Deep space probe energy management strategy design method
By employing a three-level collaborative protection strategy for the energy management of deep space probes, the energy security of deep space probes under different solar radiation intensities and electric propulsion systems has been solved, achieving stable control and efficient utilization of spacecraft load power.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-12-05
- Publication Date
- 2026-03-27
AI Technical Summary
Existing technologies struggle to effectively manage the energy security of deep space probes under varying solar radiation intensities and electric propulsion system operating points, leading to significant variations in spacecraft load power and impacting the probe's stable operation.
A deep space probe energy management strategy was designed, including a three-level coordinated strategy of undervoltage protection for the electric propulsion power unit, fixed operating point protection for the power controller, and energy security protection for the entire platform. Energy security is ensured by adjusting the combined power supply of the solar array and the lithium-ion battery.
By effectively managing the spacecraft's load power in response to changes in solar intensity and the operating point of the electric propulsion system, the electrical safety of the probe's equipment is ensured, and energy efficiency and stability are improved.
Smart Images
Figure CN121734699A_ABST
Abstract
Description
Technical Field
[0001] This invention belongs to the field of energy control and management technology for deep space exploration spacecraft, and particularly relates to a design method for energy management strategies for deep space probes. Background Technology
[0002] With the development of my country's aerospace technology, the exploration of the unknown realms of outer space is deepening. The operational range of spacecraft has expanded to interplanetary space, and how to conduct space exploration in deep space poses new challenges to space power systems.
[0003] The distance between deep-space spacecraft and the sun ranges from 1 AU to several AU or even tens of AU, and the solar intensity ranges from 1 AM0 near Earth to 0.1 AM0 or even lower. This results in a wide variation in the output power of the solar arrays. Simultaneously, the spacecraft employs an electric propulsion system, which has many operating points. The long-term load power of the spacecraft varies greatly, from tens of kilowatts at the beginning of its lifespan to hundreds of watts at the end. Therefore, it is necessary to rationally manage the spacecraft's load power, ensuring that the electric propulsion system operates at its highest possible operating point. This guarantees that the spacecraft can achieve mission fulfillment while maintaining a lightweight design, posing a significant challenge to the energy safety management strategy of the probe. Summary of the Invention
[0004] The technical problem solved by this invention is to overcome the shortcomings of the prior art and provide a design method for energy management strategy of deep space probes, which ensures energy security during the flight phase of deep space electric propulsion probes.
[0005] The objective of this invention is achieved through the following technical solution: a deep space probe energy management strategy design method, comprising: when electric propulsion is in operation, the overall energy safety strategy is executed in the logical order of undervoltage protection of the electric propulsion power supply unit, fixed operating point protection of the power controller, and energy safety protection of the entire probe platform; when electric propulsion is not in operation, the overall energy safety strategy is executed in the logical order of fixed operating point protection of the power controller and energy safety protection of the entire probe platform.
[0006] In the aforementioned deep space probe energy management strategy design method, the undervoltage protection of the electric propulsion power unit includes: when the power of the electric propulsion power unit exceeds the tolerance or the output power of the solar array is abnormal, the sum of the electric propulsion power and the platform power exceeds the output power of the solar array, and the operating point of the solar array will shift to the left until it reaches the undervoltage protection point V of the electric propulsion power unit. u V is required u <V Hbus This triggers the undervoltage protection shutdown of the electric propulsion power unit; where V Hbus This is the output voltage of the high-voltage bus. If the output power of the solar array meets the power requirements of the platform after the electric propulsion power unit is shut down, the solar array will work at a new operating point, and the output voltage of the solar array will be within the normal range.
[0007] In the aforementioned deep space probe energy management strategy design method, the power controller's fixed operating point protection includes: if the output power of the solar array still cannot meet the platform's power requirements after the electric propulsion power unit is shut down, in order to improve the energy utilization rate of the solar array, the power controller will adjust the solar array's operating point to the fixed operating point V of the solar array. s V is required s <V u <V Hbus The lithium-ion battery participates in the discharge, and the solar cell array discharges together with the lithium-ion battery to ensure the stable operation of the detector. When the detector load decreases or the output power of the solar cell array increases, causing the detector load power to be less than the output power of the solar cell array, the power controller exits the fixed operating point mode and operates at the new operating point.
[0008] In the aforementioned deep space probe energy management strategy design method, the overall platform energy safety protection includes: when the battery discharge causes the battery discharge depth to increase, when the battery discharge depth increases by more than 20%, and the actual battery discharge depth reaches 40% to 60%, the entire probe will automatically activate the system-level energy safety protection strategy, including controlling the probe to turn towards the sun and shutting down the equipment on the probe in order of load priority from lowest to highest, reducing power demand, and waiting for ground processing and recovery.
[0009] In the above-mentioned deep space probe energy management strategy design method, when the probe is working normally during illumination, the output power of the solar cell array is greater than the load power of the probe, the output voltage of the solar cell array is located to the right of the optimal operating point of the solar cell array IV curve, and the output voltage of the solar cell array changes accordingly with the size of the load.
[0010] In the aforementioned deep space probe power management strategy design method, the high-voltage bus output voltage is 70V~110V, and the low-voltage bus output voltage is V Lbus The voltage range is 23V to 29V.
[0011] A deep space probe energy management strategy design system includes: a first module, used when electric propulsion is in operation, the overall energy safety strategy is executed in the logical order of undervoltage protection of the electric propulsion power supply unit, fixed operating point protection of the power controller, and energy safety protection of the entire probe platform; and a second module, used when electric propulsion is not in operation, the overall energy safety strategy is executed in the logical order of fixed operating point protection of the power controller and energy safety protection of the entire probe platform.
[0012] In the aforementioned deep space probe energy management strategy design system, the undervoltage protection of the electric propulsion power unit includes: when the power of the electric propulsion power unit exceeds the tolerance or the output power of the solar array is abnormal, the sum of the electric propulsion power and the platform power exceeds the output power of the solar array, and the operating point of the solar array will shift to the left until it reaches the undervoltage protection point V of the electric propulsion power unit. u V is required u <V Hbus This triggers the undervoltage protection shutdown of the electric propulsion power unit; where V Hbus This is the output voltage of the high-voltage bus. If the output power of the solar array meets the power requirements of the platform after the electric propulsion power unit is shut down, the solar array will work at a new operating point, and the output voltage of the solar array will be within the normal range.
[0013] In the aforementioned deep space probe energy management strategy design system, the power controller's fixed operating point protection includes: if the output power of the solar array is still insufficient to meet the platform's power requirements after the electric propulsion power unit is shut down, the power controller will adjust the solar array's operating point to the fixed operating point V of the solar array in order to improve the energy utilization rate of the solar array. s V is required s <V u <V Hbus The lithium-ion battery participates in the discharge, and the solar cell array discharges together with the lithium-ion battery to ensure the stable operation of the detector. When the detector load decreases or the output power of the solar cell array increases, causing the detector load power to be less than the output power of the solar cell array, the power controller exits the fixed operating point mode and operates at the new operating point.
[0014] In the aforementioned deep space probe energy management strategy design system, the overall platform energy safety protection includes: when the battery discharge causes the battery discharge depth to increase, when the battery discharge depth increases by more than 20%, and the actual battery discharge depth reaches 40% to 60%, the entire probe will automatically activate the system-level energy safety protection strategy, including controlling the probe to turn towards the sun and shutting down the equipment on the probe in order of load priority from lowest to highest, reducing power demand, and waiting for ground processing and recovery.
[0015] Compared with the prior art, the present invention has the following advantages:
[0016] (1) This invention, through the coordinated cooperation of three-level energy security strategies—undervoltage protection of the electric propulsion power unit, fixed operating point protection of the power controller, and energy security protection of the entire platform—ensures the energy security of the entire platform equipment while guaranteeing the high operating point operation of the electric propulsion system, and ensures that the power safety of the detector equipment is not endangered; the load power is controlled according to the power output of the solar cell array; for high-voltage, high-power loads, the working power level is controlled; when the output power of the solar cell array is tight, the switching control of high-voltage, high-power loads is carried out; for low-voltage loads, the switching control of the load is carried out according to the power load priority.
[0017] (2) The present invention adopts a variable operating point control strategy for the solar cell array. When the power of the solar cell array meets the load, the operating point of the solar cell array changes accordingly with the load. When the solar cell array cannot meet the load power requirements, a fixed operating point control strategy for the solar cell array is adopted to make the most of the solar cell array energy. The lithium-ion battery pack participates in the discharge, and the low-voltage load of the platform is jointly powered by the solar cell array and the lithium-ion battery pack. Attached Figure Description
[0018] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings:
[0019] Figure 1 This is a structural block diagram of the deep space probe power system provided in an embodiment of the present invention;
[0020] Figure 2 This is a schematic diagram of the energy management and control structure provided in an embodiment of the present invention;
[0021] Figure 3 This is a schematic diagram of the energy management control logic provided in an embodiment of the present invention. Detailed Implementation
[0022] Exemplary embodiments of the present disclosure will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided to enable a more thorough understanding of the present disclosure and to fully convey the scope of the disclosure to those skilled in the art. It should be noted that, unless otherwise specified, the embodiments and features described herein can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.
[0023] This embodiment provides a design method for energy management strategy of a deep space probe. The method includes: when the electric propulsion is working, the overall energy safety strategy is executed in the logical order of undervoltage protection of the electric propulsion power supply unit, fixed operating point protection of the power controller, and energy safety protection of the entire probe platform; when the electric propulsion is not working, the overall energy safety strategy is executed in the logical order of fixed operating point protection of the power controller and energy safety protection of the entire probe platform.
[0024] The undervoltage protection for the electric propulsion power unit includes: when the power output of the electric propulsion power unit exceeds the tolerance or the output power of the solar array is abnormal, the sum of the electric propulsion power and the platform power exceeds the output power of the solar array. The operating point of the solar array will then shift to the left until it reaches the undervoltage protection point V of the electric propulsion power unit. u V is required u <V Hbus This triggers the undervoltage protection shutdown of the electric propulsion power unit; where V Hbus This is the output voltage of the high-voltage bus. If the output power of the solar array meets the power requirements of the platform after the electric propulsion power unit is shut down, the solar array will work at a new operating point, and the output voltage of the solar array will be within the normal range.
[0025] The power controller's fixed operating point protection includes: if the output power of the solar array is still insufficient to meet the platform's power requirements after the electric propulsion power unit is shut down, the power controller will adjust the solar array's operating point to the fixed operating point V of the solar array in order to improve the energy utilization rate of the solar array. s V is required s <V u <V Hbus The lithium-ion battery participates in the discharge, and the solar cell array discharges together with the lithium-ion battery to ensure the stable operation of the detector. When the detector load decreases or the output power of the solar cell array increases, causing the detector load power to be less than the output power of the solar cell array, the power controller exits the fixed operating point mode and operates at the new operating point.
[0026] The energy safety protection of the entire platform includes: when the battery discharge causes the battery discharge depth to increase, when the battery discharge depth increases by more than 20%, and the actual discharge depth of the battery reaches 40% to 60%, the entire device will automatically activate the system-level energy safety protection strategy, including controlling the detector to turn towards the sun and shutting down the equipment on the device in order of load priority from lowest to highest, reducing power demand, and waiting for ground processing and restoration.
[0027] When the detector is operating normally during illumination, the output power of the solar array is greater than the load power of the detector. The output voltage of the solar array is located to the right of the optimal operating point of the IV curve of the solar array, and the output voltage of the solar array changes accordingly with the size of the load.
[0028] The high-voltage bus output voltage is 70V~110V, and the low-voltage bus output voltage is V. Lbus The voltage range is 23V to 29V.
[0029] This method specifically includes a three-level coordinated energy safety design: undervoltage protection for the electric propulsion power unit, fixed operating point of the power controller, and overall energy safety protection. When the electric propulsion is operating, the detector's energy control strategy is executed sequentially according to the logical order of undervoltage protection for the electric propulsion power unit, fixed operating point of the power controller, and overall energy safety protection. When the electric propulsion is not operating, the overall energy safety strategy is executed sequentially according to the logical order of fixed operating point of the power controller and overall energy safety protection. Based on the power output of the solar array, load power is controlled. For high-voltage, high-power loads, operating power levels are controlled. When the solar array's output power is insufficient, high-voltage, high-power loads are switched on and off. For low-voltage loads, switching control is performed according to power load priority.
[0030] A variable operating point control strategy is adopted for the solar cell array. When the power of the solar cell array meets the load, the operating point of the solar cell array is changed accordingly. When the power of the solar cell array cannot meet the load power requirements, a fixed operating point control strategy is adopted to make the most of the solar cell array energy. The lithium-ion battery pack participates in the discharge, and the low-voltage load of the platform is jointly powered by the solar cell array and the lithium-ion battery pack.
[0031] The undervoltage protection point voltage of the electric propulsion power supply unit needs to be higher than the fixed operating point voltage of the solar cell array. At the same time, the undervoltage protection point voltage of the electric propulsion power supply unit needs to be lower than the high voltage bus voltage, and the fixed operating point voltage of the solar cell array needs to be higher than the low voltage bus voltage.
[0032] 1) Undervoltage protection for electric propulsion power supply unit
[0033] When the detector is operating normally under illumination, the output power of the solar array is greater than the detector's load power. The output voltage of the solar array is located to the right of the optimal operating point on the solar array's IV curve, and the output voltage varies accordingly with the load. For example, the high-voltage bus output voltage V... Hbus The low-voltage bus output voltage is 70V to 110V. Lbus The voltage range is 23V to 29V.
[0034] When the power output of the electric propulsion unit exceeds the tolerance or the output power of the solar array is abnormal (such as abnormal attitude or predicted deviation of the solar array), the sum of the electric propulsion power and the platform power exceeds the output power of the solar array. The operating point of the solar array will shift to the left until it reaches the undervoltage protection point V of the electric propulsion unit. u V is required u <V Hbus For example, the undervoltage protection point V of the electric drive power supply unit uThe voltage is 60V, which triggers the undervoltage protection shutdown of the electric drive power supply unit.
[0035] If the output power of the solar array can meet the platform's power requirements after the electric propulsion power unit is shut down, the solar array will operate at a new operating point, and the output voltage of the solar array will be within the normal range. In this case, the operation of the platform equipment will not be affected. Otherwise, the fixed operating point protection function of the power controller will be triggered.
[0036] 2) Power controller fixed operating point protection
[0037] If the output power of the solar array is still insufficient to meet the platform's power requirements after the electric propulsion power unit is shut down, the power controller will adjust the solar array's operating point to the fixed operating point V of the solar array in order to improve the energy utilization rate of the solar array. s V is required s <V u <V Hbus For example, the fixed operating point of the solar array is 50V, with the lithium-ion battery participating in the discharge. The solar array and the lithium-ion battery discharge together to ensure the stable operation of the detector. When the detector load decreases or the output power of the solar array increases, causing the detector load power to be less than the output power of the solar array, the power controller exits the fixed operating point mode and operates at the new operating point. Otherwise, the overall power safety protection will be triggered.
[0038] 3) Energy security protection of the entire platform
[0039] Under normal circumstances, the electric propulsion system is powered by the solar array, and the battery is in a storage state. During storage, the battery's state of charge is 60% to 80%. Considering the possibility of increased battery discharge depth due to abnormal conditions, when the battery discharge depth increases by more than 20%, and the actual battery discharge depth reaches 40% to 60%, the entire unit will automatically activate the system-level energy safety protection strategy. This includes controlling the detector to turn towards the sun and shutting down the equipment on the unit in order of load priority from lowest to highest, in order to minimize power demand and wait for ground handling and restoration.
[0040] When the electric propulsion is working, the overall energy security strategy is executed in the logical order of items 1) to 3) above; when the electric propulsion is not working, the overall energy security strategy is executed in the logical order of items 2) to 3) above.
[0041] Figure 1 This is a structural block diagram of the deep space probe system provided in an embodiment of the present invention. Figure 1 As shown, the deep space probe system includes: ±Y solar arrays, a power controller, an electric propulsion power unit, a lithium-ion battery pack, and a platform load. The power system includes the ±Y solar arrays, a power controller, an electric propulsion power unit, and a lithium-ion battery pack.
[0042] The ±Y solar array's power supply inputs to the power controller via diodes, and after regulation, outputs to the high-voltage and low-voltage buses. The high-voltage bus supplies power to the electric propulsion power unit, while the low-voltage bus supplies power to the platform load. The input terminal of the high-voltage bus power supply circuit is positively connected to the solar array power bus via a diode, and its output terminal is connected to the electric propulsion power unit. Similarly, the input terminal of the low-voltage bus power supply circuit is positively connected to the solar array power bus via a diode, and its output terminal is connected to both the lithium-ion battery pack and the platform load. The lithium-ion battery pack is connected to the low-voltage bus. The high-voltage bus voltage is 70V–110V, and the low-voltage bus output voltage is 23V–29V.
[0043] The electric propulsion power supply unit internally uses MOSFETs to control the on / off switching of the high-voltage bus, with the specific on / off control handled by the controller. Power conversion is achieved through a high-voltage power converter to supply power to the high-voltage load. The power controller internally uses a low-voltage power converter to convert power to supply power to the low-voltage load. The power controller's set voltage point control is also handled by the controller itself. Internally, switches K2 and K3 control the charging and discharging of the lithium-ion battery pack. Each low-voltage power load has a corresponding switch for load control.
[0044] Specifically, in the early stages of its lifespan, the Earth-Sun distance is small, resulting in high output power from the solar array. High-voltage, high-power loads, such as electric propulsion systems, can operate at high power, far exceeding the power output of low-voltage bus loads. High-voltage, high-power loads range from several kW to 10 kW, while low-voltage loads are around 1 kW. Due to variations in sunlight intensity, the high-voltage bus voltage varies from 70V to 110V, with the solar array's operating voltage adjusted by the power controller based on the load. Because the solar array provides ample energy and the system has sufficient power margin, high-voltage electric propulsion loads can operate on demand without triggering undervoltage protection in the propulsion power unit, the power controller's fixed operating point function, or the overall spacecraft's energy safety protection strategy. The lithium-ion battery pack remains largely in storage unless the spacecraft enters emergency mode, triggering the corresponding functions.
[0045] During the middle of its lifespan, as the Earth-Sun distance increases, the output power of the solar array decreases, leading to insufficient system power margin. If the electric propulsion operating point is improperly set, the solar array output power may not meet the combined power requirements of the electric propulsion load and the platform load. When the solar array power is insufficient, the solar array operating point will gradually decrease. When the solar array voltage falls below the undervoltage protection point of the electric propulsion power unit (60V±2V), the undervoltage protection of the electric propulsion power unit will be triggered, and the unit will shut down. Under normal circumstances, the solar array output power will exceed the platform load power requirement, and the solar array output voltage will increase accordingly. If the solar array output power still cannot meet the platform load requirements, the power controller's fixed operating point function will be triggered. The solar array operating voltage will be adjusted and fixed at the set operating voltage point (50V±1V). The battery pack may discharge. When the battery pack's state of charge further decreases, the overall energy safety protection strategy of the device may be triggered.
[0046] Towards the end of its lifespan, the distance between the Earth and the Sun increases further, and the output power of the solar array decreases further. With limited output power, the electric propulsion load cannot operate, and the MOSFETs of the electric propulsion power unit are turned off. All the power of the solar array is used to supply the low-voltage bus. If the platform load is not set properly, the output power of the solar array may not meet the platform load power. In this case, the fixed operating point function of the power controller will be triggered, and the battery pack may discharge. When the state of charge of the battery pack further decreases, the energy safety protection strategy of the whole device may be triggered.
[0047] Figure 2 This is a schematic diagram of the energy management and control structure. Figure 3 This is a schematic diagram of the energy management control logic. The central processing unit includes a central control unit, controller 1, controller 2, and controller 3.
[0048] Controller 2 is based on the solar array voltage Vsolar and the high-voltage load voltage V HL Control of the high-voltage power converter is performed. MOS switch control is based on a comparison of the solar array voltage Vsolar with a set value, including the undervoltage protection of the electric drive power unit mentioned in this paper. When Vsolar falls below the undervoltage protection point V of the electric drive power unit... u The 60V triggers the undervoltage protection shutdown of the electric drive power supply unit.
[0049] Controller 3 is based on the solar array voltage Vsolar and the battery voltage V BAT and bus voltage V BUS Control of the low-voltage power converter. Control of the fixed operating point of the solar array based on a comparison between the solar array voltage Vsolar and a set value. When Vsolar is lower than the fixed operating point V... sWhen the voltage is 50V, the power controller will adjust the operating point of the solar array to the fixed operating point V of the solar array. s The power controller enters the fixed operating point protection mode.
[0050] Controller 1 uses the solar array voltage Vsolar and the battery voltage V BAT The central processing unit generates control signals and performs switching control of battery packs K2 to K3 and low-voltage loads.
[0051] This embodiment also provides a deep space probe energy management strategy design system, which includes: a first module, used when electric propulsion is working, the whole spacecraft energy safety strategy is executed in the logical order of undervoltage protection of electric propulsion power supply unit, fixed operating point protection of power controller and energy safety protection of whole spacecraft platform; and a second module, used when electric propulsion is not working, the whole spacecraft energy safety strategy is executed in the logical order of fixed operating point protection of power controller and energy safety protection of whole spacecraft platform.
[0052] This embodiment employs a three-tiered energy security strategy, combining undervoltage protection for the electric propulsion power unit, fixed operating point protection for the power controller, and energy security protection for the entire platform. This ensures the energy security of the entire platform equipment while guaranteeing high operating point operation of the electric propulsion system, preventing any jeopardy to the detector's electrical safety. Load power is controlled based on the solar array's power output. For high-voltage, high-power loads, operating power levels are controlled, and when the solar array's output power is insufficient, high-voltage, high-power loads are switched on and off. For low-voltage loads, switching is controlled based on power load priority.
[0053] In this embodiment, a variable operating point control strategy is adopted for the solar cell array. When the power of the solar cell array meets the load, the operating point of the solar cell array changes accordingly with the load. When the solar cell array cannot meet the load power requirements, a fixed operating point control strategy is adopted to make the most of the solar cell array energy. The lithium-ion battery pack participates in the discharge, and the low-voltage load of the platform is jointly powered by the solar cell array and the lithium-ion battery pack.
[0054] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.
Claims
1. A design method for energy management strategies of deep space probes, characterized in that... include: During electric propulsion operation, the overall energy safety strategy is executed in the logical order of undervoltage protection of the electric propulsion power supply unit, fixed operating point protection of the power controller, and energy safety protection of the entire propulsion platform. When the electric propulsion system is not in operation, the overall energy safety strategy is executed in the logical order of the power controller fixed operating point protection and the overall platform energy safety protection.
2. The deep space probe energy management strategy design method according to claim 1, characterized in that: The undervoltage protection of the electric propulsion power supply unit includes: When the power output of the electric propulsion power unit exceeds the tolerance or the output power of the solar array is abnormal, the sum of the electric propulsion power and the platform power will exceed the output power of the solar array. The operating point of the solar array will then shift to the left until it reaches the undervoltage protection point V of the electric propulsion power unit. u V is required u <V Hbus This triggers the undervoltage protection shutdown of the electric propulsion power unit; where V Hbus This is the output voltage of the high-voltage bus. If the output power of the solar array meets the platform's power requirements after the electric propulsion power unit is shut down, the solar array will operate at a new operating point, and the output voltage of the solar array will be within the normal range.
3. The deep space probe energy management strategy design method according to claim 1, characterized in that: Fixed operating point protection for the power controller includes: If the output power of the solar array is still insufficient to meet the platform's power requirements after the electric propulsion power unit is shut down, the power controller will adjust the solar array's operating point to the fixed operating point V of the solar array in order to improve the energy utilization rate of the solar array. s V is required s <V u <V Hbus The lithium-ion battery participates in the discharge, and the solar cell array discharges together with the lithium-ion battery to ensure the stable operation of the detector. When the detector load decreases or the output power of the solar cell array increases, causing the detector load power to be less than the output power of the solar cell array, the power controller exits the fixed operating point mode and operates at the new operating point.
4. The deep space probe energy management strategy design method according to claim 1, characterized in that: The energy security protection of the entire platform includes: Battery discharge leads to an increase in battery discharge depth. When the battery discharge depth increases by more than 20%, and the actual discharge depth of the battery reaches 40% to 60%, the device will automatically activate the system-level energy safety protection strategy, including controlling the detector to turn towards the sun and shutting down the equipment on the device in order of load priority from lowest to highest, reducing power demand, and waiting for ground processing and restoration.
5. The deep space probe energy management strategy design method according to claim 2, characterized in that: When the detector is operating normally during illumination, the output power of the solar array is greater than the load power of the detector. The output voltage of the solar array is located to the right of the optimal operating point of the IV curve of the solar array, and the output voltage of the solar array changes accordingly with the size of the load.
6. The deep space probe energy management strategy design method according to claim 2, characterized in that: The high-voltage bus output voltage is 70V~110V, and the low-voltage bus output voltage is V. Lbus The voltage range is 23V to 29V.
7. A deep space probe energy management strategy design system, characterized in that... include: The first module is used when the electric propulsion is working. The overall energy safety strategy is executed in the logical order of undervoltage protection of the electric propulsion power supply unit, fixed operating point protection of the power controller, and energy safety protection of the entire platform. The second module is used to ensure that when the electric propulsion system is not in operation, the overall energy safety strategy is executed in the logical order of the power controller's fixed operating point protection and the overall platform energy safety protection.
8. The deep space probe energy management strategy design system according to claim 7, characterized in that: The undervoltage protection of the electric propulsion power supply unit includes: When the power output of the electric propulsion power unit exceeds the tolerance or the output power of the solar array is abnormal, the sum of the electric propulsion power and the platform power will exceed the output power of the solar array. The operating point of the solar array will then shift to the left until it reaches the undervoltage protection point V of the electric propulsion power unit. u V is required u <V Hbus This triggers the undervoltage protection shutdown of the electric propulsion power unit; where V Hbus This is the output voltage of the high-voltage bus. If the output power of the solar array meets the platform's power requirements after the electric propulsion power unit is shut down, the solar array will operate at a new operating point, and the output voltage of the solar array will be within the normal range.
9. The deep space probe energy management strategy design system according to claim 7, characterized in that: Fixed operating point protection for the power controller includes: If the output power of the solar array is still insufficient to meet the platform's power requirements after the electric propulsion power unit is shut down, the power controller will adjust the solar array's operating point to the fixed operating point V of the solar array in order to improve the energy utilization rate of the solar array. s V is required s <V u <V Hbus The lithium-ion battery participates in the discharge, and the solar cell array discharges together with the lithium-ion battery to ensure the stable operation of the detector. When the detector load decreases or the output power of the solar cell array increases, causing the detector load power to be less than the output power of the solar cell array, the power controller exits the fixed operating point mode and operates at the new operating point.
10. The deep space probe energy management strategy design system according to claim 7, characterized in that: The energy security protection of the entire platform includes: Battery discharge leads to an increase in battery discharge depth. When the battery discharge depth increases by more than 20%, and the actual discharge depth of the battery reaches 40% to 60%, the device will automatically activate the system-level energy safety protection strategy, including controlling the detector to turn towards the sun and shutting down the equipment on the device in order of load priority from lowest to highest, reducing power demand, and waiting for ground processing and restoration.