Spacecraft test energy adaptive control system

Abstract

The application relates to a spacecraft test energy adaptive control system, which comprises a telemetry subscription and processing unit, a ground power energy list is obtained by telemetry data, the bus and load working conditions of a spacecraft, and the charging and discharging conditions of a storage battery; the ground power energy list contains the volt-ampere characteristics and the maximum power supply current of a corresponding ground power system under each typical working condition; a data analysis and statistics unit, based on a second-order RC circuit model and a storage battery state of charge calculation model, adopts an extended Kalman filter algorithm to calculate the state of charge SOC of the storage battery; an energy planning unit compares the output voltage U bat of the storage battery with preset charging cutoff voltage U GC and discharging cutoff voltage U GF , and distributes energy to each ground power source according to the state of charge SOC of the storage battery; and an energy management unit performs equalization control on each storage battery monomer according to the state of charge and the monomer voltage dispersion.

Description

TECHNICAL FIELD

[0001] The present application relates to a spacecraft test energy adaptive control system, belonging to the technical field of spacecraft comprehensive testing, especially for the spacecraft load fast changing speed, large range power ground test platform and test method. BACKGROUND

[0002] In the traditional spacecraft test process, the energy adjustment mode of the whole satellite is to supply energy according to the actual load demand by manually selecting the specific volt-ampere curve of the spacecraft under the typical working condition to meet the energy safety under different test conditions.

[0003] But with the rapid development of space technology, the number of concurrent models is large, the comprehensive test cycle is short, the cost constraint is strong, and the safety and reliability of the power supply and distribution system test are put forward higher requirements. The original energy adjustment mode needs to manually evaluate the ground power supply capacity and the whole satellite load situation, and dynamically select the appropriate volt-ampere curve to meet the power distribution of the whole system. This method needs to pay close attention to the working condition of the spacecraft for manual adjustment, which greatly reduces the test efficiency, and lacks real-time evaluation means for the use of spacecraft energy, including battery state of charge, ground power supply capacity, spacecraft load power consumption, etc., which is difficult to realize intelligent management of energy in the model test process. SUMMARY

[0004] The technical problem solved by the present application is that the traditional mode uses manual adjustment of spacecraft test energy supply capacity, and provides a spacecraft test energy adaptive control system, which can effectively carry out load power consumption analysis in the whole cycle of spacecraft test process while releasing human resources, and realizes intelligent energy management.

[0005] The technical problem solving scheme of the present application is: a spacecraft test energy adaptive control system, the system comprises a telemetry subscription and processing unit, a data analysis and statistics unit, an energy planning unit and an energy management unit.

[0006] The telemetry subscription and processing unit is connected with the spacecraft general control test system, subscribes to the telemetry data of the ground power supply and the spacecraft general control test system, obtains the bus and load working condition of the spacecraft, the charging and discharging condition of the battery through the telemetry data, and calculates the energy list of the ground power supply; the energy list of the ground power supply contains the volt-ampere characteristics and the maximum power supply current of the corresponding ground power supply system under each typical working condition;

[0007] The data analysis and statistics unit constructs a second-order RC circuit model of the battery, establishes a calculation model of the state of charge of the battery by using the ampere-hour integral method, and calculates the state of charge SOC of the battery based on the second-order RC circuit model and the calculation model of the state of charge of the battery by using an extended Kalman filter algorithm.

[0008] The energy planning unit compares the output voltage U bat of the battery with preset charging cutoff voltage U GC and discharging cutoff voltage U GF . bat If U GC > U bat , the ground power supply is prohibited from outputting and a warning is given; if U GF <U mp , the ground power supply selects the voltage-current characteristic corresponding to the maximum power supply current in the energy source list to output and gives a warning; otherwise, the ground power supply is distributed according to the state of charge SOC of the battery.

[0009] The energy management unit disables the equalization management function and stops all equalization actions if the battery is in a charging and discharging state, and enables the equalization management function and controls the battery cells according to the state of charge of the battery and the dispersion of the cell voltage.

[0010] Preferably, the spacecraft test energy adaptive control system is time-synchronized with a spacecraft general control test system.

[0011] Preferably, the telemetry data includes running time t, voltage U mp and current I mp of the maximum operating point of the ground power supply, bus voltage U bus and total load current I bus of the spacecraft, cell voltage of the battery, output voltage U bat of the battery, charging and discharging current I bat of the battery, and charging voltage level setting value U set of the battery.

[0012] Preferably, the maximum power supply capacity of the corresponding ground power supply equipment under each typical working condition is obtained by the following method:

[0013] The maximum operating point voltage of all ground power supplies under different typical working conditions is compared with the bus voltage of the spacecraft, and the maximum operating point current of the ground power supply higher than the bus voltage is accumulated, so that the maximum power supply current of the corresponding ground power supply under different typical working conditions is obtained.

[0014] Preferably, the second-order RC circuit model of the battery includes resistors R0, R b , R p , and capacitors C b , Cp , an equivalent power supply;

[0015] resistor R b and capacitor C b are connected in parallel to form a first RC parallel circuit; resistor R p and capacitor C p are connected in parallel to form a second RC parallel circuit; one end of resistor R0 of the equivalent power supply is connected to resistor R0, the other end of resistor R0 is connected in series with the first RC parallel circuit and the second RC parallel circuit, the output end of the second RC parallel circuit is the positive electrode of the battery end voltage, and the negative electrode of the equivalent power supply is the negative electrode of the battery end voltage.

[0016] Preferably, the R b and C b values are the double-layer capacitance and resistance of the battery; R p and C p values are the internal diffusion capacitance and resistance of the battery.

[0017] Preferably, the state of charge SOC of the battery is calculated by the following formula:

[0018]

[0019] wherein Q n is the rated capacity of the battery, I bat is the charging and discharging current of the battery, η is the charging and discharging rate, Δt is the calculation period, SOC k is the state of charge of the battery in the kth calculation period, and SOC k+1 is the state of charge of the battery in the k+1th calculation period.

[0020] Preferably, the state quantity of the Kalman filter equation is:

[0021] The state quantity is: [SOC U b U p ] T

[0022] The state equation is:

[0023]

[0024] The input quantity is: I bat

[0025] The observation quantity is: U bat

[0026] The observation equation is:

[0027]

[0028] wherein SOC is the state of charge of the battery, and Ts U is the battery terminal voltage; U bat U is the battery terminal voltage; U OC U is the battery terminal voltage; U b U is the battery terminal voltage; U p U is the battery terminal voltage; U b R is the resistance of the resistor R b C is the capacitance of the capacitor C b R is the resistance of the resistor R b C is the capacitance of the capacitor C p R is the resistance of the resistor R p C is the capacitance of the capacitor C p R is the resistance of the resistor R p C is the capacitance of the capacitor C bat U is the output voltage of the battery; I bat I is the charge and discharge current of the battery; k and k+1 represent the kth and k+1th calculation periods, respectively; Q n Q is the nominal capacity of the battery.

[0029] Preferably, the energy management method is:

[0030] The average total current I bus of the load in a preset time period before the current time is calculated. bus When the current state of charge SOC of the battery is greater than 1.05, the ground power system selects the maximum power supply current corresponding to the voltage-current characteristic curve that is lower than I bus from the maximum power supply capability list, and if it does not exist, the ground power supply is prohibited from outputting and a warning is given.

[0031] Preferably, the spacecraft sets an equalization switch for each battery monomer, and the equalization switch is turned on when the battery output voltage is unchanged, and the equalization switch is turned on when the battery monomer output voltage is reduced; the state of the equalization switch of the battery monomer is obtained through telemetry data acquisition;

[0032] The equalization method is: monitoring all valid battery monomer voltages, selecting the lowest voltage monomer in the battery, and when the voltage difference between other monomers and the lowest voltage is greater than a first threshold U JHK , if the number of battery monomers with the equalization switch turned on is ≤N MAX , the equalization switch of the battery monomer with higher output voltage is turned on, and the number of monomers with the equalization switch turned on is increased by 1; when the voltage difference between the monomer with the equalization switch turned on and the lowest monomer is less than a second threshold U JHGWhen the number of battery monomers with the equalization switch turned on is greater than or equal to 0, the equalization switch of the battery monomer with a lower output voltage is turned off, the number of battery monomers with the equalization switch turned on is reduced by 1, and N MAX is the total number of battery monomers.

[0033] Compared with the prior art, the present application has the following beneficial effects:

[0034] (1) The spacecraft test energy adaptive control system provided by the present application establishes a communication interface with the general control test system, and realizes real-time calculation of the current ground energy list, spacecraft load working condition and battery state of charge based on real-time satellite-ground telemetry information, and realizes autonomous control of the satellite-ground energy flow direction by using a spacecraft energy management technology based on multi-criteria definition.

[0035] (2) According to the battery state of charge and the monomer voltage dispersion, the control of the equalization instruction can be autonomously completed, and the service life of the spacecraft battery pack is improved.

[0036] (3) The entire system not only can reduce the labor cost and realize energy adaptation in the spacecraft test process, but also can complete autonomous management of the battery and improve the efficiency of the spacecraft comprehensive test and the ability of the automatic test. BRIEF DESCRIPTION OF DRAWINGS

[0037] Figure 1 is a platform architecture diagram of the spacecraft test energy adaptive control system of the embodiment of the present application;

[0038] Figure 2 is a double-RC battery equivalent circuit model diagram of the embodiment of the present application;

[0039] Figure 3 is a spacecraft energy management flowchart based on multi-criteria definition of the embodiment of the present application. DETAILED DESCRIPTION

[0040] The present application will be further described below in conjunction with the embodiments.

[0041] The technical solutions in the embodiments of the present application will be described clearly and completely below in conjunction with the drawings of the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.

[0042] In order to overcome the situation of manual adjustment of the power supply curve by relying on manual interpretation in the spacecraft comprehensive test process, the present application provides a spacecraft test energy adaptive control system to analyze, count and manage the energy flow direction of the entire system, and realize adaptive adjustment of the energy in the type test process.

[0043] The spacecraft test energy adaptive control system is composed of ① telemetry subscription and processing unit, ② data analysis and statistical unit, and ③ energy planning and management unit.

[0044] The ① telemetry subscription and processing unit is connected with the spacecraft general control test system through TCP / IP protocol, subscribes to the telemetry data of the ground power supply and the spacecraft general control test system, obtains the bus and load working conditions of the spacecraft and the charging and discharging conditions of the storage battery through the telemetry data, and statistically calculates the energy list of the ground power supply; the energy list of the ground power supply contains the voltage-current characteristics and the maximum power supply current of the corresponding ground power supply system under each typical working condition.

[0045] The ② data analysis and statistical unit constructs a second-order RC circuit model of the storage battery, establishes a calculation model of the state of charge (SOC) of the storage battery by using the ampere-hour integral method, and calculates the SOC of the storage battery based on the second-order RC circuit model and the calculation model of the SOC of the storage battery by using the Extended Kalman Filter (EKF) algorithm. However, the accuracy of this method is based on the accurate measurement of the battery current. In order to obtain high estimation accuracy using this method, it is necessary to ensure high current measurement accuracy. Therefore, according to the characteristics of the spacecraft comprehensive test, calibration measures are added to eliminate the influence of cumulative errors on the estimation of the SOC of the storage battery.

[0046] The ③ energy planning and management unit adopts a spacecraft energy management technology based on multi-criteria definition, plans and manages the use of the ground energy curve according to the current ground energy list, spacecraft load working conditions, and SOC of the storage battery, and completes the equalization control according to the SOC of the storage battery and the dispersion of single battery voltage.

[0047] The energy planning and management unit includes an energy planning unit and an energy management unit.

[0048] The energy planning unit compares the output voltage U bat of the storage battery with the preset charging cutoff voltage U GC and the discharge cutoff voltage U GF , and if U bat > U GC , the ground power supply is prohibited from outputting and a warning is given, if U bat <U GF , the ground power supply selects the voltage-current characteristic corresponding to the maximum power supply current in the energy list to output and gives a warning; otherwise, the ground power supply is distributed according to the SOC of the storage battery.

[0049] The energy management unit, if the battery is in the charging and discharging state, disables the equalization management function, stops all equalization actions, otherwise enables the equalization management function, and controls the battery monomer according to the battery state of charge and the monomer voltage dispersion.

[0050] By this design, the spacecraft test energy adaptive control system is time-synchronized with the whole satellite, the actual working state of the ground power supply is judged through the telemetry data between the satellite and the ground, and the adaptive control of the energy in the comprehensive test stage and the equalization control of the spacecraft battery pack are realized.

[0051] The core idea of the present application is that the power supply capacity of the ground power supply, the bus system of the spacecraft, the load working condition, the charging and discharging condition of the battery and other data are taken as the external input of the spacecraft test energy adaptive control system, and are respectively brought into ① telemetry subscription and processing unit, ② data analysis and statistics unit, ③ energy planning and management unit for simulation calculation, to calculate the current ground energy list, spacecraft load working condition, battery state of charge and monomer voltage dispersion, realize the adaptive management of the spacecraft test energy and the autonomous equalization control of the battery pack.

[0052] The implementation process of the present application will be described in detail below, and the present application provides an energy flow management design for spacecraft comprehensive test, as shown in Figure 1 The spacecraft test energy adaptive control system is constructed, and specifically includes the following steps:

[0053] (1) The spacecraft energy adaptive control system is built using the labview platform, and the telemetry parameter subscription configuration is performed in the background, including the spacecraft time, the bus and load working condition of the spacecraft, the working state of the battery, etc., the TCP / IP protocol is used to establish a connection with the spacecraft general control test system, and the data acquisition of the corresponding telemetry code is completed through the RTS data service interface.

[0054] (2) Obtain the original telemetry data, the original telemetry data includes the real-time running time t, the voltage U mp and the current I mp of the maximum working point of the ground power supply, the bus voltage U bus and the total load current I bus of the spacecraft, the monomer voltage and the whole group voltage U bat of the battery, the charging and discharging current I bat of the battery, and the charging voltage grade setting value U set .

[0055] According to the information of the telemetry data, the maximum power supply capacity of the corresponding ground power supply equipment under each typical working condition is obtained by the following method:

[0056] The maximum working point voltage of all ground power supplies under typical working conditions is compared with the bus voltage of the spacecraft, and the maximum working point current of the ground power supply higher than the bus voltage is accumulated, so as to obtain the maximum power supply current of the ground power supply corresponding to the typical working condition.

[0057] (3), the construction of the secondary RC circuit model of the battery

[0058] As shown in Figure 2 , the secondary RC circuit model of the battery includes resistors R0, R b , R p , capacitors C b , C p , and an equivalent power supply.

[0059] The resistor R b and the capacitor C b are connected in parallel to form a first RC parallel circuit; the resistor R p and the capacitor C p are connected in parallel to form a second RC parallel circuit; one end of the resistor R0 connected to the positive electrode of the equivalent power supply, the other end of the resistor R0 is connected in series with the first RC parallel circuit and the second RC parallel circuit, the output end of the second RC parallel circuit is the positive electrode of the battery terminal voltage, and the negative electrode of the equivalent power supply is the negative electrode of the battery terminal voltage.

[0060] The zero-state response equation of the battery terminal voltage is:

[0061]

[0062] Where U bat is the battery terminal voltage; U OC is the open-circuit voltage of the battery; R0 represents the internal resistance of the battery, including the resistance generated by various film layers on the electrode surface; U b and U p are the voltages of the two RC circuits; the values of R b and C b are the double-layer capacitance and resistance of the battery, when the conductivity of the two phases is high, the charge will be redistributed, this process can be simulated by double-layer capacitance and resistance; the values of R p and C p are the capacitance and resistance of the internal diffusion phenomenon of the battery.

[0063] In actual engineering applications, the battery can only directly measure the battery terminal voltage U bat and current I bat and temperature, and other parameters of the battery can be obtained by factory providing or using experimental data for identification.

[0064] (4) The calculation model of the battery state of charge is established by using the ampere-hour integration method. Assuming that the initial value of the SOC of the battery at the time t0 before work is SOC0, the SOC value of the battery at the time t is:

[0065]

[0066] wherein Q n is the rated capacity of the battery, I bat is the charging and discharging current of the battery, τ is the time integral quantity, and η is the charging and discharging rate. In order to facilitate calculation, the above formula is discretized to obtain the discrete equation expression of the ampere-hour integration method as follows:

[0067]

[0068] wherein Q n is the rated capacity of the battery, I bat is the charging and discharging current of the battery, η is the charging and discharging rate, Δt is the calculation period, SOC k is the state of charge of the storage battery in the kth calculation period, and SOC k+1 is the state of charge of the storage battery in the k+1th calculation period.

[0069] The above model can be used to calculate the battery power change at each time to estimate the remaining battery power in real time.

[0070] (5) The system model of the EKF algorithm based on the second-order RC circuit is established to estimate the SOC, wherein SOC and U b , U p are taken as the state vectors of the algorithm system, and the battery terminal voltage equation is taken as the observation equation of the system. The equivalent model and the ampere-hour integration definition formula are discretized to obtain the discretized state equation of the model as follows:

[0071]

[0072] The input quantity is I bat

[0073] The observation quantity is U bat

[0074] The discretized observation equation of the model is:

[0075]

[0076] wherein SOC is the state of charge of the storage battery, T s is the calculation period, U bat is the battery terminal voltage, U OC is the open-circuit voltage of the battery, R0 represents the internal group of the battery, U b , and U pare voltages of the first RC parallel circuit and the second RC parallel circuit, respectively; R b and C b are resistance value and capacitance value of the resistance R b and the capacitance C b , respectively; R p and C p are resistance value and capacitance value of the resistance R p and the capacitance C p , respectively; U bat is output voltage of the battery, I bat is charge-discharge current of the battery, k and k+1 represent the kth calculation period and the k+1th calculation period, respectively, and Q n is the calibrated capacity of the battery.

[0077] The above equation is substituted into the EKF algorithm to estimate a more accurate SOC value.

[0078] (6) Energy management method

[0079] To ensure the safety of the spacecraft integrated test, the charging cutoff voltage U GC and the discharging cutoff voltage U GF are set: ① when U bat > U GC , the ground power supply is prohibited to output and a warning is given; ② when U bat <U GF , the ground power supply selects the maximum power supply current corresponding to the volt-ampere characteristic and outputs and gives a warning; otherwise, the energy sources are distributed according to the state of charge SOC of the battery:

[0080] Based on the current state of charge SOC of the battery, the spacecraft energy management monitoring point is set, and when the estimated SOC reaches the monitoring point, the average total current I bus of the load in the current 5 minutes is calculated. The power supply curve is selected: ① when SOC>1.05, the ground power supply system needs to select the maximum volt-ampere characteristic curve lower than I bus from the maximum power supply capability list to output; ② when SOC<0.95, the ground power supply system needs to select the minimum volt-ampere characteristic curve higher than I bus from the maximum power supply capability list to output; ③ when 0.95<SOC<1.05, the current state is maintained without action.

[0081] (8) Equalization management

[0082] The equalization management needs to be performed when the battery is not in the state of charging and discharging, i.e., |I bat |<2A, if not satisfied, the equalization management function is prohibited and all equalization actions are stopped; if satisfied, the equalization management function is enabled.

[0083] The spacecraft sets an equalization switch for each battery monomer, the equalization switch is off, the battery output voltage is unchanged, the equalization switch is on, and the battery monomer output voltage is reduced; the equalization switch state of the battery monomer is obtained through telemetry data acquisition;

[0084] In the equalization management function enabled state, the equalization management process is as follows: Figure 3 As shown: monitor all valid battery monomer voltages, select the lowest voltage monomer in the battery, and the voltage difference between other monomers and the lowest voltage is greater than the first threshold U JHK When the number of battery monomers with the equalization switch turned on is ≤N MAX , the equalization switch of the battery monomer with a higher output voltage is turned on, and the number of monomers with the equalization switch turned on is increased by 1; when the voltage difference between the monomer with the equalization switch turned on and the lowest monomer is less than the second threshold U JHG , if the number of battery monomers with the equalization switch turned on is ≥0, the equalization switch of the battery monomer with a lower output voltage is turned off, the number of battery monomers with the equalization switch turned on is reduced by 1, and N MAX is the total number of battery monomers.

[0085] If the current spacecraft comprehensive test is completed, exit, otherwise continue to perform the energy adaptive management of the spacecraft test.

[0086] The application has been successfully applied to the whole satellite system level test of a traditional remote sensing satellite, and the effect is good, and the application can be further popularized to other remote sensing satellites or other field tests.

[0087] Although the application has been disclosed as above with a preferred embodiment, it is not intended to limit the application, and any person skilled in the art can make possible changes and modifications to the technical solutions of the application by using the disclosed methods and technical contents without departing from the spirit and scope of the application, therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the application, which does not deviate from the technical solutions of the application, belongs to the protection scope of the technical solutions of the application.

Claims

1. A spacecraft test energy adaptive control system, characterized by The telemetry subscription and processing unit, the data analysis and statistics unit, the energy planning unit, and the energy management unit are included. The telemetry subscription and processing unit is connected with the spacecraft general control test system, subscribes to the telemetry data of the ground power supply and the spacecraft general control test system, obtains the bus and load working conditions of the spacecraft and the charging and discharging conditions of the storage battery through the telemetry data, and statistically calculates the energy list of the ground power supply; the energy list of the ground power supply includes the voltage-current characteristics and the maximum power supply current of the ground power supply system corresponding to each typical working condition; The data analysis and statistics unit constructs a second-order RC circuit model of the storage battery, establishes a calculation model of the state of charge of the storage battery by using the ampere-hour integral method, and calculates the state of charge SOC of the storage battery based on the second-order RC circuit model and the calculation model of the state of charge of the storage battery by using an extended Kalman filter algorithm; The energy planning unit compares the output voltage U of the battery bat with the preset charging cutoff voltage U GC and the discharging cutoff voltage U GF . If U bat > U GC , the ground power supply is prohibited from outputting and a warning is given. If U bat < U GF , the ground power supply outputs the voltage-current characteristic corresponding to the maximum power supply current in the energy source list and a warning is given. Otherwise, the energy of each ground power supply is allocated according to the state of charge SOC of the storage battery. The energy management unit disables the equalization management function and stops all equalization actions if the storage battery is in a charging and discharging state, and enables the equalization management function otherwise, and performs equalization control on the storage battery cells according to the state of charge and the voltage dispersion of the storage battery cells.

2. The spacecraft test energy adaptive control system of claim 1, wherein The spacecraft test energy adaptive control system is time-synchronized with the spacecraft general control test system.

3. The spacecraft test energy adaptive control system of claim 1, wherein The telemetry data comprises the run time t, the voltage U of the maximum operating point of the ground power supply mp and the current I mp , the spacecraft bus voltage U bus and the total load current I bus , the individual cell voltage of the battery, the output voltage U of the battery bat , the charge and discharge current I of the battery bat , the battery charging voltage step setting value U set .

4. The spacecraft test energy adaptive control system of claim 1, wherein, The maximum power supply capacity of the ground power supply equipment corresponding to each typical working condition is obtained by the following method: The maximum working point voltage of all ground power supplies under the typical working condition is compared with the bus voltage of the spacecraft, the maximum working point current of the ground power supply higher than the bus voltage is accumulated, and the maximum power supply current of the ground power supply corresponding to the typical working condition is obtained.

5. The spacecraft test energy adaptive control system of claim 1, wherein, The second-order RC circuit model of the battery includes resistors R0, R b , R p , capacitors C b , C p , and an equivalent power source; Resistor R b and capacitor C b are connected in parallel to form a first RC parallel circuit; resistor R p and capacitor C p are connected in parallel to form a second RC parallel circuit; one end of resistor R0 connected to the positive pole of the equivalent power source, the other end of resistor R0 connected in series to the first RC parallel circuit and the second RC parallel circuit, the output end of the second RC parallel circuit being the positive pole of the battery terminal voltage, and the negative pole of the equivalent power source being the negative pole of the battery terminal voltage.

6. The spacecraft test energy adaptive control system of claim 5, wherein, The R b and C b values are the double-layer capacitance and resistance of the battery; R p and C p values are the capacitance and resistance of the diffusion phenomena inside the battery.

7. The spacecraft test energy adaptive control system of claim 1, wherein, The state of charge SOC of the storage battery is calculated by the following formula: wherein Q n is the battery rated capacity, I bat is the battery charge and discharge current, η is the charge and discharge rate, Δt is the calculation period, SOC k is the battery state of charge in the kth calculation period, SOC k+1 is the battery state of charge in the k+1th calculation period.

8. The spacecraft test energy adaptive control system of claim 1, wherein, The state quantity of the Kalman filter equation is: State quantities are: [SOC U b U p ] T The state equation is: The input quantity is: I bat The observation is: U bat The observation equation is: wherein SOC is the battery state of charge, T s is the calculation period, U bat is the battery terminal voltage; U OC is the battery open circuit voltage; R0represents the battery internal resistance; U b and U p are the voltages of the first and second RC parallel circuits, respectively; R b and C b are the resistance value of the resistor R b and the capacitance value of the capacitor C b , respectively; R p and C p are the resistance value of the resistor R p and the capacitance value of the capacitor C p , respectively; U bat is the battery output voltage, I bat is the battery charge and discharge current, k and k+1 represent the kth and k+1th calculation periods, respectively, and Q n is the battery rated capacity.

9. The spacecraft test energy adaptive control system of claim 1, wherein, The energy management method is: Calculate the average total load current I over the preset time period up to the current moment. bus By comparing the current state of charge (SOC) of the battery with the preset spacecraft energy management monitoring point, when the current SOC of the battery is greater than 1.05, the ground power system selects a value lower than 1 from the list of maximum power supply capabilities. bus The maximum supply current corresponding to the volt-ampere characteristic curve is output. If it does not exist, the ground power output is prohibited and a warning is given. If the current state of charge (SOC) of the battery is less than 0.95%, the ground power system selects a value higher than I from the list of maximum supply capacity. bus If the maximum supply current corresponding to the volt-ampere characteristic curve is not output, the current state will be maintained and no action will be taken.

10. The spacecraft test energy adaptive control system according to claim 1, wherein: The spacecraft is provided with an equalization switch for each storage battery cell, the equalization switch is turned on, the output voltage of the storage battery remains unchanged, the equalization switch is turned on, and the output voltage of the storage battery cell is reduced; the state of the equalization switch of the storage battery cell is obtained through telemetry data acquisition. The equalization method is: monitoring all effective battery monomer voltage, selecting the lowest voltage monomer in the battery, and the voltage difference between other monomers and the lowest voltage is greater than the first threshold value U JHK When the number of battery monomers with the equalization switch turned on is less than or equal to N MAX , the equalization switch of the battery monomer with higher output voltage is turned on, and the number of monomers that have been turned on is increased by 1; when the voltage difference between the monomer with the equalization switch turned on and the lowest monomer is less than the second threshold value U JHG , if the number of battery monomers with the equalization switch turned on is greater than or equal to 0, the equalization switch of the battery monomer with lower output voltage is turned off, the number of battery monomers with the equalization switch turned on is reduced by 1, and N MAX is the total number of battery monomers.

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