Satellite storage battery capacity attenuation evaluation method and device and electronic equipment

Abstract

The invention provides a satellite storage battery capacity attenuation evaluation method and device and electronic equipment, and the method comprises the steps: carrying out the discharge of a fully-charged satellite storage battery, and obtaining the discharge capacity of the satellite storage battery and a corresponding cut-off voltage; based on the initial discharge capacity and charge state curve of the satellite storage battery, obtaining an initial charge state delta 1 under the condition of the discharge capacity Q1; after the capacity of the storage battery declines, the discharge cut-off voltage corresponding to the storage battery under the same discharge capacity Q1 condition is obtained, the approximate charge state delta2 corresponding to the discharge cut-off voltage is obtained based on the initial charge state and cut-off voltage curve of the satellite storage battery, the capacity decline Q of the satellite storage battery is calculated, and Q = delta1-delta2. According to the method, the capacity attenuation condition of the satellite storage battery can be approximately speculated, and the method is simple and high in adaptability.

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 made by humans and launched into space for various scientific research, communication, reconnaissance and other tasks. The role of satellite batteries is mainly reflected in providing continuous and stable power support for satellites, especially when solar panels cannot work. Various general equipment on satellites, including communications, positioning, remote sensing, etc., require power. Satellites with different purposes require different equipment, but all require power to maintain operation. Batteries can ensure that when the solar panels are insufficient or unable to supply power, they can provide stable power support for satellites, allowing satellites to operate continuously and stably.

[0003] Satellite battery health assessment is a key link to ensure the stable operation of the satellite power system. Battery health assessment mainly evaluates the degree of capacity decay relative to new batteries after multiple charge and discharge cycles or after being shelved for a period of time. On the ground, battery health assessment generally uses capacity and internal resistance as health factors to characterize the health of the battery. Using capacity as a characteristic factor to implement health assessment requires the battery to be fully charged and discharged, and then the actual capacity of the battery can be obtained through the ampere-hour integration method. For medium and high orbit satellites, in order to ensure the long life of the battery, the maximum discharge depth of the battery design does not exceed 70%, and full discharge cannot be achieved, so the actual capacity of the battery cannot be directly obtained. Using internal resistance as a characteristic factor to implement health assessment requires providing certain excitations under ground conditions and using instruments to measure the internal resistance of the battery, which cannot be achieved under orbit conditions.

[0004] The existing satellite battery health assessment methods mainly include establishing a multi-level assessment indicator system, using a data-driven model and a confidence rule base BRB assessment model, etc. These assessment methods can comprehensively and accurately assess the health status of the battery and provide a scientific basis for satellite system maintenance or replacement of backup batteries, 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 the first aspect, the present invention provides a method for evaluating the capacity degradation of a satellite battery, comprising: discharging the satellite battery after being fully charged 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 condition of discharge capacity Q1, 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; calculating the capacity degradation △Q of the satellite battery, △Q=δ1-δ2.

[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, 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.

[0012] Optionally, a least square 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 an evaluation device for satellite battery capacity degradation, comprising: an acquisition module, used to discharge the satellite battery after full charge, and obtain the discharge capacity and corresponding cut-off voltage of the satellite battery; a first obtaining module, used to obtain the initial state of charge δ1 under the condition of discharge capacity Q1 based on the initial discharge capacity and charge state curve of the satellite battery; a second obtaining module, 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; a calculation module, used to calculate the capacity decay △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, the satellite battery after being fully charged is discharged to obtain the discharge capacity and the corresponding cut-off voltage of the satellite battery; then, based on the initial discharge capacity and charge state curve of the satellite battery, the initial charge state δ1 under the discharge capacity Q1 condition is obtained; after the battery capacity decays, the discharge cut-off voltage of the battery corresponding to the same discharge capacity Q1 condition is obtained, and based on the initial charge state and cut-off voltage curve of the satellite battery, the approximate charge state δ2 corresponding to the discharge cut-off voltage is obtained; finally, the capacity decay △Q of the satellite battery is calculated, △Q=δ1-δ2, and then the capacity decay of the satellite battery can be approximately inferred, and the method is simple and has strong adaptability. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0018] Figure 1 It 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 It 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. 4 is a schematic diagram of an electronic device according to an embodiment of the present invention. DETAILED DESCRIPTION

[0023] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following is a brief introduction to the drawings required for the description of the embodiments. Obviously, the drawings described below are only some examples or embodiments of the present application. For ordinary technicians in this field, the present application can also be applied to other similar scenarios based on these drawings without creative work. Unless it is obvious from the language environment or otherwise explained, the same reference numerals in the figures represent the same structure or operation.

[0024] As shown in this application and claims, unless the context clearly indicates an exception, the words "a", "an", "an" and / or "the" do not refer to the singular and may also include the plural. Generally speaking, the terms "include" and "comprise" only indicate the inclusion of the steps and elements that have been clearly identified, and these steps and elements do not constitute an exclusive list. The method or device may also include other steps or elements.

[0025] Flowcharts are used in the present application to illustrate the operations performed by the system according to the embodiments of the present application. It should be understood that the preceding or following operations are not necessarily performed accurately in order. On the contrary, various steps may be processed in reverse order or simultaneously. At the same time, other operations may be added to these processes, or one or more operations may be removed from these processes.

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

[0027] S110, discharge the satellite battery after full charge to obtain the discharge capacity and corresponding cut-off voltage of the satellite battery; S120, based on the initial discharge capacity and charge state curve of the satellite battery, obtain the initial charge state δ1 under the discharge capacity Q1 condition; S130, after the battery capacity decays, obtain the discharge cut-off voltage of the corresponding battery under the same discharge capacity Q1 condition, and based on the initial charge state and cut-off voltage curve of the satellite battery, obtain the approximate charge state δ2 corresponding to the discharge cut-off voltage; S140, calculate the capacity decay △Q of the satellite battery, △Q=δ1-δ2.

[0028] After the satellite battery is activated, its battery capacity will always be in the process of decay. Unlike on the ground, when the satellite is in orbit, its battery cannot be tested by some ground testing methods to obtain the battery decay degree. The existing technology often estimates the decay degree of satellite batteries through various simulations or designs of some algorithms. These simulations or algorithms have certain advantages when more accurate predictions or estimates of battery decay degree are needed, but these calculation methods are more complicated when only a rough understanding of battery decay is needed.

[0029] In this embodiment, reference Figure 2 As shown, Figure 2 It is a schematic diagram of the relationship between the battery's state of charge and cut-off voltage under initial / ideal conditions. However, in actual situations, as the battery performance declines, the relationship curve between the battery's state of charge and cut-off voltage also changes, and deviates from the curve measured at the factory. The full charge capacity of the battery without decline is set to Q, and the unknown capacity after decline is set to Q'. Under the premise that the battery discharges the same discharge capacity Q1, the early and late stages of life correspond to two different discharge cut-off voltages VD1 and VD1', respectively, and the corresponding states of charge are δ1 and δ1', respectively. If the battery has no capacity decline, VD1 should be equal to VD1', and δ1 should be equal to δ1'.

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

[0031] However, based on the current situation, the degradation of the battery of the satellite in orbit is unknown, that is, the battery capacity Q' is unknown. Therefore, when applying the formula δ1'*Q'+Q1=Q', it is assumed that the battery state of charge and voltage curve do not change, and Q' is approximately equal to Q. Then according to Figure 2 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 decay △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 discharge amount. The above evaluation method can be used to approximately calculate the capacity decline of the battery, but since the battery is in a declining state at all times, in order to optimize the calculation method, the method of this embodiment can set the discharge amount of each calculation process to the same value, so that each calculation of the battery decline is simpler, and calculation deviation caused by different benchmarks for each calculation can be avoided.

[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 the corrected cut-off voltage.

[0036] For satellites in orbit, the discharge amount corresponding to the deepest discharge cut-off voltage in each earth shadow season is affected by the actual load in orbit, so it is difficult to benchmark the discharge amount with a fixed discharge amount. It can be seen that in most cases, it is difficult to obtain the same discharge amount in practical applications. In order to be able to use a fixed discharge amount to calculate the degradation degree of the battery in this embodiment, the existing discharge amount can be corrected in the case of a non-fixed discharge amount by correction.

[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 and voltage during the Earth shadow season on orbit

[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 the 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 size under the condition of a fixed discharge amount. In the face of 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] Exemplarily, when correcting the discharge amount, the discharge amount and the cut-off voltage are in a linear relationship, and the discharge amount is corrected based on the linear relationship between the discharge amount and the cut-off voltage. Further, the linear relationship is determined based on the maximum and minimum values ​​of the discharge amount.

[0042] For example, the battery discharge cut-off voltage corresponding to the Nth earth shadow season obtained by the actual track 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 of the jth (n∈2~N) earth shadow season corresponding to the discharge amount Q1.

[0043] Assuming that the full charge voltage corresponding to the fully charged state of the battery in the jth ground shadow season is UMj, the voltage of the battery when the discharge amount is 0 in the ground shadow season and the voltage when the discharge amount is Qj are 0|UMj and Qj|Udj respectively. Here, it is assumed that the discharge amount and the battery voltage are in a linear relationship, and the following formula can be obtained: as shown in the figure below.

[0044]

[0045] Then the battery discharge cut-off voltage corresponding to the discharge amount Q1 is obtained:

[0046]

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

[0048]

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

[0050] In addition, the linear relationship between the two points closest to the fixed discharge amount can also be used. Compared with determining the linear relationship by the maximum and minimum values ​​of the discharge amount, this method of determining the linear relationship is closer to the fixed discharge amount, so the fixed discharge amount derived by this method is more accurate, but the calculation method is not as simple as the method of determining the linear relationship by the maximum and minimum values ​​of the discharge amount.

[0051] In one example, when correcting the discharge capacity, the discharge capacity and the cut-off voltage are in a fitted curve relationship, and the discharge capacity is corrected based on the curve relationship between the discharge capacity and the cut-off voltage. Further, the least square method is used to fit the curve relationship between the discharge capacity and the cut-off voltage.

[0052] Function fitting or curve fitting is to find a mathematical function (model) to best describe the relationship between these points given a set of data points. This process usually includes selecting a function form and then using an algorithm to determine the parameters in this function so that the function is as close to or passes through all data points as possible. Among them, 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 squares of the error, and the least squares method is a method to minimize 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 initial discharge capacity and charge state curve of the satellite battery, the initial charge state δ1 under the discharge capacity Q1 condition is obtained; after the battery capacity is degraded, the discharge cut-off voltage of the corresponding battery under the same discharge capacity Q1 condition is obtained, and based on the initial charge state and cut-off voltage curve of the satellite battery, the approximate charge state δ2 corresponding to the discharge cut-off voltage is obtained; finally, the capacity degradation △Q of the satellite battery is calculated, △Q=δ1-δ2, and the capacity degradation of the satellite battery can be approximately inferred. The method is simple and has strong adaptability.

[0054] Another embodiment of the present invention is a device for evaluating the degradation of satellite battery capacity, referring to Figure 4 As shown, the device 400 mainly includes: an acquisition module 401, which is used to discharge the satellite battery after full charge, 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 charge state 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; a calculation module 404, which is used to calculate the capacity decay △Q of the satellite battery, △Q=δ1-δ2.

[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 the 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 amount 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 the fully charged satellite battery to obtain the discharge capacity and corresponding cut-off voltage of the satellite battery; then, based on the initial discharge capacity and charge state curve of the satellite battery, the initial charge state δ1 under the discharge capacity Q1 condition is obtained; after the battery capacity is degraded, the discharge cut-off voltage of the corresponding battery under the same discharge capacity Q1 condition is obtained, and based on the initial charge state and cut-off voltage curve of the satellite battery, the approximate charge state δ2 corresponding to the discharge cut-off voltage is obtained; finally, the capacity degradation △Q of the satellite battery is calculated, △Q=δ1-δ2, and the capacity degradation of the satellite battery can be approximately inferred. The method is simple and has strong adaptability.

[0063] In the embodiment of the present application, a device for evaluating the degradation of satellite battery capacity may be a device, or a component, integrated circuit, or chip in a terminal. In the embodiment of the present application, a device for evaluating the degradation of satellite battery capacity may be a device having an operating system. The operating system may be an Android operating system, an iOS operating system, or other possible operating systems, which are not specifically limited in the embodiment 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-mentioned 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 55 is a schematic diagram of an electronic device according to an embodiment of the present invention. The electronic device 500 may include an internal communication bus 501, a processor (Processor) 502, a read-only memory (ROM) 503, a random access memory (RAM) 504, and a communication port 505. When applied to a personal computer, the electronic device 500 may also include a hard disk 506. The internal communication bus 501 can realize data communication between components of the electronic device 500. The processor 502 can make judgments and issue prompts. In some embodiments, the processor 502 can be composed of one or more processors. The communication port 505 can realize data communication between the electronic device 500 and the outside. In some embodiments, the electronic device 500 can send and receive information and data from the network through the communication port 505. The electronic device 500 may also include different 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, which can store various data files used for computer processing and / or communication, and possible programs or instructions executed by the processor 502. The processing result of 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 can be 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 describing the number of components and attributes are used. 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 specified, "about", "approximately" or "substantially" indicate that the numbers are allowed to vary by ±20%. Accordingly, in some embodiments, the numerical parameters used in the specification 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 setting of such numerical values ​​is 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 may 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 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 the discharge capacity and 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 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; Calculate the capacity decay ΔQ of the satellite battery, ΔQ = δ1-δ2.

2. The method for evaluating satellite battery capacity degradation as claimed in claim 1, characterized in that: The discharge amount is a fixed discharge amount.

3. The satellite battery capacity degradation evaluation method according to claim 2, characterized in that: 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 as claimed in claim 3, characterized in that: When the discharge amount is corrected, 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 satellite battery capacity degradation evaluation method according to claim 4, characterized in that: The linear relationship is determined by the maximum and minimum values ​​of the discharge amount.

6. The method for evaluating satellite battery capacity degradation as claimed in claim 3, characterized in that: When the discharge amount is corrected, 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 as claimed in claim 6, characterized in that: The least square method is used to fit the curve relationship between the discharge amount and the cut-off voltage.

8. A satellite battery capacity degradation assessment device, characterized in that: include: An acquisition module, used for discharging the satellite battery after being fully charged, and acquiring the discharge capacity of the satellite battery and the corresponding cut-off voltage; A first obtaining module is used 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 used to obtain the discharge cut-off voltage of the 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 programs or instructions that can be run on the processor, and when the programs or instructions are 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.

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 1-7 are implemented.

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