Method and system for autonomously reducing power consumption in shadow period of low earth orbit satellite

Abstract

The invention provides a method for autonomously reducing power consumption in a shadow period of a low-orbit satellite, and the method comprises the steps: setting a first threshold configuration and a second threshold configuration which comprise different threshold ranges for each heater, and enabling the upper and lower limits of the second threshold configuration to be not lower than those of the first threshold configuration; establishing a mapping relation between a satellite orbital plane solar incident angle and an orbital period illumination duration, and setting a critical solar incident angle as a shadow period control starting condition; the method comprises the following steps: monitoring accumulation time of non-discharge of a storage battery pack in real time, triggering threshold switching condition judgment when a solar incident angle is within a certain range in combination with current illumination period duration and preset heater advanced temperature rise time, and switching from first threshold configuration to second threshold configuration for preheating if a specified condition is met. And after the storage battery is discharged, the first configuration is automatically recovered. Therefore, according to the invention, the discharge depth and the peak discharge current of the storage battery can be autonomously reduced, and the on-orbit energy safety management capability is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite control, and particularly to a method and system for an LEO satellite to autonomously reduce power consumption during the shadow period. Background Art

[0002] During the illumination period, the energy supply of a low-earth orbit (LEO) satellite is relatively sufficient, and the combined discharge of the solar panels and the battery can meet the maximum power load of the entire satellite. However, during the shadow period, only the battery powers the entire satellite. Constrained by cost and launch mass, the design margin of the battery capacity of an LEO satellite is relatively small. However, the service requirements demand that the payload equipment be powered on, and at the same time, the temperature reduction during the shadow period causes the thermal control heaters to operate, resulting in the satellite power consumption during the shadow period often exceeding that during the illumination period, and it is easy to occur that the discharge depth and peak discharge current during the shadow period exceed the upper limit.

[0003] The current heater control method for spacecraft is as follows: when the temperature of the temperature-controlled object is lower than the lower limit of the temperature control threshold, the heater switch is turned on to heat the temperature-controlled object; when the temperature of the temperature-controlled object is higher than the upper limit of the temperature control threshold, the heater switch is turned off to stop heating. Further, each heater can be independently controlled for heating.

[0004] The invention patent with the publication number of CN111086655B discloses a method and system for saving the thermal control compensation power during the shadow period of the non-measurement and control arc segment, including: Step 1: Determine the heater states during the illumination period and the shadow period of the satellite through thermal simulation; Step 2: During the measurement and control arc segment of the satellite, send a thermal control heater program prohibition instruction and a thermal control heater state setting instruction according to the heater state during the illumination period; Step 3: Before the satellite exits the measurement and control arc segment and enters the non-measurement and control arc segment, send a delayed instruction with a time code according to the shadow time prediction of the non-measurement and control arc segment and the heater state during the shadow period, and respectively set the thermal control heater states when entering and exiting the shadow of the non-measurement and control arc segment; Step 4: After the end of the non-measurement and control arc segment and the satellite re-enters the measurement and control arc segment, send a thermal control heater program permission instruction and perform closed-loop control on the heater according to the threshold. This patent is a method for implementing energy management during the shadow period by ground remote control, rather than being autonomously completed by the satellite.

[0005] The invention patent with the publication number CN112528488A discloses a method and system for saving thermal compensation power consumption during the satellite shadow period based on heat capacity differences, including the following steps: Modeling step: Establish a thermal simulation model of the satellite to obtain the temperature change curve of each electronic device over time; Correction step: Correct the heat capacity parameters of each electronic device through a thermal balance test; First calculation step: Calculate the temperature change rate of the electronic device according to the temperature change curve of the electronic device; Determination step: Determine the startup time of the thermal compensation heater before the shadow based on the temperature change curve of the electronic device; Shutdown step: One minute before the satellite enters the shadow period, turn off the thermal compensation heater; Second calculation step: Calculate the shutdown time of the heater during the shadow period; Upload step: Design a delay command according to the startup time and shutdown time of the heater and upload it. This patent implements the on-off control of the thermal compensation heater by means of ground simulation calculation and uploading delay commands for the power control requirements of geostationary satellites, rather than being autonomously completed by the satellite itself.

[0006] The invention patent with the publication number CN117622524A discloses a satellite adaptive energy self-regulating thermal control method and system, including the following steps: Step S1: Set different thermal control modes 1 to N according to the high and low temperature control thresholds of the on-board heaters; Step S2: Based on the judgment of the on-board MEA voltage, when the satellite is in the S3R, BCR, or BDR control area, obtain the output power of the on-board solar array, the charge and discharge of the battery, and the load conditions; Step S3: Calculate the sum of the solar panel voltages and set the reference voltage value of the energy margin; Step S4: The satellite program autonomously selects a thermal control mode according to the energy supply situation. This patent selects corresponding thermal control modes for different MEA voltages for the power control requirements of geostationary satellites, and obviously cannot solve the technical problems existing in low-earth orbit satellites either.

[0007] The invention patent with the publication number CN113734471B discloses a method and system for autonomously coping with the energy shortage during the shadow period of a geostationary satellite, including the following steps: Step S1: The on-board computer forecasts the time and total duration of the satellite entering and leaving the shadow period; Step S2: Calculate the maximum discharge depth of the battery during the shadow period according to the forecast content; Step S3: Develop a targeted energy coping strategy for the shadow period based on the result of the maximum discharge depth of the satellite battery during the shadow period; Step S4: Autonomously generate a programmed delay control command; Step S5: Autonomously execute the strategy before the satellite enters the shadow; Step S6: Autonomously execute the strategy after the satellite enters the shadow; Step S7: Autonomously monitor the energy during the shadow period and take corresponding actions according to the status; Step S8: After the satellite exits the shadow, execute the post-shadow whole-satellite strategy and switch back to the normal output mode. This patent performs different operations for different battery discharge depths for the power control requirements of geostationary satellites, including methods such as shadow period forecasting, whole-satellite synchronous heating, and forced shutdown of heaters during the shadow period, and obviously cannot solve the technical problems existing in low-earth orbit satellites either.

[0008] Therefore, there is an urgent need for a method that can solve the problem that the discharge depth and peak discharge current are likely to exceed the upper limit during the shadow period of low-earth orbit satellites. Summary of the Invention

[0009] In view of the above defects, the object of the present invention is to provide a method and system for a low-earth orbit satellite to autonomously reduce power consumption during the shadow period, which can autonomously reduce the discharge depth and peak discharge current of the battery and improve the on-orbit energy safety management ability.

[0010] To achieve the above technical effects, on the one hand, the present invention provides a method for a low-earth orbit satellite to autonomously reduce power consumption during the shadow period, including the steps of:

[0011] Set a first threshold configuration and a second threshold configuration for each heater of the satellite, where the first threshold configuration includes a first threshold upper limit and a first threshold lower limit, and the second threshold configuration includes a second threshold upper limit and a second threshold lower limit; wherein, the second threshold upper limit is greater than or equal to the first threshold upper limit, and the second threshold lower limit is greater than the first threshold lower limit;

[0012] Establish a correspondence between the solar incidence angle of the satellite orbital plane and the duration of the illuminated period within one orbital period, and set a critical solar incidence angle β for starting power consumption control during the shadow period f ;

[0013] Set a preheating time t for each of the heaters during the shadow period f ;

[0014] Real-time monitor the cumulative undischarged time t of the satellite battery pack B ;

[0015] Real-time calculate the solar incidence angle of the satellite orbital plane, and when the solar incidence angle of the satellite orbital plane is within the range of [-β f , β f , determine whether the specified condition is satisfied, and the specified condition is: t B ≥(t r -t f );

[0016] If the specified condition is satisfied and the heater is currently in the first threshold configuration, switch to the second threshold configuration; where t r is the duration of the illuminated period corresponding to the current solar incidence angle of the satellite orbital plane;

[0017] If the specified condition is not satisfied and the cumulative undischarged time drops to 0, and the heater is currently in the second threshold configuration, switch to the first threshold configuration.

[0018] Further, the lower limit of the first threshold does not exceed the minimum allowable temperature range of the single machine or component, and an engineering margin is reserved;

[0019] The upper limit of the second threshold does not exceed the maximum allowable temperature range of the single machine or component, and an engineering margin is reserved;

[0020] The temperature difference between the lower limit of the first threshold and the lower limit of the second threshold is greater than the temperature drop of the temperature-controlled object when the heater is disconnected during the longest shadow period.

[0021] Further, the critical solar incidence angle is determined based on the impact of the heater on the energy system during the shadow period and supports dynamic adjustment of the instruction.

[0022] Further, the statistical method of the undischarged cumulative time is as follows: when the discharge current of the satellite battery pack drops from a positive value to zero, the undischarged cumulative time starts to accumulate by one per second from zero until the discharge current of the satellite battery pack becomes positive again and is cleared.

[0023] Further, the early warming-up time during the shadow period is less than the minimum value of the illumination period duration in the current satellite orbit and greater than the time required for the heater to warm up from the lower limit of the first threshold to the lower limit of the second threshold.

[0024] On the other hand, the present invention also provides a system for a low-earth orbit satellite to autonomously reduce power consumption during the shadow period. The system is used to execute the method described above and includes:

[0025] A threshold configuration module for storing and managing the first threshold configuration and the second threshold configuration of the heater;

[0026] A parameter setting module for setting the critical solar incidence angle for starting power consumption control during the shadow period and setting the early warming-up time during the shadow period for each heater respectively;

[0027] An orbit parameter calculation module for calculating the solar incidence angle of the satellite orbit plane and the corresponding illumination period duration in real time;

[0028] A battery monitoring module for counting the undischarged cumulative time;

[0029] An autonomous control module for dynamically switching the heater threshold configuration according to the critical solar incidence angle, the early warming-up time during the shadow period, the solar incidence angle of the satellite orbit plane and the corresponding illumination period duration, and the undischarged cumulative time.

[0030] Further, the autonomous control module supports enabling or disabling the power consumption control function during the shadow period through an instruction, and when disabled, it forcibly switches the heater to the first threshold configuration and exits the control logic.

[0031] The method for the low-earth orbit satellite to autonomously reduce power consumption during the shadow period in the present invention is to set a first threshold configuration and a second threshold configuration with different threshold ranges for each heater, where the upper and lower limits of the second threshold configuration are not lower than those of the first threshold configuration; establish a mapping relationship between the solar incidence angle of the satellite orbital plane and the duration of the illuminated period of the orbital period, and set a critical solar incidence angle as the starting condition for shadow period control; by real-time monitoring of the cumulative time of the battery pack not being discharged, combined with the current illuminated period duration and the preset preheating time of the heater, when the solar incidence angle is within a certain range, trigger the judgment of the threshold switching condition. If the specified condition is met, switch from the first configuration to the second configuration for preheating, and automatically restore the first configuration after the battery discharges. In this way, through the coordinated control of the orbital parameters and the battery state, the present invention can autonomously reduce the depth of discharge and peak discharge current of the battery while ensuring the stable temperature of the equipment, effectively reduce the energy consumption during the shadow period, extend the on-orbit operation life of the satellite, and improve the on-orbit energy safety management ability. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 The flowchart of the steps of the method for the low-earth orbit satellite to autonomously reduce power consumption during the shadow period provided by the first embodiment of the present invention;

[0033] Figure 2 The specific control flowchart of the method for the low-earth orbit satellite to autonomously reduce power consumption during the shadow period provided by the first embodiment of the present invention;

[0034] Figure 3 The structural schematic diagram of the system for the low-earth orbit satellite to autonomously reduce power consumption during the shadow period provided by the second embodiment of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0035] In order to make the objectives, technical solutions and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention, and are not used to limit the present invention.

[0036] It should be noted that the references to "one embodiment", "embodiment", "example embodiment", etc. in this specification mean that the described embodiment may include specific features, structures or characteristics, but not every embodiment must include these specific features, structures or characteristics. In addition, such expressions do not refer to the same embodiment. Further, when combining an embodiment to describe specific features, structures or characteristics, whether or not there is an explicit description, it has been shown that it is within the knowledge of those skilled in the art to combine such features, structures or characteristics into other embodiments.

[0037] In addition, certain words are used in the specification and subsequent claims to refer to specific components or parts. Those with ordinary knowledge in the relevant field should understand that manufacturers can use different nouns or terms to refer to the same component or part. This specification and subsequent claims do not use differences in names as a way to distinguish components or parts, but use differences in the functions of components or parts as the criteria for distinction. "Including" and "including" mentioned throughout the specification and subsequent claims are open-ended terms and should be interpreted as "including but not limited to". In addition, the word "connected" here includes any direct and indirect electrical connection means. Indirect electrical connection means include connection through other devices.

[0038] Before describing the embodiments of the present application in detail, the technical concept of the present application is briefly described:

[0039] The present invention uses an onboard computer to autonomously control and dynamically adjust the heater threshold to optimize energy distribution.

[0040] 1. Dual threshold switching: Set two sets of temperature control thresholds for each heater (configuration one and configuration two). 2. Orbit and energy coordination: Establish the relationship between the solar incidence angle and the duration of illumination on the orbital plane, and set the critical angle trigger control logic; monitor the battery undischarge time in real time, and determine the timing of threshold switching based on the remaining illumination time to ensure that the temperature rises before the shadow period. 3. Autonomous closed-loop control: The onboard computer makes autonomous decisions based on the solar incidence angle, the remaining illumination time and the threshold status. It switches to configuration two for heating before the end of the illumination period, and switches back to configuration one to disconnect the heater during the shadow period. No ground intervention is required throughout the process. Adapt to different working conditions through dynamic parameter configuration to improve energy utilization and system reliability.

[0041] The specific principles of the method for autonomously reducing shadow period power consumption of a low-orbit satellite of the present application are described below in conjunction with specific embodiments.

[0042] Figure 1 A method for autonomously reducing power consumption during a shadow period of a low-orbit satellite provided by an embodiment of the present invention is shown. The method is applied to power consumption control of a satellite and includes the following steps:

[0043] S101: Set a first threshold configuration and a second threshold configuration for each heater of the satellite respectively, wherein the first threshold configuration includes a first threshold upper limit and a first threshold lower limit, and the second threshold configuration includes a second threshold upper limit and a second threshold lower limit; wherein the second threshold upper limit is greater than or equal to the first threshold upper limit, and the second threshold lower limit is greater than the first threshold lower limit.

[0044] In this embodiment, the first threshold configuration (T L1 , T H1 ), the second threshold configuration (T L2 , TH2 ) is taken as an example for illustration. T L1 is the lower limit of the first threshold, and T H1 is the upper limit of the first threshold, and T L2 is the lower limit of the second threshold, and T H2 is the upper limit of the second threshold; among them, T H1 > T L1 , and T H2 > T L2 ; and T L2 > T L1 , and T H2 ≥T H1 .

[0045] Furthermore, the lower limit of the first threshold in this embodiment does not exceed the lowest allowable temperature range of the single machine and components, and engineering margin is reserved; the upper limit of the second threshold does not exceed the highest allowable temperature range of the single machine and components, and engineering margin is reserved; the temperature difference between the lower limit of the first threshold and the lower limit of the second threshold is greater than the temperature drop of the temperature-controlled object when the heater is disconnected during the longest shadow period. That is, the setting principle of the first threshold configuration in this embodiment is: T L1 cannot exceed the lowest allowable temperature range of the single machine and components, and the smallest engineering margin is left. This engineering margin is jointly determined by the temperature acquisition accuracy and the low-temperature overshoot of the heater closed-loop control. The setting principle of the second threshold configuration is: 1) T L2 > T L1 , and T H2 ≥T H1 ; 2) T H2 cannot exceed the highest allowable temperature range of the single machine and components, and the smallest engineering margin is left; this engineering margin is jointly determined by the temperature acquisition accuracy and the high-temperature overshoot of the heater closed-loop control; 3) The temperature difference between T L2 and T L1 needs to be greater than the temperature drop of the temperature-controlled object when the heater is disconnected during the longest shadow period; this temperature drop can be obtained through thermal analysis model simulation or calculated based on on-orbit telemetry data.

[0046] In a specific embodiment, at the part that needs to be heated and temperature-controlled, different independent heaters and their switches are set according to the region, heating power, and heating time characteristics to form a temperature-controlled heater. For example, a certain satellite has a total of 100 heaters. Each heater can independently perform autonomous heating control and temperature control threshold parameter setting, and can be prohibited from temperature control or enabled for temperature control. Each heater is respectively configured with its corresponding first threshold configuration and second threshold configuration. For example, the first threshold configuration of a certain "heater 1" is set to [-5°C, 0°C], and the second threshold configuration is set to [2°C, 7°C]. At this time, the temperature difference between -5°C and 2°C is greater than the temperature drop of the temperature-controlled object when the heater is disconnected during the longest 30-minute shadow period.

[0047] S102: Establish the corresponding relationship between the solar incident angle of the satellite orbital plane and the duration of the illumination period in an orbital cycle, and set the critical solar incident angle β for starting the power consumption control during the shadow period f .

[0048] Specifically, the relationship between the solar incidence angle β on the satellite orbit plane and the duration of the illumination period t in one orbital cycle can be established by simulation or based on on-orbit telemetry data. r The corresponding relationship.

[0049] In the setting shadow period, the power consumption control starts the orbital plane solar incidence angle β f When the shadow period is longer than a certain length, the shadow period power consumption control is implemented, β f Determined by the effect of the heater on the energy system during the shadow period; and can be changed by command f That is, the critical solar incident angle β f The influence of the heater on the energy system is determined based on the shadow period, and dynamic adjustment of instructions is supported. f =55° is used as an example for explanation.

[0050] S103: Setting the shadow period advance heating time t for each heater f . Shadow period advance heating time t f Dynamic adjustment of instructions is also supported.

[0051] Furthermore, the advance warm-up time in the shadow period is less than the minimum length of the illumination period in the current satellite orbit, and is greater than the time required for the heater to warm up from the first lower threshold to the second lower threshold.

[0052] That is, the advance temperature rise time t during the shadow period f The setting principles are: 1) The temperature rise time t in advance during the shadow period f Less than the duration of the illumination period in the current satellite orbit t f Minimum value; 2) Advance heating time t during shadow period f It needs to be greater than the temperature of the controlled object after the heater is turned on from T L1 Heating to T L2 time; this heating time can be obtained through thermal analysis model simulation, or by fitting the temperature change curve of on-orbit telemetry data and extrapolating it.

[0053] Combined with the first threshold configuration [-5°C, 0°C] and the second threshold configuration [2°C, 7°C] provided in the above specific example, this embodiment can specifically set the shadow period advance heating time t for the "heater 1" f =900s, at this time 900 seconds can meet the time for the temperature-controlled object to rise from -5°C to 2°C after the heater 1 is turned on.

[0054] S104: Real-time monitor the cumulative undischarged time t of the satellite battery pack B . Specifically, the on-board computer monitors the cumulative undischarged time t in real time B .

[0055] In specific implementation, the statistical method of the cumulative undischarged time is as follows: when the discharge current of the satellite battery pack drops from a positive value to zero, the cumulative undischarged time starts to increment by one per second from zero until the discharge current of the satellite battery pack becomes positive again and is cleared. That is, when the battery discharge current changes from a positive value to 0, t B starts to increment by 1 per second from 0 until the next time the battery discharge current becomes positive, and t B is cleared.

[0056] S105: Real-time calculate the solar incidence angle of the satellite orbital plane, and when the solar incidence angle of the satellite orbital plane is within the range of [-β f , β f , determine whether the specified condition is met. The specified condition is: t B ≥(t r -t f ). The on-board computer monitors the cumulative undischarged time t B in real time, and compares the magnitudes of t B and (t r -t f ), and then determines the subsequent execution steps according to the comparison result.

[0057] In this embodiment, the on-board computer calculates the solar incidence angle β of the satellite orbit in real time, and then determines whether the β angle is within the range of [-β f , β f ; if the β angle is not within the range of [-β f , β f , no operation is performed, this control cycle ends, and it continues to execute in the next control cycle.

[0058] If the β angle falls within the range of [-β f , β f , then further determine whether it satisfies: t B ≥(t r -t f ); if this condition is met, go to step S106, otherwise go to step S107.

[0059] S106: If the specified condition is met and the heater is currently configured with the first threshold, switch to the second threshold configuration; where t r is the illumination period duration corresponding to the current solar incidence angle of the satellite orbital plane. t rThe value of is determined based on the corresponding relationship between the solar incidence angle of the satellite orbital plane in step S102 and the illumination duration within an orbital period.

[0060] That is, the following conditions are satisfied simultaneously: t B ≥(t r -t f ), and the heater is currently set to the first threshold configuration; then change the heater threshold to the second threshold configuration, end this control cycle, and wait for the next control cycle to continue calculating the solar incidence angle of the satellite orbital plane in real time.

[0061] S107: If the specified conditions are not satisfied and the cumulative undischarged time drops to 0, and the heater is currently in the second threshold configuration, then switch to the first threshold configuration. That is, the following conditions are satisfied simultaneously: t B <(t r -t f ), and t B changes from "non-zero" to "0", and the heater threshold is in the second threshold configuration; then change the heater threshold to the first threshold configuration and end this control cycle, waiting for the next control cycle to continue calculating the solar incidence angle of the satellite orbital plane in real time. When the heater is switched to the corresponding threshold configuration, the collected temperature value will be compared with the temperature control threshold. If it is greater than the upper threshold, the heater will be disconnected for control; if it is less than the lower threshold, the heater will be turned on for control.

[0062] After on-orbit verification, the on-board computer software changes the temperature control threshold of heater 1 to [2°C, 7°C] 900 s before entering the shadow period, turns on the heater, and the temperature of the temperature control object rises; after entering the shadow period, the temperature control threshold of heater 1 is changed to [-5°C, 0°C], and the heater is turned off throughout the shadow period. The on-board computer autonomously reduces the discharge depth and peak power during the shadow period on orbit.

[0063] Furthermore, the method provided in this embodiment can be enabled or disabled as needed. When changing from enabled to disabled, regardless of which step in the policy the software is running to, query the current heater threshold configuration status. If it is in the second threshold configuration, then change the heater threshold to the first threshold configuration and exit the software policy at the same time; if it is in the first threshold configuration, directly exit the software policy.

[0064] The method provided in this embodiment realizes autonomous reduction of the battery discharge depth and peak discharge current through the coordinated control of orbital parameters and battery status, effectively reduces the energy consumption during the shadow period, extends the on-orbit operation life of the satellite, and improves the on-orbit energy safety management ability while ensuring that the device temperature meets the requirements.

[0065] See Figure 2 , the specific implementation process of the method provided in this embodiment is as follows:

[0066] 1. First, set the first threshold configuration and the second threshold configuration for each heater, and the specific setting principle is as described above.

[0067] 2. Establish the correspondence between the solar incidence angle of the satellite orbital plane and the duration of the illuminated period within one orbital period.

[0068] 3. Set the critical solar incidence angle β for starting the power consumption control during the shadow period f .

[0069] 4. Set the preheating time t for the heater during the shadow period f .

[0070] 5. Accumulate the undischarged timing in real time, that is, the undischarged cumulative time t B .

[0071] 6. Determine whether the power consumption control function during the shadow period is enabled. If it is prohibited, end the process; otherwise, go to step 7.

[0072] 7. Calculate the solar incidence angle of the orbital plane in real time.

[0073] 8. Determine whether the solar incidence angle of the orbital plane is within the range of [-β f , β f . If it is not within this range, end this control cycle; otherwise, go to step 9.

[0074] 9. Determine whether the following conditions are met: t B ≥(t r -t f ), and the heater is currently set to the first threshold configuration; if the conditions are met, go to step 10; otherwise, go to step 11.

[0075] 10. Change the heater threshold to the second threshold configuration, and end this control cycle.

[0076] 11. Determine whether the following conditions are met: t B changes from "non-zero" to "zero", and the heater threshold is the second threshold configuration; if the conditions are met, change the heater threshold to the first threshold configuration and end this control cycle; otherwise, do nothing and end this control cycle.

[0077] When this control cycle ends, wait for the start of the next control cycle and return to step 6 to loop and execute the subsequent process.

[0078] Figure 3Fig. 0 shows a low-earth orbit satellite autonomous power consumption reduction system 100 during the shadow period provided by another embodiment of the present invention. The system 100 is used to execute the method described in the above embodiment, and includes a threshold configuration module 10, a parameter setting module 20, an orbital parameter calculation module 30, a battery monitoring module 40, and an autonomous control module 50; where:

[0079] The threshold configuration module 10 is used to store and manage the first threshold configuration and the second threshold configuration of the heater; the parameter setting module 20 is used to set the critical solar incidence angle for starting the power consumption control during the shadow period, and set the preheating time in advance for each heater during the shadow period; the orbital parameter calculation module 30 is used to calculate the solar incidence angle of the satellite orbital plane and the corresponding illumination period duration in real time; the battery monitoring module 40 is used to count the cumulative undischarged time; the autonomous control module 50 is used to dynamically switch the heater threshold configuration according to the critical solar incidence angle, the preheating time in advance during the shadow period, the solar incidence angle of the satellite orbital plane and the corresponding illumination period duration, and the cumulative undischarged time.

[0080] Furthermore, the autonomous control module 50 supports enabling or disabling the power consumption control function during the shadow period through an instruction, and when disabled, it forcibly switches the heater to the first threshold configuration and exits the control logic.

[0081] In summary, the method for the low-earth orbit satellite to autonomously reduce the power consumption during the shadow period of the present invention realizes the autonomous reduction of the power consumption of the low-earth orbit satellite during the shadow period, reduces the ground labor cost, improves the operation and management efficiency, and enhances the usability of the satellite. The present invention autonomously completes the adjustment of the heater threshold before and after the shadow period, realizes the disconnection of the heater during the satellite shadow period, reduces the energy consumption during the shadow period, and is beneficial to the energy security of the satellite. Since the shunt energy of the solar wing during the trickle charging stage of the battery before entering the shadow period is used to supply the heater, the utilization rate of the output energy of the solar wing is improved, which is beneficial to the energy balance of the satellite. Moreover, the satellite heater can be controlled separately by the preheating time and threshold in advance, and the parameters can be set, which can adapt to the flexible combination and rapid switching of different on-orbit working conditions. Without changing the current satellite thermal control temperature control logic, the present invention can be widely applied to spacecrafts with the ability of agile switching of heaters, or other devices similar to the satellite temperature control logic.

[0082] It should be noted that the present invention can be implemented in software and / or a combination of software and hardware. For example, it can be implemented using an application specific integrated circuit (ASIC), a general purpose computer, or any other similar hardware device. In one embodiment, the software program of the present invention can be executed by a processor to implement the above steps or functions. Similarly, the software program of the present invention (including related data structures) can be stored in a computer-readable recording medium, such as a RAM memory, a magnetic or optical drive, or a floppy disk and similar devices. Additionally, some steps or functions of the present invention can be implemented using hardware, for example, as a circuit that cooperates with the processor to execute each step or function.

[0083] The present invention can be implemented on a computer as a computer-implemented method, or in dedicated hardware, or in a combination of both. The executable code or portions thereof for the method according to the present invention can be stored on a computer program product. Examples of computer program products include memory devices, optical storage devices, integrated circuits, servers, online software, etc. Optionally, the computer program product includes non-temporary program code components stored on a computer-readable medium for executing the method according to the present invention when the program product is executed on a computer.

[0084] In an alternative embodiment, the computer program includes computer program code components suitable for executing all the steps of the method according to the present invention when the computer program is run on a computer. Optionally, the computer program is embodied on a computer-readable medium.

[0085] It should be noted that in this document, the term "comprising", "including" or any other variation thereof is intended to cover non-exclusive inclusion, such that a process, method, article or device comprising a series of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article or device. Without further limitation, an element defined by the phrase "comprising a..." does not exclude the presence of additional identical elements in the process, method, article or device comprising such element. In addition, it should be pointed out that the scope of the methods and devices in the embodiments of the present invention is not limited to performing functions in the order shown or discussed, and may also include performing functions in a substantially simultaneous manner or in a reverse order according to the functions involved. For example, the described methods can be performed in an order different from that described, and various steps can be added, omitted, or combined. Additionally, features described with reference to certain examples can be combined in other examples.

[0086] Of course, the present invention may have many other embodiments. Without departing from the spirit and essence of the present invention, those skilled in the art can make various corresponding changes and modifications according to the present invention. However, these corresponding changes and modifications should all fall within the protection scope of the appended claims of the present invention.

Claims

1. A method for autonomously reducing power consumption during shadow period of low-orbit satellite, characterized in that: Includes steps: Setting a first threshold configuration and a second threshold configuration for each heater of the satellite respectively, wherein the first threshold configuration includes a first threshold upper limit and a first threshold lower limit, and the second threshold configuration includes a second threshold upper limit and a second threshold lower limit; wherein the second threshold upper limit is greater than or equal to the first threshold upper limit, and the second threshold lower limit is greater than the first threshold lower limit; Establish the corresponding relationship between the solar incidence angle of the satellite orbital plane and the duration of the illumination period within an orbital cycle, and set the critical solar incidence angle β for starting the power consumption control during the shadow period f ; Set the shadow period advance heating time t for each heater respectively f ; Real-time monitoring of the satellite battery pack's undischarged cumulative time t B ; The solar incident angle of the satellite orbit plane is calculated in real time, and when the solar incident angle of the satellite orbit plane is between [-β f , β f ] range, determine whether the specified condition is met, the specified condition is: t B ≥(t r -t f ); If the specified condition is met and the heater is currently in the first threshold configuration, it is switched to the second threshold configuration; wherein, t r The duration of the illumination period corresponding to the solar incidence angle of the current satellite orbital plane; If the specified condition is not met, and the accumulated non-discharge time drops to 0, and the heater is currently in the second threshold configuration, then it is switched to the first threshold configuration.

2. The method for autonomously reducing power consumption during shadow period of low-orbit satellite according to claim 1, characterized in that: The lower limit of the first threshold does not exceed the minimum allowable temperature range of a single machine or component, and a project margin is reserved; The upper limit of the second threshold value does not exceed the maximum allowable temperature range of a single machine or component, and a project margin is reserved; The temperature difference between the first threshold lower limit and the second threshold lower limit is greater than the temperature drop of the temperature-controlled object when the heater is disconnected during the longest shadow period.

3. The method for autonomously reducing shadow period power consumption of a low-orbit satellite according to claim 1, characterized in that: The critical solar incidence angle is determined based on the impact of the heater on the energy system during the shadow period, and supports dynamic adjustment of instructions.

4. The method for autonomously reducing shadow period power consumption of a low-orbit satellite according to claim 1, characterized in that: The statistical method of the non-discharge cumulative time is: when the discharge current of the satellite battery pack drops from a positive value to zero, the non-discharge cumulative time starts from zero and increases by one per second until it is reset to zero when the discharge current of the satellite battery pack becomes positive again.

5. The method for autonomously reducing shadow period power consumption of a low-orbit satellite according to claim 1, characterized in that: The shadow period advance heating time is less than the minimum length of the illumination period in the current satellite orbit, and is greater than the time required for the heater to heat up from the first threshold lower limit to the second threshold lower limit.

6. A system for autonomously reducing power consumption during shadow period of low-orbit satellite, characterized in that: The system is used to execute the method according to any one of claims 1 to 5, comprising: a threshold configuration module, configured to store and manage the first threshold configuration and the second threshold configuration of the heater; A parameter setting module, used to set a critical solar incident angle for starting power consumption control during the shadow period, and to set an advance heating time during the shadow period for each of the heaters; An orbital parameter calculation module is used to calculate the solar incidence angle of the satellite orbital plane and the corresponding illumination period in real time; A battery monitoring module, used to count the accumulated non-discharge time; The autonomous control module is used to dynamically switch the heater threshold configuration according to the critical solar incident angle, the advance heating time during the shadow period, the solar incident angle of the satellite orbit plane and the corresponding illumination period length, and the accumulated non-discharge time.

7. The system for autonomously reducing power consumption during shadow period of low-orbit satellite according to claim 6 is characterized in that: The autonomous control module supports enabling or disabling the shadow period power consumption control function through instructions, and when disabled, forces the heater to switch to the first threshold configuration and exits the control logic.

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