CN117416532A - Main and standby independent and partition controlled satellite power distribution method based on power supply priority - Google Patents

Main and standby independent and partition controlled satellite power distribution method based on power supply priority Download PDF

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Publication number
CN117416532A
CN117416532A CN202311233348.0A CN202311233348A CN117416532A CN 117416532 A CN117416532 A CN 117416532A CN 202311233348 A CN202311233348 A CN 202311233348A CN 117416532 A CN117416532 A CN 117416532A
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load
power
satellite
power distribution
lcl
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Inventor
王赫余
孙海涛
吴乐群
井元良
许晨航
刘艳丽
赵冰欣
陈曦
李小飞
刘亚利
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China Academy of Space Technology CAST
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China Academy of Space Technology CAST
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Priority to CN202311233348.0A priority Critical patent/CN117416532A/en
Publication of CN117416532A publication Critical patent/CN117416532A/en
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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
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02H—EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS
    • H02H3/00—Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition with or without subsequent reconnection ; integrated protection
    • H02H3/08—Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition with or without subsequent reconnection ; integrated protection responsive to excess current
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02H—EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS
    • H02H9/00—Emergency protective circuit arrangements for limiting excess current or voltage without disconnection
    • H02H9/02—Emergency protective circuit arrangements for limiting excess current or voltage without disconnection responsive to excess current
    • 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
    • H02J7/0029—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with safety or protection devices or circuits
    • H02J7/00304—Overcurrent protection
    • 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
    • H02J7/0063—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with circuits adapted for supplying loads from the battery
    • 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
    • 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
    • H02J9/00—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting
    • H02J9/04—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source
    • H02J9/06—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems
    • H02J9/068—Electronic means for switching from one power supply to another power supply, e.g. to avoid parallel connection

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  • Engineering & Computer Science (AREA)
  • Power Engineering (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Business, Economics & Management (AREA)
  • Emergency Management (AREA)
  • Direct Current Feeding And Distribution (AREA)

Abstract

The invention relates to a main and standby independent and partition controlled high-reliability satellite power distribution method based on power supply priority division, which comprises the following steps of counting power utilization load equipment of each subsystem of a satellite according to the design state of a product selected by the satellite as a whole; determining the power supply priority of the satellite to the power utilization load according to the single-machine power supply requirements of different subsystems of the satellite and the importance of the different subsystems of the satellite to flight safety and task completion; determining control methods of distribution paths of load devices with different priorities; selecting a current limiting protection switch LCL, and designing matching between the LCL and an electric load; selecting an overcurrent protection switch SSPC, and designing the matching property of the SSPC and an electric load; performing main and standby redundancy design on power distribution channels in different power distribution partitions; and repeatedly iterating the steps to finally determine the satellite power distribution architecture.

Description

Main and standby independent and partition controlled satellite power distribution method based on power supply priority
Technical Field
The invention belongs to the technical field of power supply and distribution of aerospace vehicles, and relates to a main and standby independent and partition control high-reliability satellite power distribution method based on power supply priority division.
Background
Satellite power distribution systems are systems that reasonably distribute energy generated by a power supply system to individual power loads and provide protection for the distribution links, and generally include a power distributor and a protection portion for each load side interface. Reasonable distribution of satellite power resources and ensuring of high-reliability power distribution safety of satellites are key works of power distribution systems.
The conventional power distribution system is a direct power distribution architecture system and is characterized in that a power distributor directly distributes power to each power consumption unit of a satellite through a power distribution path with fixed power. And then a fuse is arranged at a single-machine port to protect a single-way distribution channel, so that simple current monitoring can be carried out on the single-way distribution channel. The power distribution architecture design of 'guarantor' can be compatible with various power distribution load forms, but lacks the satellite overall control over power distribution and fault handling means.
Another commonly used power distribution architecture is a hierarchical power distribution architecture. The satellite power distribution system is characterized in that a power distribution channel with a power distribution control switch is arranged in the power distributor equipment and is connected with a subsystem power distribution single machine to form a satellite first-stage power distribution system, and a first-stage power distributor end can monitor subsystem current and realize subsystem first-stage power distribution control. And the subsystem power distribution single machine distributes power to related equipment of the subsystem to be a second-stage power distribution system, so that power consumption distribution in the subsystem is realized. The distribution form has a certain limit on the distribution architecture of the first stage of the distribution system, and the problem that the main and the standby of the distribution channels of the equipment are not independent due to the fact that the single channel capacity is large and the distribution channels are small in number can exist in a shared distribution channel.
In summary, the above existing power distribution architecture equally treats the power consumption load of the rear satellite, does not differentiate flight safety and task completion importance, equally treats the power consumption load of the rear satellite, and does not have a design means for improving the reliability of the power consumption load of the key single machine. With the increasing complexity of satellites, the single power distribution architecture is unfavorable for the improvement of the reliability of a satellite power distribution system and the reasonable distribution of satellite power utilization resources.
Disclosure of Invention
The invention solves the technical problems that: the power supply priority division-based high-reliability satellite power distribution method has the advantages that the defects of the prior art are overcome, and the main and standby independent and partition control method based on the power supply priority division is provided. The satellite flight safety and mission completion key loads are identified through the power utilization load priority division, and the reliability of a power distribution channel is improved on the power utilization loads related to the success and failure of the satellite; different control methods are selected through the use methods of different loads, so that reasonable distribution of electricity resources is realized, and the reliability of a power distribution channel is improved from the use modes of the loads; the reliability of each power distribution control partition is improved through a main and standby independent method based on power supply priority in different power distribution control partitions.
The solution of the invention is as follows:
the main and standby independent and partition controlled satellite power distribution method based on the power supply priority comprises the following steps:
step S1: according to the product design state of the satellite overall selection, counting the power utilization load equipment of each satellite subsystem;
step S2: determining the power supply priority of the satellite to the power utilization load according to the single-machine power supply requirements of different subsystems of the satellite and the importance of the different subsystems of the satellite to flight safety and task completion;
step S3: determining control methods of distribution paths of load equipment with different priorities according to power supply priorities of satellites to different power utilization loads and the states of existing products;
step S4: selecting a solid-state current-limiting protection switch LCL, and designing matching between the LCL and an electric load;
step S5: selecting a solid overcurrent protection switch SSPC, and designing the matching property of the SSPC and an electric load;
step S6: performing main and standby redundancy design on power distribution channels in different power distribution partitions;
step S7: and repeatedly iterating the steps S4-S6 to finally determine the satellite power distribution architecture.
Preferably, in the step S2, the method for determining the power supply priority of the satellite to the power load is as follows:
if the satellite flight task fails after power failure of a certain load device, the load device is considered as a flight key load;
if the satellite main task function is lost after power failure of a certain load device, the load device is considered as a task key load;
if the satellite additional function is lost or has no influence after the power of a certain load device is lost, the load device is considered to be a general load;
the flight critical load has the highest power supply priority at any time, the mission critical load has the higher power supply priority, and the power supply priority of the general load is the lowest.
Preferably, in the step S3, the control method of the distribution paths of the load devices with different priorities is as follows:
flight critical loads: under any condition, the primary power distribution is not allowed to be powered off, and the secondary power distribution is completed in the subsystem; the primary power distribution adopts a relay mode, is used for ground test, and is subjected to contact short circuit before satellite transmission, so that the long power-on state of a flight key load is ensured;
task critical load: the primary power distribution is not powered off except in emergency, and an LCL control method is selected from the subsystem which directly distributes power to a single load according to the whole satellite working mode and the satellite power supply condition; a subsystem of a primary power distribution to subsystem distributor, selecting an SSPC control method;
general load: the primary power distribution is not powered off except in emergency, and an LCL control method is selected from the subsystem which directly distributes power to a single load according to the whole satellite working mode and the satellite power supply condition; the first stage distributes power to the sub-system of the sub-system distributor, and an SSPC control method is selected.
Preferably, in the step S4, the matching design of the LCL and the electric load is performed, specifically as follows:
if the surge current of the rear-stage load is lower than 1.2Ie, the LCL does not enter a current limiting state when the rear-stage load is started, the rear-stage load can be directly started with load, and Ie is the rated current of the LCL;
if the surge current of the rear-stage load is higher than 1.2Ie, the starting current of the rear-stage load is required to be within 1.5 times or within 2A of the corresponding rated current, the larger one is selected, the duration is not more than 5ms, and the rising slope is not more than 105A/s.
Preferably, once the load device is short-circuited, the LCL access is protected by the fuse, the load device is controlled to be shut down by a remote control instruction, the short-circuit fault is removed, the load device sharing the LCL access is ensured to be normally powered, or the main backup channel is switched by the LCL.
Preferably, in the step S5, the SSPC should not be turned off when the rear load is started or the rear load overcurrent fuse is blown, so as to ensure that other single machines in the subsystem work normally;
the peak value of the surge current at the starting of the rear-stage load is not allowed to exceed the lower limit of the SSPC overcurrent protection curve:
if the peak value of the surge current started by the loads at the later stage is smaller than the starting point of the overcurrent protection, the load is directly used;
if the peak value of the surge current started by a plurality of loads at the later stage exceeds 1.4Se, the duration of the peak value of the surge current is smaller than the SSPC protection delay time under the same current, and Se is the rated current of the SSPC.
Preferably, in step S6, the power distribution partition is determined according to a power distribution control method, and the power distribution partition includes a relay control partition, an LCL control partition, and an SSPC control partition.
Preferably, the electric load equipment in the relay control partition is a flight key load, and the ground control uses a relay and is short-circuited in an on-orbit manner.
Preferably, the power utilization load equipment in the LCL control partition is a task key load and a general load which are directly distributed to a single machine;
on the premise of meeting the matching property of LCL and power consumption load, the task key load needs to control a power supply path by an independent LCL, one LCL is used by a later-stage load, and one LCL is used by backup; multiple general loads can share one LCL control power supply path.
Preferably, the method comprises the steps of,
the SSPC controls the power load equipment in the partition to be a mission critical load and a general load;
on the premise of meeting the matching between the SSPC and the power consumption load, the task-critical load needs to control a power supply path by an independent SSPC; multiple general loads can share one SSPC control power supply.
Compared with the prior art, the invention has the beneficial effects that:
(1) The method of the invention divides the power utilization priority of the load of the equipment in the initial stage of design, and carries out the power distribution control method required by identifying the satellite according to the importance degree.
(2) The first proposed power distribution design method of the invention relies on a power distribution control method to carry out partition power distribution, and a single power distribution control mode of a satellite in the past is abandoned. The complex satellites can be matched with different partitions, and are more suitable for a plurality of complex satellites of a subsystem. Different partitions have no physical connection channels, so that faults in a single distribution control partition are prevented from spreading, and satellite distribution safety is effectively improved. And the complete main and standby independence of the distribution channel is realized in each partition, and the high reliability in the distribution partition is improved.
(3) The power distribution method provided by the invention is a composite power distribution system, is different from other satellite pure direct power distribution or grading power distribution systems, and has strong inclusion for rear-end load equipment. The design method can directly distribute power to a single machine or to a subsystem for grading power distribution. Significant benefits are realized in satellite economics and development progress.
(4) The power distribution link uses different link protection methods such as inverse time limit, current limiting and the like, and realizes high reliability of the power distribution link.
Drawings
FIG. 1 is a schematic diagram of a back-end main-standby independent hierarchical power distribution part in a relay control partition according to the embodiment;
fig. 2 is a schematic diagram of a main-standby independent direct-current power distribution part controlled by a current-limiting solid-state switch in an LCL partition in the embodiment;
FIG. 3 is a schematic diagram of a main-standby independent composite power distribution part controlled by SSPC switches in an SSPC partition according to the embodiment;
fig. 4 is a high-reliability satellite power distribution architecture of the present embodiment.
Detailed Description
The invention is further illustrated in the following figures and examples.
The invention provides a main and standby independent and partition controlled high-reliability satellite power distribution method based on power supply priority division, which comprises the following steps:
step S1: and counting the power utilization load equipment of each satellite subsystem according to the product design state of the satellite overall selection. The satellite power distribution system and the power distribution capacity can be primarily determined by the power of the electric load equipment and the power distribution mode of the subsystem.
Step S2: and designing the power supply priority of the satellite power distribution output load according to the single power supply requirements of different subsystems of the satellite and the importance of the different subsystems of the satellite to flight safety and task completion.
The satellite equipment power utilization authority is classified according to the influence on the satellite after the load equipment of different subsystems fails in power failure, for example: the satellite flight task fails after the equipment is powered down, and is a flight key load; the main task function of the satellite is lost after the equipment is powered down, and the main task function is a key task load; the satellite additional function is lost or has no influence after the equipment is powered down, and is a general load; the flight critical load has the highest power supply priority at any time, the mission critical load has the higher power supply priority, and the priority of the general load is the lowest.
Step S3: and determining the control method of the distribution paths of the load equipment with different power utilization priorities according to the priorities of the distribution output loads of different satellites and the state of the existing products.
Load devices of different power utilization priorities have different demands on the control method of the distribution path. The conventional satellite flying key load does not allow power failure under any condition, and the secondary power distribution is completed in the subsystem. Therefore, the primary power distribution control of the flight critical load adopts a relay mode for ground test. And the contacts are short-circuited before satellite transmission, so that the long power-on state of the flight key load is ensured. The primary power distribution is not powered off under the emergency state of the mission critical load, and an LCL (solid-state current limiting protection switch) control method can be selected according to the whole satellite working mode and the subsystem of the existing satellite product state direct power distribution to a single load; the subsystem of the primary distribution to subsystem distributor may select SSPC (solid state over current protection switch) control methods.
Step S4: and selecting a current limiting protection switch LCL, and designing the matching property of the LCL and the electric load.
The control method of the MOSFET-based current-limiting protection type power supply switch (LCL) +fuse is LCL current-limiting protection and fuse inverse time-limiting protection (I) 2 And R) front and back ends cooperate to protect the distribution link.
Step S5: and selecting an overcurrent protection switch SSPC to perform matching design of the SSPC and an electric load.
MOSFET-based I 2 the control method of the t inverse time characteristic protection type power Supply Switch (SSPC) +fuse is SSPC and fuse inverse time protection (I) 2 And R) front and back ends cooperate to protect the distribution link.
Step S6: different control methods adopt the independent design of the main and the standby of the distribution channel in the partition.
According to different control methods, the designed distribution channel is partitioned; the designed power distribution control system is a compound type assembled modularized power distribution control system, and can also be a plurality of single machines scattered at different positions of a complex satellite. The power distribution system is divided into different power distribution parts according to different power distribution control methods: relay control division, LCL control division, SSPC control division. The equipment with different power supply priorities adopts the main and standby redundancy design of the power distribution channel in different partitions. The single machine control circuit with high power supply priority and the power distribution channel are designed in a main-standby redundancy mode and are independent from other equipment. The equipment with low power supply priority can share a power distribution path between different equipment on the basis of ensuring the primary and secondary redundancy design. It is worth mentioning that the back-end distribution equipment is the equipment of subsystem distributor, and under hierarchical distribution system, subsystem primary distribution is also main redundant.
Step S7: and repeatedly iterating the design combination of the steps S4-S6 to finally determine the satellite power distribution architecture. The power distribution scheme designed according to the steps has different combination methods and different power distribution circuit numbers. The satellite power distribution architecture is finally determined from the aspects of actual working mode use, fault mode and economic value.
Examples:
aiming at the high-reliability power distribution framework with independent main and standby and partition control based on the priority division of load equipment shown in fig. 4, the invention discloses a power distribution design method by taking a conventional system product framework composition for the existing large-scale complex optical satellite as an example.
The satellite power distribution method comprises the following steps:
1) Satellite electrical load statistics
According to the power consumption statistics of the electric equipment of each subsystem of the satellite, preliminary information such as preliminary power consumption statistics of the satellite, primary electric equipment in each subsystem, subsystem power distribution modes and the like is obtained and is collected into a satellite power consumption load condition statistical table of the following table 1-1; the table is the input for the following design steps.
TABLE 1-1 satellite Power load Condition statistics
2) Load power supply prioritization
All electrical loads on board a satellite are classified into three categories according to their importance for flight safety and task completion: flight critical load, mission critical load, general load.
The load power supply prioritization method comprises the following steps:
when the power supply and distribution system is normal, the flight critical load, the mission critical load and the general load can be normally powered;
when the power supply and distribution system fails and normal power supply cannot be ensured, the power supply of the general electric load is cut off, and the power supply of as many mission-critical loads and flight-critical loads as possible is ensured as much as possible.
The power supply capability cannot meet the power demand of completing the flight mission, i.e., the general load and the mission critical load stop supplying power. The power supply and distribution system only supplies power to the flight key load, so that the basic measurement and control of the satellite, the attitude maintenance and the power consumption requirement of the power supply system are ensured.
In summary, the flight critical load has the highest power supply priority at any time, the task load has higher power supply priority, and the power supply priority of the general load is the lowest. The electrical load priority matrix is shown in tables 1-2.
TABLE 1-2 Power load priority matrix
3) Power distribution path control method determination
Flight critical loads: in any case, the primary power distribution is not allowed to be powered off, and the secondary power distribution is independently completed in the subsystem, so that the primary power distribution control of the flight key load adopts a relay mode for ground test. Shorting the relay contacts before satellite transmission to ensure a long power-on state of a flight key load;
task critical load: except for emergency, the primary power distribution is not powered off, and secondary power distribution control is independently completed in a subsystem according to the whole satellite working mode and satellite power supply condition, so that the primary power distribution control of a mission-critical load is controlled by adopting SSPC or LCL;
general load: except for emergency, the primary power distribution is not powered off, and secondary power distribution control is independently completed in the subsystem according to the whole satellite working mode and satellite power supply condition, so that the primary power distribution control of the general load is also controlled by adopting SSPC or LCL.
4) LCL and electric load matching design
The rated current Ie of the selected current-limiting protection switch LCL is 4A, the current limiting point is 1.2 Ie-1.4 Ie (full life cycle), the typical value is 1.3 ie+/-0.05A, the current-limiting protection time is 5 ms-9 ms (full life cycle), and the typical value is 7 ms-8 ms.
Therefore, if the LCL matches the electrical load, the LCL electrical load characteristics design method is as follows.
a) Capacitive load impedance interface
The LCL has a capacitive load rejection capability, with a maximum capacitance capability of 300uF at rated current 4A.
b) Surge suppression circuit interface
If the surge current of the rear-stage load is smaller and is lower than 1.2Ie (4.8A), the LCL does not enter a current limiting state when the load is started, and the load can be directly started in a loaded mode;
if the surge current of the load at the later stage is larger and is higher than 1.2Ie (4.8A), the LCL enters a current limiting state when the load is started, the LCL is not fully opened in the current limiting period, the bus voltage is jointly born by the LCL and the load, and if the load voltage still cannot be established to meet the starting requirement when the current limiting process is ended, the load cannot work normally.
Therefore, the starting current of the primary load electric equipment is required to be within 1.5 times or within 2A (taking the larger one) of the corresponding rated current, the duration is not more than 5ms, and the rising slope is not more than 105A/s.
Once the equipment is short-circuited, the LCL access is protected by the fuse, the equipment can be controlled to be shut down by a remote control instruction, and the short-circuit fault is removed, so that the normal power supply of the equipment sharing the LCL access is ensured, or the main backup is switched through the LCL channel.
5) SSPC and power load matching design
The rated current Se of the overcurrent protection switch SSPC of the SSPC is 20A, and the SSPC is not protected to be turned off when the rear-stage load is started or the rear-stage load overcurrent fuse is fused, so that other single machines in the subsystem can work normally.
The peak value of the surge current at the starting of the rear-stage load is not allowed to exceed the lower limit of the SSPC overcurrent protection curve:
if the peak value of the load starting surge circuits of the later stages is smaller than 1.4Se (28A) of the overcurrent protection starting point, the load starting surge circuits can be directly used;
if the peak value of the surge current started by the plurality of loads at the later stage exceeds 1.4Se, rechecking is needed according to the lower limit of the overcurrent protection curve, and the time nearby the peak value of the surge current is smaller than the SSPC protection delay time under the same current. 6) Main and standby redundancy design of distribution channels in different distribution partitions
The design schematic of the independent grading power distribution of the main and the standby of the rear end in the relay control partition is shown in fig. 1, and the electric load equipment in the partition is a flight key load. The satellite flight key load is measurement and control, control and measurement and control subsystem internal equipment, as shown in tables 1-2, 3 paths of power supply paths are provided for different subsystems, and a relay is used for ground control and in-orbit short circuit is realized.
The power consuming load devices within the LCL control section are mission critical and general loads that are distributed directly to the single machine as shown in tables 1-2. According to the power utilization priority division, on the premise of meeting the matching between the LCL and the power utilization load, the task key load needs to control a power supply path by an independent LCL, and as shown in fig. 2, the later-stage load uses one LCL and the backup uses one LCL. A general load can share one LCL control power supply by a plurality of load devices. As shown in fig. 2, the general load 1 primary and the general load 2 backup share one LCL path, and the general load 1 backup and the general load 2 primary share 1 LCL path.
SSPCs are commonly used for high power subsystem power distributors, single machines with multiple independent modules, or multiple single machines sharing a distribution path. The power capacity of the single-path SSPC is relatively large, the main and standby design combination states of the load equipment are many, and fig. 3 is an example of a back-end main and standby independent hierarchical power distribution design combination mode in one SSPC control partition. The electrical load devices within the SSPC partition are mission critical and general loads. According to the power utilization priority division, on the premise of meeting the matching between the SSPC and the power utilization load, the task key load needs to independently control a power supply path by the SSPC, as shown in fig. 3, the main parts of the back-end task key loads 1 and 2 respectively use one SSPC, and the backup uses one SSPC respectively. A typical load may share one SSPC control power supply with multiple load devices. As shown in fig. 3, the general load 1 master shares one SSPC path with the general load 2 backup, and the general load 1 backup shares 1 SSPC path with the general load 2 master.
7) Primary power distribution path status determination
Through the power distribution architecture design of the different power distribution control partitions divided based on the power supply priority; and (4) repeatedly iterating the steps 4-6 by considering the matching performance with the load and the independence of the main and standby load devices in the partition under different control methods of the front end and the rear end. The resulting power distribution architecture final scenario is shown in fig. 4.
The relay control partition part is used for integrating electronic, measurement and control subsystems in total in 3 paths, receiving wired instruction control, sending the switch state to a ground wired platform to finish measurement, shorting the relay contacts through a star meter connector before entering a track, and enabling the relay to not act after entering the track
The LCL controls the partition part, and the total of the LCL control part is 4A multiplied by 6 paths; MOSFET-based current limiting protection type power supply switch (LCL) with a double-tube serial redundancy design; the main characteristics are that 4 paths are task key loads, and 2 paths are common loads to be used in combination.
SSPC controls the partitioning section, 20A×12 paths total, MOSFET-based I 2 the anti-time characteristic protection type power Supply Switch (SSPC) is mainly characterized in that 4-path main parts/4-path backup is used as a key flying load and used as a subsystem distributor. The other paths are common loads and are used in combination under the condition of keeping the main and the standby independent.
As can be seen from the above examples, the method of the present invention: the satellite fault plan is designed according to the power supply priority partition design, so that the satellite fault plan is designed according to the load single machine, and the state of the important single machine is better monitored.
The satellite power distribution system has strong adaptability to the rear-end load, can directly distribute power to a single machine, can distribute power to a subsystem distributor and then distribute power to the single machine, can select a product to realize satellite functions, does not need to change the technical state of the single machine because of the adaptability of a power distribution channel, has good economic value and shortens the development progress of the satellite.
The power distribution method with multiple control modes coexisting is more suitable for large satellites with multiple single machines and complex functions, and meets the power distribution requirements of subsystems with different characteristics.
By designing and adopting different distribution protection matching methods, the reliability of satellite distribution is improved.
Although the present invention has been described in terms of the preferred embodiments, it is not intended to be limited to the embodiments, and any person skilled in the art can make any possible variations and modifications to the technical solution of the present invention by using the methods and technical matters disclosed above without departing from the spirit and scope of the present invention, so any simple modifications, equivalent variations and modifications to the embodiments described above according to the technical matters of the present invention are within the scope of the technical matters of the present invention.

Claims (10)

1. The main and standby independent and partition controlled satellite power distribution method based on the power supply priority is characterized by comprising the following steps of:
step S1: according to the product design state of the satellite overall selection, counting the power utilization load equipment of each satellite subsystem;
step S2: determining the power supply priority of the satellite to the power utilization load according to the single-machine power supply requirements of different subsystems of the satellite and the importance of the different subsystems of the satellite to flight safety and task completion;
step S3: determining control methods of distribution paths of load equipment with different priorities according to power supply priorities of satellites to different power utilization loads and the states of existing products;
step S4: selecting a solid-state current-limiting protection switch LCL, and designing matching between the LCL and an electric load;
step S5: selecting a solid overcurrent protection switch SSPC, and designing the matching property of the SSPC and an electric load;
step S6: performing main and standby redundancy design on power distribution channels in different power distribution partitions;
step S7: and repeatedly iterating the steps S4-S6 to finally determine the satellite power distribution architecture.
2. The power priority based master-slave independent, zone controlled satellite power distribution method of claim 1, wherein: in the step S2, the method for determining the power supply priority of the satellite to the power load is as follows:
if the satellite flight task fails after power failure of a certain load device, the load device is considered as a flight key load;
if the satellite main task function is lost after power failure of a certain load device, the load device is considered as a task key load;
if the satellite additional function is lost or has no influence after the power of a certain load device is lost, the load device is considered to be a general load;
the flight critical load has the highest power supply priority at any time, the mission critical load has the higher power supply priority, and the power supply priority of the general load is the lowest.
3. The power priority based master-slave independent, zone controlled satellite power distribution method of claim 2, wherein: in the step S3, the control method of the distribution paths of the load devices with different priorities is as follows:
flight critical loads: under any condition, the primary power distribution is not allowed to be powered off, and the secondary power distribution is completed in the subsystem; the primary power distribution adopts a relay mode, is used for ground test, and is subjected to contact short circuit before satellite transmission, so that the long power-on state of a flight key load is ensured;
task critical load: the primary power distribution is not powered off except in emergency, and an LCL control method is selected from the subsystem which directly distributes power to a single load according to the whole satellite working mode and the satellite power supply condition; a subsystem of a primary power distribution to subsystem distributor, selecting an SSPC control method;
general load: the primary power distribution is not powered off except in emergency, and an LCL control method is selected from the subsystem which directly distributes power to a single load according to the whole satellite working mode and the satellite power supply condition; the first stage distributes power to the sub-system of the sub-system distributor, and an SSPC control method is selected.
4. The power priority based master-slave independent, zone controlled satellite power distribution method of claim 1, wherein: in the step S4, the matching design between the LCL and the electric load is performed, specifically as follows:
if the surge current of the rear-stage load is lower than 1.2Ie, the LCL does not enter a current limiting state when the rear-stage load is started, the rear-stage load can be directly started with load, and Ie is the rated current of the LCL;
if the surge current of the rear-stage load is higher than 1.2Ie, the starting current of the rear-stage load is required to be within 1.5 times or within 2A of the corresponding rated current, the larger one is selected, the duration is not more than 5ms, and the rising slope is not more than 105A/s.
5. The power priority based master-slave independent, zone controlled satellite power distribution method of claim 4, wherein: once the load equipment is short-circuited, the LCL access is protected by the fuse, the load equipment is controlled to be shut down by a remote control instruction, the short-circuit fault is removed, the load equipment sharing the LCL access is ensured to be normally powered, or the main backup channel is switched by the LCL.
6. The power priority based master-slave independent, zone controlled satellite power distribution method of claim 1, wherein: in the step S5, the SSPC should not be turned off when the post-stage load is started or the post-stage load overcurrent fuse is blown, so as to ensure that other single machines in the subsystem work normally;
the peak value of the surge current at the starting of the rear-stage load is not allowed to exceed the lower limit of the SSPC overcurrent protection curve:
if the peak value of the surge current started by the loads at the later stage is smaller than the starting point of the overcurrent protection, the load is directly used;
if the peak value of the surge current started by a plurality of loads at the later stage exceeds 1.4Se, the duration of the peak value of the surge current is smaller than the SSPC protection delay time under the same current, and Se is the rated current of the SSPC.
7. The power priority based master-slave independent, zone controlled satellite power distribution method of claim 2, wherein: in step S6, a power distribution partition is determined according to a power distribution control method, and the power distribution partition includes a relay control partition, an LCL control partition, and an SSPC control partition.
8. The power priority based master-slave independent, zone controlled satellite power distribution method of claim 7, wherein: the electric load equipment in the relay control partition is a flight key load, the ground control uses a relay, and the relay is short-circuited in an on-orbit manner.
9. The power priority based master-slave independent, zone controlled satellite power distribution method of claim 7, wherein: the LCL controls the power utilization load equipment in the subarea to be a task key load and a general load which are directly distributed to a single machine;
on the premise of meeting the matching property of LCL and power consumption load, the task key load needs to control a power supply path by an independent LCL, one LCL is used by a later-stage load, and one LCL is used by backup; multiple general loads can share one LCL control power supply path.
10. The power priority based master-slave independent, zone controlled satellite power distribution method of claim 7, wherein:
the SSPC controls the power load equipment in the partition to be a mission critical load and a general load;
on the premise of meeting the matching between the SSPC and the power consumption load, the task-critical load needs to control a power supply path by an independent SSPC; multiple general loads can share one SSPC control power supply.
CN202311233348.0A 2023-09-21 2023-09-21 Main and standby independent and partition controlled satellite power distribution method based on power supply priority Pending CN117416532A (en)

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