CN113071717A - Space low-rail high-voltage power supply system supporting on-rail maintenance - Google Patents
Space low-rail high-voltage power supply system supporting on-rail maintenance Download PDFInfo
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- CN113071717A CN113071717A CN202110336175.XA CN202110336175A CN113071717A CN 113071717 A CN113071717 A CN 113071717A CN 202110336175 A CN202110336175 A CN 202110336175A CN 113071717 A CN113071717 A CN 113071717A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/428—Power distribution and management
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
- B64G1/443—Photovoltaic cell arrays
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J1/00—Circuit arrangements for dc mains or dc distribution networks
- H02J1/10—Parallel operation of dc sources
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/34—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering
- H02J7/35—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering with light sensitive cells
Abstract
A space low-rail high-voltage power supply system supporting on-rail maintenance belongs to the technical field of space power supplies. The spacecraft load power supply system comprises two independent power channels, wherein the two power channels have the same functional composition and provide energy for a spacecraft load through energy grid connection; each power channel takes the solar cell wing as a starting point and the bus filter as an end point to form an independent 100V power supply bus; each power channel comprises a solar cell wing, a driving mechanism, a shunt regulator, a bus filter, a comprehensive driving controller, a charge-discharge regulator, a lithium ion storage battery pack and a power manager; the solar cell wing, the shunt regulator, the bus filter, the comprehensive drive controller, the charge-discharge regulator, the lithium ion storage battery pack and the power supply manager are minimum replaceable units ORUs. According to the invention, when the related products of the power supply system have faults, the maintenance operation is carried out on the track by astronauts, so that the service life of the power supply system is prolonged.
Description
Technical Field
The invention relates to a space low-rail high-voltage power supply system supporting on-rail maintenance, and belongs to the technical field of space power supplies.
Background
In early space projects, space systems were short-lived, low power, simpler systems, and constrained by human activities out of ground, and it was common practice to achieve high availability and high safety of space vehicles by using highly reliable (zero) components or a large number of redundant designs and on-orbit backups. With the development of the third stage of manned aerospace in China, a space station where people reside for a long time is built in China. The space station is different from any on-orbit aircraft in China in the past, is a manned aircraft with long service life, high reliability, high voltage and high power, and has a more complex system. To meet the task requirements of long service life and high availability in 15 years on-orbit, the cost of improving the reliability of the component is high or even unrealistic, and due to various factors such as the launching weight of a spacecraft, the power consumption, the overall layout, the final assembly and the like, a large amount of redundant designs and on-orbit backups cannot be used. How to prolong the service life of the space system and reduce the operation cost becomes an important problem. Foreign space stations such as peace marks and international space stations realize and even prolong the service life of the spacecraft through a large amount of on-orbit maintenance. Therefore, maintenance is an indispensable means for ensuring long-term on-orbit reliable operation of the space station.
The power supply system is used as energy supply of the spacecraft, is one of key systems for ensuring high reliability and long service life of the spacecraft, and is also one of systems with higher failure frequency in the spacecraft. According to statistics, the power supply system fault proportion accounts for 24% of the whole spacecraft system. Compared with the power supply system of the conventional spacecraft, the power demand of the power supply system of the space station is higher, and the system composition is more complex. In order to ensure the on-rail long-term reliable operation of the power supply system and simplify the design of the power supply system, the maintainability design work must be carried out in combination with the reliability.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, the space low-rail high-voltage power supply system supporting on-rail maintenance is provided, and the service life of the power supply system is prolonged by performing on-rail maintenance operation on astronauts when related products of the power supply system break down.
The technical solution of the invention is as follows: a space low-rail high-voltage power supply system supporting on-rail maintenance comprises two independent power channels, wherein the two power channels have the same functional composition and provide energy for a spacecraft load through energy grid connection;
each power channel takes the solar cell wing as a starting point and the bus filter as an end point to form an independent 100V power supply bus;
each power channel comprises a solar cell wing, a driving mechanism, a shunt regulator, a bus filter, a comprehensive driving controller, a charge-discharge regulator, a lithium ion storage battery pack and a power manager; the solar cell wing, the shunt regulator, the bus filter, the comprehensive drive controller, the charge-discharge regulator, the lithium ion storage battery pack and the power supply manager are minimum replaceable units ORUs.
Furthermore, a charging and discharging regulator and a group of lithium ion storage battery packs form a unit;
the number of the units is configured according to the load requirement of the power channel;
the units are independent of each other and are connected in parallel.
Further, the working modes comprise three maintenance working modes of power channel power-off, unit power-off and ORU power-off only.
Further, the solar cell wing provides continuous electric energy through photoelectric conversion into a power channel; the shunt regulator supplies power and shunts and regulates the electric energy provided by the solar cell wing according to the load requirement; the bus filter collects the energy of the solar battery wing and the storage battery pack and supplies power to the load through energy grid connection;
the solar cell wing, the shunt regulator and the bus filter adopt a power channel power-off maintenance working mode.
Furthermore, a voltage stabilizing power supply switch is arranged in the bus filter and used for electrifying the power channel again after maintenance through the ORU of power channel power-off maintenance; the voltage-stabilizing power supply switch is a relay, and the power supply of a relay coil is provided by another power channel general circuit 28V instruction bus.
Further, the lithium ion storage battery pack performs charge regulation and discharge output through a charge-discharge regulator of the unit where the lithium ion storage battery pack is located; the functions of all units are independent and are accessed into the system in parallel;
the charging and discharging regulator and the lithium ion storage battery pack adopt a single-unit power-off maintenance working mode.
Further, the lithium ion storage battery pack performs charge control and discharge regulation through a charge-discharge regulator; a storage battery charging switch and a discharging switch are arranged in the charging and discharging regulator, so that the power failure of the lithium ion storage battery is realized;
the charging switch and the discharging switch both adopt relays;
furthermore, the comprehensive driving controller is used for unfolding and folding the solar cell wings and driving the solar cell wings to directionally control the sun; the power supply manager is used for managing the system state, and descending and uploading state parameters and instructions of various products of the system through interactive communication with the measurement and control system;
the comprehensive driving controller and the power supply manager adopt an ORU-only power-off maintenance working mode.
Furthermore, 100V power supply of the charging and discharging regulator, the comprehensive driving controller and the power manager is provided by the bus filter, and power supply switches are respectively arranged to realize independent power failure of the single controller; the power supply switch is a relay.
Further, the power channel is configured by adopting a distributed secondary power supply;
the shunt regulator, the charge-discharge regulator, the comprehensive drive controller and the power supply manager are all converted into +/-12V and 5V secondary power supplies required by 100V power supply buses in the single machine;
the bus filter performs 28V instruction bus conversion through a 100V power supply bus in the single machine and is used for supplying power to the relay coil and other product power supply relay coils.
Compared with the prior art, the invention has the advantages that:
compared with the existing space power supply system, the space low-rail high-voltage power supply system provided by the invention supports on-rail maintenance and replacement of astronauts. With the gradual establishment of space stations in China, the on-orbit mobility of spacecrafts is gradually enhanced, and under the condition that a large number of high-reliability zero components, redundancy and on-orbit backup cannot be used due to various constraints of spacecraft launching cost, weight, power consumption, overall layout, final assembly and the like, the on-orbit mobility enhancement method is beneficial to prolonging the on-orbit service life of a power supply system. In order to ensure personal safety of astronauts during maintenance operation and reduce the power-off times of a power supply system, different maintenance power-off modes are provided according to different functions of products. Meanwhile, key parameters and instructions of hard-line redundancy are identified, the possibility that the whole power supply system needs to be powered off and maintained under the fault condition is reduced, and the influence of system power-off on the spacecraft is greatly reduced.
Drawings
FIG. 1 is a block diagram of a space power system that supports on-rail maintenance.
Detailed Description
In order to better understand the technical solutions, the technical solutions of the present application are described in detail below with reference to the drawings and specific embodiments, and it should be understood that the specific features in the embodiments and examples of the present application are detailed descriptions of the technical solutions of the present application, and are not limitations of the technical solutions of the present application, and the technical features in the embodiments and examples of the present application may be combined with each other without conflict.
The following describes in further detail a spatial low-rail high-voltage power supply system supporting on-rail maintenance provided in an embodiment of the present application with reference to the drawings in the specification, and specific implementations may include (as shown in fig. 1):
in the scheme provided by the embodiment of the application, the power supply system comprises 2 independent power channels, the 2 power channels have the same functional composition, and energy is provided for spacecraft loads through energy grid connection. Each power channel takes the solar cell wing as a starting point and the bus filter as an end point to form an independent 100V power supply bus. Each power channel consists of a solar cell wing, a driving mechanism, a comprehensive driving controller, a shunt regulator, a charge-discharge regulator 1, a charge-discharge regulator 2, a charge-discharge regulator 3, a lithium ion storage battery pack 1, a lithium ion storage battery pack 2, a lithium ion storage battery pack 3, a bus filter and a power manager. The charging and discharging regulator 1 and the lithium ion storage battery pack 1 form a unit 1, the charging and discharging regulator 2 and the lithium ion storage battery pack 2 form a unit 2, and the charging and discharging regulator 3 and the lithium ion storage battery pack 3 form a unit 3. The power supply system is composed of a block diagram as shown in figure 1.
The solar cell wing provides continuous electric energy through photoelectric conversion into a power channel; the shunt regulator supplies power and shunts and regulates the electric energy provided by the solar cell wing according to the load requirement; the bus filter collects the energy of the solar battery wing and the storage battery pack and supplies power to the load through energy grid connection; the lithium ion storage battery pack performs charge regulation and discharge output through a charge-discharge regulator of the unit in which the lithium ion storage battery pack is arranged; the comprehensive driving controller is mainly used for unfolding and folding the solar cell wings and driving the solar cell wings to directionally control the sun; the power supply manager is mainly used for system state management, and is used for downlink and upload of state parameters and instructions of various products of the system through interactive communication with the measurement and control system.
1) In the power supply system, a solar battery wing, a comprehensive drive controller, a shunt regulator, a charge-discharge regulator 1/2/3, a lithium ion battery 1/2/3, a bus filter, and a power supply manager are determined as ORUs.
2) For personal safety when guaranteeing the maintenance operation of astronaut, and reduce power channel outage number of times, according to the functional characteristic of each ORU, adopt different outage modes to carry out the maintenance in orbit, mainly include:
the power channel power-off maintenance work mode is as follows: solar cell wings, shunt regulators and bus filters;
the single unit power-off maintenance work mode: a charge-discharge regulator 1/2/3, a lithium ion battery 1/2/3;
ORU-only power-off maintenance mode: the integrated drive controller and the power supply manager.
3) The charging and discharging regulator 1/2/3, the comprehensive driving controller and the power manager 100V power supply bus are provided by a bus filter, and are respectively provided with a power supply switch, so that the independent power failure of the single machine is controlled. The power supply switch adopts a relay;
4) a storage battery charging switch and a discharging switch are arranged in the charging and discharging regulator, so that the power failure of the lithium ion storage battery pack of the unit is realized. The charging switch and the discharging switch both adopt relays;
5) and a voltage stabilizing power supply switch is arranged in the bus filter and used for electrifying the power channel again after the ORU of the power channel power-off maintenance is maintained. The switch adopts a relay, and a voltage-stabilizing power supply relay coil supplies power to a power channel general circuit 28V instruction bus;
6) the key parameters and instructions of the system and the parameters and instructions related to maintenance of all ORUs adopt a bus and hard line redundancy mode, and reliability is improved. All bus parameters and instructions of the power supply system are transmitted to the ground through the power supply manager and the measurement and control system in an interactive communication way; when the power manager is maintained, in order to ensure normal power supply of the system, key parameters and instructions of the system are downloaded to the ground in a hard-wire mode through the digital system.
Table 1 and table 2 show typical key parameters and commands of the system and parameters and commands related to maintenance of the ORU, which can be increased or decreased according to the characteristics and task requirements of the power system when applied.
TABLE 1 hard-wired redundancy key parameter table of system
TABLE 2 hard-wired redundancy key instruction list of system
| Serial number | Instruction | Receiving product | |
| 1. | Solar cell wing capture command | Comprehensive driving controller | |
| 2. | Integrated drive controller power supply relay on/off command | Bus filter | |
| 3. | Power manager power supply relay on/off command | Bus filter | |
| 4. | Switching-off instruction of power supply relay of charging and discharging |
Bus filter | |
| 5. | Charging and discharging regulator 2 power supply relay disconnection instruction | Bus filter | |
| 6. | Switching-off instruction of power supply relay of charging and discharging regulator 3 | Bus filter | |
| 7. | Charging relay disconnection instruction of charging and discharging |
Charging and discharging |
|
| 8. | Charging relay disconnection instruction of charging and discharging regulator 2 | Charging and discharging regulator 2 | |
| 9. | Charging relay disconnection instruction of charging and discharging regulator 3 | Charging and discharging regulator 3 | |
| 10. | Discharging relay disconnection instruction of charging and discharging |
Charging and discharging |
|
| 11. | Discharging relay disconnection instruction of charging and discharging regulator 2 | Charging and discharging regulator 2 | |
| 12. | Discharging relay disconnection instruction of charging and discharging regulator 3 | Charging and discharging regulator 3 |
6) The power channel adopts distributed secondary power supply configuration: the shunt regulator, the charge-discharge regulator 1/2/3, the comprehensive drive controller and the power supply manager all automatically convert +/-12V and 5V secondary power supplies required by products through a 100V power supply bus in the single machine; the bus filter performs 28V instruction bus conversion through a 100V power supply bus in the single machine and is used for supplying power to the relay coil and other product power supply relay coils.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below.
1) The power supply system consists of 2 independent 100V power supply power channels, the 2 power channels have the same functional composition, and provide energy for spacecraft loads through grid connection;
2) each power channel consists of the following products: the device comprises a solar cell wing, a driving mechanism, a comprehensive driving controller, a shunt regulator, a charge-discharge regulator 1, a charge-discharge regulator 2, a charge-discharge regulator 3, a lithium ion storage battery pack 1, a lithium ion storage battery pack 2, a lithium ion storage battery pack 3, a bus filter and a power manager;
3) the charging and discharging regulator 1 and the lithium ion storage battery pack 1 form a unit 1;
4) the charging and discharging regulator 2 and the lithium ion storage battery pack 2 form a unit 2;
5) the charging and discharging regulator 3 and the lithium ion storage battery 3 form a unit 3;
6) determining a power supply system ORU: the solar energy power generation system comprises a solar cell wing, a comprehensive driving controller, a shunt regulator, a charge-discharge regulator 1, a charge-discharge regulator 2, a charge-discharge regulator 3, a lithium ion storage battery pack 1, a lithium ion storage battery pack 2, a lithium ion storage battery pack 3, a bus filter and a power manager;
7) the charging and discharging regulator 1/2/3, the comprehensive driving controller and the power supply manager 100V power supply bus are provided by a bus filter, and a power supply switch is arranged for each product;
8) the comprehensive driving controller corresponds to a power supply switch 1 in the bus filter, and the power supply switch adopts a relay;
9) the power supply manager corresponds to a power supply switch 2 in the bus filter, and the power supply switch adopts a relay;
10) the charging and discharging regulator 1 corresponds to a power supply switch 3 in the bus filter, and the power supply switch adopts a relay;
11) the charging and discharging regulator 2 corresponds to a power supply switch 4 in the bus filter, and the power supply switch adopts a relay;
12) the charging and discharging regulator 3 corresponds to a power supply switch 5 in the bus filter, and the power supply switch adopts a relay;
13) the single power channel is configured by adopting a distributed secondary power supply, and the shunt regulator, the charge-discharge regulator 1, the charge-discharge regulator 2, the charge-discharge regulator 3, the comprehensive driving controller and the power supply manager all automatically convert +/-12V and 5V secondary power supplies required by products through a 100V power supply bus in the single machine;
14) the bus filter performs 28V instruction bus conversion through a 100V power supply bus in the single machine and is used for supplying power to a power supply switch 1, a power supply switch 2, a power supply switch 3, a power supply switch 4, a power supply switch 5 and other product relay coils;
15) the lithium ion battery pack 1 performs charge control and discharge regulation by a charge/discharge regulator 1. A charging switch K1 and a discharging switch K2 of the lithium ion storage battery pack 1 are arranged in the charging and discharging regulator 1, and power supply switches are relays;
16) the lithium ion battery pack 2 performs charge control and discharge regulation by a charge/discharge regulator 2. A charging switch K3 and a discharging switch K4 of the lithium ion storage battery pack 2 are arranged in the charging and discharging regulator 2, and power supply switches are relays;
17) the lithium ion battery pack 3 performs charge control and discharge regulation by a charge/discharge regulator 3. A charging switch K5 and a discharging switch K6 of the lithium ion storage battery pack 3 are arranged in the charging and discharging regulator 3, and power supply switches are relays;
18) the bus filter is arranged at a 100V power supply input interface of the rail voltage stabilizing source, a 100V power supply bus of the rail voltage stabilizing source is connected through a power supply switch 6 in the bus filter, and the power supply switch adopts a relay;
19) the bus filter is provided with an input interface of a 28V command bus (provided by another power channel) of the overall circuit, and is used for supplying power to the relay coil of the power supply switch 6;
20) the parameters in the table 1 adopt a bus and hard line redundancy mode, so that the reliability is improved. Of course, table 1 shows a typical parameter set for the application of the system, which can be increased or decreased according to the characteristics of the power system and the task requirements. The bus parameters are interactively communicated with the measurement and control system through the power manager and are downloaded to the ground; the hard wire parameters are directly downloaded to the ground through a counting system;
21) the instructions in table 2 adopt a bus and hard line redundancy mode, so that the reliability is improved. Of course, table 2 shows a typical instruction set for the application of the system, which can be increased or decreased according to the characteristics of the power system and the task requirements. The bus instruction is transmitted to the spacecraft from the ground through the interactive communication between the power manager and the measurement and control system; the hard wire instruction is directly uploaded to the spacecraft from the ground through the system of the number pipes;
22) when the solar cell wing, the shunt regulator or the bus filter are maintained and replaced, a power channel power-off mode is adopted, and the spacecraft load is allocated to the other power channel. The solar battery wings perform back-to-back control, and the ground measurement and control system sends instructions to disconnect the power supply switches 1 and 2 and the power supply switches K1, K2, K3, K4, K5 and K6, so that the power supply system of the power channel is powered off. When the power supply is powered on after maintenance, 100V power supply of the power channel is provided by an on-rail voltage-stabilizing source, a voltage-stabilizing power supply switch 6 is provided by a 28V instruction bus of another channel overall circuit, and the state of the power channel is recovered;
23) when the charging and discharging regulator 1 or the lithium ion storage battery pack 1 is maintained and replaced, the power-off mode of the unit 1 is adopted, and the ground measurement and control system sends an instruction to disconnect the power supply switch 3 and the power supply switches K1 and K2. The load of the power channel on the spacecraft is adjusted, and the power of 1 unit is reduced or the power is allocated to another power channel. When the power is on after maintenance, the state of the unit can be directly recovered;
24) when the charging and discharging regulator 2 or the lithium ion storage battery pack 2 is maintained and replaced, the power-off mode of the unit 2 is adopted, and the ground measurement and control system sends an instruction to disconnect the power supply switch 4 and the power supply switches K3 and K4. The load of the power channel on the spacecraft is adjusted, and the power of 1 unit is reduced or the power is allocated to another power channel. When the power is on after maintenance, the state of the unit can be directly recovered;
25) when the charging and discharging regulator 3 or the lithium ion storage battery 3 is maintained and replaced, the power-off mode of the unit 3 is adopted, and the ground measurement and control system sends an instruction to disconnect the power supply switch 5 and the power supply switches K5 and K6. The load of the power channel on the spacecraft is adjusted, and the power of 1 unit is reduced or the power is allocated to another power channel. When the power is on after maintenance, the state of the unit can be directly recovered;
26) when the integrated drive controller is maintained, after the solar battery wing is biased to the maximum sun-facing angle, the ground measurement and control system sends an instruction to disconnect the power supply switch 1, and the power channel on the spacecraft reduces the load or is allocated to another power channel according to the biased power supply capacity. When the power is on after maintenance, the product state can be directly recovered;
27) when the power manager is maintained, the ground measurement and control system sends an instruction to disconnect the power supply switch 2, the power channel on the spacecraft supplies power normally, and the system state is displayed through key parameters in a table 1. When the power is on after maintenance, the product state can be directly recovered.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present application without departing from the spirit and scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is intended to include such modifications and variations as well.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (10)
1. The utility model provides a support space low rail high voltage power supply system of in-orbit maintenance which characterized in that: the system comprises two independent power channels, wherein the two power channels have the same functional composition and provide energy for spacecraft loads through energy grid connection;
each power channel takes the solar cell wing as a starting point and the bus filter as an end point to form an independent 100V power supply bus;
each power channel comprises a solar cell wing, a driving mechanism, a shunt regulator, a bus filter, a comprehensive driving controller, a charge-discharge regulator, a lithium ion storage battery pack and a power manager; the solar cell wing, the shunt regulator, the bus filter, the comprehensive drive controller, the charge-discharge regulator, the lithium ion storage battery pack and the power supply manager are minimum replaceable units ORUs.
2. A space low-rail high-voltage power supply system supporting on-rail maintenance according to claim 1, wherein: a charging and discharging regulator and a group of lithium ion storage battery packs form a unit;
the number of the units is configured according to the load requirement of the power channel;
the units are independent of each other and are connected in parallel.
3. A space low-rail high-voltage power supply system supporting on-rail maintenance according to claim 1, wherein: the working modes comprise three maintenance working modes of power channel power-off, unit power-off and ORU power-off only.
4. A space low-rail high-voltage power supply system supporting on-rail maintenance according to claim 3, wherein: the solar cell wing provides continuous electric energy through photoelectric conversion into a power channel; the shunt regulator supplies power and shunts and regulates the electric energy provided by the solar cell wing according to the load requirement; the bus filter collects the energy of the solar battery wing and the storage battery pack and supplies power to the load through energy grid connection;
the solar cell wing, the shunt regulator and the bus filter adopt a power channel power-off maintenance working mode.
5. A space low-rail high-voltage power supply system supporting on-rail maintenance according to claim 4, wherein: a voltage stabilizing power supply switch is arranged in the bus filter and used for electrifying the power channel again after maintenance through the ORU of power channel power-off maintenance; the voltage-stabilizing power supply switch is a relay, and the power supply of a relay coil is provided by another power channel general circuit 28V instruction bus.
6. A space low-rail high-voltage power supply system supporting on-rail maintenance according to claim 3, wherein: the lithium ion storage battery pack performs charge regulation and discharge output through a charge-discharge regulator of the unit in which the lithium ion storage battery pack is arranged; the functions of all units are independent and are accessed into the system in parallel;
the charging and discharging regulator and the lithium ion storage battery pack adopt a single-unit power-off maintenance working mode.
7. A space low-rail high-voltage power supply system supporting on-rail maintenance according to claim 6, wherein: the lithium ion storage battery pack performs charge control and discharge regulation through a charge-discharge regulator; a storage battery charging switch and a discharging switch are arranged in the charging and discharging regulator, so that the power failure of the lithium ion storage battery is realized;
the charging switch and the discharging switch both adopt relays;
8. a space low-rail high-voltage power supply system supporting on-rail maintenance according to claim 3, wherein: the comprehensive driving controller is used for unfolding and folding the solar cell wings and driving the solar cell wings to directionally control the sun; the power supply manager is used for managing the system state, and descending and uploading state parameters and instructions of various products of the system through interactive communication with the measurement and control system;
the comprehensive driving controller and the power supply manager adopt an ORU-only power-off maintenance working mode.
9. A space low-rail high-voltage power supply system supporting on-rail maintenance according to claim 1, wherein: 100V power supply of the charging and discharging regulator, the comprehensive driving controller and the power supply manager is provided by a bus filter, and power supply switches are respectively arranged to realize independent power failure of the single controller; the power supply switch is a relay.
10. A space low-rail high-voltage power supply system supporting on-rail maintenance according to claim 1, wherein: the power channel is configured by adopting a distributed secondary power supply;
the shunt regulator, the charge-discharge regulator, the comprehensive drive controller and the power supply manager are all converted into +/-12V and 5V secondary power supplies required by 100V power supply buses in the single machine;
the bus filter performs 28V instruction bus conversion through a 100V power supply bus in the single machine and is used for supplying power to the relay coil and other product power supply relay coils.
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