A distributed ring power distribution system architecture based on multi-bus configuration on board

Abstract

The present invention relates to a distributed annular power distribution system architecture based on a multi-bus configuration on a satellite, belonging to the field of satellite power supply and distribution system design; the architecture comprises a first ring network switch, a second ring network switch, a third ring network switch, a fourth ring network switch, a BUS1 bus, a BUS2 bus, a BUS3 bus, a BUS4 bus, an emergency bus, a first power module, a second power module, a third power module, a fourth power module, an emergency power module and an isolating switch; the present invention effectively avoids the single point failure problem caused by a single bus, significantly improves the reliability of the satellite power supply and distribution system and the entire satellite, and at the same time, the distributed annular structure can effectively reduce the cable laying length and the weight of the power distribution module, which is conducive to reducing the weight of the entire satellite.

Description

Technical Field

[0001] The present invention belongs to the field of satellite power supply and distribution system design, and relates to a distributed ring power distribution system architecture based on a multi-bus configuration on a satellite. Background Art

[0002] The power supply and distribution subsystem is an important component of the satellite, and is mainly responsible for providing and distributing electrical energy to the payload and platform during various flight phases of the satellite.

[0003] At present, the power distribution method of domestic high-orbit high-power communication satellites generally adopts centralized 100V single bus distribution, that is, a power control unit (PCU) collects energy transmitted from the solar array and battery through the internal shunt regulation module (SUN module) and charge and discharge regulation module (BCDR module), and then outputs 100V bus through the SUN module to send the power to the distribution module, and the distribution module distributes the power to the platform and payload equipment. PCU is the core of the entire satellite power supply and distribution system and is a key product of the entire satellite. PCU adopts a modular design concept, and modules with different functions have redundant designs. If a module fails, other modules will replace it to work. In order to ensure the safety of PCU and bus power supply, it has undergone multiple rounds of rigorous verification and inspection in design, process, and production.

[0004] With the introduction of all-electric propulsion and the enhancement of payload functions in the future, the power level of satellites will become higher and higher, and the scale and volume of satellites will also become larger and larger. Modular expandable satellites, compartment board design, synchronous testing and assembly will become more and more popular. If the satellite's power distribution system still uses a centralized single busbar power distribution method, the main power cable routing distance of a single PCU will increase further after the satellite cabin becomes larger, the weight of the entire satellite cable network will increase significantly, and the laying difficulty will also increase; in addition, the main power cables will be tied together from the SADA to the PCU. When the power of the entire satellite increases, the current of the power cable increases, the number of wire harnesses increases, and the heating at the unified cable binding will become more serious, which will increase the thermal control cost. On the other hand, as a single machine, the PCU cannot increase its own module configuration number infinitely as the power level of the entire satellite increases. Moreover, if there is a weak link in the production control process, resulting in a short circuit fault on the busbar at the output end of the PCU, the large current generated instantly will affect all modules in the single machine. Because there is no fuse protection on the power supply side, the fault is likely to spread rapidly, leading to a series of serious consequences. Summary of the invention

[0005] The technical problem solved by the present invention is: to overcome the shortcomings of the prior art and propose a distributed ring distribution system architecture based on a multi-bus configuration on board the satellite, effectively avoiding the single point failure problem caused by a single bus, and significantly improving the reliability of the satellite power supply and distribution system and the entire satellite. At the same time, the distributed ring structure can effectively reduce the cable laying length and the weight of the distribution module, which helps to reduce the weight of the entire satellite.

[0006] The solution of the present invention is:

[0007] A distributed ring power distribution system architecture based on a multi-bus configuration on a satellite, comprising a first ring network switch, a second ring network switch, a third ring network switch, a fourth ring network switch, a BUS1 bus, a BUS2 bus, a BUS3 bus, a BUS4 bus, an emergency bus, a first power module, a second power module, a third power module, a fourth power module, an emergency power module and an isolating switch;

[0008] Among them, the BUS1 bus is set on the south board of the satellite's communication cabin; the BUS2 bus is set on the instrument cabin of the satellite; the BUS3 bus is set on the north board of the satellite's communication cabin; the BUS4 bus is set on the ground plane of the satellite; and the BUS1 bus, BUS2 bus, BUS3 bus, and BUS4 bus are connected end to end in sequence to form a rectangular ring frame; the first ring network switch is set at the junction of the BUS1 bus and the BUS4 bus; the second ring network switch is set at the junction of the BUS1 bus and the BUS2 bus; the third ring network switch is set at the BUS2 The fourth ring network switch is arranged at the joint of BUS3 bus and BUS4 bus; the first power module is arranged on BUS1 bus; the second power module is arranged on BUS2 bus; the third power module is arranged on BUS3 bus; the fourth power module is arranged on BUS4 bus; the emergency power module, emergency bus and isolating switch are arranged in the instrument cabin; the emergency power module is connected to the equipment on BUS1 bus, BUS2 bus and BUS3 bus respectively through the emergency bus and isolating switch.

[0009] In the above-mentioned distributed ring distribution system architecture based on a multi-bus configuration on a satellite, the power of the entire satellite is evenly distributed on the BUS1 bus, BUS2 bus, BUS3 bus, and BUS4 bus; the power of each bus is 10kW and the voltage is 100V.

[0010] In the above-mentioned distributed ring distribution system architecture based on a multi-bus configuration on a satellite, the first power module supplies power to each device on the BUS1 bus through the BUS1 bus; the second power module supplies power to each device on the BUS2 bus through the BUS2 bus; the third power module supplies power to each device on the BUS3 bus through the BUS3 bus; and the fourth power module supplies power to each device on the BUS4 bus through the BUS4 bus.

[0011] In the above-mentioned distributed ring distribution system architecture based on a multi-bus configuration on a star, the first ring network switch, the second ring network switch, the third ring network switch, and the fourth ring network switch are identical ring network switches, each including a current limiting relay and five power relays; after the current limiting relay and the five power relays are connected in parallel, they are respectively connected to the busbars on both sides; the current limiting relay includes a power relay and a current limiting resistor, and the power relay and the current limiting resistor are connected in series to form a current limiting relay.

[0012] In the above-mentioned distributed ring distribution system architecture based on a multi-bus configuration on a satellite, the parameter of the current limiting relay is 110V / 2A; the parameter of the power relay is 110V / 25A; and the parameter of the current limiting resistor is 470Ω / 25W.

[0013] In the above-mentioned distributed ring power distribution system architecture based on a multi-bus configuration on a satellite, the ring network switch realizes the reconstruction of the two buses when the corresponding two buses are in a fault state of insufficient power supply or power failure, specifically:

[0014] When there is no fault in the two busbars corresponding to the ring network switch, the current limiting relay and the five power relays in the ring network switch are in a normally open state; when one of the busbars has a fault state of insufficient power supply or no power supply, and there is no short-circuit point on the faulty busbar, the current limiting relay and the five power relays in the ring network switch are closed to achieve reconstruction.

[0015] In the above-mentioned distributed ring distribution system architecture based on multi-bus configuration on a satellite, when one of the buses is in a fault state of insufficient power supply or unable to supply power, the current limiting relay is first closed to form a small current path to charge the faulty bus. During the charging process, the voltage drop between the power contacts of the unclosed power relay gradually decreases until the faulty bus voltage continues to rise to the normal bus voltage with charging, and the voltage drop between the power contacts of the unclosed power relay approaches 0, and 5 power relays are closed in sequence; the interconnection of the two buses and the reconstruction of the power circuit are completed.

[0016] In the above-mentioned distributed ring distribution system architecture based on a multi-bus configuration on a satellite, the withstand voltage of the power relays among the five power relays and the current limiting relay is 110V, which is greater than the maximum voltage difference ΔU between the access bus and the fault bus.

[0017] In the above-mentioned distributed ring power distribution system architecture based on multi-bus configuration on a satellite, when charging the power supply bus, the charging current is limited to 213mA by the current limiting resistor; the instantaneous maximum power consumption P of the charging max for:

[0018] P max =ΔU 2 / R

[0019] Where ΔU is the maximum voltage difference between the access bus and the fault bus, which is equal to the access bus voltage 100V minus the fault bus voltage 0V;

[0020] R is the resistance of the current limiting resistor.

[0021] In the above-mentioned distributed ring distribution system architecture based on a multi-bus configuration on a satellite, when a short circuit fault occurs on any bus, the emergency bus is started, the disconnector is closed, and power is supplied to the equipment on the faulty bus through the emergency power supply module.

[0022] The beneficial effects of the present invention compared with the prior art are:

[0023] (1) The reliability of the power distribution system of the present invention is significantly improved. There is no single point failure mode of the bus or PCU on the satellite. Through reconstruction, power can be supplied to other devices on the satellite uninterruptedly.

[0024] (2) The present invention can reasonably utilize the direction of cables and wire harnesses, solve the problem of reciprocating power cable directions when using a single PCU, save cable laying length and weight, and reduce costs;

[0025] (3) The present invention can flexibly eliminate faults under various fault conditions to ensure business continuity and safe operation of the entire satellite. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 This is a schematic diagram of the power distribution system architecture of the present invention;

[0027] Figure 2 This is a schematic diagram of the ring network switch of the present invention. DETAILED DESCRIPTION

[0028] The present invention will be further described below in conjunction with the embodiments.

[0029] The present invention provides a distributed ring power distribution system architecture based on multiple buses on a satellite, which overcomes the single-point failure problem of the current single-bus centralized power distribution and is more suitable for future satellites with high power levels of 30kW to 100kW. Once a bus fails, it can be reconstructed through a ring network switch to supply the power of other buses to the equipment on the bus to achieve continuity of on-board services. For key equipment, an emergency bus is set up for reconstruction to ensure the safety of the entire satellite. The reliability of the power supply and distribution system and the entire satellite has been significantly improved due to this architecture.

[0030] Distributed ring distribution system architecture based on multi-bus configuration, such as Figure 1As shown, it includes a first ring network switch, a second ring network switch, a third ring network switch, a fourth ring network switch, a BUS1 bus, a BUS2 bus, a BUS3 bus, a BUS4 bus, an emergency bus, a first power module, a second power module, a third power module, a fourth power module, an emergency power module and an isolating switch;

[0031] Among them, the BUS1 bus is set on the south board of the satellite's communication cabin; the BUS2 bus is set on the instrument cabin of the satellite; the BUS3 bus is set on the north board of the satellite's communication cabin; the BUS4 bus is set on the ground plane of the satellite; and the BUS1 bus, BUS2 bus, BUS3 bus, and BUS4 bus are connected end to end in sequence to form a rectangular ring frame; the first ring network switch is set at the junction of the BUS1 bus and the BUS4 bus; the second ring network switch is set at the junction of the BUS1 bus and the BUS2 bus; the third ring network switch is set at the BUS2 The fourth ring network switch is arranged at the joint of BUS3 bus and BUS4 bus; the first power module is arranged on BUS1 bus; the second power module is arranged on BUS2 bus; the third power module is arranged on BUS3 bus; the fourth power module is arranged on BUS4 bus; the emergency power module, emergency bus and isolating switch are arranged in the instrument cabin; the emergency power module is connected to the equipment on BUS1 bus, BUS2 bus and BUS3 bus respectively through the emergency bus and isolating switch.

[0032] The power of the entire satellite is evenly distributed on the BUS1 bus, BUS2 bus, BUS3 bus, and BUS4 bus; the power of each bus is 10kW and the voltage is 100V. The first power module supplies power to each device on the BUS1 bus through the BUS1 bus; the second power module supplies power to each device on the BUS2 bus through the BUS2 bus; the third power module supplies power to each device on the BUS3 bus through the BUS3 bus; and the fourth power module supplies power to each device on the BUS4 bus through the BUS4 bus.

[0033] like Figure 2 As shown, the first ring network switch, the second ring network switch, the third ring network switch, and the fourth ring network switch are identical ring network switches, each including a current limiting relay and five power relays; the current limiting relay and the five power relays are connected in parallel and are connected to the busbars on both sides respectively; the current limiting relay includes a power relay and a current limiting resistor, and the power relay and the current limiting resistor are connected in series to form a current limiting relay. The parameters of the current limiting relay are 110V / 2A; the parameters of the power relay are 110V / 25A; and the parameters of the current limiting resistor are 470Ω / 25W.

[0034] The ring network switch can reconstruct the two buses when the corresponding two buses are in a power supply shortage or power failure state. Specifically:

[0035] When there is no fault in the two busbars corresponding to the ring network switch, the current limiting relay and the five power relays in the ring network switch are in a normally open state; when one of the busbars has a fault state of insufficient power supply or no power supply, and there is no short-circuit point on the faulty busbar, the current limiting relay and the five power relays in the ring network switch are closed to achieve reconstruction.

[0036] When one of the busbars is in a power supply shortage or power failure state, the current limiting relay is closed first to form a small current path to charge the faulty busbar. During the charging process, the voltage drop between the power contacts of the unclosed power relay gradually decreases until the faulty busbar voltage continues to rise to the normal busbar voltage with charging, and the voltage drop between the power contacts of the unclosed power relay approaches 0, and 5 power relays are closed in sequence; the interconnection of the two buses and the reconstruction of the power circuit are completed.

[0037] The withstand voltage of the power relays among the five power relays and the current limiting relay is 110V, which is greater than the maximum voltage difference ΔU between the access bus and the fault bus.

[0038] When charging the power supply bus, the charging current is limited to 213mA by the current limiting resistor; the instantaneous maximum power consumption of charging is P max for:

[0039] P max =ΔU 2 / R

[0040] Where ΔU is the maximum voltage difference between the access bus and the fault bus, which is equal to the access bus voltage 100V minus the fault bus voltage 0V;

[0041] R is the resistance of the current limiting resistor.

[0042] When a short circuit occurs on any bus, the emergency bus is started, the disconnector is closed, and the emergency power supply module is used to supply power to the equipment on the faulty bus.

[0043] Example

[0044] Taking the DFH-4E platform satellite as an example, it is divided into three parts: the service module, the propulsion module and the communication module. After the three modules are docked, the entire satellite has a rectangular structure with a power level of 10 to 18kW. Assuming that the basic structure of future high-power communication satellites is still similar to this, according to the rationality of the distributed layout, the power distribution system adopts a grouping method to operate independently. A bus and a set of power supply devices can be set in the service-propulsion module (back floor), the south plate of the communication module, the north plate of the communication module and the floor. The location of the power supply device is the area where the number of active units is relatively concentrated. The number and position can be adjusted according to different satellite configurations;

[0045] b) A ring network switch is set between two adjacent busbars to achieve the reconstruction of the distribution network. All busbars are connected end to end to form a ring network. Under normal circumstances, the ring network switch is in the disconnected state, and each busbar is an independent sub-distribution system, supplying power to the load equipment in its own area. Fuses or electronic fuses are set at the load connection points of the distribution lines to achieve fault isolation;

[0046] c) The sub-distribution systems are connected end to end through a ring network switch to form a distribution system for the entire star. Any two adjacent busbars are powered by two independent power supply devices to form a redundant backup. When one of the busbars fails, the entire star distribution system can be reconstructed through the ring network switch.

[0047] d) Establish an emergency bus. For on-board electrical equipment, classify them according to their functional properties and importance to determine the quality requirements and priority levels of their electricity. Among them, key electrical equipment is the electrical equipment necessary to ensure the safety of the satellite, generally including the satellite's propulsion equipment, attitude and orbit control equipment, and central computer equipment. This type of equipment requires secondary redundancy design on the power distribution network. The emergency bus connects all key equipment on the satellite and is isolated from the main circuit by a safety switch. Once a short circuit occurs in the power supply bus where the key equipment is located, and it is impossible to determine whether the fault point has been eliminated, the emergency bus should be started and the key equipment should be transferred to the emergency bus for use to ensure the normal operation of the satellite's key equipment, thereby ensuring the safety of the entire satellite.

[0048] Taking the 40kW DFH-4E platform satellite as an example, its main structure is a rectangular parallelepiped structure with a load-bearing cylinder. The instrument cabin and the communication cabin are docked during the B phase test. DFH-4E platform satellite layout: The instrument cabin is the majority of the platform equipment, including control and propulsion equipment, central computers, attitude and orbit control computers, telemetry and remote control equipment, etc.; the east and west boards of the communication cabin are generally equipped with spot beam antennas and other passive equipment; the north and south boards of the communication cabin are equipped with tracking subsystems (fixed placement, transponders, measurement and control antennas) and electric propulsion systems, as well as most of the payload active equipment. Payload equipment such as phased array antennas and payload controllers are arranged on the floor.

[0049] According to the layout and power consumption analysis, a multi-bus structure is used for ring configuration. Active equipment is mainly concentrated in the instrument cabin, the north and south boards of the communication cabin, and the floor, so 4 independent busbars are required: a busbar BUS1 is configured in the instrument cabin, a busbar BUS2 and BUS3 are configured in the north and south boards of the communication cabin, and a busbar BUS4 is configured in the floor.

[0050] The power of the entire satellite is evenly distributed on each bus, with a power level of 10kW and a voltage of 100V. Considering the need for ring configuration reconstruction, the power design margin of the PCU in each power module is selected at 1.5 times to ensure that the power level of the PCU on the two buses can simultaneously power all devices on the three buses. The solar cell interface and battery specifications in the power module are arranged and selected according to 15kW.

[0051] For on-board electrical equipment, they are classified according to their functional properties and importance to determine the quality requirements and priority levels of their power. Among them, key electrical equipment is the electrical equipment necessary to ensure satellite safety, important equipment is the equipment necessary to ensure satellite business continuity, and the rest are general equipment. The equipment classification is shown in Table 1.

[0052] Table 1

[0053]

[0054] The key equipment on BUS1 is the central computer, attitude and orbit control computer, Taisen, Starsensor, and reaction wheel; the key equipment on BUS2 and BUS3 is the fixed release, transponder, and electric propulsion unit. These devices are key equipment to ensure satellite safety. There is no key equipment on BUS4. The important equipment is the phased array and payload controller, which are the equipment that determines the main functions of the payload and mainly ensures the continuity of satellite payload business.

[0055] In order to ensure the safety of the satellite and deal with short-circuit faults in important parts of the satellite, it is necessary to set up an emergency bus to connect all key equipment on the satellite and isolate it from the main circuit through a safety switch. Once a short circuit occurs in the power supply bus where the key equipment is located, and it is impossible to determine whether the fault point has been eliminated, the emergency bus should be started and the key equipment should be transferred to the emergency bus for use to ensure the normal operation of the satellite's key equipment, thereby ensuring the safety of the entire satellite. According to analysis, key equipment is mainly distributed in the north and south plates of the instrument cabin and the communication cabin, and the layout of the fixed placement, transponder and electric propulsion unit should be relatively close to the instrument cabin. Therefore, the location of the emergency bus is set in the instrument cabin to minimize the cable route, while ensuring the multiple redundant design and reliability of key equipment.

[0056] The ring network switch is responsible for interconnecting and reconstructing the two busbars in the event of an open circuit or insufficient power supply. The switch power circuit is composed of five 110V / 25A magnetic latching relays (or high-power solid-state electronic switches) in parallel, and a 110V / 2A magnetic latching relay and a current limiting resistor (470Ω / 25W) are connected in series to form a current limiting switch path. The main function of the control circuit is to complete the command reception, status output and on-off drive of the ring network switch.

[0057] Working mode of the ring network switch: when no fault occurs, all relays are in the normally off state. The ring network switch can only be closed when there is a power shortage or power failure on the adjacent bus and there is no short-circuit point on the faulty bus. When it is necessary to reconstruct the two buses, first turn on the current limiting relay to form a small current path to charge the bus capacitor. When the capacitor voltage continues to rise to the bus voltage level as the charging continues, turn on the power relays 1 to 5 in sequence, and the power circuit is fully connected. When the current limiting relay is turned on, the maximum voltage difference of the relay power contact (main contact) is 100V (connected bus voltage 100V, faulty bus 0V, the worst case), which does not exceed the relay's 110V action withstand voltage indicator. When charging the bus capacitor, the charging current is limited by the power resistor, which is about 213mA (100V / 470Ω), and the instantaneous maximum power consumption is

[0058] Pmax=△U 2 / R=(100-0)2 / 470=21.3W

[0059] The current limiting resistor is 470Ω / 25W, which does not exceed the rated power consumption of the resistor. As the busbar capacitor charge increases, the capacitor voltage increases, the voltage drop on the power resistor continues to decrease, and the power also continues to decrease. After a period of time, the voltage drop between the relay power contacts tends to zero. At this time, a command can be sent to connect other power relays to complete the interconnection of the two buses and the reconstruction of the power circuit.

[0060] The busbar configuration and ring network switch configuration can be adaptively adjusted as the power of the entire satellite increases and the layout changes.

[0061] The present invention proposes a distributed ring power distribution system architecture based on multiple buses on board, which adopts a ring network configuration mode of multiple buses and multiple sources, effectively avoiding the single point failure problem under the single bus centralized power distribution architecture, and greatly improving the reliability of the satellite power supply and distribution system. At the same time, the ring power distribution method can reduce the laying length and weight of the power cable, and contribute to the weight reduction of the whole satellite. This architecture can be applied to the power distribution system of future 30kW-100kW high-orbit high-power communication satellites.

[0062] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A distributed ring power distribution system architecture based on multi-bus configuration on a satellite, characterized by: It includes a first ring network switch, a second ring network switch, a third ring network switch, a fourth ring network switch, a BUS1 bus, a BUS2 bus, a BUS3 bus, a BUS4 bus, an emergency bus, a first power module, a second power module, a third power module, a fourth power module, an emergency power module and an isolating switch; Among them, the BUS1 bus is set on the south board of the satellite's communication cabin; the BUS2 bus is set on the instrument cabin of the satellite; the BUS3 bus is set on the north board of the satellite's communication cabin; the BUS4 bus is set on the ground plane of the satellite; and the BUS1 bus, BUS2 bus, BUS3 bus, and BUS4 bus are connected end to end in sequence to form a rectangular ring frame; the first ring network switch is set at the junction of the BUS1 bus and the BUS4 bus; the second ring network switch is set at the junction of the BUS1 bus and the BUS2 bus; the third ring network switch is set at the BUS2 The fourth ring network switch is set at the joint of the BUS3 busbar and the BUS4 busbar; the first power module is set on the BUS1 busbar; the second power module is set on the BUS2 busbar; the third power module is set on the BUS3 busbar; the fourth power module is set on the BUS4 busbar; the emergency power module, the emergency busbar and the isolating switch are set in the instrument cabin; the emergency power module is connected to the equipment on the BUS1 busbar, the BUS2 busbar and the BUS3 busbar respectively through the emergency busbar and the isolating switch; The first ring network switch, the second ring network switch, the third ring network switch, and the fourth ring network switch are identical ring network switches, and each includes a current limiting relay and five power relays; the current limiting relay and the five power relays are connected in parallel and are respectively connected to the busbars on both sides; the current limiting relay includes a power relay and a current limiting resistor, and the power relay and the current limiting resistor are connected in series to form a current limiting relay; The parameters of the current limiting relay are 110V / 2A; the parameters of the power relay are 110V / 25A; the parameters of the current limiting resistor are 470Ω / 25W; The ring network switch realizes the reconstruction of the two busbars when the corresponding two busbars are in a fault state of insufficient power supply or power failure, specifically: When the two busbars corresponding to the ring network switch are not faulty, the current limiting relay and the five power relays in the ring network switch are in a normally disconnected state; when one of the busbars has a power supply shortage or power failure, and there is no short-circuit point on the faulty busbar, the current limiting relay and the five power relays in the ring network switch are closed to achieve reconstruction; When one of the busbars is in a power supply shortage or power failure state, the current limiting relay is closed first to form a small current path to charge the faulty busbar. During the charging process, the voltage drop between the power contacts of the unclosed power relay gradually decreases until the faulty busbar voltage continues to rise to the normal busbar voltage with charging, and the voltage drop between the power contacts of the unclosed power relay approaches 0. Then, 5 power relays are closed in sequence to complete the interconnection of the two buses and the reconstruction of the power circuit.

2. According to claim 1, a distributed ring power distribution system architecture based on multi-bus configuration on a satellite, characterized in that: The power of the entire satellite is evenly distributed on the BUS1 bus, BUS2 bus, BUS3 bus, and BUS4 bus; the power of each bus is 10kW and the voltage is 100V.

3. According to claim 2, a distributed ring power distribution system architecture based on multi-bus configuration on a satellite, characterized in that: The first power module supplies power to each device on the BUS1 bus through the BUS1 bus; the second power module supplies power to each device on the BUS2 bus through the BUS2 bus; the third power module supplies power to each device on the BUS3 bus through the BUS3 bus; the fourth power module supplies power to each device on the BUS4 bus through the BUS4 bus.

4. The distributed ring power distribution system architecture based on multi-bus configuration on a satellite according to claim 3, characterized in that: The withstand voltage of the power relays among the five power relays and the current limiting relay is 110V, which is greater than the maximum voltage difference ΔU between the access bus and the fault bus.

5. The distributed ring power distribution system architecture based on multi-bus configuration on a satellite according to claim 4, characterized in that: When charging the power supply bus, the charging current is limited to 213mA by the current limiting resistor; the instantaneous maximum power consumption of charging is P max for: P max =ΔU 2 / R Where ΔU is the maximum voltage difference between the access bus and the fault bus, which is equal to the access bus voltage 100V minus the fault bus voltage 0V; R is the resistance of the current limiting resistor.

6. The distributed ring power distribution system architecture based on multi-bus configuration on a satellite according to claim 1, characterized in that: When a short circuit occurs on any bus, the emergency bus is started, the disconnector is closed, and the emergency power supply module is used to supply power to the equipment on the faulty bus.

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