A distributed power system applied to a multi-mission spacecraft constellation

Abstract

A kind of distributed power system applied to multi-task spacecraft assembly, including first power system, second power system and third power system, power supply energy sharing is realized between first power system, second power system, power supply energy sharing is realized between third power system, second power system, power supply energy sharing is realized between first power system, third power system, power supply and charging of first power system are realized to second power system, power supply and charging of third power system are realized to second power system.The technical scheme of the present application solves the power supply problem of one-off multi-task detection spacecraft assembly, the power regulation capability and adaptive capacity of system are strong, adapt to launch, earth-moon transfer, near-moon braking, circumlunar, power descent, moon surface work and other multi-task working condition under power supply demand, compared with prior art, with light weight, good expansibility, system adaptive capacity is strong, response speed is fast and the like advantages.

Description

Technical Field

[0001] This invention relates to the field of spacecraft power technology, and more specifically to a distributed power system applied to multi-mission spacecraft assemblies. Background Technology

[0002] In spacecraft power systems, solar arrays typically generate electricity through the photoelectric effect, providing power to the spacecraft and charging battery banks during periods of sunlight. Battery banks, in turn, provide power to the spacecraft during periods of non-sunlight. When the spacecraft's short-term power demand exceeds the solar array's output, the battery banks also serve as a backup power source in the combined power supply. According to the next phase of China's lunar exploration mission plan, my country will launch a probe assembly to complete multiple lunar exploration missions in a single mission, including a soft landing, lunar rover exploration, and lunar flyby. The traditional method of uniformly arranging solar arrays and using a single MEA (Mechanical Equipment Assembly) for individual spacecraft will not meet the power system requirements of a combined spacecraft for multiple missions. More flexible, efficient, and lightweight power system technologies are needed.

[0003] Therefore, it is necessary to propose a more flexible and efficient distributed power system for multi-mission spacecraft assemblies. Summary of the Invention

[0004] The technical problem solved by this invention is to overcome the shortcomings of existing technologies, such as low energy reuse rate, poor scalability, and heavy system weight, and to design a distributed power system for multi-mission spacecraft combinations, thus solving the technical and power expansion problems of power systems for one-off, multi-mission lunar probes such as lunar soft landing, lunar roving, and lunar flyby.

[0005] To address the aforementioned problems, this invention provides a distributed power system for multi-mission spacecraft assemblies, comprising: a first power system and a second power system, wherein...

[0006] The first power system includes a first solar cell array, a first power regulator, a first battery pack, a first power line, a first discharge switch, a first diode, a second diode, and a first bus parallel switch. One end of the first power regulator is connected to the first solar cell array, and the other end is connected to the first power line, for outputting stable power and voltage to the first power line. One end of the first discharge switch is connected to the first battery pack, and the other end is connected to the first power line, for controlling whether the first battery pack supplies power to the first power line. The positive terminal of the first diode is connected to the first power line, and the negative terminal outputs a power supply. The negative terminal of the second diode is connected to the first power line, and one end of the positive terminal is connected to the second power system, for receiving electrical energy from the second power system. One end of the first bus parallel switch is connected to the negative terminal of the first diode, and the other end is connected to the second power system.

[0007] The second power system includes a second solar cell array, a third solar cell array, a second power regulator, a third power regulator, a second battery pack, a second power line, a second discharge switch, a first charging switch, a third diode, and a second bus parallel switch. One end of the second power regulator is connected to the second solar cell array, and the other end is connected to the second power line, for outputting stable power and voltage to the second power line. One end of the third power regulator is connected to the third solar cell array, and the other end is connected to the first charging switch, for outputting stable power and voltage to the second power line or the first power system. One end of the second discharge switch is connected to the second battery pack, and the other end is connected to the second power line, for controlling whether to supply power from the second battery pack to the second power line. The positive terminal of the third diode is connected to the second power line, and the negative terminal outputs a power supply. One end of the second bus parallel switch is connected to the negative terminal of the third diode, and the other end is connected to the first power system, for controlling the circuit connection between the first power system and the second power system.

[0008] Preferably, a third power supply system is also included.

[0009] The second power system also includes a fourth solar cell array, a fourth power regulator, a second charging switch, and a third bus parallel switch. One end of the fourth power regulator is connected to the fourth solar cell array, and the other end is connected to the second charging switch, for outputting a power supply to the second power line or the third power system. One end of the third bus parallel switch is connected to the second power system, and the other end is connected to the third power system, for controlling the parallel connection between the second power system and the third power system.

[0010] The third power system includes a fifth solar cell array, a fifth power regulator, a third battery pack, a third power line, a third discharge switch, a fourth diode, a fifth diode, and a third bus parallel switch. The fifth power regulator is connected at one end to the fifth solar cell array and at the other end to the third power line. It receives power generated by the fifth solar cell array and, after regulation, outputs stable power and voltage to the third power line. The third discharge switch is connected at one end to the third battery pack and at the other end to the third power line. It receives electrical energy stored in the third battery pack and, after control, provides it to the third power line. The fourth diode has its positive terminal connected to the third power line and its negative terminal outputting power. The fifth diode has its negative terminal connected to the third power line and its positive terminal connected to the second power system, receiving electrical energy from the second power system to charge the third battery pack. The fourth bus parallel switch is connected at one end to the third power system and at the other end to the second power system, controlling the parallel connection between the third and second power system buses.

[0011] Optionally, the first power system further includes a first power bus for receiving the power output from the first diode and outputting it to the first power system load; the second power system further includes a second power bus for receiving the power output from the third diode and outputting it to the second power system load; and the third power system further includes a third power bus for receiving the power output from the fourth diode and outputting it to the third power system load.

[0012] The voltage output from the first power system bus is 23V to 31V, the voltage output from the second power system bus is 23V to 30V, and the voltage output from the third power system bus is 23V to 30V.

[0013] Optionally, the first power regulator adopts the S3R regulation control method; the second power regulator adopts the S3R regulation control method; the third power regulator adopts the S4R regulation control method; the fourth power regulator adopts the S4R regulation control method; and the fifth power regulator adopts the S3R regulation control method.

[0014] Optionally, the output voltage of the first power regulator is higher than the output voltage of the second power regulator, with a voltage difference of not less than 0.2V; the output voltage of the second power regulator is higher than the output voltage of the fifth power regulator, with a voltage difference of not less than 0.2V; the output voltage of the fifth power regulator is higher than the output voltage of the third power regulator, with a voltage difference of not less than 0.2V; and the output voltages of the third power regulator and the fourth power regulator are the same.

[0015] Optionally, when both the first bus parallel switch and the second bus parallel switch are closed, the first power system bus and the second power system bus are connected in parallel for power supply, and the power supply of the first power system and the second power system can flow in both directions; when both the third bus parallel switch and the fourth bus parallel switch are closed, the third power system bus and the second power system bus are connected in parallel for power supply, and the power supply of the third power system and the second power system can flow in both directions.

[0016] Optionally, when the first charging switch is switched to the second power line, the third power regulator supplies power to the second power line or charges the second battery pack; when the first charging switch is switched to the first power system, the third power regulator supplies power to the first power line or charges the first battery pack.

[0017] Optionally, when the second charging switch is switched to the second power line, the fourth power regulator supplies power to the second power line or charges the second battery pack; when the second charging switch is switched to the third power system, the fourth power regulator supplies power to the third power line or charges the third battery pack.

[0018] Optionally, the number of third power regulators can be multiple, realizing the power expansion of the second power system supplying power to the first power system; the number of fourth power regulators can be multiple, realizing the power expansion of the second power system supplying power to the third power system.

[0019] The advantages of this invention compared to the prior art are:

[0020] Compared with the prior art, this invention proposes a distributed power system for multi-mission spacecraft assemblies, which can meet the power system requirements of multi-mission exploration spacecraft assemblies and solve the technical problems of power systems for multi-mission lunar probe assemblies such as soft landing, lunar roving and lunar flyby. The system has strong power regulation and adaptability and can meet the power requirements of various mission conditions such as launch, Earth-Moon transfer, lunar braking, lunar orbit, powered descent and lunar surface operation.

[0021] Compared with the prior art, the power regulator of this invention has a high degree of versatility and strong system power scalability, and can be applied to various types of lunar exploration missions such as lunar orbit exploration, lunar landing, lunar rover exploration, and lunar flyby.

[0022] Compared with existing technologies, the present invention has a lighter system weight and a higher energy reuse rate. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of a distributed power system applied to a multi-mission spacecraft assembly according to the present invention. Detailed Implementation

[0024] The following is in conjunction with the appendix Figure 1 The following detailed description, along with specific embodiments, provides a further detailed explanation of the distributed power system proposed in this invention for use in multi-mission spacecraft assemblies. The advantages and features of the invention will become clearer from the following description. It should be noted that the accompanying drawings are in a very simplified form and are only used to facilitate and clarify the illustration of the invention.

[0025] In the description of this invention, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature.

[0026] This invention addresses the shortcomings of existing technologies, such as low energy reuse rate, poor scalability, and heavy system weight. It designs a distributed power system for multi-mission spacecraft assemblies, solving the technical challenges and power expansion difficulties of power systems for single-mission, multi-mission lunar probes, including those for soft landings, lunar roving, and lunar flybys. The invention will now be described in detail with reference to the accompanying drawings.

[0027] like Figure 1 The diagram shows a distributed power system applied to a multi-mission spacecraft assembly, including a first power system, a second power system, a third power system, a load of the first power system, a load of the second power system, and a load of the third power system.

[0028] The first power system includes a first solar cell array, a first power regulator, a first battery pack, a first discharge switch, a first power line, a first diode, a second diode, and a first bus parallel switch. One end of the first power regulator is connected to the first solar cell array, and the other end is connected to the first power line, used to output stable power and voltage to the first power line. One end of the first discharge switch is connected to the first battery pack, and the other end is connected to the first power line, used to control whether the first battery pack supplies power to the first power line. One end of the positive terminal of the first diode is connected to the first power line, and the negative end outputs power through the first power system bus to the first power system load. The negative terminal of the second diode is connected to the first power line, and the positive terminal is connected to the second power system, used to receive electrical energy from the second power system to charge the first battery pack. One end of the first bus parallel switch is connected to the negative terminal of the first diode, and the other end is connected to the second power system, controlling the parallel connection between the first power system bus and the second power system bus. The first power regulator is used to regulate the voltage of the first power system bus, using S3R regulation control, and the bus voltage of the first power system is 23V to 31V.

[0029] The second power system includes a second solar array, a third solar array, a fourth solar array, a second power regulator, a third power regulator, a fourth power regulator, a second battery bank, a second power line, a second discharge switch, a first charging switch, a second charging switch, a third diode, a second bus parallel switch, and a third bus parallel switch. The second power regulator is connected at one end to the second solar array and at the other end to the second power line. It receives power generated by the solar array and, after regulation, outputs stable power and voltage to the second power line. The third power regulator is connected at one end to the third solar array and at the other end to the first charging switch. It receives power generated by the solar array and, after control, outputs stable power and voltage to the second power line, or outputs charging energy to the first power system. The fourth power regulator is connected at one end to the fourth solar array and at the other end to the second charging switch. It receives power generated by the fourth solar array and, after control, outputs stable power and voltage to the second power line, or outputs charging energy to the third power system. Electrical energy; one end of the second discharge switch is connected to the second battery pack, and the other end is connected to the second power line, used to receive the electrical energy stored in the second battery pack and supply it to the second power line after control; the positive terminal of the third diode is connected to the second power line, and the negative terminal outputs a power supply to the load of the second power system through the second power system bus; one end of the second bus parallel switch is connected to the second power system bus, and the other end is connected to the first power system, controlling the parallel connection between the first power system bus and the second power system bus; one end of the third bus parallel switch is connected to the second power system bus, and the other end is connected to the third power system, controlling the parallel connection between the second power system bus and the third power system bus. The second, third, and fourth power regulators jointly regulate the voltage of the second power system bus. The second power regulator uses S3R regulation control, the third power regulator uses S4R regulation control, and the fourth power regulator uses S4R regulation control; the voltage of the second power system bus is 23V~30V.

[0030] The third power system includes a fifth solar array, a fifth power regulator, a third battery bank, a third power line, a third discharge switch, a fourth diode, a fifth diode, and a third bus parallel switch. The fifth power regulator is connected at one end to the fifth solar array and at the other end to the third power line. It receives power generated by the fifth solar array and, after regulation, outputs stable power and voltage to the third power line. The third discharge switch is connected at one end to the third battery bank and at the other end to the third power line. It receives the electrical energy stored in the third battery bank and, after control, supplies it to the third power line. The fourth diode has its positive terminal connected to the third power line and its negative terminal connected to the third power system bus, from which the third power system bus supplies power to the loads of the third power system. The fifth diode has its negative terminal connected to the third power line and its positive terminal connected to the second power system, receiving electrical energy from the second power system to charge the third battery bank. The fourth bus parallel switch is connected at one end to the third power system bus and at the other end to the second power system, controlling the parallel connection between the third and second power system buses. The third power regulator is used to regulate the voltage of the third power system bus. The power regulation method adopts S3R regulation control. The voltage of the third power system bus is 23V~30V.

[0031] When the first bus parallel switch and the second bus parallel switch are turned on, the first power system bus and the second power system bus are connected in parallel to supply power, and the power supply of the first power system and the second power system can flow in both directions; when the third bus parallel switch and the fourth bus parallel switch are turned on, the third power system bus and the second power system bus are connected in parallel to supply power, and the power supply of the third power system and the second power system can flow in both directions.

[0032] When the first charging switch is switched to the second power line, the third power regulator supplies power to the second power line or charges the second battery pack; when the first charging switch is switched to the first power system, the third power regulator supplies power to the first power line or charges the first battery pack.

[0033] When the second charging switch is switched to the second power line, the fourth power regulator supplies power to the second power line or charges the second battery pack; when the second charging switch is switched to the third power system, the fourth power regulator supplies power to the third power line or charges the third battery pack.

[0034] The output voltage of the first power regulator is higher than that of the second power regulator, with a voltage difference of not less than 0.2V; the output voltage of the second power regulator is higher than that of the fifth power regulator, with a voltage difference of not less than 0.2V; the output voltage of the fifth power regulator is higher than that of the third power regulator, with a voltage difference of not less than 0.2V; the output voltages of the third and fourth power regulators are the same.

[0035] Furthermore, the first power system, second power system, and third power system involved in this invention can expand the output power of the first power system by increasing the number of first power regulators, expand the output power of the second power system by increasing the number of second, third, and fourth power regulators, expand the output power of the third power system by increasing the number of fifth power regulators, expand the power supply and charging power of the second power system to the first power system by increasing the number of third power regulators, and expand the power supply and charging power of the second power system to the third power system by increasing the number of fourth power regulators.

[0036] The distributed power system proposed in this invention for use in multi-mission spacecraft assemblies has the following advantages:

[0037] (1) The first and third power supply systems using S3R regulation;

[0038] The first and third power systems involved in this invention use S3R for power regulation and charge the battery pack. After the battery pack is fully charged, it supplies power to the bus.

[0039] (2) A second power supply system using S3R regulation and S4R regulation;

[0040] The second power supply system involved in this invention uses S3R and S4R for power regulation and charges each battery pack. Once each battery pack is fully charged, it can supply power to each power line.

[0041] (3) The power supply priority is, in order, the first power system, the second power system, and the third power system;

[0042] The first power system, the second power system, and the third power system involved in this invention achieve priority power supply from the first power system, followed by power supply from the second power system, and then power supply from the third power system by setting the voltage difference between the output voltages of the power regulators of the three power systems.

[0043] (4) Power supply energy sharing is achieved between the first power system and the second power system;

[0044] The first and second power supply systems involved in this invention can achieve bidirectional energy sharing. When the first bus parallel switch and the second bus parallel switch are closed, the first and second power supply systems can achieve bidirectional grid connection; when the first power supply system experiences a power shortage and the second power supply system has a power surplus, grid-connected energy flows from the second power supply system to the first power supply system; when the second power supply system experiences a power shortage and the first power supply system has a power surplus, grid-connected energy flows from the first power supply system to the second power supply system.

[0045] (5) Energy sharing is achieved between the third power system and the second power system;

[0046] The third and second power supply systems involved in this invention can achieve bidirectional energy sharing. When the third bus parallel switch and the fourth bus parallel switch are closed, the third and second power supply systems can achieve bidirectional grid connection; when the third power supply system experiences a power shortage and the second power supply system has a power surplus, grid-connected energy flows from the second power supply system to the third power supply system; when the second power supply system experiences a power shortage and the third power supply system has a power surplus, grid-connected energy flows from the third power supply system to the second power supply system.

[0047] (6) Power supply energy sharing is achieved between the first power system and the third power system;

[0048] The first and third power systems involved in this invention can achieve bidirectional energy sharing. When the first bus parallel switch, the second bus parallel switch, the third bus parallel switch, and the fourth bus parallel switch are closed, the first and third power systems can achieve bidirectional grid connection. When the first power system experiences a power shortage and the third power system has a power surplus, grid-connected energy flows from the third power system to the first power system; when the third power system experiences a power shortage and the first power system has a power surplus, grid-connected energy flows from the first power system to the third power system.

[0049] (7) The second power system provides power and charges the first power system;

[0050] The second power supply system involved in this invention can supply power to the bus of the first power supply system and charge the first battery pack. When the first charging switch is switched to the first power supply system, the second power supply system charges the first battery pack; after the first battery pack is fully charged, the second power supply system supplies power to the first power supply system.

[0051] (8) The second power system provides power and charge to the third power system;

[0052] The second power supply system involved in this invention can supply power to the bus of the third power supply system and charge the third battery pack. When the second charging switch is switched to the third power supply system, the second power supply system charges the third battery pack. After the third battery pack is fully charged, the second power supply system supplies power to the third power supply system.

[0053] (9) The first power system, the second power system, and the third power system can achieve power expansion.

[0054] This invention designs a distributed power system for multi-mission spacecraft assemblies, solving the technical challenges and power expansion difficulties of power systems for single-mission, multi-mission lunar probes such as soft landings, lunar roving, and lunar flybys. It can be applied to various types of lunar exploration missions, including lunar orbiting, landing, roving, and flybys. The system features strong power regulation and adaptability, light weight, and high energy reuse rate.

[0055] The above description is merely a description of preferred embodiments of the present invention and is not intended to limit the scope of protection of the present invention in any way. Any changes or modifications made by those skilled in the art based on the above disclosure shall fall within the scope of protection of the present invention. Contents not described in detail in this specification are well-known to those skilled in the art.

Claims

1. A distributed power supply system applied to a multi-mission spacecraft assembly, characterized in that, It includes a first power system and a second power system, wherein, The first power system includes a first solar cell array, a first power regulator, a first battery pack, a first power line, a first discharge switch, a first diode, a second diode, and a first bus parallel switch. One end of the first power regulator is connected to the first solar cell array, and the other end is connected to the first power line, for outputting stable power and voltage to the first power line. One end of the first discharge switch is connected to the first battery pack, and the other end is connected to the first power line, for controlling whether the first battery pack supplies power to the first power line. The positive terminal of the first diode is connected to the first power line, and the negative terminal outputs a power supply. The negative terminal of the second diode is connected to the first power line, and one end of the positive terminal is connected to the second power system, for receiving electrical energy from the second power system. One end of the first bus parallel switch is connected to the negative terminal of the first diode, and the other end is connected to the second power system. The second power system includes a second solar cell array, a third solar cell array, a second power regulator, a third power regulator, a second battery pack, a second power line, a second discharge switch, a first charging switch, a third diode, and a second bus parallel switch. One end of the second power regulator is connected to the second solar cell array, and the other end is connected to the second power line, for outputting stable power and voltage to the second power line. One end of the third power regulator is connected to the third solar cell array, and the other end is connected to the first charging switch, for outputting stable power and voltage to the second power line or the first power system. One end of the second discharge switch is connected to the second battery pack, and the other end is connected to the second power line, for controlling whether to supply power from the second battery pack to the second power line. The positive terminal of the third diode is connected to the second power line, and the negative terminal outputs a power supply. One end of the second bus parallel switch is connected to the negative terminal of the third diode, and the other end is connected to the first power system, for controlling the circuit connection between the first power system and the second power system. It also includes a third power supply system; When both the first bus parallel switch and the second bus parallel switch are closed, the first power system bus and the second power system bus are connected in parallel for power supply, and the power supply of the first power system and the second power system flows bidirectionally; when both the third bus parallel switch and the fourth bus parallel switch are closed, the third power system bus and the second power system bus are connected in parallel for power supply, and the power supply of the third power system and the second power system flows bidirectionally.

2. The distributed power system applied to a multi-mission spacecraft assembly as described in claim 1, characterized in that: The second power system also includes a fourth solar cell array, a fourth power regulator, a second charging switch, and the third bus parallel switch. One end of the fourth power regulator is connected to the fourth solar cell array, and the other end is connected to the second charging switch, for outputting a power supply to the second power line or the third power system. One end of the third bus parallel switch is connected to the second power system, and the other end is connected to the third power system, for controlling the parallel connection between the second power system and the third power system. The third power system includes a fifth solar cell array, a fifth power regulator, a third battery bank, a third power line, a third discharge switch, a fourth diode, a fifth diode, and a third busbar parallel switch. The fifth power regulator is connected at one end to the fifth solar cell array and at the other end to the third power line. It receives power generated by the fifth solar cell array and, after regulation, outputs stable power and voltage to the third power line. The third discharge switch is connected at one end to the third battery bank and at the other end to the third power line. It receives electrical energy stored in the third battery bank and, after control, provides it to the third power line. The fourth diode has its positive terminal connected to the third power line and its negative terminal outputting power. The fifth diode has its negative terminal connected to the third power line and its positive terminal connected to the second power system, receiving electrical energy from the second power system to charge the third battery pack; the fourth bus parallel switch has its one end connected to the third power system and its other end connected to the second power system, controlling the parallel connection between the third power system bus and the second power system bus.

3. The distributed power system applied to a multi-mission spacecraft assembly according to claim 2, characterized in that: The first power system further includes a first power bus for receiving the power output from the first diode and outputting it to the first power system load; the second power system further includes a second power bus for receiving the power output from the third diode and outputting it to the second power system load; the third power system further includes a third power bus for receiving the power output from the fourth diode and outputting it to the third power system load. The voltage output from the first power system bus is 23V~31V, the voltage output from the second power system bus is 23V~30V, and the voltage output from the third power system bus is 23V~30V.

4. The distributed power system applied to a multi-mission spacecraft assembly according to claim 3, characterized in that: The first power regulator adopts the S3R regulation control method; the second power regulator adopts the S3R regulation control method; the third power regulator adopts the S4R regulation control method; and the fourth power regulator adopts the S4R regulation control method. The fifth power regulator adopts the S3R regulation control method.

5. The distributed power system applied to a multi-mission spacecraft assembly according to claim 4, characterized in that: The output voltage of the first power regulator is higher than that of the second power regulator, with a voltage difference of not less than 0.2V; the output voltage of the second power regulator is higher than that of the fifth power regulator, with a voltage difference of not less than 0.2V; the output voltage of the fifth power regulator is higher than that of the third power regulator, with a voltage difference of not less than 0.2V; the output voltages of the third power regulator and the fourth power regulator are the same.

6. The distributed power system applied to a multi-mission spacecraft assembly according to claim 4, characterized in that: When both the first bus parallel switch and the second bus parallel switch are closed, the first power system bus and the second power system bus are connected in parallel for power supply, and the power supply of the first power system and the second power system flows bidirectionally; when both the third bus parallel switch and the fourth bus parallel switch are closed, the third power system bus and the second power system bus are connected in parallel for power supply, and the power supply of the third power system and the second power system flows bidirectionally.

7. The distributed power system applied to a multi-mission spacecraft assembly according to claim 4, characterized in that: When the first charging switch is switched to the second power line, the third power regulator supplies power to the second power line or charges the second battery pack; when the first charging switch is switched to the first power system, the third power regulator supplies power to the first power line or charges the first battery pack.

8. The distributed power system applied to a multi-mission spacecraft assembly according to claim 4, characterized in that: When the second charging switch is switched to the second power line, the fourth power regulator supplies power to the second power line or charges the second battery pack; when the second charging switch is switched to the third power system, the fourth power regulator supplies power to the third power line or charges the third battery pack.

9. The distributed power system applied to a multi-mission spacecraft assembly according to claim 4, characterized in that: The third power regulator is multiple in number, enabling the power expansion of the second power system supplying power to the first power system; the fourth power regulator is multiple in number, enabling the power expansion of the second power system supplying power to the third power system.

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