Spacecraft multi-loop energy balance design method and system

Abstract

The application provides a spacecraft multi-loop energy balance design method and system, relates to the technical field of spacecraft design and simulation, and comprises solar cell array series number design, solar cell array parallel number design, storage battery group series number design and storage battery group parallel number design. The energy balance design method is suitable for the multi-loop energy balance state of a spacecraft. The application effectively solves the problem that the volume and weight of the power supply and distribution subsystem are over-limited when the overall spacecraft load power is too large, provides a feasible scheme for the power supply and distribution subsystem design of the multi-loop energy balance of a spacecraft, and expands the application range of the energy balance design method.

Description

Technical Field

[0001] This invention relates to the field of spacecraft design and simulation technology, specifically to a method and system for designing multi-cycle energy balance for spacecraft. Background Technology

[0002] The main energy sources for spacecraft include zinc-silver batteries, hydrogen-oxygen fuel cells, isotope thermoelectric cells, and solar array-lithium-ion battery packs. Currently, the most widely used is the solar array-lithium-ion battery pack, which uses gallium arsenide and other solar cells to convert solar energy into electrical energy through the photovoltaic effect. The battery pack stores excess electrical energy during periods of sunshine and provides power during periods of shade or high power consumption.

[0003] Spacecraft that use solar arrays and lithium-ion battery packs as their energy source need to undergo energy balance analysis and calculation based on a series of factors such as orbital parameters and load power consumption in order to determine the required number of series and parallel connections for the solar arrays and battery packs.

[0004] Traditional spacecraft typically require energy balance per orbit, meaning that the amount of electricity charged to the batteries during one orbit is greater than or equal to the amount of electricity consumed by the batteries. With the diversification of spacecraft missions and the increasing power of payloads, the short-term power of spacecraft is rising. If energy balance per orbit is still required, the area and weight of the required solar array and the volume and weight of the battery pack need to increase accordingly. Limited by launch capacity, the size and weight of spacecraft cannot increase indefinitely. When the area and weight of the required solar array and the volume and weight of the battery pack exceed the allowable range, it is necessary to adjust the on-orbit operating mode and implement multi-orbit energy balance design to reduce the area and weight of the solar array and the volume and weight of the battery pack.

[0005] Chinese invention patent document CN106324631B discloses a remote sensing satellite energy balance constraint analysis system and method, describing a dynamic analysis of the satellite's energy balance for complex mission planning and configurations of high-resolution remote sensing satellites with rapid attitude maneuvering requirements, applicable to the energy balance state within a single orbit. Chinese invention patent document CN102928714B discloses a method for predicting the lifetime of a small satellite solar array based on IV curves and energy balance, describing a method for predicting the lifetime of a solar array based on energy balance, focusing on the application of energy balance. Chinese invention patent document CN106208038B discloses a spacecraft dual-busbar energy balance analysis method, describing the energy balance design of dual-busbar spacecraft, but not covering the energy balance state across multiple orbits. Chinese patent document CN108460218A discloses a method for power consumption budgeting and energy balance analysis of small optical imaging satellites. First, based on user requirements, the satellite power consumption value in a single operating mode is calculated. Then, according to the satellite's operating mode, the power consumption value is reasonably considered according to the single-track operating state to calculate the total energy consumption of the satellite per track. Based on the selection and design margin of different solar cell arrays, the parameters of the solar cell array that meet the energy balance requirements are then calculated, including the minimum energy per track, minimum power, minimum effective area, minimum design area, design area considering margin, effective area considering margin, power considering margin, and energy per track considering margin. Finally, the energy requirements of the lithium battery pack are calculated, and battery selection is performed.

[0006] The aforementioned patents are all related to spacecraft energy balance design under the condition of current balance. They cannot adapt to the trend of diversified spacecraft missions and short-term power increases after the payload becomes more powerful, which greatly limits the applicability of energy balance design methods. Summary of the Invention

[0007] To address the shortcomings of existing technologies, the purpose of this invention is to provide a spacecraft multi-cycle energy balance design method and system.

[0008] A spacecraft multi-orbit energy balance design method according to the present invention includes the following steps:

[0009] Step S1: Input condition parameters, which include orbit parameters, load parameters, solar cell parameters, battery cell parameters, space environment parameters, and limiting condition parameters;

[0010] Step S2: Select solar cells and battery cells, and obtain the parameters of solar cells and battery cells;

[0011] Step S3: Select the bus regulation method and bus voltage based on the power consumption and model requirements of the entire spacecraft;

[0012] Step S4: Calculate the number of batteries connected in series;

[0013] Step S5: Calculate the number of solar cells connected in series;

[0014] Step S6: Calculate the number of parallel solar cell arrays using a multi-cycle balancing algorithm;

[0015] Step S7: Calculate the number of battery banks connected in parallel;

[0016] Step S8: Perform energy balance verification analysis;

[0017] Step S9: Determine whether the spacecraft meets the performance requirements. If it does, output the design results. If it does not, optimize the design of the parallel connection of the solar array and the battery. After optimization, re-enter step S8 for analysis.

[0018] Preferably, the orbital parameters include orbital period, longest shadow duration per orbit, shortest illumination duration per orbit, and illumination angle; the load parameters include long-term power consumption, short-term power consumption, and average power consumption under various operating modes of the spacecraft; the solar cell parameters include optimal operating voltage per cell, surface current density, cell area, and loss factor; the battery cell parameters include rated capacity per cell, rated voltage per cell, average discharge voltage per cell, and discharge cutoff voltage per cell; the space environment parameters include space environment temperature, solar intensity factor, and irradiance flux; and the limiting condition parameters include allowable discharge depth of the battery pack, solar array line voltage drop, and number of balance cycles.

[0019] Preferably, the method for calculating the number of batteries connected in series is as follows:

[0020]

[0021] In the formula, N BS U represents the number of batteries connected in series. Busmin Indicates the minimum bus voltage, V rated This indicates the rated voltage of a single battery cell.

[0022] Preferably, the method for calculating the number of solar cells in series is as follows:

[0023] The total output voltage required to obtain the solar cell array is:

[0024] V SA =V Busmax +V w

[0025] V mp =VmpΦ ×F u +β vp (T op –T o )

[0026] In the formula, V SA This indicates the total output voltage of the solar cell array;

[0027] V Busmax Indicates the highest voltage of the busbar;

[0028] V w Indicates bus voltage drop;

[0029] V mp This indicates the operating voltage of a single solar cell at the end of its lifespan.

[0030] V mpΦ This indicates that the solar cell has an electron irradiance flux of Φe·cm at 1 MeV energy. -2 Then, at the standard temperature T o Operating voltage at that time;

[0031] F u This represents the voltage combination loss factor at the end of the lifespan.

[0032] β vp This represents the temperature coefficient of the operating voltage of a solar cell.

[0033] T op Indicates the operating temperature of the solar cell;

[0034] T o This indicates that the standard test temperature for solar cells is 25°C.

[0035] The formula for calculating the number of solar cell arrays in series is:

[0036] N s =V SA / V mp .

[0037] Preferably, the method for calculating the number of parallel solar cell arrays is as follows:

[0038] Calculate the final operating current of the solar cell:

[0039] I mp =[I mpΦ +β IP (T op –T o )]×S×S'×F m ×F SH

[0040] In the formula, I mpΦThis indicates that the solar cell has an electron irradiance flux of Φe·cm at 1 MeV energy. -2 Then, at the standard temperature T o Operating current surface density at that time;

[0041] β IP Indicates the average temperature coefficient;

[0042] S represents the effective light-illuminated area;

[0043] S' represents the influence coefficient of solar cell on Earth-Sun distance;

[0044] F m This represents the current combination loss factor at the end of the lifespan.

[0045] F SH F represents the shading factor of a solar cell. When the solar cell is unshaded, F SH =1;

[0046] Calculate the current required to supply the load:

[0047]

[0048]

[0049] I = I C +I D

[0050] In the formula, I C Indicates the current required by the load;

[0051] P LL This indicates the long-term load power during the illumination period;

[0052] I represents the total current required during the satellite's illumination period;

[0053] I C Indicates the current required by the load;

[0054] I D This represents the average current required to charge the battery pack.

[0055] P LS This indicates the long-term load power during the shadow period;

[0056] T S Indicates the longest shadow duration of the satellite;

[0057] m represents the number of orbits required for the satellite to achieve balancing.

[0058] P S This indicates short-term load power, excluding long-term load power;

[0059] t represents the duration of operation of each short-term power during the shadow period, with the upper limit being the longest shadow duration;

[0060] T L Indicates the shortest duration of sunlight exposure for the satellite;

[0061] η d Indicates discharge efficiency;

[0062] η c Indicates charging efficiency;

[0063] N represents the number of individual battery cells connected in series in the battery pack;

[0064] V D This indicates the average discharge voltage of a single battery cell;

[0065] Calculate the number of parallel solar cell arrays:

[0066]

[0067] In the formula, θ is the worst illumination angle within a year, and considering design margin, N p Round up to the nearest whole number, and take an appropriate margin.

[0068] Preferably, the method for calculating the number of battery packs connected in parallel is as follows:

[0069] Calculate the maximum discharge capacity of a single battery bank per revolution:

[0070]

[0071] In the formula, P LS This indicates the long-term load power during the shadow period;

[0072] T S Indicates the longest shadow duration;

[0073] P S This indicates short-term load power, excluding long-term load power;

[0074] t represents the duration of operation of various short-term power consumption items during the shadow period, with the upper limit being the longest shadow duration T. S ;

[0075] n represents the number of battery packs;

[0076] η d Indicates discharge efficiency;

[0077] N represents the number of individual battery cells connected in series in the battery pack;

[0078] V D This indicates the average discharge voltage of a single cell in the battery pack.

[0079] The minimum capacity required for a single battery pack is:

[0080] Q = Q d / DOD

[0081] In the formula, DOD represents the maximum permissible depth of discharge.

[0082] The number of parallel connections for a single battery bank is obtained:

[0083] N BP =Q / Q n

[0084] In the formula, Q n This refers to the capacity of a single unit.

[0085] Preferably, the energy balance verification analysis includes: verifying and calculating the energy balance of a single orbit at the end of the on-orbit period based on the set bus voltage, the number of solar cell arrays connected in series and parallel, and the number of battery banks connected in series and parallel.

[0086] A spacecraft multi-cycle energy balance design system according to the present invention is characterized by comprising the following modules:

[0087] Module M1: Input condition parameters, including orbit parameters, load parameters, solar cell parameters, battery cell parameters, space environment parameters, and limiting condition parameters;

[0088] Module M2: Selects solar cells and battery cells, and obtains parameters for solar cells and battery cells.

[0089] Module M3: Select the bus regulation method and bus voltage based on the power consumption and model requirements of the entire spacecraft;

[0090] Module M4: Calculates the number of batteries connected in series;

[0091] Module M5: Calculates the number of solar cell arrays connected in series;

[0092] Module M6: Calculates the number of parallel solar cell arrays using a multi-turn balancing algorithm;

[0093] Module M7: Calculates the number of battery banks connected in parallel;

[0094] Module M8: Performs energy balance verification analysis;

[0095] Module M9: Determines whether the spacecraft meets the performance requirements. If it does, the design results are output. If it does not, the parallel design of the solar array and the number of batteries is optimized. After optimization, the process re-enters step S8 for analysis.

[0096] Compared with the prior art, the present invention has the following beneficial effects:

[0097] 1. This invention effectively solves the problem of the power supply and distribution subsystem exceeding the size and weight limits when the total satellite load power is too large, provides a feasible solution for the design of the power supply and distribution subsystem for multi-cycle energy balance of spacecraft, and expands the applicability of energy balance design methods;

[0098] 2. The energy balance design method of the present invention is applicable to the multi-cycle balance state of spacecraft and adapts to the trend of short-term power increase after the diversification of spacecraft missions and the high power of payloads;

[0099] 3. This invention greatly expands the applicability of spacecraft energy balance design methods. Attached Figure Description

[0100] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0101] Figure 1 This is a flowchart of the spacecraft multi-orbit energy balance design method in an embodiment of the present invention;

[0102] Figure 2 This is a flowchart illustrating the calculation of the number of series connections in a battery pack according to an embodiment of the present invention.

[0103] Figure 3 This is a flowchart illustrating the calculation of the number of solar cell arrays in an embodiment of the present invention.

[0104] Figure 4 This is a flowchart illustrating the calculation of the number of parallel solar cell arrays in an embodiment of the present invention.

[0105] Figure 5 This is a flowchart for calculating the number of parallel battery packs according to the present invention. Detailed Implementation

[0106] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0107] A spacecraft multi-cycle energy balance design method, such as Figure 1 As shown, it includes the following steps:

[0108] Step S1: Input condition parameters, which include orbit parameters, load parameters, solar cell parameters, battery cell parameters, space environment parameters, and limiting condition parameters.

[0109] The orbital parameters include orbital period, longest shadow duration per orbit, shortest illumination duration per orbit, and illumination angle; the load parameters include long-term power consumption, short-term power consumption, and average power consumption under various operating modes of the spacecraft; the solar cell parameters include optimal operating voltage, surface current density, cell area, and loss factor; the battery cell parameters include rated capacity, rated voltage, average discharge voltage, and discharge cutoff voltage; the space environment parameters include space environment temperature, solar intensity factor, and irradiance flux; and the limiting condition parameters include the allowable discharge depth of the battery pack, the voltage drop across the solar array lines, and the number of balance cycles.

[0110] Step S2: Select solar cells and battery cells, and obtain the parameters of the solar cells and battery cells.

[0111] Step S3: Select the bus regulation method and bus voltage based on the power consumption and model requirements of the entire spacecraft.

[0112] Step S4: Calculate the number of batteries connected in series.

[0113] like Figure 2 As shown, the method for calculating the number of batteries connected in series is as follows:

[0114]

[0115] In the formula, N BS U represents the number of batteries connected in series. Busmin Indicates the minimum bus voltage, V rated This indicates the rated voltage of a single battery cell.

[0116] Step S5: Calculate the number of solar cell arrays connected in series.

[0117] like Figure 3 As shown, the method for calculating the number of solar cell arrays in series is as follows:

[0118] The total output voltage required to obtain the solar cell array is:

[0119] V SA =V Busmax +V w

[0120] V mp =V mpΦ ×F u +β vp (T op –T o )

[0121] In the formula, V SA This indicates the total output voltage of the solar cell array;

[0122] VBusmax Indicates the highest voltage of the busbar;

[0123] V w Indicates bus voltage drop;

[0124] V mp This indicates the operating voltage of a single solar cell at the end of its lifespan.

[0125] V mpΦ This indicates that the solar cell has an electron irradiance flux of Φe·cm at 1 MeV energy. -2 Then, at the standard temperature T o Operating voltage at that time;

[0126] F u This represents the voltage combination loss factor at the end of the lifespan.

[0127] β vp This represents the temperature coefficient of the operating voltage of a solar cell.

[0128] T op Indicates the operating temperature of the solar cell;

[0129] T o This indicates that the standard test temperature for solar cells is 25°C.

[0130] The formula for calculating the number of solar cell arrays in series is:

[0131] N s =V SA / V mp .

[0132] Step S6: Calculate the number of parallel solar cell arrays using a multi-cycle balancing algorithm.

[0133] like Figure 4 As shown, the method for calculating the number of parallel solar cell arrays is as follows:

[0134] Calculate the final operating current of the solar cell:

[0135] I mp =[I mpΦ +β IP (T op –T o )]×S×S'×F m ×F SH

[0136] In the formula, I mpΦ This indicates that the solar cell has an electron irradiance flux of Φe·cm at 1 MeV energy. -2 Then, at the standard temperature T o Operating current surface density at that time;

[0137] βIP Indicates the average temperature coefficient;

[0138] S represents the effective light-illuminated area;

[0139] S' represents the influence coefficient of solar cell on Earth-Sun distance;

[0140] F m This represents the current combination loss factor at the end of the lifespan.

[0141] F SH F represents the shading factor of a solar cell. When the solar cell is unshaded, F SH =1;

[0142] Calculate the current required to supply the load:

[0143]

[0144]

[0145] I = I C +I D

[0146] In the formula, I C Indicates the current required by the load;

[0147] P LL This indicates the long-term load power during the illumination period;

[0148] I represents the total current required during the satellite's illumination period;

[0149] I C Indicates the current required by the load;

[0150] I D This represents the average current required to charge the battery pack.

[0151] P LS This indicates the long-term load power during the shadow period;

[0152] T S Indicates the longest shadow duration of the satellite;

[0153] m represents the number of orbits required for the satellite to achieve balancing.

[0154] P S This indicates short-term load power (excluding long-term load power);

[0155] t represents the duration of operation of each short-term power during the shadow period, with the upper limit being the longest shadow duration;

[0156] T L Indicates the shortest duration of sunlight exposure for the satellite;

[0157] ηd Indicates discharge efficiency;

[0158] η c Indicates charging efficiency;

[0159] N represents the number of individual battery cells connected in series in the battery pack;

[0160] V D This indicates the average discharge voltage of a single battery cell.

[0161] Calculate the number of parallel solar cell arrays:

[0162]

[0163] In the formula, θ is the worst illumination angle within a year, and considering design margin, N p Round up to the nearest whole number, and take an appropriate margin.

[0164] Step S7: Calculate the number of battery packs connected in parallel.

[0165] like Figure 5 As shown, the method for calculating the number of battery banks connected in parallel is as follows:

[0166] Calculate the maximum discharge capacity of a single battery bank per revolution:

[0167]

[0168] In the formula, P LS This indicates the long-term load power during the shadow period;

[0169] T S Indicates the longest shadow duration;

[0170] P S This indicates short-term load power, excluding long-term load power;

[0171] t represents the duration of operation of various short-term power consumption items during the shadow period, with the upper limit being the longest shadow duration T. S ;

[0172] n represents the number of battery packs;

[0173] η d Indicates discharge efficiency;

[0174] N represents the number of individual battery cells connected in series in the battery pack;

[0175] V D This indicates the average discharge voltage of a single cell in the battery pack.

[0176] The minimum capacity required for a single battery pack is:

[0177] Q = Q d / DOD

[0178] In the formula, DOD represents the maximum permissible depth of discharge.

[0179] The number of parallel connections for a single battery bank is obtained:

[0180] N BP =Q / Q n

[0181] In the formula, Q n This refers to the capacity of a single unit.

[0182] Step S8: Perform energy balance verification analysis.

[0183] Step S9: Determine whether the spacecraft meets the performance requirements. If it does, output the design results. If it does not, optimize the design of the parallel connection of the solar array and the battery. After optimization, re-enter step S8 for analysis.

[0184] After completing the energy balance design, it is necessary to verify and calculate the energy balance status during the end of the on-orbit period based on the set bus voltage, the number of solar cell arrays connected in series and parallel, and the number of battery banks connected in series and parallel.

[0185] Bus voltage U Bus Number of solar cell arrays in series N s Total number of parallel connections N p Number of batteries connected in series N BS Total number of parallel connections N BP .

[0186] The multi-turn balancing (the number of balancing turns is m) operating conditions are divided into two types: the first rail and the second to m rails. The first rail operates under short-term load, while the second to m rails only operate under long-term load.

[0187] Taking the worst illumination angle θ1 of the first track (if the duration of the worst illumination angle is very short, the average illumination angle can be used), the total output power of the solar cell array of the first track is:

[0188] Q SA1 =I mp ×N p ×cosθ1×T L1 / 60

[0189] In the formula, T L1 — Illumination duration (min) for track 1;

[0190] I mp —Last-stage operating current of the solar cell (A).

[0191] Power consumption of the load during the first illumination period:

[0192]

[0193] In the formula, P LL —Long-term load power (W) during the illumination period;

[0194] T L1 — Illumination duration (min) for track 1;

[0195] P S —Short-term load power (W), excluding long-term load power;

[0196] t L1 —Duration (min) of various short-term power consumption parameters during illumination in track 1;

[0197] U Bus —Bus voltage (V), without adjusting the bus, use the lowest bus voltage U. Bus min calculate;

[0198] η T — The transmission efficiency of the power controller or power converter can be assumed to be 1 under near-ideal conditions.

[0199] The maximum charging capacity that can be provided to the battery during the first track illumination period:

[0200] Q c1 =(Q SA1 -Q L1 )×η c

[0201] In the formula, η c —Charging efficiency.

[0202] Maximum total discharge during the shadow period of the first track battery pack:

[0203]

[0204] In the formula: P LS —Long-term load power (W) during the shadow period;

[0205] T S1 —Shadow duration (min) of track 1;

[0206] P S —Short-term load power (W), excluding long-term load power;

[0207] t S1 —Duration (min) of various short-term power consumption parameters during the shadow period in track 1;

[0208] η d —Discharge efficiency;

[0209] N—Number of battery cells connected in series in the battery pack;

[0210] V D —Average discharge voltage of individual cells in the battery pack.

[0211] At the end of track 1, the theoretical cumulative electricity consumption is:

[0212] Q r1 =Q c1 -Q d1

[0213] Take the worst illumination angle θ of the nth track (2≤n≤m) n (When the worst illumination angle lasts for a very short time, the average illumination angle can be used), the total output power of the solar array on the nth track:

[0214] Q SAn =I mp ×N p ×cosθ n ×T Ln / 60

[0215] In the formula, T Ln — Illumination duration (min) of track n;

[0216] I mp —Last-stage operating current of the solar cell (A).

[0217] Power consumption of the load during the nth orbit illumination period:

[0218]

[0219] In the formula, P LL —Long-term load power (W) during the illumination period;

[0220] T Ln — Illumination duration (min) of track n;

[0221] U Bus —Bus voltage (V), without adjusting the bus, use the lowest bus voltage U. Bus min calculate;

[0222] η T —The transmission efficiency of the power controller or power converter can be assumed to be 1 under near-ideal conditions.

[0223] The maximum charging capacity that can be provided to the battery during the nth orbit illumination period:

[0224] Q cn =(Q SAn -Q Ln )×η c

[0225] In the formula, η c —Charging efficiency.

[0226] Maximum total discharge during the shadow period of the nth track battery pack:

[0227]

[0228] In the formula: P LS —Long-term load power (W) during the shadow period;

[0229] T Sn —Shadow duration (min) of track n;

[0230] η d —Discharge efficiency;

[0231] N—Number of battery cells connected in series in the battery pack;

[0232] V D —Average discharge voltage of individual cells in the battery pack.

[0233] Theoretically, the cumulative electricity at the end of the nth track is:

[0234] Q rn =Q cn -Q dn

[0235] Based on the above calculation results, an energy balance analysis table can be generated, as shown in the table below.

[0236] Table 1 Energy Balance Analysis Table

[0237]

[0238] First appeared on orbit m If the discharge depth of each battery is within the allowable range, the satellite can achieve m-cycle balance.

[0239] This invention also discloses a spacecraft multi-cycle energy balance design system, comprising the following modules:

[0240] Module M1: Input condition parameters, including orbit parameters, load parameters, solar cell parameters, battery cell parameters, space environment parameters, and limiting condition parameters;

[0241] Module M2: Selects solar cells and battery cells, and obtains parameters for solar cells and battery cells;

[0242] Module M3: Select the bus regulation method and bus voltage based on the power consumption and model requirements of the entire spacecraft;

[0243] Module M4: Calculates the number of batteries connected in series;

[0244] Module M5: Calculates the number of solar cell arrays connected in series;

[0245] Module M6: Calculates the number of parallel solar cell arrays using a multi-turn balancing algorithm;

[0246] Module M7: Calculates the number of battery banks connected in parallel;

[0247] Module M8: Performs energy balance verification analysis;

[0248] Module M9: Determines whether the spacecraft meets the performance requirements. If it does, the design results are output. If it does not, the parallel design of the solar array and the number of batteries is optimized. After optimization, the process re-enters step S8 for analysis.

[0249] Those skilled in the art will understand that, besides implementing the system and its various devices, modules, and units provided by this invention in the form of purely computer-readable program code, the same functions can be achieved entirely through logical programming of the method steps, making the system and its various devices, modules, and units of this invention function in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers. Therefore, the system and its various devices, modules, and units provided by this invention can be considered as a hardware component, and the devices, modules, and units included therein for implementing various functions can also be considered as structures within the hardware component; alternatively, the devices, modules, and units for implementing various functions can be considered as both software modules implementing the method and structures within the hardware component.

[0250] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A spacecraft multi-cycle energy balance design method, characterized in that, Includes the following steps: Step S1: Input condition parameters, which include orbit parameters, load parameters, solar cell parameters, battery cell parameters, space environment parameters, and limiting condition parameters; Step S2: Select solar cells and battery cells, and obtain the parameters of solar cells and battery cells; Step S3: Select the bus regulation method and bus voltage based on the power consumption and model requirements of the entire spacecraft; Step S4: Calculate the number of batteries connected in series; Step S5: Calculate the number of solar cells connected in series; Step S6: Calculate the number of parallel solar cell arrays using a multi-cycle balancing algorithm; Step S7: Calculate the number of battery banks connected in parallel; Step S8: Perform energy balance verification analysis; Step S9: Determine whether the spacecraft meets the performance requirements. If it does, output the design results. If the requirements are not met, the parallel connection of the solar cell array and the number of batteries will be optimized. After optimization, the process will re-enter step S8 for analysis. The method for calculating the number of parallel solar cell arrays is as follows: Calculate the final operating current of the solar cell: I mp = [ I mpΦ + β IP ( T op – T o )] × S × S ’× F m × F SH In the formula, I mpΦ This indicates that the solar cell has an electron irradiance flux of Φe·cm at 1 MeV energy. -2 Then, at standard temperature T o Operating current surface density at that time; β IP Indicates the average temperature coefficient; S Indicates the effective illuminated area; S ' indicates the influence coefficient of solar cell on Earth-Sun distance; F m This represents the current combination loss factor at the end of the lifespan. F SH This represents the shading factor of a solar cell when it is unshaded. F SH =1; Calculate the current required to supply the load: I = I C + I D In the formula, I C Indicates the current required by the load; P LL This indicates the long-term load power during the illumination period; I indicate Total current required during satellite illumination period; I C Indicates the current required by the load; I D This represents the average current required to charge the battery pack. P LS This indicates the long-term load power during the shadow period; T S Indicates the longest shadow duration of the satellite; m Indicates the number of orbits required for the satellite to achieve equilibrium; P S This indicates short-term load power, excluding long-term load power; t This indicates the duration of operation of various short-term power parameters during the shadow period, with the upper limit being the longest shadow duration. T L Indicates the shortest duration of sunlight exposure for the satellite; η d Indicates discharge efficiency; η c Indicates charging efficiency; N Indicates the number of individual battery cells connected in series in the battery pack; V D This indicates the average discharge voltage of a single battery cell; Calculate the number of parallel solar cell arrays: In the formula, θ Take the worst illumination angle within a year, and consider design margins. N p Round up to the nearest whole number, and take an appropriate margin.

2. The spacecraft multi-cycle energy balance design method according to claim 1, characterized in that: The orbital parameters include orbital period, longest shadow duration per orbit, shortest illumination duration per orbit, and illumination angle; the load parameters include long-term power consumption, short-term power consumption, and average power consumption under various operating modes of the spacecraft; the solar cell parameters include optimal operating voltage per cell, surface current density, cell area, and loss factor. The individual battery parameters include the rated capacity, rated voltage, average discharge voltage, and discharge cutoff voltage of the individual battery; the space environment parameters include the space environment temperature, solar intensity factor, and irradiance; and the limiting condition parameters include the allowable depth of discharge of the battery pack, the voltage drop of the solar array line, and the number of balance turns.

3. The spacecraft multi-cycle energy balance design method according to claim 1, characterized in that: The method for calculating the number of batteries connected in series is as follows: In the formula, Indicates the number of batteries connected in series. Indicates the minimum bus voltage. This indicates the rated voltage of a single battery cell.

4. The spacecraft multi-cycle energy balance design method according to claim 1, characterized in that: The method for calculating the number of solar cell arrays connected in series is as follows: The total output voltage required to obtain the solar cell array is: V SA = V Busmax + V w V mp = V mpΦ × F u + β vp ( T op – T o ) In the formula, V SA This indicates the total output voltage of the solar cell array; V Busmax Indicates the highest voltage of the busbar; V w Indicates bus voltage drop; V mp This indicates the operating voltage of a single solar cell at the end of its lifespan. V mpΦ This indicates that the solar cell has an electron irradiance flux of Φe·cm at 1 MeV energy. -2 Then, at standard temperature T o Operating voltage at that time; F u This represents the voltage combination loss factor at the end of the lifespan. β vp This indicates the temperature coefficient of the operating voltage of a solar cell. T op Indicates the operating temperature of the solar cell; T o This indicates that the standard test temperature for solar cells is 25°C. The formula for calculating the number of solar cell arrays in series is: N s = V SA / V mp。 5. The spacecraft multi-cycle energy balance design method according to claim 1, characterized in that: The method for calculating the number of parallel battery packs is as follows: Calculate the maximum discharge capacity of a single battery bank per revolution: In the formula, P LS This indicates the long-term load power during the shadow period; T S Indicates the longest shadow duration; P S This indicates short-term load power, excluding long-term load power; t This indicates the duration of operation of various short-term power consumption items during the shadow period, with the upper limit being the longest shadow duration. T S ; n Indicates the number of battery packs; η d Indicates discharge efficiency; N Indicates the number of individual battery cells connected in series in the battery pack; V D This indicates the average discharge voltage of a single cell in the battery pack. The minimum capacity required for a single battery pack is: Q = Q d / DOD In the formula, DOD This indicates the maximum permissible depth of discharge. The number of parallel connections for a single battery bank is obtained: N BP = Q / Q n In the formula, Q n This refers to the capacity of a single unit.

6. The spacecraft multi-cycle energy balance design method according to claim 1, characterized in that: The energy balance verification analysis includes: verifying and calculating the energy balance of a single orbit at the end of the on-orbit period based on the set bus voltage, the number of solar cell arrays connected in series and parallel, and the number of battery banks connected in series and parallel.

7. A spacecraft multi-cycle energy balance design system, characterized in that, Includes the following modules: Module M1: Input condition parameters, including orbit parameters, load parameters, solar cell parameters, battery cell parameters, space environment parameters, and limiting condition parameters; Module M2: Selects solar cells and battery cells, and obtains parameters for solar cells and battery cells. Module M3: Select the bus regulation method and bus voltage based on the power consumption and model requirements of the entire spacecraft; Module M4: Calculates the number of batteries connected in series; Module M5: Calculates the number of solar cell arrays connected in series; Module M6: Calculates the number of parallel solar cell arrays using a multi-turn balancing algorithm; Module M7: Calculates the number of battery banks connected in parallel; Module M8: Performs energy balance verification analysis; Module M9: Determines whether the spacecraft meets the performance requirements; if so, outputs the design results. If the requirements are not met, the parallel connection of the solar cell array and the number of batteries will be optimized, and the analysis will be re-entered into module M8 after optimization. The method for calculating the number of parallel solar cell arrays is as follows: Calculate the final operating current of the solar cell: I mp = [ I mpΦ + β IP ( T op – T o )] × S × S ’× F m × F SH In the formula, I mpΦ This indicates that the solar cell has an electron irradiance flux of Φe·cm at 1 MeV energy. -2 Then, at standard temperature T o Operating current surface density at that time; β IP Indicates the average temperature coefficient; S Indicates the effective illuminated area; S ' indicates the influence coefficient of solar cell on Earth-Sun distance; F m This represents the current combination loss factor at the end of the lifespan. F SH This represents the shading factor of a solar cell when it is unshaded. F SH =1; Calculate the current required to supply the load: I = I C + I D In the formula, I C Indicates the current required by the load; P LL This indicates the long-term load power during the illumination period; I indicate Total current required during satellite illumination period; I C Indicates the current required by the load; I D This represents the average current required to charge the battery pack. P LS This indicates the long-term load power during the shadow period; T S Indicates the longest shadow duration of the satellite; m Indicates the number of orbits required for the satellite to achieve equilibrium; P S This indicates short-term load power, excluding long-term load power; t This indicates the duration of operation of various short-term power parameters during the shadow period, with the upper limit being the longest shadow duration. T L Indicates the shortest duration of sunlight exposure for the satellite; η d Indicates discharge efficiency; η c Indicates charging efficiency; N Indicates the number of individual cells connected in series in the battery pack; V D This indicates the average discharge voltage of a single battery cell; Calculate the number of parallel solar cell arrays: In the formula, θ Take the worst illumination angle within a year, and consider design margins. N p Round up to the nearest whole number, and take an appropriate margin.

Images