeated charge and discharge of the storage battery can be avoided.
For example, referring to fig. 2, the simulation method of the aircraft battery may include:
s110, determining the resistance value of the thermistor at any working temperature in a normal working temperature range under the normal power-on state of the storage battery.
The storage battery can normally work in a normal working temperature range limited by the upper temperature limit and the lower temperature limit, and any working temperature can be selected in the normal working temperature range to serve as a reference basis for simulating the working temperature, wherein the resistance value of the thermistor at the working temperature is the resistance value of the first resistor in the simulation method of the storage battery.
For example, when the normal operating temperature range is 20 ℃ to 60 ℃, the optional temperature values include 20 ℃, 60 ℃, 40 ℃ or other temperature values within the above temperature range, which is not repeated in the embodiments of the present invention.
In other embodiments, the normal operating temperature range may vary from battery model to battery, and the present embodiment is not limited in this regard.
Based on this, this step may include testing, reading or calculating the resistance of the thermistor of the battery at a normal operating temperature in preparation for S120.
S120, providing a first resistor with a fixed resistance value which is the same as the resistance value of the thermistor.
Based on S110, this step may include selecting a resistor having the same resistance as the resistor determined in S110 as the first resistor.
Thus, S110 and S120 complete the simulation of the temperature sensor in the battery.
S130, determining the resistance of the internal load of the storage battery.
This step provides for an analog voltage sensor.
And S140, providing a second resistor with a fixed resistance value which is the same as the resistance value of the resistor of the internal load.
On the basis of S130, the step of giving may include selecting the same resistance as the resistance determined in S130 as the second resistance.
Thus, S130 and S140 complete the simulation of the voltage sensor in the battery.
S150, providing a ground power supply and a connector.
This step provides for the connection and supply of the analog accumulator.
S160, electrically connecting a first resistor between two interfaces of the connector, and connecting a second resistor in series between the ground power supply and the connector.
Based on S110-S150, the ground power supply, the connector, the first resistor and the second resistor are cooperatively and electrically connected to realize the power supply of the simulated storage battery.
In other embodiments, the voltage sensor simulation may be performed first, and then the temperature sensor simulation may be performed, that is, S130 and S140 are performed before S110 and S120, which is not limited by the embodiment of the present invention.
Next, exemplary detailed descriptions are made of the steps shown in fig. 2.
In one embodiment, S110 may include:
Step one, a storage battery is provided.
The temperature sensor in the storage battery can be a thermistor, and the model of the storage battery is matched with the model of the airplane.
And secondly, normally electrifying the storage battery, and recording the temperature T of the storage battery when the storage battery works normally.
For example, according to the parameters displayed on the power profile page in the normal power-on state, the temperature T of the storage battery in normal operation is recorded.
And thirdly, placing the storage battery in the environment with the temperature T for at least one hour.
The temperature of the storage battery can be stabilized by the step, so that a stable and accurate resistance value can be measured in the next step.
For example, the placement time may be one hour, or a duration of more than one hour, which may be set according to the requirements of the simulation method, which is not limited by the embodiment of the present invention.
And fourthly, detecting the resistance value of the thermistor of the storage battery.
Illustratively, detecting the resistance value between the pinholes of the temperature sensor circuit of the storage battery can be included to obtain the resistance value of the thermistor at normal temperature.
Thus, the simulation basis for the temperature sensor in the storage battery is formed.
In one embodiment, S130 may include:
and firstly, connecting a test resistor with a resistance value of R0 in series and electrically between the anode and the cathode of the storage battery.
The voltage sensor in the storage battery can directly detect the voltage between the positive electrode and the negative electrode of the storage battery, and two loads are connected in series in a circuit, and the resistance values of the loads are respectively represented by R1 and R2. To calculate the resistance of the load, a resistor R0 with a fixed resistance (e.g., 10K ohms) may be connected in series outside the battery.
And step two, testing the voltage at two ends of the test resistor and marking the voltage as UR0.
This step provides for the subsequent calculation of the resistance of the internal load.
Illustratively, this step may include measuring the voltage across the test resistor using a multimeter, UR0.
And thirdly, calculating to obtain the resistance of the internal load of the storage battery.
Wherein, the calculation formula is R1=R2= [ UP/(UR 0/R0) -R0]/2, wherein UP is the voltage between the positive electrode and the negative electrode of the storage battery, and R1 and R2 are the resistances of the internal loads of the positive electrode terminal and the negative electrode terminal respectively.
UP may also be understood as the voltage value at which the battery is operating normally (e.g., the voltage value at which an aircraft battery is operating normally may be 28V).
For example, a schematic diagram of the analog signal interface of the battery may be shown in fig. 3. Referring to fig. 3, the interfaces 6 and 13 are positive and negative interfaces, which can be electrically connected with the positive and negative poles of the ground power supply through a load at the positive pole (shown as R1) and a load at the negative pole (shown as R2), respectively, and the interfaces 7 and 8, 9 and 10, 11 and 12 are three signal interfaces, which can provide temperature information of the storage battery to three different devices of the aircraft, and the resistance value of the resistor represents the temperature (shown as T1, T2 and T3 in the figure). The figure can be understood as a circuit simulation diagram of the inside of the battery, in which the temperature is sensed by a thermistor in a real internal circuit of the battery.
In one embodiment, S150 may include:
providing a ground power supply meeting the requirements of an aircraft direct current system.
In this step, it is necessary to select a suitable ground power supply adapted to the direct current system of the aircraft, so as to avoid excessive processing of the ground power supply, which is advantageous in simplifying the simulation method.
And step two, providing a connector with the same model as the storage battery.
The connectors of the storage batteries of different models and different models are different, so that the connectors of the storage batteries of the same model are required to be selected to simulate the storage batteries.
In one embodiment, referring to FIG. 4, the connector 220 includes a first connector 221 (also shown as "J1") and a second connector 222 (also shown as "J2"), the positive interface (shown as "+") and the negative interface (shown as "-") of the first connector 221 are electrically connected to the positive pole (shown as "+") and the negative pole (shown as "-") of the ground power source, respectively, the positive interface of the second connector 222 is electrically connected to the positive pole of the ground power source 210 through a second first resistor (shown as R1), the negative interface of the second connector 222 is electrically connected to the negative pole of the ground power source 210 through a second resistor (shown as R2), and the resistances of the second first resistor and the second resistor are equal to the resistances of the internal loads of the positive pole terminal and the negative pole terminal, respectively.
The selection of the connector varies according to the model of the storage battery, namely, the connector is suitable for the simulated storage battery. The illustration in fig. 4 is given only by way of example in which the connectors comprise a first connector and a second connector. In other embodiments, the connector 220 may be configured in other forms selected according to the battery, which is not limited by the embodiment of the present invention.
Up to this point, the circuit configuration shown in fig. 4 can realize the simulation of the power supply function of the storage battery.
In one embodiment, with continued reference to fig. 4, the second connector 220 includes multiple sets of interfaces (interfaces 2 and 3, interfaces 4 and 5, and interfaces 6 and 7 are respectively grouped in the second connector 220 shown in fig. 4 and connected to a resistor for simulating a temperature sensor) for connecting first resistors (respectively shown as R T1、RT2 and R TN), wherein the resistance of each first resistor is equal to the resistance of the thermistor of a different battery.
For example, in different types of aircraft, even if a nickel-cadmium battery (a storage battery) is also selected, the output temperature signals may have 3 groups, 4 groups or more, and here, in order to illustrate that the simulation method of the storage battery of the aircraft may be applicable to different types of aircraft, N groups of signals are used for identification (R T1、RT2 and R TN, one resistor represents one group of temperature signals).
It should be noted that the first resistor with a fixed resistance value is selected according to the resistance value measured at the normal temperature T above instead of the thermistor, so as to ensure that the temperature signal obtained by the aircraft is always in a normal state.
On the basis of the above embodiments, the present invention further provides a simulation device for an aircraft battery, where the simulation device for an aircraft battery may be formed by the simulation method for an aircraft battery provided in any one of the above embodiments. Therefore, the simulation device of the aircraft battery also has the technical effects of the simulation method of the aircraft battery, and the simulation device can be understood by referring to the above description and is not repeated herein.
By way of example, referring to FIG. 4, the aircraft battery simulation device 20 includes a ground power supply 210, a connector 220, a first resistor (shown as R T1、RT2 and R TN, respectively) and a second resistor (shown as R1 and R2, respectively), wherein the first resistor is electrically connected between two interfaces of the connector 220 to simulate a temperature sensor of the battery, and the second resistor is connected in series between the ground power supply 210 and the connector 220 to simulate a voltage sensor of the battery.
In one embodiment, the connector 220 includes a first connector 221 (or represented by "J1") and a second connector 222 (or represented by "J2"), the positive and negative interfaces of the first connector 221 are electrically connected to the positive and negative poles of the ground power supply, respectively, the positive interface of the second connector 222 is electrically connected to the positive pole of the ground power supply 210 through a second first resistor (shown as R1), the negative interface of the second connector 222 is electrically connected to the negative pole of the ground power supply 210 through a second resistor (shown as R2), and the resistances of the second first and second resistors are equal to the resistances of the internal loads of the positive and negative poles, respectively.
The selection of the connector varies according to the model of the storage battery, namely, the connector is suitable for the simulated storage battery. The illustration in fig. 4 is given only by way of example in which the connectors comprise a first connector and a second connector.
Up to this point, the circuit configuration shown in fig. 4 can realize the simulation of the power supply function of the storage battery.
In other embodiments, the connector 220 may be configured in other forms selected according to the battery, and may be configured according to the requirement of the simulation device 20 of the battery, which is not limited in the embodiment of the present invention.
Note that the above is only a preferred embodiment of the present invention and the technical principle applied. It will be understood by those skilled in the art that the present invention is not limited to the particular embodiments described herein, but is capable of various obvious changes, rearrangements and substitutions as will now become apparent to those skilled in the art without departing from the scope of the invention. Therefore, while the invention has been described in connection with the above embodiments, the invention is not limited to the embodiments, but may be embodied in many other equivalent forms without departing from the spirit or scope of the invention, which is set forth in the following claims.
Claims (7)
1. A method of simulating an aircraft battery, comprising:
Determining the resistance value of the thermistor at any working temperature in a normal working temperature range under the normal power-on state of the storage battery;
providing a first resistor with a fixed resistance value which is the same as the resistance value of the thermistor;
determining the resistance of the internal load of the battery;
providing a second resistor of a fixed resistance value identical to the resistance value of the resistor of the internal load;
Providing a ground power supply and a connector;
Electrically connecting the first resistor between two interfaces of the connector, and connecting the second resistor in series between the ground power supply and the connector;
the two interfaces are a group of signal interfaces and are used for providing temperature information of the storage battery for equipment of the aircraft.
2. The method for simulating an aircraft battery according to claim 1, wherein determining the resistance of the thermistor at any operating temperature within a normal operating temperature range during a normal power-on state of the battery comprises:
Providing a storage battery;
Normally powering up the storage battery and recording the temperature T of the storage battery when the storage battery works normally;
placing the battery in an environment at a temperature T for at least one hour;
And detecting the resistance value of the thermistor of the storage battery.
3.A method of modeling an aircraft battery as claimed in claim 1 wherein determining the resistance of the internal load of the battery comprises:
Connecting a test resistor with a resistance value of R0 in series and electrically between the positive electrode and the negative electrode of the storage battery;
testing the voltage at two ends of the test resistor, and recording the voltage as UR0;
calculating to obtain the resistance of the internal load of the storage battery;
wherein, the calculation formula is R1=R2= [ UP/(UR 0/R0) -R0]/2;
where UP is the voltage between the positive and negative electrodes of the battery, and R1 and R2 are the resistances of the internal loads at the positive and negative electrodes, respectively.
4. The method of simulating an aircraft battery of claim 3, wherein the connector comprises a first connector and a second connector, and wherein the second resistor comprises a second resistor A and a second resistor B;
The positive electrode interface and the negative electrode interface of the first connector are respectively and electrically connected with the positive electrode and the negative electrode of the ground power supply;
The positive electrode interface of the second connector is electrically connected with the positive electrode of the ground power supply through a second first resistor, the negative electrode interface of the second connector is electrically connected with the negative electrode of the ground power supply through a second resistor, and the resistance values of the second first resistor and the second resistor are respectively equal to the resistance values of the resistors of the internal loads of the positive electrode end and the negative electrode end.
5. The method of claim 4, wherein the second connector includes a plurality of sets of interfaces connecting the first resistor;
The resistance of each first resistor is equal to the resistance of the thermistor of different storage batteries.
6. The method of simulating an aircraft battery of claim 1, wherein providing a ground power supply and connector comprises:
Providing a ground power supply meeting the requirements of an aircraft direct current system;
a connector of the same type as the battery is provided.
7. An apparatus for simulating an aircraft battery, formed by the method for simulating an aircraft battery according to any one of claims 1 to 6, comprising a ground power supply, a connector, a first resistor, and a second resistor;
Wherein the first resistor is electrically connected between two interfaces of the connector, and the second resistor is connected in series between the ground power supply and the connector.
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102714422A (en) * | 2009-11-30 | 2012-10-03 | 前瞻思维产品有限公司 | Battery Simulator and How to Use It |
| CN109991492A (en) * | 2019-03-25 | 2019-07-09 | 飞依诺科技(苏州)有限公司 | Simulated battery circuit |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR200258760Y1 (en) * | 2001-10-08 | 2001-12-29 | 강태영 | Apparatus for testing a battery |
| JP2011158354A (en) * | 2010-02-01 | 2011-08-18 | Sinfonia Technology Co Ltd | Battery simulator |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102714422A (en) * | 2009-11-30 | 2012-10-03 | 前瞻思维产品有限公司 | Battery Simulator and How to Use It |
| CN109991492A (en) * | 2019-03-25 | 2019-07-09 | 飞依诺科技(苏州)有限公司 | Simulated battery circuit |
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