CN114802820A - Power management control structure and method for spacecraft payload - Google Patents
Power management control structure and method for spacecraft payload Download PDFInfo
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- CN114802820A CN114802820A CN202210512765.8A CN202210512765A CN114802820A CN 114802820 A CN114802820 A CN 114802820A CN 202210512765 A CN202210512765 A CN 202210512765A CN 114802820 A CN114802820 A CN 114802820A
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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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- 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
- H02J13/00—Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the network; Circuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network
- H02J13/00001—Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the network; Circuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network characterised by the display of information or by user interaction, e.g. supervisory control and data acquisition systems [SCADA] or graphical user interfaces [GUI]
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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
- H02J13/00—Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the network; Circuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network
- H02J13/00002—Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the network; Circuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network characterised by monitoring
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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
- H02J13/00—Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the network; Circuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network
- H02J13/00006—Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the network; Circuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network characterised by information or instructions transport means between the monitoring, controlling or managing units and monitored, controlled or operated power network element or electrical equipment
- H02J13/00016—Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the network; Circuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network characterised by information or instructions transport means between the monitoring, controlling or managing units and monitored, controlled or operated power network element or electrical equipment using a wired telecommunication network or a data transmission bus
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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
- H02J13/00—Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the network; Circuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network
- H02J13/00032—Systems characterised by the controlled or operated power network elements or equipment, the power network elements or equipment not otherwise provided for
- H02J13/00036—Systems characterised by the controlled or operated power network elements or equipment, the power network elements or equipment not otherwise provided for the elements or equipment being or involving switches, relays or circuit breakers
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- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
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- Aviation & Aerospace Engineering (AREA)
- Human Computer Interaction (AREA)
- Computer Networks & Wireless Communication (AREA)
- Power Sources (AREA)
Abstract
The invention discloses a power management control structure and a method for a spacecraft payload, wherein the power management control structure comprises the following components: two paths of CAN buses are used as main and standby buses; the master control node is hung on the CAN bus and used for receiving circuit state information on the CAN bus and sending a power control instruction to the slave node through the CAN bus; and the plurality of slave nodes are connected to the CAN bus and used for acquiring the circuit state information of the slave nodes and powering on and powering off other functional circuits according to the power control instruction transmitted by the master control node so as to realize the power management control of the spacecraft payload. This application realizes issuing of power control instruction and the collection and uploading of a plurality of node circuit state through the interactive communication of master node and a plurality of slave node on the CAN bus, has promoted load equipment's scalability, has higher flexibility, and the upgrading transformation of being convenient for has simultaneously significantly reduced the inside power control signal quantity of payload equipment, has reduced the complexity of system.
Description
Technical Field
The invention relates to the field of spacecraft payload power control, in particular to a power management control structure and method for a spacecraft payload.
Background
The spacecraft payload refers to an instrument, equipment, a test piece and the like which are loaded on a spacecraft and directly complete a specific task. The payload is of a wide variety and the payload for a particular function is typically made up of multiple electronic devices or modules. In order to reduce the power consumption of the payload, it is usually powered on during the execution of the task, and in other states it is in a standby state or a power-off state. Therefore, there is a need to control the powering on and off of the payload while monitoring its operational status by an effective and reliable means. The existing payload power management is usually realized by adopting an OC instruction mode, and an upper computer of a spacecraft platform is connected with a lower-level control module through an OC instruction line and an OC instruction bus. Each controlled node module is provided with a relay switch and is connected with an OC instruction and an instruction bus. When power is needed to be supplied and discharged, the upper computer sends OC instruction pulses to drive the relay switch state of the lower module to change, and therefore power supply and discharge control of the modules are achieved.
The above method has the following disadvantages:
(1) the method is limited by the initial design of the OC instruction, and once the system hardware is fixed, a new OC instruction line is difficult to add, so that the subsequent system upgrading and reconstruction cannot expand the control node according to the requirement, and the method cannot adapt to the requirement of the aerospace electronic equipment integration.
(2) In order to ensure the reliability of the OC control signal, a two-wire two-point redundancy backup is usually required for each OC command, and the more modules are wired, so that the wiring and the structural complexity of the system are increased.
(3) The system module power-on and power-off system lacks flexibility and an effective power supply monitoring means in a scene with complex flow requirements, and does not meet the technical development requirements of interface standardization, high integration, design integration and the like.
The above is only for the purpose of assisting understanding of the technical aspects of the present invention, and does not represent an admission that the above is prior art.
Disclosure of Invention
The invention mainly aims to provide a power management control structure and a power management control method for an effective load of a spacecraft, and aims to solve the technical problems of complex system, poor expandability and low control flexibility of the existing effective load power control scheme.
To achieve the above object, the present invention provides a power management control structure for a spacecraft payload, the power management control structure comprising:
two paths of CAN buses are used as main and standby buses;
the main control node is connected with the CAN bus in a hanging mode and used for receiving circuit state information on the CAN bus and sending a power control instruction to the CAN bus;
and the plurality of slave nodes are connected with the CAN bus in a hanging mode and used for acquiring the circuit state information of the slave nodes and controlling the power access states of other functional circuits according to the power control instruction transmitted by the CAN bus.
Optionally, the spacecraft payload further includes a power supply bus, and the power supply bus is respectively connected to the master control node and the plurality of slave nodes.
Optionally, the slave node comprises a first power conversion circuit and a slave node power control circuit; wherein:
the power supply input end of the first power supply conversion circuit is connected with a power supply bus, and the output end of the first power supply conversion circuit is connected with the first power supply control circuit and other functional circuits and is used for supplying power to the first power supply control circuit and other functional circuits of the payload;
the slave node power supply control circuit is used for acquiring a power supply control instruction of the CAN bus, generating an enabling control signal according to the power supply control instruction, and sending the enabling control signal to the first power supply conversion circuit so as to drive the first power supply conversion circuit to supply power to other functional circuits.
Optionally, the first power conversion circuit includes a first power conversion chip and a second power conversion chip; wherein:
the power supply input end of the first power supply conversion chip is connected with a power supply bus, and the power supply output end of the first power supply conversion chip is connected with a power supply control circuit;
and the power supply input end of the second power supply conversion chip is connected with a power supply bus, and the power supply output end of the second power supply conversion chip is connected with other functional circuits.
Optionally, the slave node power supply control circuit includes:
the circuit state monitoring circuit is used for acquiring the circuit state information of the slave node;
the slave node MCU controller is connected with the circuit state monitoring circuit and the second power supply conversion chip and is used for receiving circuit state information, generating an enabling control signal according to a power supply control instruction and sending the enabling control signal to the second power supply conversion chip;
the CAN bus transceiver circuits are respectively connected with the CAN buses and are used for conversion control of CAN bus electric signals;
and the CAN protocol control units are connected with the slave node MCU controller and the CAN bus transceiving circuit and used for analyzing a CAN bus protocol and realizing the transmission of power control instructions and circuit state information between the slave node MCU controller and the CAN bus.
Optionally, the master control node includes a second power conversion circuit and a master control node power control circuit; wherein:
the power supply input end of the second power supply conversion circuit is connected with a power supply bus, and the output end of the second power supply conversion circuit is connected with the main control node power supply control circuit and used for supplying power to the main control node power supply control circuit;
the master control node power supply control circuit is used for acquiring circuit state information of the CAN bus, generating a power supply control instruction according to the circuit state information and sending the power supply control instruction to the CAN bus.
Optionally, the second power conversion circuit includes a second power conversion chip, a power input end of the second power conversion chip is connected to the power supply bus, and a power output end of the second power conversion chip is connected to the master control node power control circuit and other functional circuits.
Optionally, the power control circuit of the master control node includes:
the CAN bus receiving and transmitting circuits are respectively connected with the CAN buses and used for conversion control of electric signals of the CAN buses;
the CAN protocol control units are connected with the MCU controller of the master control node and the CAN bus transceiving circuit and used for analyzing a CAN bus protocol and realizing the transmission of power control instructions and circuit state information between the MCU controller of the master control node and a CAN bus;
and the main control node MCU controller is connected with the plurality of CAN protocol control units and is used for generating a power supply control instruction according to the operation requirement of the effective load.
Furthermore, in order to achieve the above object, the present invention also provides a power management control method for a spacecraft payload, for a power management control structure for a spacecraft payload as described above, the method comprising the steps of:
when a task needs to be executed, the master control node sends a power-on command to the slave node through the CAN bus; the slave node is connected with a power conversion circuit;
the slave node analyzes the instruction, if the instruction is a power-on instruction, an enabling control signal is sent to the power conversion circuit, and the power conversion circuit is driven to access a power supply bus to other functional circuits;
the method comprises the steps that circuit state information of a payload is collected from a node and sent to a CAN bus;
the master control node acquires circuit state information and judges whether the circuit state is normal or not; if so, stopping sending the power-on instruction, and executing the task by the effective load; if not, switching the CAN bus or switching the redundancy module.
Furthermore, in order to achieve the above object, the present invention also provides a power management control method for a spacecraft payload, for a power management control structure for a spacecraft payload as described above, the method comprising the steps of:
when the task is executed, the master control node sends a power-off instruction to the slave node through the CAN bus; the slave node is connected with a power conversion circuit;
the slave node analyzes the instruction, if the instruction is a power-off instruction, an enabling control signal is sent to the power conversion circuit, and the power conversion circuit is driven to stop connecting the power supply bus to other functional circuits;
the method comprises the steps that circuit state information of a payload is collected from a node and sent to a CAN bus;
the master control node acquires circuit state information and judges whether the circuit state is normal or not; if so, stopping sending the power-off instruction; if not, switching the CAN bus or switching the redundancy module.
In an embodiment of the application, a power management control structure and method for a spacecraft payload are provided. Compared with the prior art, the application has the following advantages and effects:
1) because each node is mounted by using the CAN bus, when a system needs to add a new function or node, hardware does not need to be changed, only a new module needs to be mounted on the CAN bus, the universal design of the system is supported, the upgrading and the expansion are convenient, and the method is particularly suitable for an aerospace comprehensive system.
2) When the number of the modules is large, the number of power supply control signal lines of each node connected with the system is only two main CAN buses and two spare CAN buses. Compared with the existing OC instruction mode, the method greatly reduces the internal wiring of the equipment, reduces the complexity of the system and improves the reliability of the equipment.
3) Each slave node omits an additional OC command receiving circuit and relay. The MCU can be combined with the board-level management controller, so that the circuit complexity of each node is reduced. Taking a system with 16 slave nodes as an example, if OC command control is adopted and two-dot two-wire backup is adopted at the same time, 32 signal wires are required to be switched and commanded, and 64 signal wires are required in total. If the CAN bus is adopted, only 4 signal lines are needed, and the complexity of the system is greatly reduced.
4) The CAN bus dual redundancy is adopted, and communication on one bus is preferentially carried out under the normal condition. When one of the buses fails, the other bus can be switched to communicate, and the faulty bus can be reinitialized for future use. Greatly improves the reliability of communication
5) The CAN bus power control protocol CAN support transmission of complex information, power supply on-off control is performed, power supply state monitoring is performed simultaneously, and testability and fault detection rate of the effective load are improved.
6) The CAN bus transmits information in the form of differential signals, is strong in electromagnetic interference resistance, and signals are not influenced by the change of the state of a power switch, meanwhile, the timeliness of communication is guaranteed, and the reduction of the power consumption of the satellite borne equipment is facilitated.
Drawings
FIG. 1 is a schematic diagram of a power management control architecture for a spacecraft payload in accordance with the present invention;
FIG. 2 is a schematic diagram of a slave node according to the present invention;
FIG. 3 is a schematic structural diagram of a master node according to the present invention;
FIG. 4 is a schematic flow chart illustrating power-on control of a power supply via a CAN bus according to the present invention;
fig. 5 is a schematic flow chart of power-off control performed through a CAN bus according to the present invention.
The implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.
Detailed Description
It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that all the directional indicators (such as up, down, left, right, front, and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, etc. in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.
In addition, the technical solutions in the embodiments may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, the combination of the technical solutions should be considered to be absent, and is not within the protection scope of the invention.
The existing payload power management is usually realized by adopting an OC instruction mode, and an upper computer of a spacecraft platform is connected with a lower-level control module through an OC instruction line and an OC instruction bus. Each controlled node module is provided with a relay switch and is connected with an OC instruction and an instruction bus. When power is needed to be supplied and discharged, the upper computer sends OC instruction pulses to drive the relay switch state of the lower module to change, and therefore power supply and discharge control of the modules are achieved.
The above method has the following disadvantages: (1) limited by the initial design of the OC instruction, once the system hardware is fixed, a new OC instruction line is difficult to add, so that the subsequent system upgrading and reconstruction cannot expand the control node according to the requirement, and the requirement of aerospace electronic equipment integration cannot be met. (2) In order to ensure the reliability of the OC control signal, a two-wire two-point redundancy backup is usually required for each OC command, and the more modules are wired, so that the wiring and the structural complexity of the system are increased. (3) The system module power-on and power-off system lacks flexibility and an effective power supply monitoring means in a scene with complex flow requirements, and does not meet the technical development requirements of interface standardization, high integration, design integration and the like.
To address this issue, various embodiments of a power management control architecture for spacecraft payloads of the present invention are presented. The power management control structure of the spacecraft payload provided by the invention realizes the issuing of the power control instruction and the collection and uploading of the circuit state information of a plurality of payloads through the interactive communication of the master control node and the plurality of slave nodes on the CAN bus, improves the expandability of the load equipment, has higher flexibility, is convenient for upgrading and reconstruction, greatly reduces the number of signals in the payload equipment, and reduces the complexity of the system.
The embodiment provides a spacecraft payload power control system, which comprises a main CAN bus, a standby CAN bus, a master control node and a plurality of slave nodes.
Specifically, a master control node is connected with the CAN bus in a hanging mode and used for receiving circuit state information on the CAN bus and sending a power control instruction to the CAN bus; the slave node is connected with the CAN bus in a hanging mode and used for collecting circuit state information of the slave node and controlling power supply access states of other functional circuits according to power supply control instructions transmitted by the CAN bus.
It should be noted that the spacecraft payload power control system further comprises a power supply bus, and the power supply bus is respectively connected with the master control node and the plurality of slave nodes.
In one embodiment, the slave node includes a first power conversion circuit and a slave node power control circuit.
On this basis, the power supply input end of the first power supply conversion circuit is connected with a power supply bus, and the output end of the first power supply conversion circuit is connected with a first power supply control circuit and other functional circuits and is used for supplying power to the first power supply control circuit and other functional circuits of the payload; the slave node power supply control circuit is used for acquiring a power supply control instruction of the CAN bus, generating an enabling control signal according to the power supply control instruction, and sending the enabling control signal to the first power supply conversion circuit so as to drive the first power supply conversion circuit to supply power to other functional circuits.
It should be noted that the first power conversion circuit includes a first power conversion chip and a second power conversion chip, a power input end of the first power conversion chip is connected to the power supply bus, and a power output end of the first power conversion chip is connected to the power control circuit; and the power supply input end of the second power supply conversion chip is connected with a power supply bus, and the power supply output end of the second power supply conversion chip is connected with other functional circuits.
It should be noted that the slave node power supply control circuit includes a circuit state monitoring circuit, a slave node MCU controller, a plurality of CAN bus transceiver circuits, and a plurality of CAN protocol control units. Wherein:
the circuit state monitoring circuit is used for acquiring the circuit state information of the slave node; the slave node MCU controller is connected with the circuit state monitoring circuit and the second power supply conversion chip and is used for receiving circuit state information, generating an enabling control signal according to a power supply control instruction and sending the enabling control signal to the second power supply conversion chip; the CAN bus transceiver circuits are respectively connected with the CAN buses and are used for conversion control of CAN bus electric signals; and the CAN protocol control units are connected with the slave node MCU controller and the CAN bus transceiving circuit and used for analyzing a CAN bus protocol and realizing the transmission of power control instructions and circuit state information between the slave node MCU controller and the CAN bus.
In another embodiment, the master node includes a second power conversion circuit and a master node power master control circuit.
On the basis, the power supply input end of the second power supply conversion circuit is connected with a power supply bus, and the output end of the second power supply conversion circuit is connected with a main control node power supply control circuit and used for supplying power to the main control node power supply control circuit; the master control node power supply control circuit is used for acquiring circuit state information of the CAN bus, generating a power supply control instruction according to the circuit state information and sending the power supply control instruction to the CAN bus.
It should be noted that the second power conversion circuit includes a second power conversion chip, a power input end of the second power conversion chip is connected to the power supply bus, and a power output end of the second power conversion chip is connected to the main control node power control circuit and other functional circuits.
It should be noted that the master control node power supply control circuit comprises a plurality of CAN bus transceiver circuits, a plurality of CAN protocol control units and a master control node MCU controller; wherein:
the CAN bus transceiver circuits are respectively connected with the CAN buses and are used for conversion control of CAN bus electric signals; the CAN protocol control units are connected with the MCU controller of the master control node and the CAN bus transceiving circuit and used for analyzing a CAN bus protocol and realizing the transmission of power control instructions and circuit state information between the MCU controller of the master control node and a CAN bus; and the MCU controller is connected with the CAN protocol control units and used for generating a power supply control instruction according to the operation requirement of the effective load.
The embodiment of the application provides a power management control structure of spacecraft payload, which comprises: two paths of CAN buses are used as main and standby buses; the master control node is hung on the CAN bus and used for receiving circuit state information on the CAN bus and sending a power control instruction to the slave node through the CAN bus; and the plurality of slave nodes are connected to the CAN bus and used for acquiring the circuit state information of the slave nodes and powering on and powering off other functional circuits according to the power control instruction transmitted by the master control node. This application realizes issuing of power control instruction and the collection and uploading of a plurality of node circuit state through the interactive communication of master node and a plurality of slave node on the CAN bus, has promoted load equipment's scalability, has higher flexibility, and the upgrading transformation of being convenient for has simultaneously significantly reduced the inside power control signal quantity of payload equipment, has reduced the complexity of system.
To facilitate understanding, the present embodiment proposes a specific example for spacecraft payload power management control, specifically as follows:
see fig. 1. The figure shows a system architecture for load power management control over a CAN bus. The system consists of a master node and a plurality of slave nodes. All the nodes are connected through two independent CAN buses and adopt the same power supply line. The master control node is used as a master device and used for sending control instructions and detecting the power supply working state of each slave node. And the slave node responds to the instruction of the master control node and reports the working state of the power supply.
See fig. 2. The figure shows a block diagram of a power management control circuit of a load slave node based on a CAN bus. The MCU is a main control unit, usually a satellite-borne high-reliability CPU, a singlechip or an FPGA, and realizes the functions of command analysis, state monitoring, logic control and the like. The CAN bus transceiver realizes the physical interface of the CAN bus and provides differential receiving and transmitting capability to the bus. And the CAN protocol control realizes the analysis of the CAN bottom layer protocol and realizes the data transmission with the rear end MCU interface. And the power supply conversion A converts the external power supply input into the voltage required by the working of the A/D sampling circuit and the MCU and CAN bus related circuits. The power supply conversion B converts the external power supply input into the voltage required by other functional circuits, and the enabling of the voltage is controlled by the MCU. The A/D sampling circuit realizes the collection of the current and the voltage of the whole node and the detection of the circuit state.
See fig. 3. The power management schematic diagram of the master control node is given in the figure, and the difference between the master control node and the slave node is that the master control node has no power conversion B, realizes power conversion and power supply of all circuits through the power conversion A, and is always in a working state under the condition that power supply input is effective.
In addition, the present application further provides a power supply power-on management control method for a spacecraft payload, based on the above power supply management control structure for a spacecraft payload, the method includes the following steps:
s100, when a task needs to be executed, the master control node sends a power-on instruction to the slave node through the CAN bus; the slave node is connected with a power conversion circuit;
s200, the slave node analyzes the instruction, if the instruction is a power-on instruction, an enabling control signal is sent to the power conversion circuit, and the power conversion circuit is driven to access the power supply bus to other functional circuits;
s300, collecting circuit state information of the effective load from the node, and sending the circuit state information to a CAN bus;
s400, the master control node acquires circuit state information and judges whether the circuit state is normal or not; if so, stopping sending the power-on instruction, and executing the task by the effective load; if not, switching the CAN bus or switching the redundancy module.
For convenience of understanding, the present embodiment provides a specific example of a power-on control method for a payload power supply of a spacecraft, which is specifically as follows:
see fig. 4. The power-up flow for load power management is shown in the figure. The system first completes initialization of power management, including initialization of a CAN bus, initialization of an MCU, and the like. The master control node is in a working state during initialization, the slave node is in a standby state, and the slave node only works in a CAN bus, an MCU and an A/D sampling related circuit. When tasks need to be executed, a power-on command is sent by the master node to the slave node through the CAN bus. And the slave node analyzes the instruction, and drives the power supply to convert the B enabling signal if the instruction is a power-on command so as to enable the slave node to enter a working state. And after the slave node detects the voltage and current state, reporting to the master control node. The main control node judges whether the current voltage state is normal or not, and if the power-on is normally finished, the follow-up execution task is started. If not, the fault is handled, such as switching CAN bus, switching redundant module, etc.
In addition, the present application further provides a power outage management control method for a spacecraft payload, based on the above power outage management control structure for a spacecraft payload, the method includes the following steps:
s500, when the task is executed, the master control node sends a power-off instruction to the slave node through the CAN bus; the slave node is connected with a power conversion circuit;
s600, the slave node analyzes the instruction, if the instruction is a power-off instruction, an enabling control signal is sent to the power conversion circuit, and the power conversion circuit is driven to stop connecting the power supply bus to other functional circuits;
s700, collecting circuit state information of a payload from a node, and sending the circuit state information to a CAN bus;
s800, the master control node acquires circuit state information and judges whether the circuit state is normal or not; if so, stopping sending the power-off instruction; if not, switching the CAN bus or switching the redundancy module.
For convenience of understanding, the present embodiment provides a specific example of a power outage control method for a payload power supply of a spacecraft, which is as follows:
see fig. 5. The figure shows the power-off flow for load power management. When the task execution is completed, the master node sends a power-off command to the slave node through the CAN bus. And the slave node analyzes the instruction, and drives the power supply to convert the B enable signal if the instruction is a power-off command, so that the slave node finishes the working state and the functional circuit stops working. And after the slave node detects the voltage and current state, reporting to the master control node. The main control node judges whether the current and voltage state is normal or not, and if the power failure is normally finished, the follow-up execution task is started. If the power failure is not successful, the fault handling is carried out, such as switching the CAN bus, switching the redundant module and the like.
Other embodiments or specific implementation manners of the power-on control method and the power-off control method for the spacecraft payload power supply of the invention can refer to the above circuit embodiments, and are not described herein again.
The embodiment of the application provides a management control method for an effective load power supply of a spacecraft. The payload sets a master node and a plurality of slave nodes based on the CAN bus. In order to realize power management control, each node comprises a CAN controller, an MCU controller, a power management chip, an A/D acquisition chip and other circuits. The master control node sends power-on and power-off control instructions to all slave nodes in a CAN bus instruction control mode, and all the slave nodes are controlled by a board-level MCU controller to control a board-level power chip to carry out power-on and power-off control, and simultaneously carry out equipment power utilization state detection and report the master control node. The method improves the expandability of the load equipment, has higher flexibility, is convenient for upgrading and reconstruction, greatly reduces the number of signals in the effective load equipment and reduces the complexity of the system. The invention can also effectively monitor the power consumption conditions of voltage, current and the like of each module of the system, is suitable for more complex systems and power-up processes, can be designed into a standard interface, and meets the requirement of integration of the effective load of the spacecraft.
The above are only preferred embodiments of the invention, and not intended to limit the scope of the invention, and all equivalent structures or equivalent flow transformations that may be applied to the present specification and drawings, or applied directly or indirectly to other related technical fields, are included in the scope of the invention.
Claims (10)
1. A power management control structure for a spacecraft payload, the power management control structure comprising:
two paths of CAN buses are used as main and standby buses;
the main control node is connected with the CAN bus in a hanging mode and used for receiving circuit state information on the CAN bus and sending a power control instruction to the CAN bus;
and the plurality of slave nodes are connected with the CAN bus in a hanging mode and used for acquiring the circuit state information of the slave nodes and controlling the power access states of other functional circuits according to the power control instruction transmitted by the CAN bus.
2. The power management control structure for a spacecraft payload of claim 1, further comprising a power bus connecting the master node and the plurality of slave nodes, respectively.
3. The power management control structure for a spacecraft payload of claim 2, wherein the slave node includes a first power conversion circuit and a slave node power control circuit; wherein:
the power supply input end of the first power supply conversion circuit is connected with a power supply bus, and the output end of the first power supply conversion circuit is connected with the first power supply control circuit and other functional circuits and is used for supplying power to the first power supply control circuit and other functional circuits of the payload;
the slave node power supply control circuit is used for acquiring a power supply control instruction of the CAN bus, generating an enabling control signal according to the power supply control instruction, and sending the enabling control signal to the first power supply conversion circuit so as to drive the first power supply conversion circuit to supply power to other functional circuits.
4. The power management control structure for a spacecraft payload of claim 3, wherein the first power conversion circuitry comprises a first power conversion chip and a second power conversion chip; wherein:
the power supply input end of the first power supply conversion chip is connected with a power supply bus, and the power supply output end of the first power supply conversion chip is connected with a power supply control circuit;
and the power supply input end of the second power supply conversion chip is connected with a power supply bus, and the power supply output end of the second power supply conversion chip is connected with other functional circuits.
5. The power management control structure for a spacecraft payload of claim 4, wherein the slave node power control circuitry comprises:
the circuit state monitoring circuit is used for acquiring the circuit state information of the slave node;
the slave node MCU controller is connected with the circuit state monitoring circuit and the second power supply conversion chip and is used for receiving circuit state information, generating an enabling control signal according to a power supply control instruction and sending the enabling control signal to the second power supply conversion chip;
the CAN bus transceiver circuits are respectively connected with the CAN buses and are used for conversion control of CAN bus electric signals;
and the CAN protocol control units are connected with the slave node MCU controller and the CAN bus transceiving circuit and used for analyzing a CAN bus protocol and realizing the transmission of power control instructions and circuit state information between the slave node MCU controller and the CAN bus.
6. The power management control structure for a spacecraft payload of claim 2, wherein the master node comprises a second power conversion circuit and a master node power control circuit; wherein:
the power supply input end of the second power supply conversion circuit is connected with a power supply bus, and the output end of the second power supply conversion circuit is connected with the main control node power supply control circuit and used for supplying power to the main control node power supply control circuit;
the master control node power supply control circuit is used for acquiring circuit state information of the CAN bus, generating a power supply control instruction according to the circuit state information and sending the power supply control instruction to the CAN bus.
7. The power management control structure for a spacecraft payload of claim 6, wherein the second power conversion circuitry comprises a second power conversion chip having power inputs connected to a power bus and power outputs connected to the master node power control circuitry and other functional circuitry.
8. The power management control structure for a spacecraft payload of claim 7, wherein the master node power control circuitry comprises:
the CAN bus transceiver circuits are respectively connected with the CAN buses and are used for conversion control of CAN bus electric signals;
the CAN protocol control units are connected with the MCU controller of the master control node and the CAN bus transceiving circuit and used for analyzing a CAN bus protocol and realizing the transmission of power control instructions and circuit state information between the MCU controller of the master control node and a CAN bus;
and the MCU controller is connected with the CAN protocol control units and used for generating a power supply control instruction according to the operation requirement of the effective load.
9. A power management control method for a spacecraft payload, for use in a power management control structure for a spacecraft payload according to any one of claims 1 to 8, the method comprising the steps of:
when a task needs to be executed, the master control node sends a power-on command to the slave node through the CAN bus; the slave node is connected with a power supply conversion circuit;
the slave node analyzes the instruction, if the instruction is a power-on instruction, an enabling control signal is sent to the power conversion circuit, and the power conversion circuit is driven to access a power supply bus to other functional circuits;
the method comprises the steps that circuit state information of a payload is collected from a node and sent to a CAN bus;
the master control node acquires circuit state information and judges whether the circuit state is normal or not; if so, stopping sending the power-on instruction, and executing the task by the effective load; if not, switching the CAN bus or switching the redundancy module.
10. A method for power management control of a spacecraft payload, for use in a power management control structure for a spacecraft payload according to any one of claims 1 to 8, the method comprising the steps of:
when the task is executed, the master control node sends a power-off instruction to the slave node through the CAN bus; the slave node is connected with a power conversion circuit;
the slave node analyzes the instruction, if the instruction is a power-off instruction, an enabling control signal is sent to the power conversion circuit, and the power conversion circuit is driven to stop connecting the power supply bus to other functional circuits;
the method comprises the steps that circuit state information of a payload is collected from a node and sent to a CAN bus;
the master control node acquires circuit state information and judges whether the circuit state is normal or not; if so, stopping sending the power-off instruction; if not, switching the CAN bus or switching the redundancy module.
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