Common working line prediction method and system for lithium battery power system

Abstract

The invention provides a common working line prediction method and system for a lithium electric power system. The method comprises the following steps: constructing a simulation dynamic model of the lithium electric power system; performing order reduction conversion on the simulation kinetic model to obtain a nonlinear equation performance constraint group; obtaining a common working line based on the nonlinear equation performance constraint group; the method further comprises the steps of solving steady-state variables of the common working lines according to different thrust requirements to obtain a series of steady-state working points under the different thrust requirements, sequentially connecting the steady-state working points according to the rotating speed from small to large to obtain a series of common working lines, and predicting the common working line in different lithium cell energy consumption states. Through the prediction method provided by the invention, the steady-state value combination of the key state of the lithium electric power system meeting the thrust requirement of the aircraft can be rapidly and accurately given, and a large amount of iterative calculation is not needed; and meanwhile, the change condition of the common working line in different lithium battery energy consumption states can be predicted.

Description

Technical Field

[0001] The present invention relates to the technical field of power systems, and in particular to a method and system for predicting a common operating line for a lithium battery power system. Background Art

[0002] The common operating line of a power system refers to the mutual restraint relationships satisfied among various components when an automotive internal combustion engine, an aero-engine, etc. are operating, such as conditions like continuous flow, power and pressure balance, etc., to ensure that the components of the power system can work in coordination to achieve optimal performance and working efficiency. The common operating line is crucial for determining the performance parameters of the power system, component coordination, and precise control; however, for the lithium battery power systems widely used in emerging electric aircraft, there is currently no method for predicting their common operating lines, so designers are unable to evaluate the component matching conditions of the designed aviation lithium battery power systems. Summary of the Invention

[0003] The purpose of the present invention is to provide a method and system for predicting a common operating line for a lithium battery power system, aiming to solve the above problems in the prior art.

[0004] An embodiment of the present invention provides a method for predicting a common operating line for a lithium battery power system, including:

[0005] Constructing a simulation dynamics model of the lithium battery power system;

[0006] Performing order reduction transformation on the simulation dynamics model to obtain a set of non-linear equality performance constraints of the lithium battery power system; and

[0007] Obtaining the common operating line of the lithium battery power system based on the set of non-linear equality performance constraints.

[0008] An embodiment of the present invention provides a system for predicting a common operating line for a lithium battery power system, including:

[0009] A construction module for constructing a simulation dynamics model of the lithium battery power system;

[0010] An order reduction module for performing order reduction transformation on the simulation dynamics model to obtain a set of non-linear equality performance constraints of the lithium battery power system; and

[0011] A prediction module for obtaining the common operating line of the lithium battery power system based on the set of non-linear equality performance constraints.

[0012] An embodiment of the present invention further provides an electronic device, including: a memory, a processor, and a computer program stored on the memory and executable on the processor, where when the computer program is executed by the processor, the steps of the above method for predicting a common operating line for a lithium battery power system are implemented.

[0013] An embodiment of the present invention further provides a computer-readable storage medium, on which an implementation program for information transmission is stored. When the program is executed by a processor, the steps of the above-mentioned common working line prediction method for a lithium battery power system are implemented.

[0014] Adopting the embodiment of the present invention may include the following beneficial effects: Through the common working line prediction method proposed in the embodiment of the present invention, the steady-state value combination of the key states of the lithium battery power system that meets the thrust requirements of the aircraft can be given quickly and accurately, without a large number of iterative calculations; at the same time, the change of the common working line under different lithium battery energy consumption states can be predicted. Description of the Drawings

[0015] In order to more clearly illustrate the technical solutions in one or more embodiments of this specification or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the drawings in the following description are only some embodiments recorded in this specification. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0016] Figure 1 It is a flowchart of the common working line prediction method for a lithium battery power system according to an embodiment of the present invention;

[0017] Figure 2 It is a flowchart of the steps of the technical solution according to an embodiment of the present invention;

[0018] Figure 3 It is a schematic diagram of the voltage balance constraint surface according to an embodiment of the present invention;

[0019] Figure 4 It is a schematic diagram of the torque balance constraint surface according to an embodiment of the present invention;

[0020] Figure 5 It is a schematic diagram of the common working line formed by the intersection of the equation constraint surfaces according to an embodiment of the present invention;

[0021] Figure 6 It is a schematic diagram of the electric power common working line when the energy consumption of each lithium battery cell is 0.5 Ah at a flight altitude of 1000 m according to an embodiment of the present invention;

[0022] Figure 7 It is a schematic diagram of the change of the electric power common working line with the energy consumption of lithium battery cells at a flight altitude of 1000 m according to an embodiment of the present invention;

[0023] Figure 8 It is a schematic diagram of the change of the electric power common working line with the energy consumption of lithium battery cells at flight altitudes of 1000 m, 3000 m, and 5000 m respectively according to an embodiment of the present invention;

[0024] Figure 9 It is a schematic diagram of the co - working line prediction system for a lithium - ion power system according to an embodiment of the present invention. Detailed implementation manners

[0025] In order to enable those skilled in the art to better understand the technical solutions in one or more embodiments of this specification, the following will clearly and completely describe the technical solutions in one or more embodiments of this specification with reference to the accompanying drawings in one or more embodiments of this specification. Obviously, the described embodiments are only a part of the embodiments of this specification, rather than all of the embodiments. Based on one or more embodiments of this specification, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of this document.

[0026] Method embodiments

[0027] According to an embodiment of the present invention, a method for predicting a co - working line for a lithium - ion power system is provided. Figure 1 It is a flowchart of the method for predicting the co - working line for a lithium - ion power system according to an embodiment of the present invention. As Figure 1 shown, the method for predicting the co - working line for a lithium - ion power system according to an embodiment of the present invention specifically includes:

[0028] Step S101, constructing a simulation dynamics model of the lithium - ion power system;

[0029] Among them, the expression of the simulation dynamics model is shown in Formula 1:

[0030]

[0031] Among them, respectively represent the time derivative of the battery's power consumption, the time derivative of the battery's polarization voltage, the time derivative of the motor current, and the time derivative of the motor speed. I B represents the current of the lithium - ion battery cell, U P represents the polarization voltage of the lithium - ion battery cell, R P represents the polarization internal resistance of the lithium - ion battery cell, C P represents the polarization capacitance of the lithium - ion battery cell, U M represents the motor voltage, I M represents the motor current, R M represents the internal resistance of the motor, K E represents the back - electromotive - force constant of the motor, ω represents the speed of the motor - propeller shaft, L M represents the inductance of the motor, K T represents the torque constant of the motor, C Q represents the torque coefficient of the propeller, D P represents the diameter of the propeller, JS represents the moment of inertia of the motor-propeller shaft, and ρ represents the local atmospheric density;

[0032] Step S102: Perform order reduction transformation on the simulation dynamics model to obtain a set of nonlinear equality performance constraints for the lithium battery power system, specifically including:

[0033] Perform order reduction transformation on the simulation dynamics model to obtain a set of nonlinear equality performance constraints for the lithium battery power system as shown in Formula 2; wherein, the set of nonlinear equality performance constraints includes voltage balance constraints between the battery pack and the motor and torque balance constraints between the motor and the propeller;

[0034]

[0035] where v represents the duty cycle of the motor controller, N S and N P respectively represent the number of series-connected and parallel-connected battery cells in the lithium battery pack, U B represents the terminal voltage of the lithium battery cell, and η E represents the efficiency of the motor controller;

[0036] Step S103: Obtain the common operating line of the lithium battery power system based on the set of nonlinear equality performance constraints, specifically including:

[0037] Taking the rotational speed, lithium battery cell current, and motor duty cycle as independent variables, plot the combinations of independent variables that satisfy the set of nonlinear equality performance constraints in three-dimensional space to obtain the voltage balance constraint surface and the torque balance constraint surface respectively, and take the intersection line of the voltage balance constraint surface and the torque balance constraint surface as the common operating line of the lithium battery power system;

[0038] The method further includes:

[0039] Solving the steady-state variables of the common operating line according to different thrust requirements to obtain a series of steady-state operating points under different thrust requirements, connecting the steady-state operating points in ascending order of rotational speed to obtain a series of common operating lines, and predicting the common operating lines under different lithium battery cell energy consumption states, specifically including:

[0040] Calculating the steady-state rotational speed according to different thrust requirements using Formula 3, calculating the steady-state lithium battery cell current based on the steady-state rotational speed using Formula 4, and calculating the steady-state motor duty cycle based on the steady-state rotational speed and the steady-state lithium battery cell current using Formula 5;

[0041]

[0042] where T R represents the given propeller thrust requirement, and C Trepresents the propeller thrust coefficient, U OC represents the open - circuit voltage of the current lithium battery cell, Δ represents an intermediate variable, R B represents the internal resistance of the lithium battery cell, I max represents the maximum available current.

[0043] The following details the above - mentioned technical solutions of the embodiments of the present invention in combination with the specific situation of the common - working - line prediction method for the lithium - battery power system of the present invention.

[0044] The embodiment of the present invention proposes a method for predicting the common - working line of an aviation lithium - battery power system. Specifically, it is applicable to an aviation lithium - battery power system that uses a lithium - battery pack to provide energy for a brushless DC motor or a permanent - magnet synchronous motor, and then the motor drives an air propeller. First, a simulation model of the aviation lithium - battery power system is established. Through order - reduction transformation, it is converted into two non - linear electric - propulsion performance equality constraints: voltage balance and torque balance. Then, the motor - propeller shaft speed, the duty cycle of the motor controller, and the load current of the lithium - battery cell are selected as key variables representing the working states of the three components of the propeller, motor, and lithium - battery cell. Furthermore, it can be determined that the two non - linear performance equality constraints are three - dimensional surfaces in the three - dimensional space composed of the above three variables, and the spatial intersection line of the two three - dimensional surfaces is the common - working line of the aviation lithium - battery power system. The embodiment of the present invention further gives a calculation method for determining the steady - state balance speed, cell current, and motor duty cycle at one time according to the thrust requirement of the aircraft, and can reflect the influence of the energy consumption of the lithium - battery cell on the working state of the lithium - battery power system, thereby realizing the rapid prediction of the common - working line.

[0045] The embodiment of the present invention specifically includes the following 4 steps:

[0046] 1. Modeling of the aviation lithium - battery power system;

[0047] 2. Order - reduction transformation of the aviation lithium - battery power system model;

[0048] 3. Forming the common - working line according to the performance - constraint surface;

[0049] 4. Solving the steady - state variables of the common - working line.

[0050] Specifically, as Figure 2 shown, the detailed steps of the embodiment of the present invention are as follows:

[0051] Step 1: Modeling of the aviation lithium - battery power system

[0052] For an aviation lithium - battery power system that directly drives an air propeller using a brushless DC motor or a permanent - magnet synchronous motor (i.e., the motor and the propeller have the same speed), the dynamic model corresponding to the involved state variables can be expressed by the following first - order ordinary differential equation:

[0053]

[0054] Among them, respectively represent the time derivative of the battery power consumption, the time derivative of the battery polarization voltage, the time derivative of the motor current, and the time derivative of the motor speed; that is, all superscripts represent time derivatives, and removing the superscripts gives the corresponding state variables; I B is the lithium battery cell current, U P is the lithium battery cell polarization voltage, R P is the lithium battery cell polarization internal resistance, C P is the lithium battery cell polarization capacitance, U M is the motor voltage, I M is the motor current, R M is the motor internal resistance, K E is the motor back electromotive force constant, ω is the speed of the motor-propeller shaft, L M is the motor inductance, K T is the motor torque constant, C Q is the propeller torque coefficient, D P is the propeller diameter, J S is the moment of inertia of the motor-propeller shaft, and ρ is the local atmospheric density.

[0055] To implement the above lithium battery power system simulation, the following auxiliary equations need to be supplemented:

[0056]

[0057] Among them, v is the duty cycle of the motor controller, U B is the lithium battery cell terminal voltage, N S and N P are the number of series-connected and parallel-connected battery cells in the lithium battery pack respectively, R B is the lithium battery cell internal resistance, U OC is the lithium battery cell open-circuit voltage, η E is the motor controller efficiency, SOC is the state of charge of the lithium battery cell, Q B is the power consumption of the lithium battery cell, Q max is the maximum capacity of the lithium battery cell, and [c1, c2, c3, c4] are the fitting constant coefficients of the lithium battery cell open-circuit voltage.

[0058] Step 2: Model order reduction transformation of the aviation lithium battery power system

[0059] To predict the common operating line of the lithium battery power system, the following merging and simplification need to be performed on the above simulation model:

[0060] 1. Substitute the expression of U M in the first fraction of Equation (2) into the second fraction to obtain the motor current:

[0061]

[0062] Among them, η E , N P are both constants, and I B and v are variables.

[0063] 2. The dynamic characteristics of the voltage drop of the lithium battery cell are mainly reflected in the non-linear expression of U OC with respect to SOC. U P is a negligible small quantity. Therefore, the terminal voltage of the lithium battery cell is simplified to:

[0064] U B = c1log(SOC) + exp(c2SOC) + c3SOC 3 + c4 - I B R B (4);

[0065] 3. Compared with the rigid body motion of the aircraft, the time taken for the motor-propeller shaft speed regulation and the motor current regulation can be ignored. Therefore, it can be considered that and are 0 during operation. Furthermore, the third and fourth fractions in Equation (1) can be transformed into the following non-linear equality performance constraint group:

[0066]

[0067] Substituting the expressions of U M , I M into Equation (5), the following equality constraint group is obtained:

[0068]

[0069] Among them, the independent variables include the duty ratio v, the rotational speed ω, and the lithium battery cell current I B . The upper and lower equalities respectively correspond to the voltage balance constraint between the battery pack and the motor and the torque balance constraint between the motor and the propeller.

[0070] Step 3: Form the common working line according to the performance constraint surface

[0071] Taking the rotational speed ω, the lithium battery cell current I B , and the duty ratio v as the three independent variables, and taking ω, I B , and v as the x, y, and z axes in turn, the combinations of independent variables (ω, I B , v) that satisfy the two equality constraints of Equation (6) are plotted in the three-dimensional phase space. For typical electric aircraft parameters, the voltage balance constraint surface is shown by Figure 3 , and the torque balance constraint surface is shown by Figure 4 . The intersection of the two forms the common working line of the lithium battery power system, as shown by Figure 5 .Figure 5 The physical meaning of the co - working line is that when the lithium - battery power system is in a steady - state operating condition, the combination of the rotational speed ω, the lithium - battery core current I B , and the duty cycle v must be located on this curve.

[0072] Step 4: Solving the steady - state variables of the co - working line

[0073] Determine a series of steady - state points on the co - working line in the following order, and connect these steady - state points to form a three - dimensional curve.

[0074] 1. Determine the open - circuit voltage: First, according to the current energy - consumption state of the lithium - battery core, that is, the power consumption Q B , determine the state of charge SOC of the lithium - battery core:

[0075]

[0076] Then, substitute the current SOC into the fourth fraction of Equation (2) to obtain the current open - circuit voltage U OC .

[0077] 2. The rotational speed ω is determined by the thrust requirement of the electric aircraft. Given that the propeller thrust requirement is T R , then the rotational speed should satisfy the following balance relationship:

[0078]

[0079] where C T is the propeller thrust coefficient, and C T is determined jointly by the propeller rotational speed and the flight speed. Then the steady - state rotational speed is:

[0080]

[0081] 3. Based on the steady - state rotational speed, the steady - state current is:

[0082]

[0083] When the required current exceeds the upper limit of the lithium - battery core current, the maximum available current I max should be taken. In the formula, the open - circuit voltage U OC is calculated from the first sub - step of this step, and the expression of the intermediate variable Δ is as follows:

[0084]

[0085] where ω is calculated from the second sub - step of this step, and the others are constant parameters of the aircraft; Q P is the propeller torque:

[0086]

[0087] 4. Calculate the steady-state motor duty cycle based on the steady-state speed and the lithium battery core current as follows:

[0088]

[0089] Using the above method, within the flight envelope of the aircraft, different flight thrust demands T are given at certain intervals R , and then the steady-state speed, the steady-state lithium battery core current, and the steady-state duty cycle are solved in turn. Connect all the steady-state operating points in ascending order of speed to form a common operating line; further, given different power consumption states Q of the lithium battery cores B , a series of common operating lines can be calculated.

[0090] In the embodiment of the present invention, the flight state of the example electric aircraft is set as follows: the speed increases from 25 m / s to 40 m / s, the altitude is 1000 m, the local atmospheric density is 1.116 kg / m 3 , the power of each lithium battery core is 0.5 Ah, and the thrust demand is provided by 2 thrust propellers. The parameters of the electric aircraft are shown in Table 1.

[0091] Table 1 Parameters of the example electric aircraft

[0092]

[0093]

[0094] According to the above settings, the changing trends of the thrust demand, the steady-state speed, the core current, and the duty cycle of each propeller of the lithium battery power system with the speed are shown in Table 2, and thus a common operating line as shown in Figure 6 is formed.

[0095] Table 2 Steady-state quantities in the case of power consumption of 0.5 Ah

[0096]

[0097]

[0098] Further set different power consumption states of the lithium battery cores to 0.5 Ah, 1.0 Ah, 1.5 Ah, 2.0 Ah, and use the method proposed in the embodiment of the present invention to predict the common operating line, as shown in Figure 7 .

[0099] Further set different flight altitudes of the aircraft to 1000 m, 3000 m, 5000 m, and different power consumption states of the lithium battery cores to 0.5 Ah, 1.0 Ah, 1.5 Ah, 2.0 Ah, and use the method proposed in the embodiment of the present invention to predict the common operating line, as shown in Figure 8 .

[0100] System Embodiment

[0101] According to an embodiment of the present invention, a co - working line prediction system for a lithium - ion power system is provided. Figure 9 It is a schematic diagram of the co - working line prediction system for a lithium - ion power system according to an embodiment of the present invention. As Figure 9 shown, the co - working line prediction system for a lithium - ion power system according to an embodiment of the present invention specifically includes:

[0102] A construction module 90, configured to construct a simulation dynamics model of the lithium - ion power system;

[0103] A reduction - order module 92, configured to perform reduction - order transformation on the simulation dynamics model to obtain a set of non - linear equality performance constraints of the lithium - ion power system; and

[0104] A prediction module 94, configured to obtain the co - working line of the lithium - ion power system based on the set of non - linear equality performance constraints.

[0105] The system further includes:

[0106] A solution module, configured to solve the steady - state variables of the co - working line according to different thrust requirements, obtain a series of steady - state operating points under different thrust requirements, connect the steady - state operating points in ascending order of rotational speed, obtain a series of co - working lines, and predict the co - working lines under different lithium - ion battery energy consumption states.

[0107] The embodiment of the present invention is a system embodiment corresponding to the above - mentioned method embodiment. The specific operations of each module can be understood with reference to the description of the method embodiment and will not be elaborated herein.

[0108] In summary, the embodiment of the present invention proposes a method for predicting the co - working line of an aviation lithium - ion power system. By reducing the order of the simulation model of the aviation lithium - ion power system, constructing the voltage balance and torque balance equality performance constraints of the lithium - ion power system, and determining that the spatial intersection line of the two constraint surfaces is the co - working line, the key variables determining the co - working line are the motor - propeller shaft rotational speed, the duty ratio of the motor controller, and the lithium - ion battery load current. A fast method for sequentially determining the steady - state rotational speed, steady - state current, and steady - state duty ratio according to the thrust requirement of the aircraft is given.

[0109] Device Embodiment 1

[0110] The embodiment of the present invention provides an electronic device, including: a memory, a processor, and a computer program stored on the memory and executable on the processor. When the computer program is executed by the processor, the steps described in the method embodiment are implemented.

[0111] Device Embodiment 2

[0112] An embodiment of the present invention provides a computer-readable storage medium, on which an implementation program for information transmission is stored, and when the program is executed by a processor, the steps described in the method embodiment are implemented.

[0113] The computer-readable storage medium described in this embodiment includes, but is not limited to, ROM, RAM, magnetic disk, optical disc, etc.

[0114] Finally, it should be noted that: the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: they can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements on some or all of the technical features; and these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A prediction method for the common working line of a lithium battery power system, characterized in that Including: Constructing a simulation dynamics model of a lithium battery power system; Performing order reduction transformation on the simulation dynamics model to obtain a set of nonlinear equality performance constraints for the lithium battery power system; And Obtaining the common operating line of the lithium battery power system based on the set of nonlinear equality performance constraints.

2. The method according to claim 1, wherein The method further includes: Solving the steady-state variables of the common operating line according to different thrust requirements to obtain a series of steady-state operating points under different thrust requirements, connecting the steady-state operating points in ascending order of rotational speed to obtain a series of common operating lines, and predicting the common operating lines under different lithium battery core energy consumption states.

3. The method according to claim 1, wherein The expression of the simulation dynamics model is shown in Formula 1: Among them, respectively represent the time derivative of the battery power consumption, the time derivative of the battery polarization voltage, the time derivative of the motor current, and the time derivative of the motor speed. I B represents the lithium battery cell current, U P represents the lithium battery cell polarization voltage, R P represents the lithium battery cell polarization internal resistance, C P represents the lithium battery cell polarization capacitance, U M represents the motor voltage, I M represents the motor current, R M represents the motor internal resistance, K E represents the motor back electromotive force constant, ω represents the speed of the motor-propeller shaft, L M represents the motor inductance, K T represents the motor torque constant, C Q represents the propeller torque coefficient, D P represents the propeller diameter, J S represents the moment of inertia of the motor-propeller shaft, and ρ represents the local atmospheric density.

4. The method according to claim 1, characterized in that Performing order reduction transformation on the simulation dynamics model to obtain a set of nonlinear equality performance constraints for the lithium battery power system specifically includes: Performing order reduction transformation on the simulation dynamics model to obtain a set of nonlinear equality performance constraints for the lithium battery power system shown in Formula 2; wherein, the set of nonlinear equality performance constraints includes a voltage balance constraint between the battery pack and the motor and a torque balance constraint between the motor and the propeller. Among them, v represents the duty cycle of the motor controller, N S and N P respectively represent the number of series-connected and parallel-connected battery cells in the lithium battery pack, U B represents the terminal voltage of the lithium battery cell, η E represents the efficiency of the motor controller.

5. The method according to claim 4, characterized in that Obtaining the common operating line of the lithium battery power system based on the set of nonlinear equality performance constraints specifically includes: Taking rotational speed, lithium battery core current, and motor duty ratio as independent variables, plotting the combinations of independent variables that satisfy the set of nonlinear equality performance constraints in three-dimensional space to obtain a voltage balance constraint surface and a torque balance constraint surface respectively, and taking the intersection line of the voltage balance constraint surface and the torque balance constraint surface as the common operating line of the lithium battery power system.

6. The method according to claim 2, characterized in that, Solving the steady-state variables of the common operating line according to different thrust requirements to obtain a series of steady-state operating points under different thrust requirements specifically includes: Calculating the steady-state rotational speed according to different thrust requirements using Formula 3, calculating the steady-state lithium battery core current based on the steady-state rotational speed using Formula 4, and calculating the steady-state motor duty ratio based on the steady-state rotational speed and the steady-state lithium battery core current using Formula 5. Among them, T R represents the given propeller thrust requirement, C T represents the propeller thrust coefficient, U OC represents the open-circuit voltage of the current lithium battery cell, Δ represents an intermediate variable, R B represents the internal resistance of the lithium battery cell, I max represents the maximum available current.

7. A co-working line prediction system for a lithium battery power system, characterized in that Including: A construction module for constructing a simulation dynamics model of a lithium battery power system; An order reduction module for performing order reduction transformation on the simulation dynamics model to obtain a set of nonlinear equality performance constraints for the lithium battery power system; And A prediction module for obtaining the common operating line of the lithium battery power system based on the set of nonlinear equality performance constraints.

8. The system according to claim 7, wherein The system further includes: A solving module for solving the steady-state variables of the common operating line according to different thrust requirements to obtain a series of steady-state operating points under different thrust requirements, connecting the steady-state operating points in ascending order of rotational speed to obtain a series of common operating lines, and predicting the common operating lines under different lithium battery core energy consumption states.

9. An electronic device, characterized in that, Including: A memory, a processor, and a computer program stored on the memory and executable on the processor, where when the computer program is executed by the processor, it implements the steps of the method for predicting the common operating line of a lithium battery power system according to any one of claims 1-6.

10. A computer-readable storage medium, characterized in that, An implementation program for information transmission is stored on the computer-readable storage medium. When the program is executed by a processor, the steps of the co-working line prediction method for a lithium battery power system as described in any one of claims 1-6 are implemented.

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