Satellite energy system on-orbit quantitative evaluation method and system based on working mode

Abstract

The invention relates to a satellite energy system on-orbit quantitative evaluation method and system based on a working mode, and the method comprises the steps: defining an index weight according to the working mode of a satellite, and constructing a satellite energy system evaluation index system; solving a satellite energy system evaluation index value; preprocessing the index value to obtain a preprocessed index value; and performing comprehensive evaluation by using the preprocessed index value and the index weight coefficient to obtain a comprehensive evaluation value. According to the working mode-based satellite energy system on-orbit quantitative evaluation method provided by the invention, according to different satellite on-orbit working modes, the total energy demand for the satellite energy system in different working modes and the working state of a main energy-consuming single machine in different working modes are considered; according to the method, the state of the energy system is comprehensively evaluated from the two aspects of internal indexes and external single machine operation states, and through long-term evaluation in different working states, state prediction and service life evaluation of the energy system are finally achieved.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite energy system evaluation, and particularly relates to an on-orbit quantitative evaluation method and system for a satellite energy system based on working modes. Background Art

[0002] With the development of spacecraft technology, as the only power supply system for spacecraft in orbit, the spacecraft energy system plays an important role in the lifespan of the spacecraft and its on-orbit working ability (maximum load limit). Currently, for the evaluation method of satellite energy systems, it mainly starts from the compliance of the energy system with system indicators, including whether the battery capacity requirement is met, charging ability, discharging ability, etc. Generally, the evaluation of the energy system is mainly completed on the ground, and the on-orbit energy system evaluation is mainly for on-board real-time energy detection to determine whether the current on-board energy system state meets the requirements of subsequent tasks (tasks to be planned), without proposing a systematic evaluation method for the on-orbit energy system.

[0003] The defects of the current evaluation methods for satellite energy systems are as follows: The first evaluation method cannot evaluate the performance of the energy system based on the on-orbit space environment and at the whole-satellite level; the second evaluation method is trigger-based and short-term, or in other words, for the calculation of real-time energy capabilities, it cannot evaluate the long-term operation of the energy system in the space environment and its sustainability based on different working modes. Summary of the Invention

[0004] In view of some or all of the problems in the prior art, the present invention provides an on-orbit quantitative evaluation method for a satellite energy system based on working modes, which includes the following steps:

[0005] Define index weights according to the working modes of the satellite, and construct an evaluation index system for the satellite energy system;

[0006] Solve the evaluation index values of the satellite energy system;

[0007] Perform preprocessing on the index values to obtain preprocessed index values; and

[0008] Comprehensively evaluate using the preprocessed index values and index weight coefficients to obtain a comprehensive evaluation value.

[0009] Further, the working modes include orbit control mode, attitude adjustment mode, mission mode, and data transmission mode.

[0010] Further, the index weights include level A, level B, and level C, and the index weight coefficients of level A, level B, and level C decrease in sequence;

[0011] The level A index is an internal index of the energy system and is related to the basic functions of the energy system;

[0012] The B-level indicators are internal indicators of the energy system and are related to the important functions of the energy system;

[0013] The C-level indicators are external indicators of the energy system.

[0014] Furthermore, the index system includes internal indicators of the power supply system, orbit control mode indicators, attitude adjustment mode indicators, mission mode indicators, data transmission mode indicators, and long-term internal power supply indicators.

[0015] Furthermore, the index weights or index weight coefficients of the same index in different working modes can be the same or different;

[0016] The indicators include positive indicators and negative indicators.

[0017] Furthermore, solving the evaluation index value of the satellite energy system includes:

[0018] Selecting the corresponding indicators for solution according to the working mode of the satellite.

[0019] Furthermore, during the orbit control mode period, the corresponding indicators include depth of discharge, power generation power, power distribution power, over-discharge protection, solenoid valve switch state, and thruster voltage;

[0020] Among them, the solenoid valve switch state and thruster voltage are telemetry values;

[0021] Depth of discharge = I 1 *T 1 / Q, where I 1 is the discharge current of the battery pack, T 1 is the discharge time of the battery pack, and Q is the rated capacity of the battery pack;

[0022] Power generation power = I 2 *V 2 where I 2 is the array current and V 2 is the power generation voltage;

[0023] Power distribution power = I 3 *V 3 where I 3 is the load current and V 3 is the power distribution voltage;

[0024] In the discharge state, when the voltage of the battery pack is lower than the over-discharge protection threshold V 4 of the battery pack voltage, stop some or all of the payload tasks for over-discharge protection.

[0025] Furthermore, performing preprocessing on the index value, the preprocessed index value includes:

[0026] The preprocessing includes dimensionless normalization and unification processing;

[0027] The obtained index values are dimensionless normalized using the deviation normalization method,

[0028]

[0029] where yi is the index in the set of obtained index values {y 1 , y 2 ,..., yn}, n is the total number of indices, max{yj} is the maximum value in the set of index values {y 1 , y 2 ,..., yn}, min{yj} is the minimum value in the set of index values {y 1 , y 2 ,..., yn}, and both i and j are integers between 1 and n;

[0030] The obtained dimensionless index values {Y 1 , Y 2 ,..., Yn} are subjected to unification processing, and the unification processing includes reciprocal unification or subtraction unification;

[0031] The reciprocal unification is to take the reciprocal of the index value, Xi = 1 / Yi;

[0032] The subtraction unification is,

[0033] Xi = M - Yi

[0034] where M is the maximum value corresponding to the index;

[0035] After preprocessing, the obtained set of index values is {X 1 , X 2 ,..., Xn}, where n is the total number of indices.

[0036] Furthermore, using the preprocessed index values and index weight coefficients for comprehensive evaluation, the obtained comprehensive evaluation value includes:

[0037] The comprehensive evaluation value is calculated using coefficient weighting,

[0038]

[0039] where Pj is the comprehensive evaluation value of the j-th arc segment, wi is the index weight coefficient of the i-th index, Xi is the preprocessed index value of the i-th index, and n is the total number of indices;

[0040] Under the same mode, the overall comprehensive evaluation value P of multiple arc segments is,

[0041]

[0042] Among them, Pm is the comprehensive evaluation value of the m-th arc segment, and m is the total number of arc segments.

[0043] The present invention also provides a system for the on-orbit quantitative evaluation method of the satellite energy system based on the working mode, and this system includes the following modules:

[0044] An index system construction module, configured to define index weights according to the working mode of the satellite and construct an evaluation index system for the satellite energy system;

[0045] An index value solving module, configured to solve the evaluation index values of the satellite energy system;

[0046] A preprocessing module, configured to perform preprocessing on the index values to obtain preprocessed index values; and

[0047] An index evaluation module, configured to perform comprehensive evaluation using the preprocessed index values and index weight coefficients to obtain a comprehensive evaluation value.

[0048] The technical solution provided by the present invention has the following beneficial effects:

[0049] 1. The on-orbit quantitative evaluation method of the satellite energy system based on the working mode provided by the present invention, according to different working modes of the satellite in orbit, considers the total energy demand for the satellite energy system under different working modes and the working states of the main energy-consuming single machines under different working modes, and comprehensively evaluates the state of the energy system from two aspects of internal indexes and external single-machine operation states. Through long-term evaluations under different working states, the state prediction and life evaluation of the energy system are finally achieved.

[0050] 2. The on-orbit quantitative evaluation method of the satellite energy system based on the working mode provided by the present invention, through the evaluation results of the energy systems of different satellites under different working modes, determines which energy system solution is better from the on-orbit performance, and comprehensively obtains the optimal energy system solution, thereby contributing to the optimization of the energy system design.

[0051] 3. The on-orbit quantitative evaluation method of the satellite energy system based on the working mode provided by the present invention monitors the trend of the evaluation results for the same satellite, the same working mode, and different times. If the evaluation results continue to decrease, it indicates that the energy system is entering the decline stage, and the life of the energy system can be predicted according to the decline rate. Description of the Drawings

[0052] To further clarify the above and other advantages and features of the embodiments of the present invention, a more specific description of the embodiments of the present invention will be presented with reference to the accompanying drawings. It can be understood that these drawings only depict typical embodiments of the present invention and thus will not be considered as limiting its scope. In the drawings, for clarity, the same or corresponding components will be denoted by the same or similar reference numerals.

[0053] Figure 1 FIG. shows a schematic flow chart of an on-orbit quantitative evaluation method for a satellite energy system based on a working mode according to an embodiment of the present invention;

[0054] Figure 2 FIG. shows a schematic diagram of an index system setting according to an embodiment of the present invention;

[0055] Figure 3 FIG. shows a schematic diagram of an index evaluation weight setting according to an embodiment of the present invention;

[0056] Figure 4 FIG. shows a schematic diagram of the evaluation results of two satellites according to an embodiment of the present invention; and

[0057] Figure 5 FIG. shows a schematic diagram of an on-orbit quantitative evaluation system for a satellite energy system based on a working mode according to an embodiment of the present invention. Detailed Embodiments

[0058] In the following description, the present invention is described with reference to the embodiments. However, those skilled in the art will recognize that the embodiments can be implemented without one or more specific details or in combination with other alternative and / or additional methods or components. In other cases, well-known structures or operations are not shown or described in detail to avoid obscuring the inventive points of the present invention. Similarly, for the purpose of explanation, specific numbers and configurations are set forth to provide a thorough understanding of the embodiments of the present invention. However, the present invention is not limited to these specific details.

[0059] In this specification, the reference to "an embodiment" or "the embodiment" means that the specific features, structures, or characteristics described in connection with the embodiment are included in at least one embodiment of the present invention. The phrase "in an embodiment" appearing throughout this specification does not necessarily refer to the same embodiment.

[0060] It should be noted that the embodiments of the present invention describe the method steps in a specific order, but this is only for the purpose of illustrating the specific embodiment and not for limiting the order of the steps. On the contrary, in different embodiments of the present invention, the order of the steps can be adjusted according to the actual requirements.

[0061] In the present invention, each module of the system according to the present invention can be implemented using software, hardware, firmware, or a combination thereof. When a module is implemented using software, the functions of the module can be realized through a computer program flow. For example, the module can be implemented through code segments (such as code segments in languages like C, C++) stored in a storage device (such as a hard disk, memory, etc.). When the code segment is executed by a processor, the corresponding functions of the module can be realized. When a module is implemented using hardware, the functions of the module can be realized by setting the corresponding hardware structure. For example, the functions of the module can be realized by hardware programming of a programmable device such as a Field Programmable Gate Array (FPGA), or by designing an Application Specific Integrated Circuit (ASIC) including multiple electronic devices such as transistors, resistors, and capacitors. When a module is implemented using firmware, the functions of the module can be written in a read-only memory such as an EPROM or EEPROM of the device in the form of program code, and when the program code is executed by a processor, the corresponding functions of the module can be realized. Additionally, certain functions of the module may need to be implemented by separate hardware or in cooperation with the hardware. For example, the detection function is realized through corresponding sensors (such as proximity sensors, acceleration sensors, gyroscopes, etc.), the signal emission function is realized through corresponding communication devices (such as Bluetooth devices, infrared communication devices, baseband communication devices, Wi-Fi communication devices, etc.), the output function is realized through corresponding output devices (such as displays, speakers, etc.), and so on.

[0062] Aiming at the defects of the existing energy system assessment, the present invention proposes a method for on-orbit quantitative assessment of a satellite energy system based on working modes. According to different working modes of the satellite in orbit, considering the total energy requirements for the satellite energy system under different working modes and the working states of the main energy-consuming single machines under different working modes, a comprehensive assessment of the energy system state is carried out from two aspects: internal indicators and the operating states of external single machines. Through long-term assessments under different working states, the state prediction and life assessment of the energy system are ultimately achieved.

[0063] The following clearly and completely describes the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention.

[0064] Figure 1 The flowchart of the method for on-orbit quantitative assessment of a satellite energy system based on working modes according to an embodiment of the present invention is shown. As Figure 1 shown, the method for on-orbit quantitative assessment of a satellite energy system based on working modes includes the following steps:

[0065] First, according to the satellite's working mode, the indicator weights are defined and the satellite energy system evaluation indicator system is constructed. The evaluation of the satellite energy system should take into account the different working modes of the satellite, including orbit control mode, attitude adjustment mode, mission mode and data transmission mode. Different working modes have different requirements for the energy system. The evaluation of the energy system should consider the state performance of the energy system under different requirements.

[0066] The satellite energy system evaluation index system consists of two parts: the internal index system of the energy system and the index system corresponding to the on-orbit working mode. This method should be based on the detailed sorting of the satellite energy index system. In different working modes, the indicators for assessing the satellite energy system are slightly different. For example, in mission mode, the load current needs to be considered, while in standby mode, this item does not need to be assessed. The weight of the same indicator in different working modes will also be different. For example, in the load mission mode, the weight of the energy system distribution power indicator is higher, while in the standby mode, the weight of the charging capacity indicator is higher.

[0067] Figure 2 FIG. 2 shows a schematic diagram of an indicator system setting of an embodiment of the present invention. Figure 2 As shown, the indicator system based on different modes, i.e. different scenarios, includes internal indicators of the power supply system, orbit control mode indicators, attitude adjustment mode indicators, mission mode indicators, data transmission mode indicators and internal long-term indicators of the power supply.

[0068] The indicator combing table template is shown in Table 1. The indicator weight configuration principle is formulated. For example, the indicator weight is divided into three levels: A, B, and C. Among them, the A-level weight is the highest level weight, and its coefficient is the highest when conducting a comprehensive evaluation of multiple indicators. The C-level weight is the lowest level weight. Indicators include positive indicators and negative indicators.

[0069] Table 1 Index sorting table template

[0070]

[0071]

[0072] The indicator weight setting table template is shown in Table 2. Class A indicators are internal indicators of the energy system and are related to the basic functions of the energy system; Class B indicators are internal indicators of the energy system and are related to the important functions of the energy system; Class C indicators are external indicators of the energy system. As shown in Table 2, the indicator weight level can also include levels other than Class A, Class B and Class C. The indicator weight coefficient of each level can be configured later, and the indicator level of each indicator in the indicator system can be adjusted later.

[0073] Table 2 Index weight setting table template

[0074]

[0075] Table 3 shows the indicator weight setting of an embodiment, where the weight coefficient of the A-level indicator is 0.6, the weight coefficient of the B-level indicator is 0.3, and the weight coefficient of the C-level indicator is 0.1.

[0076] Table 3 Index weights

[0077]

[0078]

[0079] According to the characteristics of the satellite system to be evaluated, including the satellite's on-orbit working mode, the assessment indicators under different working modes and the importance of each assessment indicator, an assessment indicator system for the satellite is established. Table 4 shows the on-orbit capability assessment indicator system for a satellite energy system.

[0080] Table 4 In-orbit capability assessment index system for a satellite energy system

[0081]

[0082]

[0083] Next, solve the satellite energy system evaluation index value. According to the satellite's working mode, select the corresponding index for solution. According to the working mode to be evaluated, select the corresponding index in sections. For example, select the orbit mode period (ti~tj). According to the index system table of this satellite, the corresponding index is the internal index of the power system and the orbit control mode index, a total of 6 indexes, including discharge depth, power generation, distribution power, over-discharge protection, solenoid valve switch state and thruster voltage. After determining the index, solve and pre-process the 6 indexes, among which the solenoid valve switch state and thruster voltage are telemetry values, and other indexes need to be solved according to other telemetry values. The solution method is obtained according to the actual definition of the satellite telemetry and the solution method of each quantity. For example, according to the actual situation of a certain model, the solution methods of the four indicators of satellite discharge depth, power generation, distribution power and over-discharge protection are as follows.

[0084] The depth of discharge is the ratio of the discharge capacity of the battery pack to the rated capacity. 1 *T 1 / Q, where I 1 is the battery pack discharge current, T 1 is the battery discharge time, Q is the rated capacity of the battery. The current capacity of the battery and the battery voltage are also measured remotely. At the same discharge depth, the battery voltage decreases, indicating that the battery capacity has declined.

[0085] The power generation is the efficiency of converting solar energy into electrical energy by the solar array in the on-orbit state. Power generation = I 2 *V 2 , where I 2 is the array current and V 2 is the power generation voltage. In the on-orbit state, the change of the array current I is mainly affected by two aspects. One is the influence of the sun's revolution. The output power of the array is the largest on the winter solstice every year, the smallest on the summer solstice, and the same on the spring equinox and the autumn equinox. The other is the change over time. The degradation of the solar cells themselves causes the array current to decrease. By evaluating the change of the array current on the same day of each year and performing linear fitting on the data, the change of the power generation of the solar array can be evaluated.

[0086] The distribution power is the ability of the power supply system to support the load power and can reflect the current power distribution of the power supply system in real time. Distribution power = I 3 *V 3 , where I 3 is the load current and V 3 is the distribution voltage.

[0087] The entire satellite's partial or even all payload missions cannot work properly due to over-discharge of the battery pack. In the discharge state, when the voltage of the battery pack is lower than the over-discharge protection threshold V 4 of the battery pack, the over-discharge protection of some or all payload missions is stopped, giving priority to ensuring the functions of the satellite platform and ensuring that the battery can be replenished during the illumination period. To prevent irreversible damage to the battery due to over-discharge of the battery pack. Entering the over-discharge protection mode under normal tasks indicates that the entire satellite's energy system can no longer meet the current payload mission requirements, and there is an obvious degradation of the energy system in orbit.

[0088] Through the above calculation method, an index set {y 1 , y 2 ,..., y 6} containing 6 indexes is obtained, and then index preprocessing is performed on the index set.

[0089] Next, preprocessing is performed on the index values to obtain the preprocessed index values. The preprocessing includes dimensionless and normalization processing.

[0090] Since the final evaluation result is a comprehensive state evaluation, it will involve indexes with different dimensions and directions. For example, the unit of power generation is W, while the unit of battery capacity is Ah. The dimension should be unified first when performing result synthesis; for example, the larger the power generation, the better, while the smaller the degradation of the battery capacity, the better. When making the comprehensive result of the indexes, the directionality of the indexes for the final scoring should be considered.

[0091] Dimensionality reduction is to scale each index data proportionally and fall into a small specific range to remove the unit limitation of the data. Min-Max normalization, also known as deviation normalization method, is the simplest method to eliminate the influence of variable dimension and variation range. For the linear transformation of the original data, the result falls into the interval [0, 1], and the conversion method is as follows.

[0092]

[0093] Among them, yi is the index in the set of index values {y 1 , y 2 ,..., yn} obtained by solving, n is the total number of indexes, max{yj} is the maximum value in the set of index values {y 1 , y 2 ,..., yn}, min{yj} is the minimum value in the set of index values {y 1 , y 2 ,..., yn}, and both i and j are integers between 1 and n.

[0094] For the index with a negative index direction, that is, the smaller the index, the better. Perform the consistency processing on the set of index values {Y 1 , Y 2 ,..., Yn} obtained by dimensionality reduction. The consistency processing includes reciprocal consistency or subtraction consistency.

[0095] The reciprocal consistency is to take the reciprocal of the index value, Xi = 1 / Yi;

[0096] The subtraction consistency is,

[0097] Xi = M - Yi

[0098] Among them, M is the maximum value corresponding to the index; for example, for the depth of discharge index, the maximum allowable depth of discharge is 60%, then M is 60%.

[0099] After preprocessing, the obtained set of index values is {X 1 , X 2 ,..., Xn}, where n is the total number of indexes.

[0100] Finally, use the preprocessed index values and index weight coefficients for comprehensive evaluation to obtain the comprehensive evaluation value.

[0101] According to the index weight determination principle and the design of the initial weight coefficient, the corresponding table for comprehensive evaluation in the orbit control mode is obtained. Among them, the index weight is a configurable item. First, read the interface configuration parameters. If there are no configuration parameters, use the initialization parameters, as shown in Table 5.

[0102] Table 5 Corresponding table for comprehensive evaluation

[0103]

[0104] The comprehensive evaluation value during the period of the orbit control mode ti to tj is calculated by weighting the usage factor.

[0105]

[0106] Among them, Pj is the comprehensive evaluation value of the j-th arc segment, wi is the index weight coefficient of the i-th index, Xi is the value of the i-th preprocessed index, and n is the total number of indexes.

[0107] Multiple orbit control arc segments (telemetry data of multiple orbit controls) can be selected, and the energy system status of multiple arc segments is statistically analyzed by this method. Under the same mode, the overall comprehensive evaluation value P of multiple arc segments is

[0108]

[0109] Among them, Pm is the comprehensive evaluation value of the m-th arc segment, and m is the total number of arc segments.

[0110] If the comprehensive evaluation result of arc segment 1 of satellite A is Pa1, the comprehensive evaluation result of arc segment 2 is Pa2, and so on, and the comprehensive evaluation result of arc segment n is Pan, then the evaluation result of the energy system under the orbit control mode of this satellite is:

[0111] Pa = (Pa1 + Pa2 +...... + Pan) / n

[0112] The comprehensive evaluation result of arc segment 1 of satellite B is Pb1, the comprehensive evaluation result of arc segment 2 is Pb2, and so on, and the comprehensive evaluation result of arc segment n is Pbn, then the evaluation result of the energy system under the orbit control mode of this satellite is:

[0113] Pb = (Pb1 + Pb2 + …… + Pbn) / n

[0114] If Pa > Pb, it means that for the selected index system, the weights defined for each index, and the selected evaluation arc segments this time, the energy state of satellite A is better than that of satellite B. Therefore, it can be determined that the energy system solution of satellite A is better than that of satellite B.

[0115] The effect of the present invention can be further illustrated by the following application examples. For example, arbitrarily select two satellites, satellite 01 and satellite 15, of a constellation system, and the evaluation weights are set as Figure 3 shown. Select the telemetry data during a period of time (from 0:26:50 on May 7, 2021 to 0:28:25 on May 7, 2021) when the working mode is the mission mode, and evaluate the energy system status of the two satellites under this mission mode. The evaluation results are as Figure 4As shown. Through real-time evaluation results, the evaluation results of the energy systems of the two satellites corresponding to each time point can be obtained. Through the overall evaluation results, the evaluation value of Satellite 01 in this time period and this working mode is 1.093, and the evaluation value of Satellite 15 in this time period and this working mode is 1.086. It can be seen that in this time period task mode, the energy system of Satellite 01 is better than that of Satellite 15.

[0116] The on-orbit quantitative evaluation method for satellite energy systems based on working modes provided by the present invention, according to different working modes of the satellite on orbit, considers the total energy requirements for the satellite energy system under different working modes and the working states of the main energy-consuming single machines under different working modes, and comprehensively evaluates the state of the energy system from two aspects: internal indicators and external single machine operating states. Through long-term evaluations under different working states, the state prediction and life evaluation of the energy system are finally achieved; through the evaluation results of the energy systems of different satellites under different working modes, it is confirmed which energy system solution is better from the on-orbit performance, and the optimal energy system solution is comprehensively obtained, which helps to optimize the energy system design; for the evaluation result trends of the same satellite, the same working mode, and different times, if the evaluation results continue to decrease, it indicates that the energy system is entering the decline stage, and the energy system life can be predicted according to the decline rate.

[0117] The present invention also provides an on-orbit quantitative evaluation system for satellite energy systems based on working modes. Figure 5 shows a schematic diagram of an on-orbit quantitative evaluation system for satellite energy systems based on working modes according to an embodiment of the present invention. As Figure 5 shown, the system includes the following modules:

[0118] An index system construction module, configured to define index weights according to the working mode of the satellite and construct an evaluation index system for the satellite energy system;

[0119] An index value solving module, configured to solve the evaluation index values of the satellite energy system;

[0120] A preprocessing module, configured to perform preprocessing on the index values to obtain preprocessed index values; and

[0121] An index evaluation module, configured to comprehensively evaluate using the preprocessed index values and index weight coefficients to obtain a comprehensive evaluation value.

[0122] Although the embodiments of the present invention have been described above, it should be understood that they are presented by way of example only and not as a limitation. It will be apparent to those skilled in the relevant art that various combinations, modifications and changes can be made thereto without departing from the spirit and scope of the present invention. Therefore, the breadth and scope of the present invention disclosed herein should not be limited by the exemplary embodiments disclosed above, but should be defined only by the technical solution of the present invention and its equivalent replacements.

Claims

1. A method for quantitative evaluation of satellite energy system on orbit based on working mode, characterized in that: The steps include: According to the satellite's working mode, define the indicator weights and build a satellite energy system evaluation indicator system; Solve the satellite energy system evaluation index values; Performing preprocessing on the indicator value to obtain a preprocessed indicator value; as well as A comprehensive evaluation is performed using the preprocessed index values ​​and index weight coefficients to obtain a comprehensive evaluation value.

2. The on-orbit quantitative evaluation method of a satellite energy system based on working mode according to claim 1 is characterized in that: The working modes include track control mode, attitude adjustment mode, mission mode and data transmission mode.

3. The on-orbit quantitative evaluation method of a satellite energy system based on working mode according to claim 1 is characterized in that: The indicator weights include A, B and C, and the indicator weight coefficients of A, B and C decrease in sequence; Level A indicators are internal indicators of the energy system and are related to the basic functions of the energy system; Class B indicators are internal indicators of the energy system and are related to important functions of the energy system; Level C indicators are external indicators of the energy system.

4. The on-orbit quantitative evaluation method of a satellite energy system based on working mode according to claim 1 is characterized in that: The indicator system includes internal indicators of the power supply system, orbit control mode indicators, attitude adjustment mode indicators, mission mode indicators, data transmission mode indicators and internal long-term indicators of the power supply.

5. The on-orbit quantitative evaluation method of a satellite energy system based on working mode according to any one of claims 2 to 4, characterized in that: The indicator weight or indicator weight coefficient of the same indicator in different working modes is the same or different; Indicators include positive indicators and negative indicators.

6. The on-orbit quantitative evaluation method of a satellite energy system based on working mode according to claim 1 is characterized in that: Solving the satellite energy system evaluation index values ​​includes: According to the working mode of the satellite, the corresponding indicators are selected for solution.

7. The on-orbit quantitative evaluation method of a satellite energy system based on working mode according to claim 6 is characterized in that: During the orbit control mode period, the corresponding indicators include discharge depth, power generation, distribution power, over-discharge protection, solenoid valve switch status and thruster voltage; Among them, the solenoid valve switch status and thruster voltage are telemetry values; Discharge depth = I1*T1 / Q, where I1 is the battery pack discharge current, T1 is the battery pack discharge time, and Q is the battery pack rated capacity; Generated power = I2*V2, where I2 is the array current and V2 is the generated voltage; Distribution power = I3*V3, where I3 is the load current and V3 is the distribution voltage; In the discharge state, when the battery pack voltage is lower than the battery pack voltage over-discharge protection threshold V4, part or all of the load task over-discharge protection is stopped.

8. The on-orbit quantitative evaluation method of a satellite energy system based on working mode according to claim 1 is characterized in that: Preprocessing is performed on the indicator value to obtain the preprocessed indicator value including: Preprocessing includes dimensionless and uniform processing; The deviation standardization method is used to perform dimensionless transformation on the obtained index values. Among them, y i The index value set {y1,y2,...,y n }, n is the total number of indicators, max{y j } is the indicator value set {y1,y2,...,y n }, min{y j } is the indicator value set {y1,y2,...,y n }, i and j are both integers between 1 and n; The dimensionless index values ​​{Y1,Y2,...,Y n }Performing a uniformization process, wherein the uniformization process includes a reciprocal uniformization or a subtractive uniformization; The reciprocal is unified as the reciprocal of the index value, X i =1 / Y i ; Subtraction is consistent with, X i =M-Y i Among them, M is the maximum value corresponding to the indicator; After preprocessing, the obtained index value set is {X1,X2,...,X n }, where n is the total number of indicators.

9. The on-orbit quantitative evaluation method of a satellite energy system based on working mode according to claim 1 is characterized in that: The comprehensive evaluation using the pre-processed index values ​​and index weight coefficients is as follows: The comprehensive evaluation value is obtained by weighted calculation using coefficients. Among them, P j is the comprehensive evaluation value of the jth arc segment, w i is the indicator weight coefficient of the i-th indicator, X i is the index value after the i-th preprocessing, and n is the total number of indicators; In the same mode, the overall comprehensive evaluation value P of multiple arc segments is, Among them, P m is the comprehensive evaluation value of the mth arc segment, and m is the total number of arc segments.

10. A system for the on-orbit quantitative evaluation method of a satellite energy system based on working mode according to any one of claims 1 to 9, characterized in that: Includes the following modules: The indicator system construction module is configured to define indicator weights according to the satellite's working mode and construct a satellite energy system evaluation indicator system; An index value solving module is configured to solve the satellite energy system evaluation index value; A preprocessing module is configured to perform preprocessing on the indicator value to obtain a preprocessed indicator value; as well as The indicator evaluation module is configured to use the preprocessed indicator value and the indicator weight coefficient for comprehensive evaluation to obtain a comprehensive evaluation value.

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