Satellite battery capacity degradation assessment method, device and electronic equipment

Abstract

The present invention provides a method, device, and electronic device for evaluating satellite battery capacity degradation. The evaluation method includes: discharging a fully charged satellite battery to obtain the satellite battery's discharge capacity and corresponding cutoff voltage; obtaining an initial state of charge (δ1) under a discharge capacity Q1 condition based on the satellite battery's initial discharge capacity versus state of charge curve; and after the battery capacity degradation, obtaining the corresponding discharge cutoff voltage of the battery under the same discharge capacity Q1 condition. Furthermore, based on the satellite battery's initial state of charge versus cutoff voltage curve, obtaining an approximate state of charge (δ2) corresponding to the discharge cutoff voltage, and calculating the satellite battery's capacity degradation (ΔQ), where ΔQ = δ1-δ2. The present invention can approximate the satellite battery's capacity degradation, and the method is simple and highly adaptable.

Description

Technical Field

[0001] The present invention mainly relates to the technical field of satellite performance monitoring, and in particular to a method, device and electronic equipment for evaluating satellite battery capacity degradation. Background Art

[0002] Satellites (artificial satellites) are devices built by humans and launched into space for various scientific research, communications, reconnaissance, and other missions. The primary function of a satellite's battery is to provide continuous and stable power to the satellite, especially when the solar panels are inoperative. Common equipment on a satellite, including communications, positioning, and remote sensing, requires power. While the equipment required varies depending on the purpose of the satellite, all require electricity to operate. Batteries ensure a stable power supply to the satellite when the solar panels are insufficient or unavailable, enabling continued and stable operation.

[0003] Satellite battery health assessment is critical to ensuring the stable operation of satellite power systems. Battery health assessment primarily evaluates the extent of capacity degradation relative to a new battery after multiple charge-discharge cycles or a period of inactivity. On the ground, battery health assessments typically use capacity and internal resistance as health factors to characterize battery health. Using capacity as the characteristic factor for health assessment requires the battery to be fully charged and discharged, from which the actual capacity can be determined using the ampere-hour integration method. For satellites in medium and high orbits, to ensure long battery life, the battery is designed to have a maximum depth of discharge of no more than 70%. Full discharge is not possible, and therefore the actual capacity cannot be directly determined. Using internal resistance as a characteristic factor for health assessment requires providing a certain level of stimulation on the ground and using instrumentation to measure the battery's internal resistance, which is not possible on orbit.

[0004] Existing satellite battery health assessment methods mainly include establishing a multi-level assessment indicator system, using data-driven models and confidence rule base (BRB) assessment models, etc. These assessment methods can comprehensively and accurately assess the health status of batteries and provide a scientific basis for satellite system maintenance or backup battery replacement, but these assessment methods are relatively complex. Summary of the Invention

[0005] The technical problem to be solved by the present invention is to provide a method, device and electronic equipment for evaluating the capacity degradation of satellite batteries, which can approximately infer the capacity degradation of satellite batteries. The method is simple and has strong adaptability.

[0006] To solve the above technical problems, in a first aspect, the present invention provides a method for evaluating the capacity degradation of a satellite battery, comprising: discharging the fully charged satellite battery to obtain the discharge capacity and the corresponding cut-off voltage of the satellite battery; obtaining the initial state of charge δ1 under the condition of discharge capacity Q1 based on the initial discharge capacity and state of charge curve of the satellite battery; after the battery capacity decays, obtaining the discharge cut-off voltage of the corresponding battery under the same discharge capacity Q1 condition, and obtaining the approximate state of charge δ2 corresponding to the discharge cut-off voltage based on the initial state of charge and cut-off voltage curve of the satellite battery; and calculating the capacity degradation △Q of the satellite battery, △Q=△1-△2.

[0007] Optionally, the discharge amount is a fixed discharge amount.

[0008] Optionally, if the obtained discharge capacity of the satellite battery is not equal to the fixed discharge capacity, the current discharge capacity is corrected to the fixed discharge capacity, thereby obtaining a corrected cut-off voltage.

[0009] Optionally, when correcting the discharge amount, there is a linear relationship between the discharge amount and the cut-off voltage, and the discharge amount is corrected based on the linear relationship between the discharge amount and the cut-off voltage.

[0010] Optionally, the linear relationship is determined by the maximum and minimum values ​​of the discharge amount.

[0011] Optionally, when correcting the discharge amount, a fitted curve relationship is formed between the discharge amount and the cut-off voltage, and the discharge amount is corrected based on the curve relationship between the discharge amount and the cut-off voltage.

[0012] Optionally, a least squares method is used to fit the curve relationship between the discharge amount and the cut-off voltage.

[0013] In a second aspect, the present invention provides a device for evaluating the capacity degradation of a satellite battery, comprising: an acquisition module for discharging the satellite battery after being fully charged, and obtaining the discharge capacity and corresponding cut-off voltage of the satellite battery; a first obtaining module for obtaining the initial state of charge δ1 under the condition of discharge capacity Q1 based on the initial discharge capacity and state of charge curve of the satellite battery; a second obtaining module for obtaining the discharge cut-off voltage of the corresponding battery under the same discharge capacity Q1 condition after the battery capacity decays, and obtaining the approximate state of charge δ2 corresponding to the discharge cut-off voltage based on the initial state of charge and cut-off voltage curve of the satellite battery; and a calculation module for calculating the capacity degradation △Q of the satellite battery, △Q=δ1-δ2.

[0014] In a third aspect, the present invention provides an electronic device comprising: a processor and a memory, wherein the memory stores programs or instructions that can be run on the processor, and when the program or instructions are executed by the processor, the steps of the satellite battery capacity degradation evaluation method as described in the first aspect are implemented.

[0015] In a fourth aspect, the present invention provides a readable storage medium storing a program or instruction. When the program or instruction is executed by a processor, the steps of the satellite battery capacity degradation evaluation method as described in the first aspect are implemented.

[0016] Compared with the prior art, the present invention has the following advantages: first, a fully charged satellite battery is discharged to obtain the discharge capacity and corresponding cut-off voltage of the satellite battery; then, based on the initial discharge capacity and state of charge curve of the satellite battery, the initial state of charge δ1 under the condition of discharge capacity Q1 is obtained; after the battery capacity decays, the discharge cut-off voltage of the battery corresponding to the same discharge capacity Q1 is obtained, and based on the initial state of charge and cut-off voltage curve of the satellite battery, the approximate state of charge δ2 corresponding to the discharge cut-off voltage is obtained; finally, the capacity decay ΔQ of the satellite battery is calculated, ΔQ=δ1-δ2, and the capacity decay of the satellite battery can be approximately inferred. The method is simple and highly adaptable. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The accompanying drawings are included to provide a further understanding of the present application. They are incorporated into and constitute a part of this application. The accompanying drawings illustrate embodiments of the present application and, together with this specification, serve to explain the principles of the present application. In the accompanying drawings:

[0018] Figure 1 1 is a flow chart of a method for evaluating satellite battery capacity degradation according to an embodiment of the present invention;

[0019] Figure 2 is a curve showing the relationship between the cut-off voltage and the state of charge of a battery in one embodiment of the present invention;

[0020] Figure 3 is a curve showing the relationship between the cut-off voltage and the discharge capacity of a battery in one embodiment of the present invention;

[0021] Figure 4 1 is a schematic structural diagram of a device for evaluating satellite battery capacity degradation according to an embodiment of the present invention;

[0022] Figure 5 FIG. 1 is a schematic diagram of an electronic device according to an embodiment of the present invention. DETAILED DESCRIPTION

[0023] To more clearly illustrate the technical solutions of the embodiments of this application, the following is a brief introduction to the drawings required for describing the embodiments. Obviously, the drawings described below are merely examples or embodiments of this application. Those skilled in the art can apply this application to other similar scenarios based on these drawings without inventive effort. Unless otherwise apparent from the context or otherwise noted, the same reference numerals in the figures represent the same structure or operation.

[0024] As used in this application and the claims, unless the context clearly indicates otherwise, the words "a," "an," "an," and / or "the" are not intended to refer to the singular but may include the plural. Generally speaking, the terms "comprises" and "include" only indicate the inclusion of the steps and elements specifically identified, and these steps and elements do not constitute an exclusive list. A method or apparatus may also include other steps or elements.

[0025] Flowcharts are used in this application to illustrate the operations performed by systems according to embodiments of the present application. It should be understood that the preceding or following operations are not necessarily performed in exact order. Instead, the various steps may be processed in reverse order or simultaneously. Furthermore, other operations may be added to these processes, or one or more operations may be removed from these processes.

[0026] An evaluation method 100 for satellite battery capacity degradation according to an embodiment of the present invention may be referred to Figure 1 As shown, the method 100 includes:

[0027] S110. Discharge the fully charged satellite battery to obtain the discharge capacity and corresponding cut-off voltage of the satellite battery. S120. Obtain the initial state of charge δ1 under the condition of discharge capacity Q1 based on the initial discharge capacity and state of charge curve of the satellite battery. S130. After the battery capacity decays, obtain the discharge cut-off voltage of the corresponding battery under the same discharge capacity Q1 condition, and obtain the approximate state of charge δ2 corresponding to the discharge cut-off voltage based on the initial state of charge and cut-off voltage curve of the satellite battery. S140. Calculate the capacity decay ΔQ of the satellite battery, ΔQ = δ1-δ2.

[0028] Satellite batteries continuously degrade in capacity from the moment they are activated. Unlike batteries on the ground, satellite batteries cannot be tested using ground-based methods to determine their degradation while in orbit. Existing techniques often rely on simulations or algorithms to estimate satellite battery degradation. While these simulations and algorithms offer advantages when a more accurate prediction or estimation of battery degradation is required, they are often complex when only a rough understanding of battery degradation is required.

[0029] In this embodiment, reference Figure 2 As shown, Figure 2 This diagram illustrates the relationship between a battery's state of charge (SOC) and cutoff voltage under initial / ideal conditions. However, in reality, as battery performance degrades, the SOC-cutoff voltage curve also changes, deviating from the curve measured at the factory. The fully charged capacity of the battery without degradation is assumed to be Q, and the unknown capacity after degradation is Q'. Assuming the battery discharges the same amount, Q1, the early and late stages of its life correspond to two different discharge cutoff voltages, VD1 and VD1', respectively, corresponding to SOCs δ1 and δ1'. If the battery has not experienced capacity degradation, VD1 should equal VD1', and δ1 should equal δ1'.

[0030] According to the battery state of charge and voltage correspondence curve, the state of charge corresponding to VD1 is δ1, and the state of charge corresponding to VD1' is δ1'. Then, δ1*Q+Q1=Q, δ1'*Q'+Q1=Q'.

[0031] However, based on the current situation, we do not know the degradation of the batteries in orbit, that is, we do not know the battery capacity Q'. Therefore, when applying the formula δ1'*Q'+Q1=Q', we assume that the battery state of charge and voltage curve do not change, and approximately assume that Q' is equal to Q. Then according to Figure 2 In the curve shown, VD1' is equal to VD2, δ1'=δ2, VD1>VD2, δ1>δ2. Then the formula δ1'*Q'+Q1=Q' can be rewritten as the formula δ2*Q+Q1=Q', based on which the battery capacity degradation △Q can be obtained:

[0032]

[0033] It can be seen that the battery capacity decay △Q is approximately equal to the difference between the theoretical state of charge under the same discharge conditions on the battery state of charge and cut-off voltage correspondence curve and the equivalent state of charge after decay.

[0034] In one example, the discharge amount is a fixed amount. The above evaluation method can approximately calculate the battery capacity degradation. However, since the battery is in a degradation state at all times, to further optimize the calculation method, the method of this embodiment can set the discharge amount for each calculation process to the same value. This simplifies the calculation of battery degradation each time and avoids calculation deviations caused by inconsistent benchmarks for each calculation.

[0035] In one example, if the obtained discharge capacity of the satellite battery is not equal to the fixed discharge capacity, the current discharge capacity is corrected to the fixed discharge capacity, thereby obtaining a corrected cut-off voltage.

[0036] For satellites in orbit, the discharge capacity corresponding to the deepest discharge cutoff voltage during each Earth shadow season is affected by the actual on-orbit load, making it difficult to benchmark the discharge capacity against a fixed discharge capacity. As can be seen, in most cases, achieving a consistent discharge capacity is difficult in practical applications. To calculate the battery degradation degree using a fixed discharge capacity in this embodiment, the existing discharge capacity can be corrected using a non-fixed discharge capacity.

[0037] For example, a navigation network satellite has been in orbit for 5 years and has experienced 10 Earth shadow seasons. The minimum discharge voltage and corresponding discharge amount of the satellite in each Earth shadow season are shown in Table 1 below.

[0038] Table 1 Corresponding relationship between discharge amount and voltage during the Earth shadow season

[0039]

[0040] As can be seen from Table 1, there is a certain functional relationship between the discharge amount and the cut-off voltage. Therefore, as long as this functional relationship can be obtained, even if the discharge amount is not a fixed discharge amount, the method of this embodiment can also infer the corresponding cut-off voltage under the condition of a fixed discharge amount. Faced with this situation, this embodiment can have two different correction methods. One is to use a linear correction method. This correction method is relatively simple and can roughly reflect the relationship between the discharge amount and the cut-off voltage. The other is a more accurate correction method. This correction method is to fit the current point into a function (curve) as much as possible. Compared with the linear method, this method can more accurately obtain the cut-off voltage under the condition of a fixed discharge amount. Therefore, in this embodiment, the corresponding correction method can be selected according to actual needs to correct the fixed discharge amount.

[0041] For example, when correcting the discharge capacity, the discharge capacity and the cut-off voltage are in a linear relationship, and the discharge capacity is corrected based on the linear relationship between the discharge capacity and the cut-off voltage. Furthermore, the linear relationship is determined based on the maximum and minimum values ​​of the discharge capacity.

[0042] For example, the battery discharge cut-off voltage corresponding to the Nth earth shadow season obtained by the actual trajectory is set to Udn, corresponding to the discharge amount Qn. Then the battery discharge cut-off voltage vector set corresponding to the discharge amount of each earth shadow season is In order to unify the deepest discharge amount of each earth shadow season to the same value Q1, it is necessary to calculate the discharge cut-off voltage Udj corresponding to the discharge amount Q1 of the jth (n∈2~N) earth shadow season.

[0043] Assuming the full-charge voltage corresponding to the battery's full charge during the jth geomorphic season is UMj, the corresponding voltages for a discharge of 0 during that geomorphic season and for a discharge of Qj are 0|UMj and Qj|Udj, respectively. Assuming a linear relationship between discharge and battery voltage, the following formula can be derived: (See the figure below for details).

[0044]

[0045] Then we can get the battery discharge cut-off voltage corresponding to the discharge amount Q1:

[0046]

[0047] The data is corrected to obtain the discharge cut-off voltage vector set corresponding to the battery discharge of 23.51AH

[0048]

[0049] According to the battery state of charge and voltage curve, refer to Figure 3 As shown in Figure 2. According to the satellite battery’s initial discharge capacity and state of charge curve, Figure 2 As shown in the figure, after 5 years in orbit, the battery capacity decays to 11.5%.

[0050] Alternatively, a linear relationship can be derived from the two points closest to the fixed discharge capacity. Compared to determining the linear relationship using the maximum and minimum discharge capacity, this method is closer to the fixed discharge capacity, so the fixed discharge capacity derived from this method is more accurate. However, the calculation method is not as simple as determining the linear relationship using the maximum and minimum discharge capacity.

[0051] In one example, when correcting the discharge capacity, a curve relationship is fitted between the discharge capacity and the cut-off voltage, and the discharge capacity is corrected based on the curve relationship between the discharge capacity and the cut-off voltage. Further, the curve relationship between the discharge capacity and the cut-off voltage is fitted using a least squares method.

[0052] Function fitting, or curve fitting, involves finding a mathematical function (model) that best describes the relationship between a given set of data points. This process typically involves selecting a functional form and then using an algorithm to determine the parameters of this function so that it approximates or passes through all data points as closely as possible. The basic principle of the least squares method is to use the difference between the data points and a preset function, called the "model function," to estimate the parameters of the model function. This difference can be measured as the sum of squared errors, and the least squares method is the method that minimizes this sum of squares.

[0053] The satellite battery capacity degradation assessment method provided in this embodiment first discharges the fully charged satellite battery to obtain the discharge capacity and corresponding cut-off voltage of the satellite battery; then, based on the satellite battery's initial discharge capacity and state of charge curve, obtains the initial state of charge δ1 under the condition of discharge capacity Q1; after the battery capacity degradation, the corresponding discharge cut-off voltage of the battery under the same discharge capacity Q1 is obtained, and based on the satellite battery's initial state of charge and cut-off voltage curve, obtains the approximate state of charge δ2 corresponding to the discharge cut-off voltage; finally, the satellite battery capacity degradation ΔQ is calculated, ΔQ = δ1-δ2, and the satellite battery capacity degradation can be approximately inferred. The method is simple and highly adaptable.

[0054] Another embodiment of the present invention is a device for evaluating the capacity degradation of satellite batteries, referring to Figure 4 As shown, the device 400 mainly includes: an acquisition module 401, which is used to discharge the satellite battery after being fully charged, and obtain the discharge capacity and corresponding cut-off voltage of the satellite battery; a first obtaining module 402, which is used to obtain the initial state of charge δ1 under the condition of discharge capacity Q1 based on the initial discharge capacity and state of charge curve of the satellite battery; a second obtaining module 403, which is used to obtain the discharge cut-off voltage of the corresponding battery under the same discharge capacity Q1 condition after the battery capacity decays, and obtain the approximate state of charge δ2 corresponding to the discharge cut-off voltage based on the initial state of charge and cut-off voltage curve of the satellite battery; and a calculation module 404, which is used to calculate the capacity decay △Q of the satellite battery, △Q=△1-△2.

[0055] In one example, the discharge amount is a fixed discharge amount.

[0056] In one example, if the obtained discharge capacity of the satellite battery is not equal to the fixed discharge capacity, the current discharge capacity is corrected to the fixed discharge capacity, thereby obtaining a corrected cut-off voltage.

[0057] In one example, when correcting the discharge amount, there is a linear relationship between the discharge amount and the cut-off voltage, and the discharge amount is corrected based on the linear relationship between the discharge amount and the cut-off voltage.

[0058] In one example, the linear relationship is determined by the maximum and minimum values ​​of the discharge amount.

[0059] When correcting the discharge amount, the discharge amount and the cut-off voltage are in a fitted curve relationship, and the discharge amount is corrected based on the curve relationship between the discharge amount and the cut-off voltage.

[0060] In one example, the least square method is used to fit the curve relationship between the discharge capacity and the cut-off voltage.

[0061] The details of other operations performed by each module in this embodiment can be referred to the aforementioned embodiments and will not be elaborated here.

[0062] The satellite battery capacity degradation assessment device provided in this embodiment first discharges a fully charged satellite battery to obtain the discharge capacity and corresponding cut-off voltage of the satellite battery; then, based on the satellite battery's initial discharge capacity and state of charge curve, obtains the initial state of charge δ1 under the condition of discharge capacity Q1; after the battery capacity decays, the corresponding discharge cut-off voltage of the battery under the same discharge capacity Q1 is obtained, and based on the satellite battery's initial state of charge and cut-off voltage curve, the approximate state of charge δ2 corresponding to the discharge cut-off voltage is obtained; finally, the satellite battery's capacity degradation ΔQ is calculated, ΔQ = δ1-δ2, and the satellite battery's capacity degradation can be approximately inferred. The method is simple and highly adaptable.

[0063] In the embodiments of the present application, a device for assessing satellite battery capacity degradation can be a device, or a component, integrated circuit, or chip within a terminal. In the embodiments of the present application, a device for assessing satellite battery capacity degradation can be a device having an operating system. This operating system can be an Android operating system, an iOS operating system, or other possible operating systems, and is not specifically limited in the embodiments of the present application.

[0064] The present application also provides an electronic device, comprising: a memory for storing programs or instructions executable by a processor; and a processor for executing the above programs or instructions to implement the various processes of the above-mentioned satellite battery capacity degradation evaluation method embodiment, and can achieve the same technical effect. To avoid repetition, it will not be repeated here.

[0065] Figure 5is a schematic diagram of an electronic device according to an embodiment of the present invention. Electronic device 500 may include an internal communication bus 501, a processor 502, a read-only memory (ROM) 503, a random access memory (RAM) 504, and a communication port 505. When used in a personal computer, electronic device 500 may also include a hard disk 506. The internal communication bus 501 enables data communication between components of electronic device 500. Processor 502 can make decisions and issue prompts. In some embodiments, processor 502 may be composed of one or more processors. Communication port 505 enables data communication between electronic device 500 and the outside world. In some embodiments, electronic device 500 can send and receive information and data from a network via communication port 505. Electronic device 500 may also include various forms of program storage units and data storage units, such as a hard disk 506, a read-only memory (ROM) 503, and a random access memory (RAM) 504, capable of storing various data files used for computer processing and / or communication, as well as possible programs or instructions executed by processor 502. The result processed by the processor 502 is transmitted to the user equipment through the communication port 505 and displayed on the user interface.

[0066] The above-mentioned satellite battery capacity degradation assessment method can be implemented as a computer program, stored in the hard disk 506, and recorded in the processor 502 for execution to implement any satellite battery capacity degradation assessment method in this application.

[0067] An embodiment of the present application also provides a readable storage medium, on which a program or instruction is stored. When the program or instruction is executed by a processor, each process of the above-mentioned satellite battery capacity degradation evaluation method embodiment is implemented, and the same technical effect can be achieved. To avoid repetition, it will not be repeated here.

[0068] In some embodiments, numbers are used to describe the quantity of components and attributes. It should be understood that such numbers used in the description of the embodiments are modified by the modifiers "about", "approximately" or "substantially" in some examples. Unless otherwise stated, "about", "approximately" or "substantially" indicate that the numbers are allowed to vary by ±20%. Accordingly, in some embodiments, the numerical parameters used in the description and claims are approximate values, which may change according to the required features of individual embodiments. In some embodiments, the numerical parameters should take into account the specified significant digits and adopt the general method of retaining digits. Although the numerical domains and parameters used to confirm the breadth of their range in some embodiments of the present application are approximate values, in specific embodiments, the settings of such numerical values ​​are as accurate as possible within the feasible range.

[0069] Although the present application has been described with reference to the current specific embodiments, ordinary technicians in this technical field should recognize that the above embodiments are only used to illustrate the present application, and various equivalent changes or substitutions can be made without departing from the spirit of the present application. Therefore, as long as the changes and modifications to the above embodiments are within the scope of the essential spirit of the present application, they will fall within the scope of the claims of the present application.

Claims

1. A method for evaluating satellite battery capacity degradation, characterized in that: include: discharging the fully charged satellite battery to obtain a discharge capacity and a corresponding cut-off voltage of the satellite battery; Based on the initial discharge capacity and state of charge curve of the satellite battery, an initial state of charge δ1 under the condition of discharge capacity Q1 is obtained; After the battery capacity decays, the discharge cut-off voltage of the corresponding battery under the same discharge capacity Q1 is obtained, and based on the initial state of charge and cut-off voltage curve of the satellite battery, the approximate state of charge δ2 corresponding to the discharge cut-off voltage is obtained; Calculate the capacity decay ΔQ of the satellite battery, ΔQ = δ1-δ2.

2. The method for evaluating satellite battery capacity degradation according to claim 1, wherein: The discharge amount is a fixed discharge amount.

3. The method for evaluating satellite battery capacity degradation according to claim 2, wherein: If the obtained discharge capacity of the satellite battery is not equal to the fixed discharge capacity, the current discharge capacity is corrected to the fixed discharge capacity, thereby obtaining a corrected cut-off voltage.

4. The method for evaluating satellite battery capacity degradation according to claim 3, wherein: When correcting the discharge amount, there is a linear relationship between the discharge amount and the cut-off voltage, and the discharge amount is corrected based on the linear relationship between the discharge amount and the cut-off voltage.

5. The method for evaluating satellite battery capacity degradation according to claim 4, wherein: The linear relationship is determined by the maximum and minimum values ​​of the discharge amount.

6. The method for evaluating satellite battery capacity degradation according to claim 3, wherein: When correcting the discharge amount, the discharge amount and the cut-off voltage are in a fitted curve relationship, and the discharge amount is corrected based on the curve relationship between the discharge amount and the cut-off voltage.

7. The method for evaluating satellite battery capacity degradation according to claim 6, wherein: The least square method is used to fit the curve relationship between the discharge capacity and the cut-off voltage.

8. A device for evaluating satellite battery capacity degradation, characterized in that: include: an acquisition module, configured to discharge the satellite battery after being fully charged, and obtain the discharge capacity and corresponding cut-off voltage of the satellite battery; A first obtaining module is configured to obtain an initial state of charge δ1 under a discharge capacity Q1 condition based on an initial discharge capacity and state of charge curve of the satellite battery; The second obtaining module is configured to obtain the discharge cut-off voltage of the corresponding battery under the same discharge capacity Q1 condition after the battery capacity decays, and obtain the approximate state of charge δ2 corresponding to the discharge cut-off voltage based on the initial state of charge and cut-off voltage curve of the satellite battery; The calculation module is used to calculate the capacity decay ΔQ of the satellite battery, ΔQ=δ1-δ2.

9. An electronic device, characterized in that: include: A processor and a memory, wherein the memory stores a program or instruction that can be run on the processor, and when the program or instruction is executed by the processor, the steps of the satellite battery capacity degradation assessment method according to any one of claims 1 to 7 are implemented.

10. A readable storage medium, characterized in that: The readable storage medium stores a program or instruction, and when the program or instruction is executed by the processor, the steps of the satellite battery capacity degradation assessment method as described in any one of claims 1 to 7 are implemented.

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