CN115663783A - Bus power interactive power supply and distribution system based on minimum satellite system - Google Patents
Bus power interactive power supply and distribution system based on minimum satellite system Download PDFInfo
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Abstract
The invention discloses a bus power interactive power supply and distribution system based on a minimum system on a satellite, which comprises: the system comprises a main power controller, a minimum system power supply, an interconnection bus and a bus interconnection switch; the main power controller is connected with the minimum system power supply through an interconnection bus, and a bus interconnection switch is arranged on the interconnection bus; the main power controller is used for supplying power to other equipment on the satellite except the minimum system envelope equipment; a minimum system power supply for supplying power to the minimum system envelope device; and the bus interconnection switch is used for controlling the on-off between the main power controller and the minimum system power supply to realize power interaction. According to the bus power interaction power supply and distribution system based on the minimum system on the satellite, the reliability of the satellite is improved, and the influence of single-point faults of the bus on the safety of the whole satellite is avoided.
Description
Technical Field
The invention belongs to the technical field of satellite power supply and distribution, and particularly relates to a bus power interactive power supply and distribution system based on a minimum system on a satellite.
Background
The power supply and distribution subsystem is an important component of the satellite and is mainly responsible for supplying and distributing electric energy to the payload and the platform in each flight phase of the satellite.
At present, a single-bus Power supply and distribution system is generally adopted for high-orbit high-Power GEO communication satellites, and only one Power supply controller (Power Conditioning Unit, PCU, power supply controller) is configured and is a single-point device. In order to ensure the power supply safety of the PCU and the bus, the PCU and the bus are subjected to multiple rounds of strict verification and inspection in design, process and production process. The single-bus power supply and distribution system has low adaptability to high-power-level scenes, and meanwhile, the system has no reconstruction capability; for important loads, except for the difference in the undervoltage protection value, no special configuration is performed on a power distribution mode, so that the system has insufficient fault tolerance capability for PCU equipment to generate single-point faults such as short circuit of a bus output end and the like.
As the power levels of satellites increase, the power supply and distribution system architecture also needs to be adapted. The reliability of the current communication satellite power supply and distribution system is more than 0.99 at the initial stage of the service life and more than 0.96 at the end stage of the service life. For a system, the reliability is high and is not equal to the influence range after a fault occurs, and the influence range is small, for example, although a power supply controller adopts a multi-module redundancy configuration, because modules are uniformly output through a bus after being connected in parallel, if a bus short-circuit fault occurs, serious consequences are caused. Therefore, the multi-module redundant cross backup cannot completely eliminate the single-point failure influence caused by the parallel output of the power controllers through the bus bars, and the fundamental solution still needs to be improved and optimized on the topological architecture of the power supply and distribution system.
Disclosure of Invention
The technical problem of the invention is solved: the defects of the prior art are overcome, the bus power interactive power supply and distribution system based on the minimum system on the satellite is provided, the reliability of the satellite is improved, and the influence of single-point faults of the bus on the safety of the whole satellite is avoided.
In order to solve the technical problem, the invention discloses a bus power interaction power supply and distribution system based on a minimum system on a satellite, which comprises: the system comprises a main power controller, a minimum system power supply, an interconnection bus and a bus interconnection switch; the main power controller is connected with the minimum system power supply through an interconnection bus, and a bus interconnection switch is arranged on the interconnection bus;
the main power supply controller is used for supplying power to other equipment on the satellite except minimum system envelope equipment;
a minimum system power supply for supplying power to the minimum system envelope device;
the bus interconnection switch is used for controlling the on-off between the main power controller and the minimum system power supply; when the bus interconnection switch is in a closed state, the main power controller is communicated with the minimum system power supply, so that power interaction between the main power controller and the minimum system power supply is realized; when the bus interconnection switch is in an off state, the main power controller is isolated from the minimum system power supply.
In the above-mentioned bus power interaction power supply and distribution system based on the minimum system on satellite, the main power controller includes: n solar modules, 2M battery charging and discharging adjusting modules and capacitor module CPA 1 And a backplane assembly a;
each solar module is respectively connected with the solar cell array and used for acquiring power supply input from the solar cell array;
each battery charge-discharge adjusting module is respectively connected with the storage battery pack and used for realizing charge-discharge of the storage battery pack;
capacitor module CPA 1 For stabilizing the bus voltage;
and the backboard component A is used for connecting the mechanical and circuit interfaces of all the modules in the main power controller together.
In the bus power interactive power supply and distribution system based on the minimum satellite system, each solar module comprises a 3-way sequential switch shunt regulating circuit which is used for realizing power regulation of the solar cell array in the illumination period and stabilizing the bus voltage at a set value.
In the bus power interactive power supply and distribution system based on the minimum satellite system, M and N are positive integers, and N is more than or equal to 4 and less than or equal to 10,6 and less than or equal to 18; the set value was 100V.
In the above bus power interactive power supply and distribution system based on the minimum system on the satellite, the minimum system power supply includes: sun module SUN N+1 BCDR (battery charging and discharging) adjusting module (M+1)A BCDR (battery charging and discharging) adjusting module (M+1)B Capacitor module CPA 2 And a back plate assembly B;
sun module SUN N+1 The solar cell array is connected with the power supply system and used for acquiring power supply input from the solar cell array;
battery charging and discharging adjusting module BCDR (M+1)A And a battery charging and discharging regulation module BCDR (M+1)B Are respectively connected with the storage battery pack and used for realizing the charging and discharging of the storage battery pack;
capacitor module CPA 2 For stabilizing the bus voltage;
a backplane assembly B for interfacing the mechanical and electrical circuits of all the modules together in a minimum system power supply.
In the bus power interactive power supply and distribution system based on the minimum system on the satellite, the SUN module SUN N+1 The system comprises a 3-path sequential switch shunt regulation circuit which is used for realizing power regulation of the solar cell array in the illumination period and stabilizing the bus voltage at a set value.
In the bus power interactive power supply and distribution system based on the minimum system on the satellite, a minimum system power supply is a module separated from a main power controller.
In the above bus power interactive power supply and distribution system based on the minimum system on the satellite, the minimum system is: the system can ensure the safety of the satellite and can complete the normal operation of the minimum load function.
In the above bus power interactive power supply and distribution system based on the minimum system on the satellite, the minimum system envelope apparatus includes: the critical load and the critical load of the satellite.
In the bus power interactive power supply and distribution system based on the minimum system on the satellite, the power range of the minimum system power supply is larger than the sum of the powers of the minimum system envelope equipment.
The invention has the following advantages:
(1) The invention discloses a bus power interactive power supply and distribution system based on a minimum system on a satellite, which is reasonably decomposed on the basis of the original PCU, increases the power supply of the minimum system power supply, ensures that the minimum system of the satellite realizes uninterrupted work, has flexible reconfiguration capability, avoids the influence of single-point faults of buses on the safety of the whole satellite, and improves the reliability of the satellite
(2) The invention discloses a bus power interactive power supply and distribution system based on a minimum system on a satellite, which has better adaptability to a high-power (more than 20 kW) communication satellite, avoids the single-point problem caused by a single bus and a single PCU, really realizes the continuity of service on the satellite and ensures the safety of the whole satellite.
Drawings
Fig. 1 is a block diagram of a bus power interactive power supply and distribution system based on a minimum satellite system in an embodiment of the present invention.
Detailed Description
To make the objects, technical solutions and advantages of the present invention more apparent, the embodiments of the present invention will be described in detail with reference to the accompanying drawings.
As shown in fig. 1, in this embodiment, the bus power interactive power supply and distribution system based on the minimum satellite system includes: the system comprises a main power controller, a minimum system power supply, an interconnection bus and a bus interconnection switch; the main power controller is connected with the minimum system power supply through an interconnection bus, and a bus interconnection switch is arranged on the interconnection bus.
And the main power controller is used for supplying power to other equipment on the satellite except the minimum system envelope equipment.
In this embodiment, the minimum system refers to: a system for ensuring the safety of a satellite and performing the normal operation of the minimum load function. This minimum system envelope equipment usually includes important loads of the satellite (i.e. a series of loads with the lowest undervoltage value in the undervoltage protection design, such as a central computer, a measurement and control system hub, an attitude and orbit control system hub, an actuator, etc.), and in order to satisfy the normal operation of the minimum function, part of the important loads also need to be listed as the envelope of the minimum system.
Taking a DFH-4E typical communication satellite as an example, the principle of selecting the minimum system envelope equipment is as follows: the equipment with the undervoltage protection threshold lower than 60V (the voltage of the whole star bus is normally 100V) is generally an important single machine of a central computer, a measurement and control system and an attitude and orbit control system. Further, in a communication satellite series, the undervoltage protection threshold of the equipment is lower than 60V, which indicates that a bus voltage drop is caused by an emergency, and the equipment still needs to work normally to ensure that the whole satellite is controllable, belongs to the key equipment of the whole satellite, and needs to be included in the minimum system envelope. In addition, although the under-voltage protection threshold of some important loads, such as antennas, traveling wave tube amplifiers, frequency converters and other devices capable of supporting communication services, is above 60V, some important loads can be properly selected according to the service level of the whole satellite to be drawn into the minimum system envelope, so that the minimum system power supply can support the continuous operation of some services of the whole satellite.
Preferably, the main power supply controller may specifically include: n solar modules, 2M battery charge-discharge adjusting module and capacitor module CPA 1 And a backplate assembly a. Each solar module is connected with the solar cell array respectively and used for obtaining power supply input from the solar cell array. And each battery charge-discharge adjusting module is respectively connected with the storage battery pack and used for realizing the charge and discharge of the storage battery pack. Capacitor module CPA 1 And is used for stabilizing the bus voltage. And the backboard component A is used for connecting the mechanical and circuit interfaces of all the modules in the main power controller together. Wherein M and N are positive integers, and N is more than or equal to 4 and less than or equal to 10,6 and less than or equal to 18.
Furthermore, each solar module comprises a 3-way sequential switch shunt regulating circuit, which is used for realizing power regulation of the solar cell array in the illumination period and stabilizing the bus voltage at a set value (such as 100V). Wherein, only 1 way of sequential switch reposition of redundant personnel regulating circuit is in the adjustment state among 3 way sequential switch reposition of redundant personnel regulating circuit, and other 2 ways sequential switch reposition of redundant personnel regulating circuit are in to the busbar power supply or to ground reposition of redundant personnel states. When the load is lightened, the 3-way sequential switch shunt regulation circuits sequentially enter a shunt state; and otherwise, the load is increased, and the 3-way sequential switch shunt regulation circuit exits the shunt state in sequence and is converted into the normal power supply state to the bus. The energy of the solar cell array is shunted to the ground or supplies power to the bus according to the requirement of the load, and is adjusted through the middle first stage, so that the stability of the bus voltage is ensured.
And the minimum system power supply is used for supplying power to the minimum system envelope equipment.
In this embodiment, the devices in the minimum system are distributed with a minimum system power supply. The minimum system power supply is a module separated from the main power controller, and the separation strategy is to ensure that the composition of the minimum system power supply is completely consistent with the basic composition of the main power controller. The minimum system power supply and the main power controller are completely independent in physical position, and common cause faults cannot occur.
Preferably, the minimum system power supply may specifically include: sun module SUN N+1 BCDR (battery charging and discharging) adjusting module (M+1)A BCDR (battery charging and discharging) adjusting module (M+1)B Capacitor module CPA 2 And a back plate assembly B. Wherein, the SUN module SUN N+1 And the solar cell array is connected with the power supply unit and is used for acquiring power supply input from the solar cell array. Battery charging and discharging adjusting module BCDR (M+1)A And a battery charging and discharging regulation module BCDR (M+1)B And the storage batteries are respectively connected with the storage battery pack and used for realizing charging and discharging of the storage battery pack. Capacitor module CPA 2 And is used for stabilizing the bus voltage. A backplane assembly B for interfacing the mechanical and electrical circuits of all the modules together in a minimum system power supply. Further, like the SUN module in the main power supply controller, the SUN module SUN in the minimum system power supply N+1 Also comprises a 3-way sequential switch shunt regulation circuit, and the function of the shunt regulation circuit is matched with that of the SUN N+1 3-way sequential switch shunting in (1)The function of the regulating circuit is the same and will not be described in detail here.
During the shadow period, the storage battery works, the output power of the module is adjusted through battery charging and discharging, and during the illumination period, the solar battery array works, and the power is output through the solar module. Assuming that the output power of a battery charging and discharging regulation module is 2kW and the output power of a solar module is 5kW, the minimum system power output power during the ground shadow is 4kW, and the minimum system power output power during the illumination is 5kW, considering that the minimum system power can be safely carried all the time, the sum of the power of the minimum system enveloping equipment is less than 4kW.
The output bus of the minimum system power supply is connected with the backup of the determined minimum system envelope equipment; and configuring corresponding solar cells and storage battery pack interfaces for the minimum system power supply according to the required power, and ensuring that the minimum system power supply can supply power uninterruptedly in the whole time under the normal working condition.
And the bus interconnection switch is used for controlling the on-off between the main power controller and the minimum system power supply.
In this embodiment, under a normal condition, the bus interconnection switch is in a closed state and is in a closed state, and the main power controller is communicated with the minimum system power supply to perform power interaction. When the main power controller has a single-point fault such as bus short circuit, the bus interconnection switch automatically disconnects when detecting a fault signal, so that the main power controller is isolated from the minimum system power supply, and the minimum system can work independently.
Based on the above embodiments, taking the high-orbit communication satellite of the DFH-4E typical platform, N =7 and M =6 as examples, there are:
the main power controller includes: sun module SUN 1 ～SUN 7 BCDR (battery charging and discharging) adjusting module 1A ～BCDR 6A BCDR (battery charging and discharging) adjusting module 1B ～BCDR 6B Capacitor module CPA 1 And a backplate assembly a. The minimum system power supply includes: sun module SUN 8 BCDR (battery charging and discharging) adjusting module 7A BCDR (battery charging and discharging) adjusting module 7B Capacitor module CPA 2 And a back plate assembly B.
For the high orbit communications satellite of the DFH-4E typical platform: for the on-board electric equipment, the electric equipment is classified according to the functional properties and importance of the on-board electric equipment so as to determine the priority level of obtaining electric energy. The key equipment is electric equipment necessary for ensuring satellite safety, the important equipment is equipment necessary for ensuring satellite service continuity, and the rest is general equipment. According to the current configuration of the typical platform communication satellite, the device classification is obtained as shown in table 1:
TABLE 1 Classification of satellite electric equipment
The minimum system envelope equipment can be determined by the undervoltage protection threshold value <60V, that is, based on the table 1, the power of the whole satellite key equipment and part of the important load equipment with the undervoltage protection threshold value <60V is combed, and the envelope list of the minimum system is obtained and shown in table 2:
TABLE 2 minimum System envelope Equipment
It can be seen that the power sum of the minimum system envelope devices for this typical satellite is about 2150W.
The minimum system is introduced, namely, the key and partial important equipment of the whole satellite is separated from the current single PCU power distribution mode, namely, the functional modules (SUN module, BCDR module, CAP module and back panel) are separated from the main PCU to form a minimum system power supply, the equipment backup with the minimum system envelope is powered, and meanwhile, the corresponding solar battery array and storage battery pack interface are configured, so that uninterrupted power supply is always provided for the minimum system, and the safety of the satellite and the normal operation of basic functions are ensured.
Because the total power of the whole satellite is not changed, two power supplies can be arranged, one power supply is a main power supply controller, the other power supply is a minimum system power supply separated from the main power supply controller, and the power range of the minimum system power supply is required to be larger than the total power of minimum system envelope equipment. The output bus of the minimum system power is connected to a backup of the devices within the envelope. A bus interconnection switch is arranged between the main power controller and the bus of the minimum system power supply, so that power interaction is facilitated, and fault isolation and system reconfiguration can be realized at an emergency (fault working condition).
And (3) fault working conditions:
1) Short circuit occurs: the bus interconnection switch is provided with current telemetering, when the fact that the current telemetering value is larger than 1.5 times of the power transmission capacity of the minimum system power supply is detected (4 kW/100V 1.5= 60A), a short-circuit fault occurs at a certain position, the bus interconnection switch is cut off rapidly at the moment, the main power controller and the minimum system power supply are guaranteed to operate independently and not to influence each other, a fault diffusion path is switched, and system reconstruction is completed.
2) Single module output failure: when other modules in the main power controller have faults to cause insufficient output power, power interaction can be carried out through an interconnection channel (a channel formed when a bus interconnection switch is closed), and the fact that the whole satellite service is normally not affected is guaranteed.
Several typical failure cases are reconstructed as follows:
1) Failure of any solar module in main power controller
The solar module comprises 3 paths of sequential switch shunt regulating circuits, and according to circuit characteristics and protection design, when single fault occurs, only one S3R circuit is always powered on, and at the moment, the solar cell array power corresponding to the S3R circuit is completely supplied to a bus. However, as the S3R circuits in all the solar modules are output after being connected in parallel, the next-stage S3R circuit can continuously participate in shunt regulation, so that redundant power is shunted, and the voltage of the bus is kept unchanged. At the moment, the bus section switch keeps closed, and the power supply of the whole satellite is not influenced.
2) Any battery charging and discharging adjusting module fault in main power supply controller
Battery with a battery cellCharging and discharging regulation module BCDR xA (x = 1-7) when the battery fails and cannot work, the battery charging and discharging adjusting module BCDR corresponding to the battery charging and discharging adjusting module BCDR needs to be shut down xB The charging and discharging states of the two groups of storage battery packs connected with the main power controller are consistent, and the service life consistency of the two groups of storage battery packs is ensured. The battery charge-discharge adjusting module of the whole satellite adopts a 14-protection 12 design, 2 battery charge-discharge adjusting modules do not output power in the main power controller, but 2 battery charge-discharge adjusting modules are provided in the minimum system power supply, the power of the storage battery pack can be sent to the main power controller through an interconnection bus, and the normal charge-discharge function of the storage battery pack of the whole satellite is ensured. At the moment, the bus interconnection switch is kept closed, and the power supply of the whole satellite is not influenced.
3) Solar module failure in minimal system power supply
The situation is similar to that of the main power controller, only the normally-on state of a certain path of S3R circuit can occur, 3 paths of S3R exist in one solar module, and the bus interconnection switch and each level of solar modules in the main power controller are also interconnected, so that the subsequent S3R circuit is ensured to participate in shunt regulation, the influence of bus output power rise caused by the normally-on state of the S3R circuit in a fault is eliminated, and the bus voltage is ensured to be unchanged. At the moment, the bus interconnection switch is kept closed, and the power supply of the whole satellite is not influenced.
4) Failure of battery charge-discharge regulation module in minimum system power supply
After a battery charging and discharging adjusting module in the minimum system power supply breaks down, the corresponding storage battery pack cannot output power to the bus, and due to the fact that the interconnection bus exists, the main power controller can transmit the power of the storage battery pack to minimum system enveloping equipment, the bus interconnection switch is kept closed, and power supply of the whole satellite is not affected.
5) Bus short circuit fault in main power controller
When the bus of the main power controller is short-circuited, the bus interconnection switch detects large current and can be automatically disconnected, so that the minimum system power supply is not influenced by the fault of the main power controller, and the problem diffusion is prevented. At the moment, the minimum system power supply works normally, and key equipment and important loads of the whole satellite platform are supported for a long time to work uninterruptedly. If the fault point is judged to be recovered through modes such as the whole satellite remote measurement state and the like and the condition that the main power controller is reconnected is met, the bus interconnection switch can be closed again through sending an instruction.
6) Bus short circuit fault of minimum system power supply
And the bus short circuit occurs in the minimum system power supply, the bus interconnection switch is quickly disconnected in the same way, and the design of the main power supply controller can completely support all functions of the whole satellite for a long time. If the fault point is judged to be recovered through modes such as the whole satellite remote measurement state and the like, and the condition that the minimum system power is connected to the main bus is met, the bus interconnection switch can be closed again through sending an instruction.
Compared with a single bus architecture, the bus power interactive power supply and distribution system based on the minimum system on the satellite provided by the invention divides the minimum system power supply from the main power controller by dividing the minimum system power supply into two parts, so that the isolation on the physical position is formed, the problem of single point of the bus is eliminated, the bus power interactive power supply and distribution system has flexible reconfigurable capability, and is a high-reliability on-satellite power supply and distribution architecture.
In this embodiment, S3R: sequential Switching shock Regulator, sequential switch Shunt regulation; BCDR: battery Charge and Discharge Regulator, battery Charge and Discharge regulation; CAP: capacitance.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Those skilled in the art will appreciate that the invention may be practiced without these specific details.
Claims (10)
1. A bus power interactive power supply and distribution system based on a minimum system on a satellite is characterized by comprising: the system comprises a main power controller, a minimum system power supply, an interconnection bus and a bus interconnection switch; the main power controller is connected with the minimum system power supply through an interconnection bus, and a bus interconnection switch is arranged on the interconnection bus;
the main power supply controller is used for supplying power to other equipment on the satellite except minimum system envelope equipment;
a minimum system power supply for supplying power to the minimum system envelope device;
the bus interconnection switch is used for controlling the on-off between the main power supply controller and the minimum system power supply; when the bus interconnection switch is in a closed state, the main power controller is communicated with the minimum system power supply, so that power interaction between the main power controller and the minimum system power supply is realized; when the bus interconnection switch is in an off state, the main power controller is isolated from the minimum system power supply.
2. The minimum on-board system-based bus power interactive supply and distribution system according to claim 1, wherein the main power controller comprises: n solar modules, 2M battery charge-discharge adjusting module and capacitor module CPA 1 And a backplane assembly a;
each solar module is respectively connected with the solar cell array and used for acquiring power supply input from the solar cell array;
each battery charge-discharge adjusting module is respectively connected with the storage battery pack and used for realizing charge and discharge of the storage battery pack;
capacitor module CPA 1 For stabilizing the bus voltage;
and the backboard component A is used for connecting the mechanical and circuit interfaces of all the modules in the main power controller together.
3. The bus power interactive power supply and distribution system based on the minimum satellite system according to claim 2, wherein each solar module comprises a 3-way sequential switch shunt regulating circuit, and the 3-way sequential switch shunt regulating circuit is used for realizing power regulation on the solar cell array in an illumination period so as to stabilize the bus voltage at a set value.
4. The minimum satellite system-based bus power interactive power supply and distribution system according to claim 3, wherein M and N are positive integers, and N is greater than or equal to 4 and less than or equal to 10,6 and less than or equal to M and less than or equal to 18; the set value was 100V.
5. The minimum-system-on-satellite-based bus power interactive supply and distribution system according to claim 1, wherein the minimum system power supply comprises: sun module SUN N+1 BCDR (battery charging and discharging) adjusting module (M+1)A BCDR (battery charging and discharging) adjusting module (M+1)B Capacitor module CPA 2 And a back plate assembly B;
sun module SUN N+1 The solar cell array is connected with the power supply system and used for acquiring power supply input from the solar cell array;
battery charging and discharging adjusting module BCDR (M+1)A And a battery charging and discharging regulation module BCDR (M+1)B Are respectively connected with the storage battery pack and used for realizing the charging and discharging of the storage battery pack;
capacitor module CPA 2 For stabilizing the bus voltage;
a backplane assembly B for interfacing the mechanical and electrical circuits of all the modules together in a minimum system power supply.
6. The minimum on-board system based bus power interactive supply and distribution system according to claim 5, wherein the SUN module SUN N+1 The system comprises a 3-way sequential switch shunt regulating circuit which is used for realizing power regulation of the solar cell array in the illumination period and stabilizing the bus voltage at a set value.
7. The minimum-system-on-satellite-based bus power interactive supply and distribution system according to claim 1, wherein the minimum system power supply is a module separate from the main power controller.
8. The minimum system on-satellite based bus power interactive power supply and distribution system according to claim 1, wherein the minimum system is: the system can ensure the safety of the satellite and can complete the normal operation of the minimum load function.
9. The minimum-system-on-satellite-based bus power interactive power supply and distribution system according to claim 1, wherein the minimum-system envelope apparatus comprises: the critical load and the critical load of the satellite.
10. The minimum-system-on-satellite-based bus power interactive supply and distribution system according to claim 1, wherein the power range of the minimum system power supply is greater than the sum of the powers of the minimum system envelope devices.
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