Satellite power supply energy balance point calculation method

Abstract

A satellite power supply energy balance point calculation method belongs to the technical field of satellite power supply method optimization, and comprises the following steps: S1: inputting satellite working parameters and power supply energy balance requirement data at a PC end; S2: constructing a power supply energy balance calculation model; and S3: generating a storage battery and solar cell panel configuration list meeting the satellite power supply energy balance requirement. Under the joint action of the related steps, the present application adopts integral calculation and cyclic calculation to replace the simple mathematical operation of the prior art, and introduces a satellite running time storage battery real-time voltage data model to replace the single storage battery voltage data calculation of the prior art, thereby improving the calculation efficiency and accuracy of the power supply energy balance, outputting the solar cell panel and storage battery configuration meeting the power supply energy balance requirement instead of a single configuration, providing multiple solar cell panel and storage battery matching selection for subsequent design and production, and avoiding overdesign.

Description

Technical Field

[0001] This invention relates to the field of satellite power supply optimization technology, and in particular to a method for calculating the energy balance point of satellite power supply. Background Technology

[0002] Existing conventional satellites typically use solar panels and batteries to power their onboard equipment. For satellites to function properly, a stable and reliable power supply is required. Therefore, appropriately sized solar panels are needed to charge batteries of suitable capacity. This means ensuring that the power output from the solar panels can reliably charge the batteries, preventing over-discharge or over-charge that could compromise the onboard equipment's power supply or shorten the battery's lifespan.

[0003] To understand whether the satellite's power supply is balanced (that the power output from the solar panels is sufficient to charge the batteries and power the onboard equipment without overcharging the batteries), and to determine the appropriate power output of the solar panels and batteries in the subsequent satellite design and manufacturing, it is necessary to calculate the balance of the satellite's power supply. Existing methods for calculating satellite power supply balance are based on simple mathematical operations, resulting in a limited range of calculations and outputs. Typically, a single calculation can only provide one configuration for both batteries and solar panels. Furthermore, the calculations neglect the impact of battery voltage variations from high to low, directly substituting the lowest possible battery voltage value into the mathematical calculations. This leads to a degree of over-design (i.e., the actual designed and manufactured onboard solar panels have excessively high output power, and the onboard batteries have excessively large capacities). Summary of the Invention

[0004] To overcome the shortcomings of existing methods for calculating the energy balance of satellite power supply, as described in the background section, due to technological limitations, this invention provides a method for calculating the energy balance point of satellite power supply. This method uses integral and iterative calculations to replace simple mathematical operations, and introduces a real-time battery voltage data model during satellite operation to replace single battery voltage data. This improves the calculation efficiency and accuracy of energy balance, and outputs solar panel and battery configuration data that meet energy balance requirements. This method can provide multiple options for matching solar panels and batteries for subsequent design and production, and avoids over-design.

[0005] The technical solution adopted by this invention to solve its technical problem is:

[0006] A method for calculating the energy balance point of satellite power supply includes the following steps: S1: Input satellite operating parameters and power supply energy balance requirements data on the PC. The satellite operating parameters include the period of one orbital revolution, satellite power supply bus voltage, satellite power supply load power consumption, load operating time, output power of onboard solar panels per unit area, onboard battery charging efficiency, and onboard battery discharging efficiency. The above parameters and data are the input conditions for building the energy balance calculation model. The power supply energy balance requirements mainly select current-cycle balance or multi-cycle balance. Current-cycle balance means that the energy reaches current-cycle balance when the accumulated remaining battery power calculated within one orbital cycle is greater than or equal to zero. Multi-cycle balance means that the energy balance is achieved when the satellite's energy balance is calculated within multiple orbital cycles. S1: Calculate the battery charge and discharge amounts per revolution. When the calculated cumulative remaining charge for a certain revolution is greater than or equal to zero, the energy reaches multi-revolution balance. S2: Based on the data obtained in step S1, construct a power supply energy balance calculation model. This model includes calculating battery charge, discharge, and remaining charge, setting calculation boundary conditions, and determining whether the energy is balanced. To improve the accuracy of the power supply energy balance calculation model, a real-time battery voltage model obtained during satellite operation is introduced into the battery calculation model. S3: Perform iterative calculations based on the various input parameters from step S1 and the model established in step S2 to generate a battery and solar panel configuration list that meets the satellite's power supply energy balance requirements.

[0007] Furthermore, in step S2, the input parameters of the real-time battery voltage model include battery voltage, discharge current, and discharge time. Based on different battery voltage, discharge current, and discharge time data, and considering the load power consumption and working time data provided by the satellite working parameters, a parameter table of battery voltage and corresponding time is formulated and output to provide accurate real-time battery voltage for the power supply energy balance calculation model in step S3.

[0008] Furthermore, in step S2, the boundary conditions refer to the upper limit values ​​of the battery capacity and solar panel area in the energy balance calculation model. The purpose is to avoid the result that the battery capacity or solar panel area is infinitely large. The energy balance only calculates the case where the value is ≤ the upper limit value, and the battery capacity and solar panel area data in the output configuration table should also be ≤ the corresponding upper limit value.

[0009] Furthermore, in step S3, the power supply energy is judged to be balanced by cyclically calculating the battery charge, battery discharge, remaining power, and battery discharge depth. Based on the calculation results, a configuration table composed of three data points—battery capacity, battery discharge depth, and solar array area—is output. Designers can select the optimal battery + solar panel configuration based on the configuration table.

[0010] Furthermore, in step S3, if the power supply balance requirement is single-cycle balance, the calculation formula is as follows:

[0011]

[0012] Remaining battery capacity = Battery charge amount - Battery discharge amount

[0013] Depth of discharge of battery = Discharge amount of battery / Set battery capacity.

[0014] To determine whether the energy has reached a balance, if the remaining charge is ≥ 0, the power supply energy has reached a balance; otherwise, it has not.

[0015] Furthermore, in step S3, if the energy balance requirement is multi-cycle balance, the calculation formula is as follows:

[0016] First lap:

[0017] Remaining battery capacity = Battery charge amount - Battery discharge amount

[0018] Specifically, if the power supply in the first cycle is not balanced, the remaining power in that cycle will be negative.

[0019] Second lap:

[0020] Remaining power = Battery charge - Battery discharge + Remaining power from the previous cycle

[0021] Battery depth of discharge = (Battery discharge amount in this cycle - Remaining charge in the previous cycle) / Set battery capacity.

[0022] Specifically, if the remaining power in a given cycle is ≥0, then the power supply has reached a balance of 2 cycles; otherwise, it has not.

[0023] Compared with the prior art, the beneficial effects of this invention are as follows: Under the combined action of related steps, this invention combines multiple real-time satellite operation data received, and uses integral calculation and cyclic calculation to replace the simple mathematical operations of the prior art. It also introduces a real-time battery voltage data model during satellite operation to replace the existing technology's calculation using a single battery voltage data, thereby improving the calculation efficiency and accuracy of power supply energy balance. The output is a solar panel and battery configuration that can meet the power supply energy balance requirements, rather than a single configuration. This can provide multiple matching options for solar panels and batteries for subsequent design and production, and avoid over-design. Attached Figure Description

[0024] Figure 1 This is a flowchart of the calculation process of the present invention. Detailed Implementation

[0025] Figure 1 As shown, a method for calculating the energy balance point of satellite power supply includes the following steps: Step (1): Input satellite operating parameters and power supply energy balance requirements data on the PC. The satellite operating parameters include the period of one orbit of the satellite (including T). 光照时间 T 阴影时间 (unit: minutes), bus voltage V 母线 (unit: V), load power consumption P 负载 (Unit: W), Working Time: T 工作时间 (Unit: minutes), Output power per unit area of ​​solar cell array (P) 单位太阳 (Unit: W / m) 2 ), charging efficiency Discharge efficiency The parameters and data mentioned above are the input conditions for building the energy balance calculation model. The main requirements for power supply energy balance are to choose between current-cycle balance and multi-cycle balance. Current-cycle balance means that the energy reaches current-cycle balance when the cumulative remaining battery charge calculated within one orbital cycle is greater than or equal to zero. Multi-cycle balance means that within multiple orbital cycles, the energy reaches multi-cycle balance when the cumulative remaining battery charge and discharge of the battery in each orbit are calculated, and the energy reaches multi-cycle balance when the cumulative remaining battery charge in a certain orbit is greater than or equal to zero.

[0026] Figure 1 As shown, step (2): Based on the data obtained in step (1), a power supply energy balance calculation model is constructed. The power supply energy balance calculation model includes calculating the battery charging amount, calculating the battery discharging amount, calculating the remaining power, setting the calculation boundary conditions, and judging whether the energy is balanced. In order to improve the accuracy of the power supply energy balance calculation model, the real-time battery voltage model obtained during satellite operation is introduced into the battery calculation model. The input parameters of the real-time battery voltage model include battery voltage, discharge current, and discharge time. Based on different battery voltage, discharge current, and discharge time data, and for the load power consumption and working time data provided by the satellite working parameters, a parameter table of battery voltage and corresponding time is formulated and output to provide accurate real-time battery voltage for the power supply energy balance calculation model in step (3), as shown in Table 1 below.

[0027] 00:00:00 4.10 00:00:10 4.10 00:00:20 4.10 。。。 。。。 00:30:00 3.85 。。。 。。。

[0028] Table 1

[0029] In Table 1, the discharge time length = T 阴影时间The time interval is tentatively set at 10 seconds (adjustable). In subsequent steps, when performing power supply energy balance calculations, battery voltage data can be input in real-time by looking up a table. Boundary conditions refer to the upper limits of the battery capacity and solar panel area in the energy balance calculation model. This is to avoid results where the battery capacity or solar panel area is infinitely large. Energy balance calculations only consider cases where the value is ≤ the upper limit, and the battery capacity and solar panel area data in the output configuration table should also be ≤ the corresponding upper limit values.

[0030] Figure 1 As shown, step (3): Based on the various input parameters in step (1) and the model established in step (2), perform iterative calculations to generate a battery and solar panel configuration list that meets the energy balance requirements of satellite power supply. In this step, the battery charging capacity (in Ah), battery discharging capacity (in Ah), remaining capacity (in Ah), and battery discharge depth are iteratively calculated to determine whether the power supply energy has reached a balance. Based on the calculation results, a configuration table consisting of three data points—battery capacity, battery discharge depth, and solar panel area—is output. Designers can select the optimal battery + solar panel configuration based on the configuration table (as shown in Table 2).

[0031]

[0032] Table 2

[0033] In the table, the percentage data represents the battery depth of discharge, and " / " indicates that the energy has not reached equilibrium under this configuration; the maximum battery capacity is 8Ah, the capacity interval is set to 0.5Ah, and the maximum solar array area is 4m². 2 The area interval is set to 0.1m. 2 Both the upper limit and interval settings can be modified according to user requirements. Designers can determine the required maximum battery discharge depth based on the working life and usage requirements, and select the corresponding battery capacity and solar array area configuration from the table. For example, when the maximum battery discharge depth requirement is 40%, the user can choose a configuration that satisfies energy balance: a battery capacity of not less than 5Ah + a solar array area of ​​not less than 2.5m². 2 .

[0034] Specifically, in step (3), if the power supply energy balance requirement is single-cycle balance, the calculation formula is as follows:

[0035]

[0036] Remaining battery capacity = Battery charge amount - Battery discharge amount

[0037] Depth of discharge of battery = Discharge amount of battery / Set battery capacity.

[0038] To determine whether the energy has reached a balance, if the remaining charge is ≥ 0, the power supply energy has reached a balance; otherwise, it has not.

[0039] If the energy balance requirement is multi-cycle balance, taking two-cycle balance as an example, the calculation formula is as follows.

[0040] First lap:

[0041] Remaining battery capacity = Battery charge amount - Battery discharge amount

[0042] Specifically, if the power supply in the first cycle is not balanced, the remaining power in that cycle will be negative.

[0043] Second lap:

[0044] Remaining power = Battery charge - Battery discharge + Remaining power from the previous cycle

[0045] Battery depth of discharge = (Battery discharge amount in this cycle - Remaining charge in the previous cycle) / Set battery capacity.

[0046] Specifically, if the remaining power in a given cycle is ≥0, then the power supply has reached a balance of 2 cycles; otherwise, it has not.

[0047] In the calculation formula, the power consumption of the first load cycle is P. 负载1 Working hours are T 时间1 The power consumption of the second load cycle is P. 负载2 Working hours are T 时间2 Because when energy requires balance across multiple cycles, the load power consumption and operating time will be different for each cycle; otherwise, it will never be possible to achieve balance.

[0048] Figure 1 As shown, through the above technical solution, this invention combines received real-time satellite operational data and uses integral and iterative calculations to replace the simple mathematical operations of existing technologies. Furthermore, it introduces a real-time battery voltage data model during satellite operation to replace the single battery voltage data calculation used in existing technologies. This improves the calculation efficiency and accuracy of power supply energy balance, outputting solar panel and battery configurations that meet power supply energy balance requirements, rather than a single configuration. This provides multiple options for matching solar panels and batteries for subsequent design and production, and avoids over-design.

[0049] The foregoing has shown and described the basic principles and main features of the present invention, as well as its advantages. It will be apparent to those skilled in the art that the present invention is limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from its spirit or basic characteristics. Therefore, the embodiments should be considered exemplary and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, it is intended that all variations falling within the meaning and scope of equivalents of the claims be included within the present invention.

[0050] Furthermore, it should be understood that although this specification describes the embodiments, the embodiments do not necessarily contain only one independent technical solution. This way of describing the specification is only for clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in the embodiments can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A method for calculating the energy balance point of satellite power supply, characterized in that, The process includes the following steps: S1: Input the satellite operating parameters and power supply energy balance requirements data on the PC. The satellite operating parameters include the cycle of one orbit, the satellite power supply bus voltage, the power consumption of the satellite power supply load, the load working time, the output power of the onboard solar panel per unit area, the charging efficiency of the onboard battery, and the discharging efficiency of the onboard battery. The above parameters and data are the input conditions for building the energy balance calculation model. The power supply energy balance requirements mainly involve selecting current-cycle balance or multi-cycle balance. Current-cycle balance means that the energy reaches current-cycle balance when the cumulative remaining battery charge calculated within one orbit cycle is greater than or equal to zero. Multi-cycle balance means that within multiple orbit cycles, the battery charge and discharge amount are calculated for each orbit of the satellite. When the cumulative remaining battery charge calculated for a certain orbit cycle is greater than or equal to zero, the energy reaches multi-cycle balance. S2: Based on the data obtained in step S1, construct a power supply energy balance calculation model. This model includes calculating battery charging capacity, battery discharging capacity, remaining battery capacity, setting calculation boundary conditions, and determining energy balance. To improve the accuracy of the power supply energy balance calculation model, a real-time battery voltage model obtained during satellite operation is introduced into the battery calculation model. S3: Based on the various input parameters from step S1 and the model established in step S2, perform iterative calculations to generate a battery and solar panel configuration list that meets the satellite's power supply energy balance requirements. In step S3, if the power supply energy balance requirement is single-cycle balance, the calculation formula is as follows: Battery charging capacity = (Set solar array area × P) 单位太阳 / V 母线 -P 负载 / V 母线 )×T 光照时间 ×ή 充 / 60, Battery discharge capacity = (P 负载 ×T 工作时间 ) / (Real-time battery voltage × ή 放 The remaining battery capacity is calculated as follows: (S1) / 60. The remaining battery capacity equals the battery charge amount minus the battery discharge amount. The battery discharge depth equals the battery discharge amount divided by the set battery capacity. To determine if energy balance has been achieved, if the remaining battery capacity is ≥ 0, the power supply is balanced; otherwise, it is not. In step S3, if the energy balance requirement is multi-turn balance, the calculation formula is as follows: First cycle: Battery charge = (Set solar array area × P) 单位太阳 / V 母线 -P 负载1 / V 母线 )×T 光照时间 ×ή 充 / 60, Battery discharge capacity = (P 负载1 ×T 工作时间1 ) / (Real-time battery voltage × ή 放 ) / 60, Remaining power = Battery charge - Battery discharge. Specifically, if the power supply in the first cycle is not balanced, the remaining power in that cycle will be negative; Second cycle: Battery charge = (Set solar array area × P) 单位太阳 / V 母线 -P 负载2 / V 母线 )×T 光照时间 ×ή 充 / 60, Battery discharge capacity = (P 负载2 ×T 工作时间2 ) / (Real-time battery voltage × ή 放 ) / 60, Remaining power = Battery charging amount - Battery discharging amount + Remaining power in the previous cycle, Battery discharge depth = (Battery discharge amount in this cycle - Remaining power in the previous cycle) / Set battery capacity. Specifically, if the remaining power in this cycle is ≥ 0, the power supply energy reaches the balance of 2 cycles, otherwise it has not reached the balance.

2. The method for calculating the energy balance point of satellite power supply according to claim 1, characterized in that, In step S2, the input parameters of the real-time battery voltage model include battery voltage, discharge current, and discharge time. Based on different battery voltage, discharge current, and discharge time data, and considering the load power consumption and working time data provided by the satellite working parameters, a parameter table of battery voltage and corresponding time is formulated and output to provide accurate real-time battery voltage for the power supply energy balance calculation model in step S3.

3. The method for calculating the energy balance point of satellite power supply according to claim 1, characterized in that, In step S2, the boundary conditions refer to the upper limit values ​​of the battery capacity and solar panel area in the energy balance calculation model. The purpose is to avoid the result that the battery capacity or solar panel area is infinitely large. The energy balance only calculates the case where the value is ≤ the upper limit value. The battery capacity and solar panel area data in the output configuration table should also be ≤ the corresponding upper limit value.

4. The method for calculating the energy balance point of satellite power supply according to claim 1, characterized in that, In step S3, the battery charging amount, battery discharging amount, remaining power, and battery discharge depth are calculated cyclically to determine whether the power supply energy has reached a balance. Based on the calculation results, a configuration table consisting of three data points—battery capacity, battery discharge depth, and solar array area—is output. Designers can select the optimal battery + solar panel configuration based on the configuration table.

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