CN115754729A - Low-orbit satellite zinc-nickel storage battery in-orbit service life prediction method - Google Patents
Low-orbit satellite zinc-nickel storage battery in-orbit service life prediction method Download PDFInfo
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Abstract
The embodiment of the disclosure relates to an on-orbit service life prediction method for a zinc-nickel storage battery of a low-orbit satellite. The method comprises the following steps: acquiring characteristic quantity related to the service life of the zinc-nickel storage battery by analyzing on-track actual data in the using process of the zinc-nickel storage battery and combining test data in the development process of the zinc-nickel storage battery; fitting the relation between the characteristic quantity and the service life of the zinc-nickel storage battery based on the test data, and constructing a battery service life model; obtaining a relation constant group of the characteristic quantity and the service life of the zinc-nickel storage battery according to the on-orbit actual data and the relation between the characteristic quantity and the service life of the zinc-nickel storage battery; and obtaining the residual life of the zinc-nickel storage battery according to the battery life model and the relation constant group. According to the method, the embodiment of the disclosure provides a nonlinear function description method, which utilizes on-orbit actual data and test data to obtain the characteristic quantity of the zinc-nickel storage battery, and obtains the relationship between the characteristic quantity and the service life of the zinc-nickel storage battery, so as to provide support for on-orbit management and risk analysis of the zinc-nickel storage battery of a follow-up low-orbit satellite.
Description
Technical Field
The embodiment of the disclosure relates to the technical field of aerospace measurement and control, in particular to an in-orbit service life prediction method for a zinc-nickel storage battery of a low-orbit satellite.
Background
The power system is one of the key subsystems of a satellite system and it assumes the important role of powering the other subsystems of the satellite and the payload. The storage battery is a key product for determining the service life of the satellite, and the development of the storage battery has the remarkable characteristics of small sample size, high service life requirement and the like. With the increasing year-by-year requirements on the service life of low-orbit satellites, the requirements on the service life and the reliability of the products are higher and higher, so that the service life verification and on-orbit service life prediction of the products are more and more difficult.
Generally, a satellite battery is a long-life product, but as the number of charge and discharge cycles increases, the life of the satellite battery is continuously reduced, specifically because: the natural degradation of the storage battery, such as the dissolution of the anode material, the self-discharge process of the storage battery, the formation of an interface film and the like; unexpected influences caused by external complex environments, such as damage to the solar ion storm and cosmic rays; linkage influence caused by the abnormality of other subsystems, human operation errors and the like. It can be seen that, during the charging and discharging process of the satellite storage battery, not only is a simple energy storage device, but also an electrochemical process closely related to the change of various factors such as temperature and the like is involved, which brings about a great obstacle to the prediction of the service life of the satellite storage battery.
Accordingly, there is a need to ameliorate one or more of the problems with the above-mentioned related art solutions.
It is noted that this section is intended to provide a background or context to the disclosure as recited in the claims. The description herein is not admitted to be prior art by inclusion in this section.
Disclosure of Invention
An object of the disclosed embodiments is to provide a method for predicting an on-orbit lifetime of a low-orbit satellite zinc-nickel storage battery, thereby overcoming, at least to some extent, one or more of the problems due to the limitations and disadvantages of the related art.
According to the embodiment of the disclosure, an in-orbit service life prediction method for a zinc-nickel storage battery of a low-orbit satellite is provided, which comprises the following steps:
acquiring characteristic quantity related to the service life of the zinc-nickel storage battery by analyzing on-orbit actual data in the using process of the zinc-nickel storage battery and combining test data in the developing process of the zinc-nickel storage battery;
fitting the relation between the characteristic quantity and the service life of the zinc-nickel storage battery based on the test data, and constructing a battery service life model;
obtaining a relation constant group of the characteristic quantity and the service life of the zinc-nickel storage battery according to the on-orbit actual data and the relation between the characteristic quantity and the service life of the zinc-nickel storage battery;
and obtaining the residual life of the zinc-nickel storage battery according to the battery life model and the relation constant group.
In an embodiment of the present disclosure, the feature amount includes:
the temperature and the depth of discharge of the zinc-nickel storage battery.
In an embodiment of the present disclosure, a relationship between the battery temperature and the service life of the zinc-nickel battery is:
under constant voltage, the service life of the zinc-nickel storage battery is shortened by 50% for every 10 ℃ rise of the temperature of the storage battery.
In an embodiment of the present disclosure, the relationship between the discharge depth and the service life of the zinc-nickel storage battery is:
at constant temperature, the zinc-nickel battery life is an inverse function of the depth of discharge.
In an embodiment of the present disclosure, the formula of the depth of discharge is:
DOD = amp-hour capacity discharged by battery after full charge/rated amp-hour capacity (1)
Wherein DOD is depth of discharge.
In an embodiment of the disclosure, the step of obtaining the remaining life of the zinc-nickel storage battery according to the battery life model and the relationship constant set includes:
substituting the relation constant group into the battery life model to obtain the average cycle number of the zinc-nickel storage battery before the first failure, namely the remaining charge and discharge number of the zinc-nickel storage battery;
obtaining the annual average cycle number of the zinc-nickel storage battery according to the on-orbit actual data;
obtaining the residual life of the zinc-nickel storage battery according to the average cycle number before the first failure and the average cycle number per year;
wherein the set of relational constants includes a first relational constant, a second relational constant, and a third relational constant.
In an embodiment of the present disclosure, the battery life model, that is, the formula of the average cycle number before the first failure, is:
wherein L is the average number of cycles before the first failure, T is the temperature of the battery, D is the DOD short, i.e., depth of discharge, C 1 Is a first relation constant of characteristic quantity and service life of zinc-nickel accumulator, C 2 Is a second relation constant of the characteristic quantity and the service life of the zinc-nickel storage battery, C 3 And E (D) is an average depth of discharge, and E (T) is an average temperature.
In an embodiment of the disclosure, the first relation constant is a fixed value.
In an embodiment of the present disclosure, the formula of the average depth of discharge is:
wherein, t 1 Time at which one deep discharge starts, t 2 The time when the deep discharge is finished.
The technical scheme provided by the embodiment of the disclosure can have the following beneficial effects:
in the embodiment of the disclosure, a nonlinear function description method is provided by the method for predicting the on-orbit service life of the low-orbit satellite zinc-nickel storage battery, the on-orbit actual data and the test data are used for obtaining the characteristic quantity of the zinc-nickel storage battery, and the relation between the characteristic quantity and the service life of the zinc-nickel storage battery is obtained, so that support is provided for the follow-up on-orbit management and risk analysis of the low-orbit satellite zinc-nickel storage battery.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present disclosure and together with the description, serve to explain the principles of the disclosure. It should be apparent that the drawings in the following description are merely examples of the disclosure and that other drawings may be derived by those of ordinary skill in the art without inventive effort.
FIG. 1 is a diagram illustrating steps of a method for predicting the in-orbit life of a zinc-nickel storage battery of a low-orbit satellite in an exemplary embodiment of the disclosure;
fig. 2 shows a graph (two years) of the discharge capacity parameter after trip point removal of a zinc-nickel storage battery of a certain satellite in an exemplary embodiment of the disclosure;
fig. 3 is a graph showing the sampling results of a zinc-nickel accumulator for a low-orbit satellite at a certain temperature in an exemplary embodiment of the present disclosure.
Detailed Description
Example embodiments will now be described more fully with reference to the accompanying drawings. Example embodiments may, however, be embodied in many different forms and should not be construed as limited to the examples set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of example embodiments to those skilled in the art. The described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments.
Furthermore, the drawings are merely schematic illustrations of embodiments of the disclosure and are not necessarily drawn to scale. The same reference numerals in the drawings denote the same or similar parts, and a repetitive description thereof will be omitted. Some of the block diagrams shown in the figures are functional entities and do not necessarily correspond to physically or logically separate entities.
The example embodiment provides a method for predicting the in-orbit service life of a zinc-nickel storage battery of a low-orbit satellite. Referring to fig. 1, the method may include: step S101 to step S104.
Step S101: acquiring characteristic quantity related to the service life of the zinc-nickel storage battery by analyzing on-orbit actual data in the using process of the zinc-nickel storage battery and combining test data in the developing process of the zinc-nickel storage battery;
step S102: fitting the relation between the characteristic quantity and the service life of the zinc-nickel storage battery based on the test data, and constructing a battery service life model;
step S103: obtaining a relation constant group of the characteristic quantity and the service life of the zinc-nickel storage battery according to the on-orbit actual data and the relation between the characteristic quantity and the service life of the zinc-nickel storage battery;
step S104: and obtaining the residual service life of the zinc-nickel storage battery according to the battery service life model and the relation constant group.
Specifically, in step S101, the design service life of the storage battery refers to a theoretical value (the required ambient temperature is 20-25 ℃, and the total discharge capacity does not exceed the rated capacity) under a specific condition, while the actual service life of the storage battery is closely related to the service condition, and factors such as the ambient temperature, the discharge depth, the charge-discharge frequency and the like all have different or even serious influences on the actual service life of the storage battery.
In the process of long-term use of the zinc-nickel storage battery, electrochemical reactions are continuously carried out in the single battery, and the electrochemical reactions can cause the phenomena of zinc migration, nickel electrode expansion, diaphragm oxidation degradation, reduction of the electrochemical activity of electrode active materials and the like in the single zinc-nickel storage battery, so that the charging voltage of the zinc-nickel storage battery is increased, the discharging voltage is reduced, the capacity of the zinc-nickel storage battery is reduced, the performance of the zinc-nickel storage battery is reduced, and the zinc-nickel storage battery completely loses the working capacity under severe conditions.
By consulting a large amount of relevant documents and analyzing the failure mechanism of the zinc-nickel storage battery, and combining test data and on-track actual data, characteristic quantities influencing the service life of the zinc-nickel storage battery are obtained through analysis. The characteristic quantities which influence the service life of the zinc-nickel storage battery are analyzed in the disclosure and are the temperature and the depth of discharge of the storage battery.
The relationship between the characteristic quantity and the service life of the zinc-nickel storage battery is fitted through step S102, and a battery service life model is constructed.
The influence of the storage battery temperature on the service life of the zinc-nickel storage battery is analyzed: the high-temperature environment is the main reason that the actual service life of the zinc-nickel storage battery cannot reach the designed service life. When the temperature of the zinc-nickel storage battery rises by 10 ℃, the acceptance of the charging current under the constant voltage is doubled, and the service life of the zinc-nickel storage battery is shortened due to the influence of the increase of the total accumulated electric quantity of the overcharge. At high temperature, the increase of the floating charge current accelerates the accumulation of the over-charge amount, accelerates the corrosion speed of the grid and the generation and escape of hydrogen, accelerates the water loss of the zinc-nickel storage battery, and shortens the service life of the zinc-nickel storage battery. It can be known that the service life of the zinc-nickel storage battery is shortened by 50% under the constant float charge pressure every time the environmental temperature of the zinc-nickel storage battery rises by 10 ℃. The satellite storage battery pack measurement parameters generally include storage battery pack temperature parameters, and storage battery pack temperature parameter data within a certain time can be extracted as data reflecting storage battery temperature characteristic quantities.
The influence of the temperature of the storage battery on the service life of the zinc-nickel storage battery is analyzed: the depth of discharge is measured as the ratio of the actual discharge capacity to the rated discharge capacity at the same discharge rate. The service life of the zinc-nickel storage battery is closely related to the discharge depth of the zinc-nickel storage battery. When the discharge depth is 20%, the service life of the zinc-nickel storage battery can reach 2000 times; when the discharge depth is 100%, the cycle life of the zinc-nickel storage battery is only 350 times, so that the deep discharge of the storage battery is avoided as much as possible in use. When the valve control storage battery pack discharges deeply, the voltage and the capacity of the single battery can be unbalanced, and in order to eliminate the imbalance, the charging voltage must be properly increased to perform equalizing charging. The equalizing charge usually adopts a 'constant voltage current limiting' mode to charge the storage battery. Such charging methods and parameters are mainly determined by the characteristics of the battery. Furthermore, after the storage battery is deeply discharged, "lagging battery" will appear in the battery pack. The more serious the overdischarge is, the less easily the "lagging battery" is recovered in the next charging, which will seriously affect the life of the battery, and in order to avoid the overdischarge, the terminal voltage of the battery must be accurately set according to the difference of the discharge rate.
As previously mentioned, the cycle life of a battery pack is primarily related to the depth of discharge and the battery temperature. The cycle life can be described by setting the number of charge and discharge cycles as independent variables and the depth of discharge and temperature as dependent variables. In constructing a battery life model, a mathematical expression must first be selected to accurately express the relationship between variables, and then a statistical distribution that best fits the test data is selected. The physical characteristics of the battery are also factors to consider when choosing the model, for example, an increase in depth of discharge and an increase in temperature can reduce the cycle life of the battery.
The characteristic quantities of the battery thus identified are the depth of discharge and the battery temperature. The Depth of discharge (DOD) can be expressed as:
DOD = amp-hour capacity/rated amp-hour capacity discharged by battery after full charge (1)
As shown in equation (1), the depth of discharge can be expressed as the discharged amp-hour capacity/rated amp-hour capacity of the battery pack after full charge. After satellite transmission, if no battery pack abnormality occurs, the rated ampere-hour capacity of the battery pack is fixed. The ampere-hour capacity discharged by the fully charged storage battery pack also has a measurement parameter, namely the discharge capacity of the storage battery pack. Therefore, the extraction method of the discharge depth can be obtained by using the discharge capacity parameter data/rated ampere-hour capacity after full charge.
In addition, the cycle life of a battery can be expressed by setting the number of charge and discharge cycles as an independent variable, the depth of discharge, and the battery temperature as a dependent variable. In constructing a battery life model, a mathematical expression must first be selected to accurately express the relationship between variables, and then a statistical distribution that best fits the test data is selected. Other physical characteristics are also factors to consider when choosing a model, for example, increased depth of discharge and increased temperature can reduce the cycle life of the battery. Various types of relationships are commonly used to analyze life test data, where more than one may be consistent with the test data, such as exponential relationships, inverse power relationships, and arrhenius equations. The best agreement between the arrhenius equation and the life test data indicates that electrochemical degradation is the root cause of limiting operating life. Namely:
wherein L is the average cycle number before the first failure, T is the temperature of the storage battery, D is the depth of discharge, C 1 、C 2 、C 3 Relation constant, C, determined by multistage decay curve fitting 1 、C 2 、C 3 The method specifically comprises the following steps: c 1 Is a first relation constant of the characteristic quantity and the service life of the zinc-nickel storage battery, C 2 Is a second relation constant of the characteristic quantity to the service life of the zinc-nickel storage battery, C 3 Is a third relation constant of the characteristic quantity and the service life of the zinc-nickel storage battery.
In step S103, in order to determine the failure model of the Zn-Ni battery of a certain satellite, C is obtained 1 、C 2 、C 3 The parameter value of (2) is to fit a curve according to the test data of the zinc-nickel storage battery and combining with some basic laws of the service life decay of the zinc-nickel storage battery.
In general, C 1 The parameters are obtained from experimental data of the battery, i.e. from test data.
At a given battery temperature, the life of the battery is an inverse function of the depth of discharge, and taking a nickel-hydrogen battery as an example, if the life of the nickel-hydrogen battery at 50% depth of discharge is 100 units, the life of the nickel-hydrogen battery at 25% depth of discharge would be around 200 units; namely:
then:
therefore, the following steps are carried out:
finally, C is obtained 3 ＝4ln2。
Under the general condition (about 10 ℃), the service life of the battery is shortened by 50% under the constant floating voltage charging when the ambient temperature of the storage battery rises by 10 ℃; namely:
then:
when T is 10 ℃:
finally, C is obtained 2 ＝-2ln2。
In step S104, for the battery life model, the above-described formula (4) is mainly directed to the case where the depth of discharge is fixed, and in practical applications, the depth of discharge is different almost every turn, especially for low-earth satellites. Therefore, in order to meet the requirements of practical application, the formula (4) needs to be improved. For low orbit satellites, as long as the sudden problem does not occur, the depth of discharge can be considered to fluctuate within a certain range, and for more accurate simulation of the depth of discharge, the mean value of the depth of discharge and the mean value of the temperature are introduced:
wherein E (D) is the average depth of discharge.
After the average cycle number L before the first failure of the zinc-nickel storage battery, namely the value of the residual charge and discharge number of the zinc-nickel storage battery is obtained through calculation according to the formula (2), the annual average cycle number of the zinc-nickel storage battery is obtained according to on-track actual data, and the residual service life of the zinc-nickel storage battery can be obtained.
By the method for predicting the on-orbit service life of the zinc-nickel storage battery of the low-orbit satellite, a nonlinear function description method is provided, the characteristic quantity of the zinc-nickel storage battery is obtained by using on-orbit actual data and test data, the relation between the characteristic quantity and the service life of the zinc-nickel storage battery is obtained, and support is provided for follow-up on-orbit management and risk analysis of the zinc-nickel storage battery of the low-orbit satellite.
In one embodiment, the characteristic quantities include: the temperature and the depth of discharge of the zinc-nickel storage battery. Specifically, the characteristic quantity influencing the service life of the zinc-nickel storage battery is obtained through looking up a large number of relevant documents and failure mechanism analysis completed on the zinc-nickel storage battery and combining test data and on-orbit actual data. The characteristic quantities which influence the service life of the zinc-nickel storage battery are analyzed in the disclosure and are the temperature and the depth of discharge of the storage battery.
In one embodiment, the battery temperature is related to the zinc-nickel battery life by: under constant voltage, the service life of the zinc-nickel storage battery is shortened by 50% for every 10 ℃ rise of the temperature of the storage battery. Specifically, at high temperature, the increase of the float current accelerates the accumulation of the charging amount, and simultaneously accelerates the corrosion speed of the grid and the generation and escape of hydrogen, and accelerates the water loss of the zinc-nickel storage battery, thereby shortening the service life of the zinc-nickel storage battery. Wherein, the service life of the zinc-nickel storage battery is shortened by 50% under the constant float charging pressure when the environmental temperature of the zinc-nickel storage battery rises by 10 ℃.
In one embodiment, the depth of discharge is related to the life of the zinc-nickel battery by: at constant temperature, the zinc-nickel battery life is an inverse function of the depth of discharge.
Specifically, when the valve-controlled storage battery pack discharges deeply, imbalance may occur in both voltage and capacity of the single battery cells, and in order to eliminate the imbalance, the charging voltage must be increased appropriately to perform equalizing charging. The equalizing charge usually adopts a 'constant voltage current limiting' mode to charge the storage battery. Such charging methods and parameters are mainly determined by the characteristics of the battery. When the discharge depth is 20%, the service life of the zinc-nickel storage battery can reach 2000 times; when the discharge depth is 100%, the cycle life of the zinc-nickel storage battery is only 350 times, so that the deep discharge of the battery is avoided as much as possible in use.
In one embodiment, the formula of the depth of discharge is:
DOD = amp-hour capacity discharged by battery after full charge/rated amp-hour capacity (1)
Wherein DOD is depth of discharge. Specifically, the depth of discharge may be expressed as the amp-hour capacity/rated amp-hour capacity discharged by the battery pack after full charge. After satellite transmission, if no battery pack abnormality occurs, the rated ampere-hour capacity of the battery pack is fixed. And the ampere-hour capacity discharged by the fully charged storage battery pack has a measurement parameter on the track, namely the discharge capacity of the storage battery pack. Therefore, the extraction method of the discharge depth can be obtained by using the discharge capacity parameter data/rated ampere-hour capacity after full charge.
In one embodiment, the step of obtaining the remaining life of the zinc-nickel storage battery according to the battery life model and the set of relation constants includes: substituting the relation constant group into the battery life model to obtain the average cycle number of the zinc-nickel storage battery before the first failure, namely the remaining charge and discharge number of the zinc-nickel storage battery; obtaining the annual average cycle number of the zinc-nickel storage battery according to the on-orbit actual data; obtaining the residual life of the zinc-nickel storage battery according to the average cycle number before the first failure and the average cycle number per year; wherein the set of relational constants includes a first relational constant, a second relational constant, and a third relational constant.
Specifically, the discharge depth calculation and the storage battery temperature calculation are respectively carried out and are brought into a battery life model to obtain the remaining charge and discharge times of the storage battery, so that the remaining life of the storage battery is obtained.
In one embodiment, the battery life model, i.e., the formula for the average number of cycles before first failure, is:
wherein L is the average number of cycles before the first failure, T is the temperature of the battery, D is the DOD short, i.e., depth of discharge, C 1 Is a first relation constant of characteristic quantity and service life of zinc-nickel accumulator, C 2 Is a second relation constant of the characteristic quantity and the service life of the zinc-nickel storage battery, C 3 Is a characteristic quantityAnd E (D) is the average depth of discharge, and E (T) is the average temperature. In particular, increased depth of discharge and increased temperature can reduce the cycle life of the battery. Various types of relationships commonly used to analyze life test data may express such relationships. Of these types of relationships, more than one may fit well with the test data, such as exponential relationships, inverse power relationships, and arrhenius equations. Where the arrhenius equation is best fit with life test data, it indicates that chemical decline is the root cause limiting operating life.
E (D) is the average depth of discharge. Specifically, for a low-earth orbit satellite, as long as a sudden problem does not occur, the depth of discharge can be considered to fluctuate within a certain range, and for more accurately simulating the depth of discharge, the mean value of the depth of discharge and the mean value of the temperature are introduced to obtain a formula (2). And (3) obtaining the average cycle number L before the first failure of the zinc-nickel storage battery, namely the value of the residual charge and discharge number of the zinc-nickel storage battery by calculation according to a formula (2), and then obtaining the annual average cycle number of the zinc-nickel storage battery according to on-orbit actual data to obtain the residual service life of the zinc-nickel storage battery.
In one embodiment, the first relationship constant is a fixed value. In particular, in general, C 1 The parameters are obtained from experimental data of the battery, i.e. from test data.
In one embodiment, the average depth of discharge is formulated as:
wherein, t 1 Time at which one deep discharge starts, t 2 The time when the deep discharge is finished.
Specifically, in the average depth of discharge calculation process, a polynomial fitting method may be adopted for each high-depth discharge peak to obtain a fitting relationship curve f (D) of the high-depth discharge peak, and a formula (3) is adopted for calculating the mean value of the f (D) curve.
The present embodiment is further described below with reference to a specific simulation example.
And (3) calculating the depth of discharge:
the discharge parameters of a certain satellite 2013, 1 month, 1 day, 0.
The satellite orbital period is about 107 minutes, with about 9825 revolutions of data for two years.
As can be seen from fig. 2, the two-year measured values of the discharge capacity parameter of a certain satellite have 9 high-depth discharge peaks, and the middle is a low-depth discharge peak. Since the mean and variance of the two data are different greatly and the depth of discharge of the low depth discharge peak is less than 1%, only the mean of the high depth discharge peak is calculated when calculating the depth of discharge mean. If the depth of discharge of the low discharge peak is not calculated, the corresponding time is reduced when the cycle period is calculated. It was calculated that there were about 941 cycles of undischarged satellite in 2013 (including low depth discharge peak) and about 843 cycles of undischarged satellite in 2014 (same above). For each high-depth discharge peak, a fitting relation curve f (D) of the high-depth discharge peak can be obtained by adopting a polynomial fitting mode, and for the f (D) curve, the mode of calculating the mean value of the f (D) curve is formula (3).
The fitting results are as follows:
the first high-depth discharge peak fitting result is shown as the 1 st high-depth discharge peak in fig. 2, and the second high-depth discharge peak fitting result is shown as the 2 nd high-depth discharge peak in fig. 2.
Obtaining the average value of the depth of discharge of the first high-depth discharge peak according to the formula (2) to be 14.32 percent; the average value of the depth of discharge of the second high-depth discharge peak was found to be 14.25%.
The third high-depth discharge peak fitting result is as the 3 rd high-depth discharge peak in fig. 2, and the fourth high-depth discharge peak fitting result is as the 4 th high-depth discharge peak in fig. 2.
Obtaining the average value of the depth of discharge of the third high-depth discharge peak according to the formula (2) to be 13.5 percent; the average value of the depth of discharge of the fourth high-depth discharge peak was found to be 13.15%.
The fifth high-depth discharge peak fitting result is as the 5 th high-depth discharge peak in fig. 2, and the sixth high-depth discharge peak fitting result is as the 6 th high-depth discharge peak in fig. 2.
Obtaining the average value of the depth of discharge of the fifth high-depth discharge peak according to the formula (2) to be 14.36 percent; the sixth high-depth peak discharge depth was found to be 13.64% on average.
The seventh high-depth discharge peak fitting result is as the 7 th high-depth discharge peak in fig. 2, and the eighth high-depth discharge peak fitting result is as the 8 th high-depth discharge peak in fig. 2.
Obtaining the average value of the depth of discharge of the seventh high-depth discharge peak to be 13.54 percent according to the formula (2); the average value of the depth of discharge of the eighth high-depth discharge peak was found to be 13.32%.
The ninth high-depth discharge peak fitting result is as the 9 th high-depth discharge peak in fig. 2.
The average value of the depth of discharge was 14.43% as determined by the formula (2).
And integrating the calculation results to obtain the discharge depths of the 9 high-depth discharge peaks as follows: 14.32%, 14.25%, 13.5%, 13.15%, 14.36%, 13.64%, 13.54%, 13.32%, 14.43%. The mean value of the depth of discharge in 2013 was 13.81% (2013 for the first four times) and 13.83% for 2014.
Calculating the temperature of the storage battery:
the temperature parameters of the storage battery from 2013, month 1, day 1 and 0.
The average value of the battery temperature at the coordinate point corresponding to the discharge peak value was taken to be 8.83.
Number of charge and discharge times calculation
According to the formula (4), the average cycle number L before the first failure of the zinc-nickel storage battery is calculated to be between 62000 and 59800.
From the above known data, if the orbit period of the satellite is 107 minutes, the satellite has about 4912 cycles per year. According to the non-cycle times of the storage battery for two years, about 4020 cycles of the storage battery between 13.15% and 14.43% of the mean value of the depth of discharge for two years can be known, and the minimum service life of the zinc-nickel low-orbit satellite storage battery which has 30% of the depth of discharge and can be cycled for about 40000 times at the temperature of 10 ℃ can be calculated to be between 14.63 and 15.16 years, which is basically close to the design service life given by a developing party.
In the description of the present specification, reference to the description of "one embodiment," "some embodiments," "an example," "a specific example," or "some examples" or the like means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present disclosure. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples described in this specification can be combined and combined by one skilled in the art.
Other embodiments of the disclosure will be apparent to those skilled in the art from consideration of the specification and practice of the invention disclosed herein. This application is intended to cover any variations, uses, or adaptations of the disclosure following, in general, the principles of the disclosure and including such departures from the present disclosure as come within known or customary practice in the art to which the disclosure pertains. It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the disclosure being indicated by the following claims.
Claims (9)
1. An on-orbit service life prediction method for a zinc-nickel storage battery of a low-orbit satellite is characterized by comprising the following steps:
acquiring characteristic quantity related to the service life of the zinc-nickel storage battery by analyzing on-track actual data in the using process of the zinc-nickel storage battery and combining test data in the development process of the zinc-nickel storage battery;
fitting the relation between the characteristic quantity and the service life of the zinc-nickel storage battery based on the test data, and constructing a battery service life model;
obtaining a relation constant group of the characteristic quantity and the service life of the zinc-nickel storage battery according to the on-orbit actual data and the relation between the characteristic quantity and the service life of the zinc-nickel storage battery;
and obtaining the residual life of the zinc-nickel storage battery according to the battery life model and the relation constant group.
2. The in-orbit service life prediction method for the zinc-nickel storage battery of the low-orbit satellite according to claim 1, wherein the characteristic quantities comprise:
the storage battery temperature and the discharge depth of the zinc-nickel storage battery.
3. The method for predicting the in-orbit service life of the zinc-nickel storage battery of the low-orbit satellite according to claim 2, wherein the relation between the temperature of the storage battery and the service life of the zinc-nickel storage battery is as follows:
under constant voltage, the service life of the zinc-nickel storage battery is shortened by 50% for every 10 ℃ rise of the temperature of the storage battery.
4. The method for predicting the in-orbit service life of the zinc-nickel storage battery of the low-orbit satellite according to claim 2, wherein the relation between the discharge depth and the service life of the zinc-nickel storage battery is as follows:
at constant temperature, the zinc-nickel battery life is an inverse function of the depth of discharge.
5. The in-orbit service life prediction method for the zinc-nickel storage battery of the low-orbit satellite according to claim 2, wherein the formula of the depth of discharge is as follows:
DOD = amp-hour capacity discharged from the battery pack after full charge/rated amp-hour capacity (1) where DOD is the depth of discharge.
6. The in-orbit life prediction method for the zinc-nickel storage battery of the low-orbit satellite according to claim 2, wherein the step of obtaining the remaining life of the zinc-nickel storage battery according to the battery life model and the relation constant set comprises:
substituting the relation constant group into the battery life model to obtain the average cycle number of the zinc-nickel storage battery before the first failure, namely the residual charge and discharge number of the zinc-nickel storage battery;
obtaining the annual average cycle number of the zinc-nickel storage battery according to the on-orbit actual data;
obtaining the residual life of the zinc-nickel storage battery according to the average cycle number before the first failure and the annual average cycle number;
wherein the set of relational constants includes a first relational constant, a second relational constant, and a third relational constant.
7. The method for predicting the in-orbit service life of the zinc-nickel storage battery of the low-orbit satellite according to claim 6, wherein the battery service life model, namely the formula of the average cycle number before the first failure, is as follows:
wherein L is the average number of cycles before the first failure, T is the temperature of the battery, D is the DOD short, i.e., depth of discharge, C 1 Is a first relation constant of the characteristic quantity and the service life of the zinc-nickel storage battery, C 2 Is a second relation constant of the characteristic quantity and the service life of the zinc-nickel storage battery, C 3 And E (D) is an average depth of discharge, and E (T) is an average temperature.
8. The method for predicting the in-orbit service life of the zinc-nickel storage battery of the low-orbit satellite according to claim 7, wherein the first relation constant is a fixed value.
9. The in-orbit service life prediction method for the zinc-nickel storage battery of the low-orbit satellite according to claim 8, wherein the average depth of discharge is represented by the formula:
wherein, t 1 Time of start of one deep discharge, t 2 The time when the deep discharge is finished.
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