CN114647928B - Satellite energy simulation method for on-orbit data curve fitting - Google Patents
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Abstract
The invention provides a satellite energy simulation method for on-orbit data curve fitting, which comprises the following steps: step one: identifying input and output contents of a certain satellite energy system; step two: identifying the components of a certain satellite energy system and the input and output contents of the components, and constructing a component model of the satellite energy system based on the functional principle and on-orbit data curve fitting; step three: for parameters with larger errors or which cannot be directly calculated, fitting calculation is carried out on the model according to the parameter data of the satellite real in-orbit energy system; step four: comparing the simulation output result of a certain satellite with real data to give a trend consistency and a correlation coefficient judgment or calculation result; from simulation results, the main parameter simulation fitting degree of the energy subsystem obtained by the simulation method is more than 91%, and engineering application requirements are met.
Description
Technical Field
The invention belongs to the field of aerospace measurement and control, and relates to an energy simulation implementation method based on an on-orbit data curve fitting of a satellite energy system working principle and output parameters.
Background
With the continuous development of a batch of satellite key engineering and the transition from technical verification to commercial application stage of commercial satellite industry, new platforms and new types of satellites are continuously increased, the number of in-orbit satellites is rapidly increased, and the long-term management task of the spacecraft faces unprecedented pressure. Meanwhile, due to the influence of space environment factors and over-life operation, various non-artificial on-orbit anomalies frequently occur, and the increase of the frequency of the anomalies is a necessary result, so that the situation of the safety management task of the on-orbit spacecraft is increasingly serious. The spacecraft body is generally composed of a gesture control subsystem, a power supply subsystem, a measurement and control subsystem, a digital pipe/satellite subsystem, a load subsystem and the like, and each subsystem has different functions and cooperates together to ensure the safe running and the playing of the spacecraft in orbit. However, from the importance of on-orbit safety management of the spacecraft, the power supply is an important guarantee that a power supply is used as a core subsystem of the spacecraft, so that a space device is communicated with a space link, the stable operation of the space device is ensured, the normal operation of service application of the space device is ensured, and the normal transmission of service data to the ground is ensured, so that the safety of the space device is ensured.
In the traditional spacecraft in-orbit safety management stage, in the spacecraft abnormality treatment, for the abnormality which is difficult to locate in time, usually, the fault treatment cannot be carried out by directly taking empirical measures (fault plans and the like), the abnormality simulation locating analysis must be carried out by adopting spacecraft simulation software according to the fault phenomenon, and the effectiveness of the spacecraft treatment can be ensured by carrying out simulation verification on a usable treatment scheme. The on-orbit anomaly generation mechanism of the spacecraft is clear, positioned and effective, and the basic ground is provided with a plan, so that the spacecraft can be rapidly treated according to the anomaly treatment plan; however, for significant or non-occurrence of spacecraft anomalies, the spacecraft design principles and simulation analysis results of the spacecraft simulation system must be combined to determine the cause of the anomaly and verify the treatment plan.
The domestic spacecraft system simulation software is ground simulation test software developed by the spacecraft development department, and has the main functions of verifying the rationality and feasibility of spacecraft design and the maturity of spaceborne software in the spacecraft development process, and functional accuracy verification is not performed generally. Therefore, the existing domestic spacecraft simulation system, in particular power simulation software, mainly starts from design principles and ground test data, and a simple model reflecting the power supply and distribution and control effects of the power supply system and basic association relations with other subsystems is established, so that simulation results and on-orbit true star data errors are larger.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides an energy simulation implementation method based on the working principle of a satellite energy system and on-orbit data curve fitting, which fully considers the influence of on-orbit factors on a power simulation system on the basis of the design principle of a power subsystem, improves the simulation fitting degree of output parameters of the power subsystem and provides simulation technical support for subsequent on-orbit anomaly analysis and treatment.
The technical scheme adopted by the invention for solving the technical problems comprises the following steps:
step one, input and output contents of a certain satellite energy system are identified. The input of the energy simulation comprises the contents of various on-orbit external environment inputs, self state inputs and the like which are normally calculated by the simulation method. The output of the energy simulation comprises load current, solar cell array output current, storage battery charging and discharging current, storage battery voltage, current electric quantity of the storage battery, energy balance result and the like; step two, according to the working principle of the energy system, identifying the components of the energy system and the input and output contents of the components, constructing a satellite energy system component model based on the functional principle and on-orbit data curve fitting, including a storage battery model, a power supply controller model, a solar array model and the like, and simultaneously constructing an energy system balance model and a bus voltage output model by combining the design constraint of the energy system;
step three, fitting calculation is carried out on the model according to the parameter data of the satellite real in-orbit energy system for the parameters with larger errors or the parameters which cannot be directly calculated;
step four: and comparing the simulation output result of a certain satellite with the real data to give a trend consistency and a correlation coefficient judgment or calculation result.
The invention provides an energy simulation implementation method based on a satellite energy system working principle and on-orbit data curve fitting, which fully considers the influence of on-orbit factors on a power simulation system on the basis of a power subsystem design principle, improves the simulation fitting degree of output parameters of the power subsystem, and provides simulation technical support for subsequent on-orbit anomaly analysis and treatment.
Drawings
FIG. 1 is a graph of comparing output current parameter results of a solar array;
FIG. 2 is a comparison of battery pack charging current parameter results;
FIG. 3 is a graph of battery pack discharge current parameter results;
FIG. 4 is a battery pack voltage parameter result comparison;
FIG. 5 is a graph of a comparison of current battery pack electrical parameter results;
FIG. 6 is a graph of bus voltage parameter results.
Detailed Description
The invention will be further illustrated with reference to the following figures and examples, which include but are not limited to the following examples.
The invention comprises the following steps:
input and output content of the satellite energy system is identified.
External environmental condition input
External environmental conditions required for normal operation of the power supply simulation, such as simulation start time, sun-earth distance factors, shadow entering and exiting marks, included angles between solar rays and the normal line of the solar cell array, and the like.
1) In and out of image level
Providing a signal of the in-out shadow level of the satellite by the control console, wherein the signal is a 1-bit state quantity, and when the in-out shadow level is 1, the signal indicates that the satellite is in an illumination period; when the in-out shadow level is 0, the satellite is indicated to be in the earth shadow period.
2) Normal incidence angle of solar cell array
According to the orbit condition, the season, the orbit position of the satellite, the attitude requirement of the satellite and the like, the normal incidence angle of the solar ray and the solar cell array changes with time, and the console provides data of the change of the normal incidence angle of the solar ray and the solar cell array of any orbit ring of any day with time. The power supply simulation module is provided with a corresponding data interface to read the incident angle value and draw a curve.
3) Simulation start time
The track time corresponding to the normal incidence angle of the solar cell array is taken as the starting time.
Self state input
The characteristic performance parameters of each component part of the power subsystem, such as solar array parameters, storage battery parameters, power controller parameters and the like, can be input by local files, and the input parameters have the functions of saving and repeatedly calling.
1) Solar array parameters
(1) Series-parallel connection number of solar cell array
(2) Solar cell performance parameters
(3) Solar cell design factor
(4) Track parameters
2) Parameters of battery pack
The method comprises the rated capacity Qj, the initial capacity Q0, the serial monomer number Nbat, the parallel monomer number Npar, the charge-discharge ratio coefficient f, the simulation calculation time step t0 and the like of the storage battery.
3) Power supply controller parameters and line voltage drop
Comprises a discharging regulator efficiency BDR, a charging regulator efficiency BCR, a solar cell array isolation diode and a power supply cable voltageSum of reduction V dioline And the power supply line loss factor eta of the storage battery pack.
Energy simulation output
The output of the energy simulation comprises load current, solar array output current, storage battery charging and discharging current, storage battery voltage, current electric quantity of the storage battery, energy balance result and the like.
And constructing a component model and an energy system model based on functional principles and on-orbit data curve fitting.
Solar array model
The solar cell array simulation model takes the characteristic points of the I-V curve in the standard state as parameters, considers the influence of various environmental factors, configures the solar cell array simulation model according to the design scheme of the power supply system, receives the sun incidence angle calculated by other simulation models, and combines simulation data such as current load power to calculate the output parameters of the solar cell array.
I＝I' SC ×(1-C 1 ×{exp[V/(C 2 ×V' oc )]-1}
C 1 ＝[1-(I' mp /I' SC )]×{exp[-V' mp /(C 2 ×V' oc )]}
C 2 ＝[(V' mp /V' oc )-1]/ln(1-I' mp /I' SC )
(1)
Wherein:
i, outputting current by a solar cell array, A;
i' SC-solar cell array short-circuit current, typical parameters or measured values, A;
c1-formula coefficient 1;
v-the output voltage of the solar cell array is approximately equal to the busbar voltage of the illumination area, V;
c2—formula coefficient 2;
v' oc-open circuit voltage of solar cell array, typical parameters or measured values, V;
i' mp-the optimal working point of the solar cell array outputs current, typical parameters or actual measurement values, A;
v' mp-the optimum operating point output voltage of the solar cell array, typical parameters or measured values, V.
V' oc ＝(V oc +b V ×ΔT)×K VAL ×K VTE ×K VRAD ×N S
V' mp ＝(V mp +b V ×ΔT)×K VAL ×K VTE ×K VRAD ×N S
I' SC ＝(I SC +a I ×ΔT)×K IAL ×K ITE ×K IRAD ×K IUV ×N P ×cosθ(t)×F rd
I' mp ＝(I mp +a I ×ΔT)×K IAL ×K ITE ×K IRAD ×K IUV ×N P ×cosθ(t)×F rd
(2)
Wherein:
voc—single cell open circuit voltage;
ISC-single solar cell short-circuit current;
imp—optimal operating point current for single cell solar cells;
the voltage combination loss factor of the KVAL-solar cell array is generally 0.98-0.99;
the voltage test error factor of the KVTE-solar cell array is generally 0.98-0.99;
the current combination loss factor of the KIAL-solar cell array is generally 0.98-0.99;
the error factor of the KITE-solar cell array current test is generally 0.98-0.99;
the KIRAD-solar cell array current space particle irradiation loss factor is determined according to a current-particle irradiation dose curve of a solar cell;
the current ultraviolet radiation loss factor of the KIUV-solar cell array is determined according to the current-ultraviolet radiation dose curve of the solar cell; θ (t) -the angle between the solar ray and the normal direction of the solar cell array;
b V -the end-of-life voltage temperature coefficient of the single solar cell (the value of the change in output voltage of the solar cell when the temperature of the solar cell changes by 1 ℃), V/°c;
a I -the end-of-life current temperature coefficient of the single solar cell (the value of the change in output current of the solar cell when its temperature changes by 1 ℃), a/°c;
NP-solar cell array parallel number, NS-solar cell array parallel number;
frd-light intensity factor.
Storage battery model
The main function of the storage battery simulation module is to simulate the working condition of the storage battery in real time when the satellite runs in orbit, and simulate the change condition of the charge and discharge current and the charge and discharge voltage of the storage battery in the charge and discharge process. The simulation model of the storage battery is based on experimental data of the storage battery selected in the design scheme of the power supply system under two groups of different charge and discharge currents, a function relation between the charge and discharge voltage of the storage battery and the current electric quantity is fitted under a certain charge and discharge current, the charge and discharge voltage of the storage battery is obtained according to the electric quantity of the storage battery at the current simulation moment and the charge and discharge current of the storage battery, and real-time data representing the current state of the storage battery is obtained through remote measurement and downloading display.
1) Discharge current calculation
The discharge current of the battery pack depends on factors such as the discharge power of the battery pack, the efficiency of the discharge regulator, the loss factor of the battery pack power supply line, the battery pack voltage, etc.
Wherein:
I ld (t) -data of load power demand of the nth turn track over time;
η BDR discharge regulator efficiency;
η line battery pack power line loss factor;
V bt a battery pack discharge voltage;
V bs bus voltage at discharge.
2) Discharge voltage calculation
Because the discharge voltage of the storage battery is not calculated by a direct formula, according to the assumption that the discharge voltage of the storage battery has an association relationship with the discharge electric quantity of the storage battery, curve fitting is carried out by a least square method, and a relationship function between the discharge voltage of the storage battery and the current electric quantity is obtained.
V＝f(Q)
(4)
3) Charging current calculation
And the solar cell array outputs power which meets the residual power outside the load power requirement, so that the maximum charging current for charging the storage battery is obtained.
Wherein:
I SA (t) -the nth turn solar array outputting current;
I ld (t) -data of load power demand of the nth turn track over time;
η BCR discharge regulator efficiency;
V bt battery pack charging voltage;
V bs bus voltage at charging.
4) Charging voltage calculation
The same as battery model 2) section content.
5) Current electric quantity and charge-discharge electric quantity calculation of storage battery pack
The method for calculating the current electric quantity of the storage battery pack comprises the following steps:
Q current (t)＝Q current (t)+Q charge (t)－Q discharge (t)
(6)
charging quantity Q charge The calculation method of (t) is as follows:
Q charge (t)＝Q charge (t)+I c (t)×t 0 /f ad
(7)
discharge electric quantity Q discharge The calculation method of (t) is as follows:
Q discharge (t)＝Q discharge (t)+I d (t)×t 0 (8)
wherein:
f ad : a charge-discharge ratio coefficient;
I c (t): a charging current;
I d (t): a discharge current;
t 0 : charge-discharge time.
Power supply controller model
1) Charge control
The charging regulator is a voltage-reducing switching power supply directly connected to the bus, and under the common control of a main error amplification signal (MEA) and a charging current set level given by a power supply lower computer, the charging regulator takes electricity from the bus to regulate proper charging current to charge the storage battery. The default operation mode of the charging regulator is a primary and a backup hot backup mode, and any one of the hot backup modes is allowed to be cut off or disabled. The input of the charging regulator model is bus voltage and bus charging current, and the output is storage battery voltage and storage battery charging current. The satellite battery pack follows a control mode of constant current charging, and the charging termination adopts a control mode of software ampere hour meter and hardware V/T curve hot backup, and firstly meets the first start control of the condition. The charging control of the ampere hour meter adopts relative electric quantity control, namely, how much electric quantity is discharged by the storage battery, the solar battery array supplements corresponding electric quantity, and the storage battery is transferred to trickle charge or stops charging after charging. The hardware V/T curve control also adopts a constant current control mode, and under the set charging current and battery temperature conditions, when the battery voltage reaches the voltage of the controlled point on the V/T curve, the charging of the battery is terminated.
2) Discharge control
The discharge regulator is a boost type switching power supply and is responsible for regulating the voltage of the storage battery to the bus voltage in a ground shadow area. The discharge regulator consists of six discharge regulating circuits, two of which are allowed to fail but are not allowed to be cut off. The input of the discharge regulator is the voltage of the storage battery and the discharge current of the storage battery, and the output is the bus voltage and the load current. When the received in-out shadow level is 0, the storage battery is controlled to start discharging, and the load power requirement is met.
3) Shunt control
The shunt state reflects the operating state of the shunt regulator, which depends on the magnitude of the shunt current. And obtaining the stage number in the full shunt state in the shunt regulator according to the calculated shunt current and the shunt current of each stage. The number of stages of the full shunt state and the telemetry value of the shunt state have the following corresponding relation:
I shunt (t)＝I SA (t)-I ld (t)-I c (t)×V bt (t)/η BCR /V bs (t)
full shunt progression = INT (I shunt (t)/per-stage shunt current
Per-stage shunt current=i SA (t)/8
(9)
Energy system model
On the basis of the simulation of each component of the energy, an energy system simulation model is built according to the internal logic relation of the energy system and by combining design constraints such as energy balance, bus voltage and the like.
1) Energy balance model
Energy balance is an important principle which the energy system design must follow, and is an important index for measuring whether the energy system is available. The energy balance result of the energy system is expressed on the current electric quantity, the discharging depth, the split electric quantity, the charging termination frequency and other parameters of the storage battery pack of each circle of track.
According to the current electric quantity of the storage battery, whether the storage battery is full or not before the next circle of shadow entering is known; according to the split electric quantity, the energy allowance of each circle of track can be known; according to the charge termination times, the energy balance times of each circle of track can be known; based on the depth of discharge, it is known whether the use of the battery pack is within a normal range.
The method for calculating the discharge depth of the storage battery pack comprises the following steps:
DOD(t)＝(Q bat -Q current (t))/Q bat
(10)
according to the satellite energy balance requirement, the discharge depth of the storage battery is not more than 17%.
2) Bus voltage
Because the bus of the object satellite energy system adopts a full regulation mode, the voltage of the bus is basically kept stable: 29.1V during charging; the discharge period was about 28.2V.
And for parameters with larger errors or which cannot be directly calculated, fitting and calculating the model according to the parameter data of the satellite real in-orbit energy system.
The battery voltage parameter needs to be obtained through least square fitting. It can be seen from fig. 2 that the battery charging current parameter is a piecewise function, and has a larger error than the model listed in the second part.
Battery pack voltage parameter fitting function
And selecting certain satellite charge-discharge electric parameters and storage battery voltage parameter data in the month 3 and 1 of 2020 to carry out least square fitting calculation. Firstly, calculating to obtain the charge quantity Q by using satellite charge and discharge electric parameter data and formulas (7) and (8) charge (t) and discharge quantity Q discharge And (t) obtaining a least square solution by using a least square algorithm, and adding the following formula (9).
U＝N×(a+b×Q/(Q-Q Variation of )+c×exp(d×Q Variation of )) (11)
Wherein:
a. b, c, d-coefficients;
n-number of batteries connected in series;
u-battery voltage;
q is the initial electric quantity of the battery monomer;
Q variation of Charge and discharge of accumulator (charge of-Q) charge (t))，A·h。
Battery pack charging current parameter fitting function
The storage battery charging control logic of a certain satellite energy system is as follows: after entering the sunlight area, if the voltage of the storage battery pack is less than 26.8V, starting high-current charging; when the voltage of the storage battery pack is equal to 26.8V, starting direct current charging; and after the direct current charging time meets a certain time, switching to low current charging until entering a shadow area. The battery pack charge current fitting function is therefore:
simulation output and real data comparison result
The invention takes the trend consistency and the correlation coefficient as the index for comparing the simulation output with the real data, wherein the trend consistency can be obtained through observation, and the nonlinear correlation coefficient R2 can be obtained through calculation.
Wherein SS is tot Represents mean square error, SS res Representing the sum of squares of the differences between the true and predicted values.
Inputting information such as an included angle between the solar ray and the normal of the satellite solar cell array, a sun-earth distance factor, a shadow entering and exiting mark and the like into simulation prototype software in month 3 and 1 of 2020; characteristic performance parameters of all the component parts of the power subsystem are input into simulation prototype software. After the operation model is calculated, parameter data of 13:45 to 15:46 of 3 months and 1 days of the true star 2020 are adopted to be compared with parameter simulation results, and compared parameters comprise: the solar cell array outputs current, the charging and discharging current of the storage battery, the voltage of the storage battery, the current electric quantity of the storage battery and the like.
Solar cell array output current
The comparison result of the true star data of the output current parameter of the solar cell array and the simulation result is shown in figure 1.
From the view of fig. 1, the output current parameter true star data of the solar cell array is basically consistent with the trend of the simulation result; the correlation coefficient calculation result was 0.94.
Charging current of storage battery
The comparison result of the true star data and the simulation result of the charging current parameter of the storage battery is shown in fig. 2.
From fig. 2, the real star data of the battery pack charging current parameter and the trend of the simulation result are basically consistent; the correlation coefficient calculation result was 0.92.
Discharge current of storage battery
The comparison result of the true star data and the simulation result of the discharge current parameter of the storage battery is shown in figure 3.
As seen from fig. 3, the true star data of the discharge current parameters of the storage battery pack are basically consistent with the trend of the simulation result; the correlation coefficient calculation result was 0.9202.
Storage battery voltage
The comparison result of the true star data and the simulation result of the discharge current parameter of the storage battery is shown in fig. 4.
From fig. 4, the voltage parameter true star data of the storage battery pack is basically consistent with the trend of the simulation result; the correlation coefficient calculation result was 0.918.
Current power and depth of discharge of battery pack
The true star data of the current electric quantity parameter of the storage battery and the comparison result of the simulation result are shown in fig. 5.
From fig. 5, the current electric quantity parameter true star data of the storage battery pack is basically consistent with the trend of the simulation result; the correlation coefficient calculation result was 0.98.
And from the current electric quantity simulation result, the discharge depth parameter result is basically close, the maximum discharge depth is 12.6 percent and is less than 17 percent, and the on-orbit actual condition is met.
Bus voltage
The comparison result of the real star data and the simulation result of the bus voltage parameter is shown in fig. 6.
From FIG. 6, the bus voltage parameter true star data and the simulation result trend are basically consistent; the correlation coefficient calculation result was 0.99. From simulation results, the main parameter simulation fitting degree of the energy subsystem obtained by the simulation method is more than 91%, and engineering application requirements are met.
Claims (1)
1. The satellite energy simulation method for the on-orbit data curve fitting is characterized by comprising the following steps of: step one: identifying input and output contents of a certain satellite energy system, wherein the input of the certain satellite energy system comprises various in-orbit external environment input and self state input contents which can be normally calculated by a simulation method; the output content of the satellite energy system comprises load current, solar cell array output current, storage battery charging and discharging current, storage battery voltage, current electric quantity of the storage battery and energy balance result;
step two: identifying the components of a certain satellite energy system and the input and output contents of the components, constructing a component model of the satellite energy system based on the functional principle and on-orbit data curve fitting, wherein the component model comprises a storage battery model, a power supply controller model and a solar array model, and simultaneously constructing an energy system balance model and a bus voltage output model by combining the energy system design constraint;
step three: for parameters which cannot be directly calculated, fitting calculation is carried out on the model according to satellite real in-orbit energy system parameter data;
step four: comparing the simulation output result of a certain satellite with real data to give a trend consistency and a correlation coefficient judgment or calculation result;
the first step is as follows: the input to the energy system includes (1) external environmental condition input: the power supply simulates external environment conditions required by normal operation, and simulates initial time, sun-earth distance factors, shadow entering and exiting marks and included angles between solar rays and the normal line of the solar cell array; (2) self status input: the characteristic performance parameters of each component part of the power subsystem, the solar cell array parameters, the storage battery parameters and the power controller parameters can be input by local files, and the input parameters have the functions of saving and repeatedly calling;
the second step is as follows: the solar cell array simulation model is configured by taking I-V curve characteristic points in a standard state as parameters and considering the influence of various environmental factors, receives solar incidence angles calculated by other simulation models, and calculates output parameters of the solar cell array by combining current load power simulation data;
the storage battery model has the functions of simulating the working condition of the storage battery in real time when the satellite runs in orbit and simulating the change condition of charge and discharge current and charge and discharge voltage of the storage battery in the charge and discharge process; the simulation model of the storage battery is based on experimental data of the storage battery under two groups of different charge and discharge currents, a functional relation between the charge and discharge voltage of the storage battery and the current electric quantity under a certain charge and discharge current is fitted, the charge and discharge voltage of the storage battery is obtained according to the electric quantity of the storage battery at the current simulation moment and the charge and discharge current of the storage battery, and real-time data representing the current state of the storage battery is obtained through telemetering downloading display;
the power supply controller model includes:
(1) The charging control, the charging regulator is a step-down type switching power supply directly connected to the bus, under the common control of a main error amplification signal (MEA) and a charging current set level given by a power supply lower computer, the charging regulator takes electricity from the bus to regulate proper charging current to charge a storage battery, the default working mode of the charging regulator is a main and standby hot backup mode, any one of the modes is allowed to be cut off or disabled, the input of a charging regulator model is bus voltage and bus charging current, and the output is storage battery voltage and storage battery charging current;
the satellite battery pack follows a control mode of constant current charging, the charging is terminated by adopting a control mode of software ampere-hour meter and hardware V/T curve hot backup, firstly, the start control of the conditions is satisfied, the ampere-hour meter charging is controlled by adopting relative electric quantity, namely, how much electric quantity is discharged by a storage battery, the corresponding electric quantity is supplemented by a solar battery array, and the trickle charging or the stopping of the charging is carried out after the storage battery charging is completed;
the hardware V/T curve control also adopts a constant current control mode, and under the set charging current and battery temperature conditions, when the battery voltage reaches the voltage of a controlled point on the V/T curve, the charging of the battery is terminated;
(2) Discharge control
The discharging regulator is a boost type switching power supply and is responsible for regulating the voltage of the storage battery to be the bus voltage in a shadow area, the discharging regulator consists of six discharging regulating circuits, two paths of the discharging regulating circuits are allowed to fail but are not allowed to be cut off, the input of the discharging regulator is the voltage of the storage battery and the discharging current of the storage battery, the output of the discharging regulator is the bus voltage and the load current, and when the shadow level is 0, the storage battery is controlled to start discharging so as to meet the load power requirement;
(3) Shunt control
According to the calculated shunt current and the shunt current of each stage, the stage number in the full shunt state in the shunt regulator can be obtained; the energy system balance model comprises the parameters of the energy system energy balance result, such as the current electric quantity, the depth of discharge, the split electric quantity and the charge termination times of the storage battery pack of each track; according to the current electric quantity of the storage battery, whether the storage battery is full or not before the next circle of shadow entering is known; according to the split electric quantity, the energy allowance of each circle of track can be known; according to the charge termination times, the energy balance times of each circle of track can be known; based on the depth of discharge, it is known whether the use of the battery pack is within a normal range.
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| CN102289535A (en) * | 2011-06-07 | 2011-12-21 | 北京航空航天大学 | Spacecraft power system energy analysis simulation platform |
| CN110048674A (en) * | 2019-04-22 | 2019-07-23 | 北京控制工程研究所 | High rail zero momentum satellite sailboard based on angular momentum estimation rotates failure judgment method |
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| CN102289535A (en) * | 2011-06-07 | 2011-12-21 | 北京航空航天大学 | Spacecraft power system energy analysis simulation platform |
| CN110048674A (en) * | 2019-04-22 | 2019-07-23 | 北京控制工程研究所 | High rail zero momentum satellite sailboard based on angular momentum estimation rotates failure judgment method |
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| 一种基于聚类的卫星太阳电池阵衰减估计方法;曹孟达;张涛;李训嘉;刘亚杰;;无线电工程;20190505(第05期);全文 * |
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