CN112395720A - Time certainty distributed spacecraft electronic system design method - Google Patents
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Abstract
The invention discloses a time certainty distributed spacecraft electronic system design method, which solves the problems of insufficient expansibility and poor data transmission time certainty of the conventional spacecraft electronic system. The method adopts a layered analysis method to determine the function distribution of the spacecraft electronic system; selecting a time-triggered Ethernet as an electronic system backbone network, wherein a distributed architecture is adopted on a network topology structure, and the system computing function is distributed to a plurality of devices; planning tasks to be executed by the electronic system, pre-estimating the service condition of system resources in advance, and realizing static configuration of computing resources in a pre-allocation mode; and the message transmission mode is planned according to the priority, so that the high-priority message has higher time certainty and transmission reliability under the condition of meeting the required bandwidth.
Description
Technical Field
The invention provides a time certainty distributed spacecraft electronic system design method, a time certainty network design technology and a spacecraft electronic system design technology, and belongs to the field of spacecraft electronic system design.
Background
With the increasing functional complexity of the spacecraft, the amount of communication information and the degree of integration are continuously improved, and electronic systems on the spacecraft are developing towards modularization, integration and standardization. The design of the spacecraft electronic system not only determines the physical architecture and the information interaction mode of the system, but also directly influences the development, verification, testability and operability of the system.
The traditional spacecraft electronic system in China generally adopts a point-to-point connection (a star structure of RS422 and a custom synchronous serial port) or a centralized system architecture taking a low-speed control bus (MIL-STD-1553B, CAN) as a bridge. The system is characterized in that each single machine interface and interconnection cable in the system are more, and the volume, the weight and the power consumption are larger; system scalability, particularly in-orbit scalability, is poor. Meanwhile, the system adopts an event-triggered communication mechanism, the mechanism adopts a bus preemption mode based on priority scheduling, and although the flexibility of bus access is enhanced by event triggering and priority preemption, the problem of uncertainty of information transmission delay exists. With the successive development of the tasks of on-orbit operation, rendezvous and docking, space attack and defense, on-orbit module replacement and the like of the spacecraft in China in the future, the requirements of system expansibility, message transmission certainty, reliability and safety are particularly outstanding, and the traditional electronic system architecture of the spacecraft cannot meet the application requirements.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the method overcomes the defects of the prior art and provides a time certainty distributed spacecraft electronic system design method.
The technical solution of the invention is as follows:
a time deterministic distributed spacecraft electronic system design method comprises the following steps: the layered model describes system functions, builds a distributed time-triggered Ethernet architecture, allocates system resources in a partitioning mode, and plans a transmission mode based on message priority. The system hierarchical architecture is used for performing hierarchical representation on functions of an electronic system of the spacecraft and is divided into an input layer, an information processing layer, a decision layer, an output layer and a driving layer from top to bottom.
A method for designing a time-deterministic distributed spacecraft electronic system, the method comprising the steps of:
(1) a layered model describes system functions, and comprises an input layer, an information processing layer, a decision layer, an output layer and a driving layer;
the input layer is used for receiving external information of the spacecraft electronic system and outputting the received external information to the information processing layer;
the information processing layer is used for receiving the external information output by the input layer, processing the received external information and outputting the processed external information to the decision layer;
the decision layer is used for receiving the processed external information output by the information processing layer, calculating according to the received processed external information and outputting a calculation result to the output layer;
the output layer is used for receiving the calculation result output by the decision layer and outputting the received calculation result to the driving layer;
the driving layer is used for receiving the calculation result output by the output layer and finishing the driving of the execution terminal according to the received calculation result;
designing electronic equipment capable of realizing the functions of the spacecraft according to the requirements of the spacecraft, and classifying the designed electronic equipment into each layer according to the functions of each layer of the layered model;
the electronic equipment (such as the electronic equipment used for attitude orbit measurement, remote control instruction receiving and human control operation) classified into the input layer receives external information of the spacecraft electronic system and outputs the received external information to the electronic equipment classified into the information processing layer;
the electronic equipment classified into the information processing layer (such as used for sensor information processing, remote control instruction processing and human control operation processing) receives external information output by the electronic equipment classified into the input layer, processes the received external information and outputs the processed external information to the electronic equipment classified into the decision layer;
the electronic equipment classified into the decision layer (such as for GNC calculation and telemetry data synthesis) receives the processed external information output by the electronic equipment classified into the information processing layer, calculates according to the received processed external information, and outputs a calculation result to the electronic equipment classified into the output layer;
the electronic equipment classified into the output layer (for example, used for control instruction generation and telemetering data downlink) receives the calculation result output by the electronic equipment classified into the decision layer, and outputs the received calculation result to the electronic equipment classified into the drive layer;
the electronic equipment which is classified into the driving layer (such as used for control instruction execution and wireless measurement and control) receives the calculation result output by the electronic equipment which is classified into the output layer, and the driving of the execution terminal is completed according to the received calculation result.
Different functions of the same layer can be realized by different electronic devices, and the functions described by different layers can also be realized by the same electronic device according to actual requirements.
(2) Building a distributed time-triggered Ethernet architecture;
the method comprises the steps that a Time Triggered Ethernet (TTE) is used as a backbone network, a computing function is decomposed into a plurality of distributed computing nodes, each device of the system (namely electronic devices which are designed according to the requirements of a spacecraft and can realize the functions of the spacecraft) is connected with a network switch, no coupling relation exists between the devices, I/O data or computing results required by task processing can be acquired by any computing node of the system through a switched network, and data in the network is transmitted through a set transmission path;
the link redundancy design of a plurality of network switches is adopted, and the autonomous switching capacity under the fault condition is guaranteed. For key equipment, a dual-machine/triple-machine redundancy mode is adopted for ensuring reliability. For equipment with Self-checking (Self-checking) function, double-machine redundancy is adopted, equipment without Self-checking function adopts a triple-machine redundancy form, a TTE (time to live) network is based on the good time synchronism, double machines/triple machines can be independently mounted on the network, and key equipment is artificially defined equipment;
the communication adopts a time triggering mode, and the occupied bandwidth and the transmission path of each node realize the static configuration of communication resources through pre-planning. According to the real-time requirement, a secondary network structure can be adopted, a secondary network is constructed for a subsystem with high real-time performance (for example, the time precision requirement of a control system reaches microsecond level, the time precision of a backbone network can meet the requirement only when the time precision is generally required to be 100 mu s level), and the local real-time performance of the secondary network is improved on the premise of ensuring the communication resources of the primary network;
(3) partition configuring system resources
The application software running on a single processor (a computing node with an operating system) is grouped according to functional coupling, and the grouping application software is guaranteed to be mutually independent in time and space through scheduling arrangement, so that the partition scheduling processing function is realized. The starting time of each partition scheduling is different relative to the starting time of the main time shaft, and a time window is distributed to each partition in a mode of alternate scheduling. Allocating memory space with fixed position and size for each partition, and when a certain partition is accessed, the memory area of other partitions is not allowed to be accessed, so that space isolation is ensured;
the mapping relation between the partitions and the computing nodes is established, high sharing of computing resources is achieved by running a plurality of tasks in one computing resource, for example, a control task and a remote measurement task may share the same computing resource, and it is required to ensure that tasks of different key types cannot interfere with each other, and especially, tasks with high importance levels cannot be interfered by tasks with low importance levels. The task priority is artificially set;
(4) scheduling transmission modes based on message priority
Electronic systems employ Time-Triggered communication techniques, including Time-Triggered (TT) messages, Rate-limited (RC) messages, and Best-Effort (BE) messages. The transmission priority TT message is the highest, the RC message is the second, and the BE message is the lowest.
TT messages are adopted for communication of messages (such as control and safety messages) with strict real-time requirements in a spacecraft electronic system; for messages (such as telemetering messages) with time certainty requirement and low real-time requirement, RC messages are adopted for communication; for messages with lowest priority and uncertain transmission delay (such as image and voice messages), BE messages are adopted for communication.
Advantageous effects
(1) According to the invention, by building a distributed system architecture and applying a time deterministic network, processing, communication and computing resources of a system core can be flexibly expanded and reconfigured according to task requirements;
(2) by applying the time deterministic network, the invention realizes the data transmission conditions of more backbone network nodes, large communication data volume and coexistence of cyclic periodic information and non-periodic information;
(3) the invention enables the data packet and the control data on the link to be responded below the appointed time delay level through the application of the time deterministic network, thereby ensuring the real-time property of message transmission;
(4) the invention ensures that the message can accurately arrive and meet the bandwidth requirement on the maximum time delay guarantee through the application of the time deterministic network, thereby ensuring the predictability and the consistency of the communication operation.
(5) The invention discloses a time certainty distributed spacecraft electronic system design method, which solves the problems of insufficient expansibility and poor data transmission time certainty of the conventional spacecraft electronic system. The method adopts a layered analysis method to determine the function distribution of the spacecraft electronic system; selecting a time-triggered Ethernet as an electronic system backbone network, wherein a distributed architecture is adopted on a network topology structure, and the system computing function is distributed to a plurality of devices; planning tasks to be executed by the electronic system, pre-estimating the service condition of system resources in advance, and realizing static configuration of computing resources in a pre-allocation mode; and the message transmission mode is planned according to the priority, so that the high-priority message has higher time certainty and transmission reliability under the condition of meeting the required bandwidth.
Drawings
FIG. 1 is a schematic view of a functional layer model of a spacecraft of the present invention;
FIG. 2 is a two-machine/three-machine redundancy;
FIG. 3 is a two-level network architecture;
FIG. 4 is a partition structure for time triggered Ethernet based;
FIG. 5 is a spacecraft image matching system design flow;
fig. 6 is a TTE network interface relationship diagram.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in detail with reference to the accompanying drawings and specific embodiments.
A method for designing a time-deterministic distributed spacecraft electronic system, the method comprising the steps of:
(1) a layered model describes system functions, and comprises an input layer, an information processing layer, a decision layer, an output layer and a driving layer;
the input layer is used for receiving external information of the spacecraft electronic system and outputting the received external information to the information processing layer;
the information processing layer is used for receiving the external information output by the input layer, processing the received external information and outputting the processed external information to the decision layer;
the decision layer is used for receiving the processed external information output by the information processing layer, calculating according to the received processed external information and outputting a calculation result to the output layer;
the output layer is used for receiving the calculation result output by the decision layer and outputting the received calculation result to the driving layer;
the driving layer is used for receiving the calculation result output by the output layer and finishing the driving of the execution terminal according to the received calculation result;
designing electronic equipment capable of realizing the functions of the spacecraft according to the requirements of the spacecraft, and classifying the designed electronic equipment into each layer according to the functions of each layer of the layered model, as shown in figure 1;
the electronic equipment (such as the electronic equipment used for attitude orbit measurement, remote control instruction receiving and human control operation) classified into the input layer receives external information of the spacecraft electronic system and outputs the received external information to the electronic equipment classified into the information processing layer;
the electronic equipment classified into the information processing layer (such as used for sensor information processing, remote control instruction processing and human control operation processing) receives external information output by the electronic equipment classified into the input layer, processes the received external information and outputs the processed external information to the electronic equipment classified into the decision layer;
the electronic equipment classified into the decision layer (such as for GNC calculation and telemetry data synthesis) receives the processed external information output by the electronic equipment classified into the information processing layer, calculates according to the received processed external information, and outputs a calculation result to the electronic equipment classified into the output layer;
the electronic equipment classified into the output layer (for example, used for control instruction generation and telemetering data downlink) receives the calculation result output by the electronic equipment classified into the decision layer, and outputs the received calculation result to the electronic equipment classified into the drive layer;
the electronic equipment which is classified into the driving layer (such as used for control instruction execution and wireless measurement and control) receives the calculation result output by the electronic equipment which is classified into the output layer, and the driving of the execution terminal is completed according to the received calculation result.
Different functions of the same layer can be realized by different electronic devices, and the functions described by different layers can also be realized by the same electronic device according to actual requirements.
(2) Building a distributed time-triggered Ethernet architecture;
the method comprises the steps that a Time Triggered Ethernet (TTE) is used as a backbone network, a computing function is decomposed into a plurality of distributed computing nodes, each device of the system (namely electronic devices which are designed according to the requirements of a spacecraft and can realize the functions of the spacecraft) is connected with a network switch, no coupling relation exists between the devices, I/O data or computing results required by task processing can be acquired by any computing node of the system through a switched network, and data in the network is transmitted through a set transmission path;
the link redundancy design of a plurality of network switches is adopted, and the autonomous switching capacity under the fault condition is guaranteed. For key equipment, a dual-machine/triple-machine redundancy mode is adopted for ensuring reliability. For a device with a Self-checking (Self-checking) function, dual redundancy is adopted, a device without a Self-checking function adopts a triple redundancy form, and a TTE-based network has good time synchronism, so that dual/triple devices can be independently mounted on the network, as shown in FIG. 2. The key equipment is artificially defined equipment;
the communication adopts a time triggering mode, and the occupied bandwidth and the transmission path of each node realize the static configuration of communication resources through pre-planning. According to the real-time requirement, a secondary network structure can be adopted, a secondary network is constructed for a subsystem with high real-time performance (for example, the time precision requirement of a control system reaches microsecond level, and the time precision of a backbone network can meet the requirement only in 100 mu s level), and the local real-time performance of the secondary network is improved on the premise of ensuring the communication resources of the primary network, as shown in fig. 3.
(3) Partition configuring system resources
The application software running on a single processor (a computing node with an operating system) is grouped according to functional coupling, and the grouping application software is guaranteed to be mutually independent in time and space through scheduling arrangement, so that the partition scheduling processing function is realized. The starting time of each partition scheduling is different relative to the starting time of the main time shaft, and a time window is distributed to each partition in a mode of alternate scheduling. Each partition is allocated a memory space with a fixed location and size, and when a certain partition is accessed, the memory area of other partitions is not allowed to be accessed, so that space isolation is ensured, as shown in fig. 4.
The mapping relation between the partitions and the computing nodes is established, high sharing of computing resources is achieved by running a plurality of tasks in one computing resource, for example, a control task and a remote measurement task may share the same computing resource, and it is required to ensure that tasks of different key types cannot interfere with each other, and especially, tasks with high importance levels cannot be interfered by tasks with low importance levels. The task priority is artificially set;
(4) scheduling transmission modes based on message priority
Electronic systems employ Time-Triggered communication techniques, including Time-Triggered (TT) messages, Rate-limited (RC) messages, and Best-Effort (BE) messages. The transmission priority TT message is the highest, the RC message is the second, and the BE message is the lowest.
TT messages are adopted for communication of messages (such as control and safety messages) with strict real-time requirements in a spacecraft electronic system; for messages (such as telemetering messages) with time certainty requirement and low real-time requirement, RC messages are adopted for communication; for messages with lowest priority and uncertain transmission delay (such as image and voice messages), BE messages are adopted for communication.
Fig. 5 is a design flow of a time deterministic distributed spacecraft electronic system design method according to the present invention, according to which a spacecraft image matching system based on time triggered ethernet is designed.
The method comprises the following steps: the system function is described according to a layered model, and the electronic equipment is classified into layers according to the functions of the layers, wherein the electronic equipment comprises an input layer (small three-axis IMU), an information processing layer (interface management module), a decision layer (control computer A/B), an output layer (interface management module) and a driving layer (high-performance image processing unit, hereinafter referred to as GPU).
The small three-axis IMU measures attitude information of the spacecraft in the directions of three sensitive axes and outputs the information to the information management module; the information management module performs coordinate conversion on the received spacecraft attitude information, converts the attitude information into the coordinates of the spacecraft body, and outputs the converted information to the control computer A/B; the control computer A/B performs GNC calculation according to the received attitude information of the system, performs telemetering group packing on the attitude information and the GNC calculation result, and outputs the GNC calculation result and telemetering data to the information management module; the information management module packages the received control quantity according to a communication protocol of a driver layer device (GPU in the example) to generate an image conversion instruction, and sends the image conversion instruction to the GPU; and after receiving the image conversion instruction information, the GPU performs rotation and projection processing on the pre-installed image, and outputs the converted image to the information management module for image comparison.
Step two: time Triggered Ethernet (TTE) is used as the backbone network. The system comprises 3 terminal nodes which are respectively a control computer A, a control computer B and an interface management module. The adopted network switch is composed of a TTE network switch 1 and a TTE network switch 2. The TTE network switch 1 and the TTE network switch 2 are designed integrally, and are called as TTE network switches. The control computer A/B has a Self-checking (Self-checking) function and is dual-computer redundancy.
Step three: establishing partitions on terminal nodes, and controlling tasks to be completed by a computer A/B to comprise an Ethernet task-sending physical flight navigation task, a GNC self-closing loop task, an image processing task, a long-period guidance task, a redundancy and fault-tolerant task, a remote measurement and package task, an instruction processing task and a Flash read-write task. The tasks to be completed by the interface management module comprise an Ethernet transceiving task, a non-Ethernet data transceiving task, an image transmitting task, a dynamics simulation task, a Flash read-write task and a telemetering package task.
The terminal node calculates resources in advance, and statically configures tasks of the control computer a/B and the interface management module, as shown in tables 1 and 2.
TABLE 1 task timing and logic correspondence table (control computer A/B)
| Serial number | Task name | Core of the place | Priority level | Period of time | Phase position |
| 1 | Ethernet task | 0 | Height of | 16ms | 0ms |
| 2 | Physical flight navigation mission | 1 | Height of | 64ms | 24ms |
| 3 | GNC self-closed-loop task | 2 | Height of | 128ms | 0ms |
| 4 | Image processing task | 3 | Height of | 256ms | 0ms |
| 5 | Long-period guidance task | 3 | In | Continuous | -- |
| 6 | Redundancy and fault tolerant tasks | 2 | In | 128ms | 32ms |
| 7 | Telemetry group packaging task | 0 | Is low in | 256ms | 8ms |
| 8 | Instruction processing task | 0 | In | 16ms | 8ms |
| 9 | Flash read-write task | 1 | In | 256ms | 48ms |
TABLE 2 task timing and logic correspondence table (interface management module)
| Serial number | Task name | Core of the place | Priority level | Period of time | Phase position |
| 1 | Ethernet transceiving tasks | 0 | Height of | 16ms | 8ms |
| 2 | non-Ethernet data transceiving tasks | 1 | Height of | 16ms | 0ms |
| 3 | Image sending task | 2 | Height of | 256ms | 128ms |
| 4 | Dynamic simulation task | 3 | Height of | 32ms | 16ms |
| 5 | Flash read-write task | 1 | In | 256ms | 8ms |
| 6 | Telemetry group packaging task | 0 | Is low in | 256ms | 16ms |
Step four: and planning the message transmission mode according to the message transmission priority in the electronic system. The electronic system in this embodiment contains pose information, GNC calculation data, telemetry packaging data, image processing instructions, and processed image information. The pose information and GNC calculation data are set as TT messages for transmission, the telemetry data are set as RC messages for transmission, and the image processing instructions and the processed image information are set as BE messages for transmission, according to the priorities of the messages, as shown in table 3.
TABLE 3 message Transmission
| Serial number | Task name | Information source | Letter and eye | Message priority | Transmission mode |
| 1 | Attitude information | Interface management module | Control computer A/B | Height of | TT |
| 2 | GNC calculation data | Control computer A/B | Interface management module | Height of | TT |
| 3 | Telemetry data | Control computer A/B | Interface management module | In | RC |
| 4 | Image processing instructions | Interface management module | GPU | Is low in | BE |
| 5 | Processed image information | GPU | Interface management module | Is low in | BE |
According to the above message transmission method, the switch interface is designed, and a 3-way TTE network interface is adopted between the terminal node (control computer a/B and interface management module) and the TTE network switch 1/2, so that TT messages and RC messages can be transmitted. As only BE information interaction exists between the GPU and the interface management module, 1 path of common Ethernet interface is arranged on the TTE network switch 1 and used for receiving and sending BE information on the network, and the signal characteristic of the interface meets the requirement of standard Ethernet signal transmission. The interface relationship between devices in the system is shown in fig. 6. Since the small-scale triaxial IMU and the interface management module use a direct connection method for message transmission and do not use a TTE network for communication, the interface between the small-scale triaxial IMU and the interface management module is not explicitly described in fig. 6.
The design method of the time certainty distributed spacecraft electronic system is completely described through the design process of the spacecraft image matching system of the embodiment, the designed system has an open system architecture and can be flexibly expanded and reconfigured according to task requirements; the periodic information and the non-periodic information coexist in the system, and the transmission time precision of the high-priority message data is high; the message can accurately reach and meet the required bandwidth, and each communication operation has predictability and consistency.
The above examples are only for illustrating the technical solutions of the present invention, and are not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art may make modifications to the technical solutions described in the foregoing embodiments, or may make equivalent substitutions for some technical features, without departing from the scope of the technical solutions of the present invention.
Claims (10)
1. A time certainty distributed spacecraft electronic system design method is characterized by comprising the following steps: the layered model describes system functions, builds a distributed time-triggered Ethernet architecture, allocates system resources in a partitioning mode, and plans a transmission mode based on message priority.
2. A time deterministic distributed spacecraft electronic system design method according to claim 1, characterized in that: the described layered model describes the system functions, namely: the method comprises the following steps of performing layered representation on functions of an electronic system of the spacecraft through a layered model, wherein a system layered architecture is divided into an input layer, an information processing layer, a decision layer, an output layer and a driving layer from top to bottom; and designing the electronic equipment capable of realizing the functions of the spacecraft according to the requirements of the spacecraft, and classifying the designed electronic equipment into each layer according to the functions of each layer of the layered model.
3. A time deterministic distributed spacecraft electronic system design method according to claim 2, characterized in that:
the input layer is used for receiving external information of the spacecraft electronic system and outputting the received external information to the information processing layer;
the information processing layer is used for receiving the external information output by the input layer, processing the received external information and outputting the processed external information to the decision layer;
the decision layer is used for receiving the processed external information output by the information processing layer, calculating according to the received processed external information and outputting a calculation result to the output layer;
the output layer is used for receiving the calculation result output by the decision layer and outputting the received calculation result to the driving layer;
the driving layer is used for receiving the calculation result output by the output layer and finishing the driving of the execution terminal according to the received calculation result.
4. A time deterministic distributed spacecraft electronic system design method according to claim 2, characterized in that:
the electronic equipment classified into the input layer receives external information of the spacecraft electronic system and outputs the received external information to the electronic equipment classified into the information processing layer;
the electronic equipment classified into the information processing layer receives external information output by the electronic equipment classified into the input layer, processes the received external information and outputs the processed external information to the electronic equipment classified into the decision layer;
the electronic equipment classified into the decision layer receives the processed external information output by the electronic equipment classified into the information processing layer, calculates according to the received processed external information, and outputs a calculation result to the electronic equipment classified into the output layer;
the electronic equipment classified into the output layer receives the calculation result output by the electronic equipment classified into the decision layer and outputs the received calculation result to the electronic equipment classified into the drive layer;
and the electronic equipment classified into the driving layer receives the calculation result output by the electronic equipment classified into the output layer, and completes the driving of the execution terminal according to the received calculation result.
5. A time deterministic distributed spacecraft electronic system design method according to claim 2, characterized in that: different functions of the same layer can be realized by different electronic devices.
6. A time deterministic distributed spacecraft electronic system design method according to claim 2, characterized in that: the functions described in different layers can also be realized by the same electronic equipment according to actual requirements.
7. A time deterministic distributed spacecraft electronic system design method according to claim 1, characterized in that: the method for constructing the distributed time-triggered Ethernet architecture comprises the following steps: the time-triggered Ethernet is used as a backbone network, the computing function is decomposed into a plurality of distributed computing nodes, all devices of the system are connected with a network switch, no coupling relation exists between the devices, I/O data or computing results required by task processing can be acquired by any computing node of the system through a switched network, and data in the network is transmitted through a set transmission path.
8. A time deterministic distributed spacecraft electronic system design method according to claim 7, characterized in that: when each device of the system is connected with a network switch, double-machine redundancy is adopted for the device with the self-detection function, and a triple-machine redundancy form is adopted for the device without the self-detection function;
the communication between each device of the system and the network switch adopts a time triggering mode, and the occupied bandwidth and the transmission path of each node realize the static configuration of communication resources through pre-planning.
9. A time deterministic distributed spacecraft electronic system design method according to claim 1, characterized in that: the method for allocating system resources by partitions comprises the following steps: grouping application software running on a single processor according to functional coupling, ensuring mutual independence of the grouped application software in time and space through scheduling arrangement, realizing a partition scheduling processing function, wherein the starting time of each partition scheduling is different relative to the starting time of a main time shaft, allocating a time window for each partition in a mode of alternate scheduling, allocating memory spaces with fixed positions and sizes for each partition, and not allowing access to the memory areas of other partitions when accessing a certain partition, so as to ensure space isolation; and establishing a mapping relation between the partitions and the computing nodes, and running a plurality of tasks in one computing resource to realize high sharing of the computing resource.
10. A time deterministic distributed spacecraft electronic system design method according to claim 1, characterized in that: the transmission mode planned based on the message priority comprises the following steps: the electronic system adopts a time triggering communication technology and comprises time triggering messages, rate limiting messages and best effort messages, wherein the time triggering messages with the highest transmission priority are the next highest, the rate limiting messages are the next lowest, and the best effort messages are the lowest; for messages with time certainty requirement and low real-time requirement, rate limiting messages are adopted for communication; for messages with the lowest priority and uncertain transmission delay, best-effort messages are used for communication.
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