Double-bus-based attitude and orbit control system construction method and system

Abstract

The invention provides an attitude and orbit control system construction method and system based on double buses. The attitude and orbit control system construction method comprises the steps that an attitude and orbit control system uses a 1553B bus and a CAN bus at the same time for communication; the CAN bus is used for information interaction in the attitude and orbit control system single machine; the 1553B bus is used for information interaction between a power supply controller of the attitude and orbit control system and a platform; according to the attitude and orbit control system, a unified power supply controller is adopted to supply power to each single machine in the system, and meanwhile analog quantity acquisition of a rear-end single machine is carried out. According to the method, the design complexity of an existing attitude and orbit control subsystem can be remarkably reduced, generalization and integration of the system are achieved, plug and play of an attitude and orbit control single machine is supported, high-concentration independence of an attitude and orbit control system is achieved, and the reliability and economical efficiency of satellite platform design are improved.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite attitude and orbit control system control, and in particular to a dual-bus-based attitude and orbit control system construction method and system. Background Art

[0002] As satellite development and production cycles continue to shrink, satellite platforms are increasingly becoming lightweight and reusable. This places demands on all satellite platform systems for highly reliable development, reusable design, and short production cycles. The attitude and orbit control system (AOC) is primarily responsible for measuring and controlling the satellite's attitude and orbit, and is crucial for its normal on-orbit operation. A universal dual-bus design for the AOC system can effectively reduce its design cycle and complexity. It eliminates the need for redesign for system upgrades and standalone expansion, supports plug-and-play standalone systems, and enables design reuse across satellite AOC systems. Therefore, a dual-bus design for satellite AOC systems is crucial for improving their design efficiency and reliability.

[0003] In the field of satellite attitude and orbit control design, according to the retrieved patents, researchers in this field have proposed a variety of methods for satellite information system design or power bus design.

[0004] Patent document CN116737649A discloses a multi-layer redundant reconfigurable computing system and implementation method for commercial spacecraft. The system uses a bus to realize communication between attitude and orbit control and onboard data packets and task allocation units, namely the satellite service software. However, the communication between individual machines within the attitude and orbit control system and the communication between the attitude and orbit control system and the entire satellite platform still adopts the traditional point-to-point design, which lacks flexibility and versatility.

[0005] Patent document CN112214902A discloses a real-time simulation system for satellite attitude and orbit control and single-machine communication. The single-machine data communication module uses the CAN bus to communicate with the attitude and orbit control unit on the satellite, and can select a single-machine communication protocol for simulation, but does not consider the communication between the attitude and orbit control system and the entire satellite platform.

[0006] Patent document CN111891398A discloses a flexible and universal intelligent satellite hardware architecture, proposing to divide the onboard bus into a data bus, a basic configuration bus, and a control bus. The attitude and orbit control application software is connected to the basic configuration bus, while the execution-type stand-alone machine and the sensor-type stand-alone machine are connected to all three buses. Although the attitude and orbit control stand-alone machines are classified and connected to different types of buses as needed, it does not take into account that the attitude and orbit control system is a relatively independent system and does not require each stand-alone machine to be connected to the bus. It can relatively independently reduce the coupling between the system and the entire satellite platform and improve reliability.

[0007] Patent document CN110040263A discloses a micro-satellite information system based on the CAN bus. The various components on the satellite are connected through the CAN bus. At the same time, an on-board attitude and orbit control computer is set up to communicate with other attitude and orbit control units and provide power supply. The communication method between the attitude and orbit control computer and other attitude and orbit control units still adopts RS422 communication. The internal communication of the attitude and orbit control system is still point-to-point communication, which does not take advantage of the convenience and sensitivity of the bus.

[0008] Patent document CN207396994U discloses a satellite integrated controller that integrates the attitude and orbit control computer with the satellite service computer, that is, the attitude and orbit control application software and the satellite service software are integrated into the same hardware computer, communicating directly internally and externally connected to other attitude and orbit control units such as star sensors and flywheels. All attitude and orbit control units are directly connected to the integrated electronic computer in a point-to-point connection, which has a complex design and greatly reduced reliability. There is a hidden danger that the failure of a single unit will affect the safety of the entire satellite.

[0009] Therefore, the market needs a universal, integrated attitude and orbit control system design that combines the sensitivity of a bus and relies on two types of buses to ensure on-board reliability. Summary of the Invention

[0010] In view of the defects in the prior art, the purpose of the present invention is to provide a method and system for constructing an attitude and orbit control system based on a dual bus.

[0011] According to the present invention, a method for constructing an attitude and orbit control system based on a dual bus is provided, comprising: the attitude and orbit control system uses a 1553B bus and a CAN bus for communication at the same time;

[0012] The CAN bus is used for information exchange within the attitude and orbit control system.

[0013] The 1553B bus is used for information exchange between the power controller of the attitude and orbit control system and the platform;

[0014] The attitude and orbit control system uses a unified power supply controller to power each unit in the system and collect analog quantities of the back-end units at the same time;

[0015] The integrated electronic computer serves as the BC end (bus controller) of the CAN bus and the 1553B bus.

[0016] Preferably, the CAN bus is managed by attitude and orbit control application software running in a comprehensive electronic computer, and the RT end (bus remote terminal) includes a star sensor, a high-precision gyroscope, a reaction flywheel, and a moment gyroscope;

[0017] The attitude and orbit control application software receives attitude data from star sensors and high-precision gyroscopes, sends command data to reaction flywheels and moment gyroscopes, and realizes on-board attitude measurement and control.

[0018] Preferably, the CAN bus adopts a dual-bus backup connection mode. During data transmission, the BC end adopts a dual-bus transmission and reception, and the RT end adopts a default bus to transmit and receive data except for multicast and RT end interactive transmission.

[0019] Preferably, the CAN dual filter for the extended frame is provided with a first filter and a second filter, wherein each filter has an acceptance code and a shielding code respectively;

[0020] For the BC side, turn off the filter setting and monitor all communication data;

[0021] For the RT side, a dual filter setting is adopted during power-on / reset. The first filter is used to receive its own nID (communication identification code) data, and the second filter is used to receive broadcast or multicast data.

[0022] For the RT end that needs to receive multicast information, the second filter needs to be set according to demand to be able to receive broadcast data and multicast data at the same time.

[0023] Preferably, the transmission types used by the attitude and orbit control system in the CAN bus include remote control transmission, system command transmission, vector word transmission, and broadcast transmission;

[0024] Preferably, the 1553B bus is managed by the satellite service software running in the integrated electronic computer. The attitude and orbit control system stand-alone unit included in the RT end only has a power controller. The power controller collects the telemetry current, magnetic torquer current, power supply unit voltage and the stand-alone state information and packages them into a fast telemetry package format and sends them to the attitude and orbit control application software on the BC end. After obtaining the data, the attitude and orbit control application software performs real-time attitude solution and then sends it to the satellite service software through the soft bus. The satellite service software uniformly organizes and manages the attitude and orbit control control command information to the RT end through the 1553B bus.

[0025] Preferably, the 1553B bus adopts a dual-bus backup connection mode. During the data transmission process, for the data transmission process initiated by the 1553B bus controller BC end, a direct update data transmission mechanism is adopted, and the BC end organizes the bus data transmission;

[0026] For the data transmission process required by the remote terminal RT, a service request mechanism is used.

[0027] Preferably, the attitude and orbit control application software and the satellite service software run together on the integrated electronic computer on board the satellite. The satellite orbit, attitude and other information are transmitted from the attitude and orbit control application software to the satellite service software through the soft bus. The satellite service software then broadcasts the data of the attitude and orbit control system on the 1553B bus for use by the entire satellite.

[0028] Preferably, the attitude and orbit control broadcast data of the CAN and 1553B buses are unified, and the broadcast data information includes the current working mode of the satellite, satellite attitude, satellite orbit valid flag, satellite orbit recursive data, satellite time energy information, and satellite positioning and orbit determination data.

[0029] According to the present invention, a dual-bus-based attitude and orbit control system construction system is provided, comprising: the attitude and orbit control system uses a 1553B bus and a CAN bus for communication at the same time;

[0030] The CAN bus is used for information exchange within the attitude and orbit control system.

[0031] The 1553B bus is used for information exchange between the power controller of the attitude and orbit control system and the platform;

[0032] The attitude and orbit control system uses a unified power supply controller to power each unit in the system and collect analog quantities of the back-end units at the same time;

[0033] The BC ends of the CAN bus and the 1553B bus are integrated electronic computers.

[0034] Compared with the prior art, the present invention has the following beneficial effects:

[0035] 1. The present invention universalizes the 1553B bus protocol and CAN bus protocol of the attitude and orbit control system, unifies the dual-bus attitude and orbit control broadcast data, and uses them for high-reliability management of onboard attitude and orbit control. This can be reused in subsequent attitude and orbit control system bus designs, effectively improving the design efficiency of the attitude and orbit control system.

[0036] 2. The present invention adopts a centralized star network topology for power supply and analog quantity acquisition, and uses a power supply controller to uniformly provide power supply and analog quantity acquisition for the attitude and orbit control unit, which is isolated from the high-power bus on the satellite, ensuring the relative independence and safety of the attitude and orbit control system.

[0037] 3. The present invention adopts two buses to design the attitude and orbit control subsystem, realizing information interaction within the attitude and orbit control system and information interaction between the system and the platform respectively. On the one hand, it ensures the real-time interaction of attitude and orbit control information, and on the other hand, it ensures the relative independence of the attitude and orbit control system, thereby improving the reliability of the entire satellite. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following drawings:

[0039] Figure 1 Schematic diagram of the dual-bus establishment method of the attitude and orbit control subsystem of the present invention;

[0040] Figure 2 This is a schematic diagram of the CAN bus multi-node transmission process of the present invention;

[0041] Figure 3 This is a schematic diagram of the 1553B bus information transmission process of the present invention. DETAILED DESCRIPTION

[0042] The present invention will be described in detail below with reference to specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those skilled in the art, several changes and improvements can be made without departing from the scope of the present invention. These all fall within the scope of protection of the present invention.

[0043] Traditional attitude and orbit control systems require customized communication, power supply, and data acquisition interfaces designed based on the individual attitude and orbit control units onboard. These point-to-point connections are complex and require redesign for system upgrades and unit expansion. This invention, with its universal and integrated features, can significantly reduce the complexity of existing attitude and orbit control subsystem designs, enabling plug-and-play integration of individual attitude and orbit control units, achieving a highly centralized and independent attitude and orbit control system, and improving the reliability and cost-effectiveness of satellite platform design.

[0044] Example 1

[0045] According to the present invention, a method for constructing an attitude and orbit control system based on a dual bus is provided. Figure 1 As shown, the attitude and orbit control system uses the 1553B bus and the CAN bus for communication at the same time, wherein the CAN bus is used for information exchange within the attitude and orbit control system unit, and the 1553B bus is used for information exchange between the attitude and orbit control system power controller and the platform. The attitude and orbit control system uses a unified power controller to power each unit in the system and simultaneously collects analog quantities from the back-end units. The BC ends of the CAN bus and the 1553B bus are integrated electronic computers. This dual-bus architecture significantly reduces the complexity of existing attitude and orbit control system designs, realizes its universality and integration, supports plug-and-play of attitude and orbit control units, realizes the highly centralized independence of the attitude and orbit control system, and improves the reliability and economy of satellite platform design.

[0046] The CAN bus serves as the internal information exchange bus of the attitude and orbit control system, and is managed by the attitude and orbit control application software running in the integrated electronic computer. The RT end includes star sensors, high-precision gyroscopes, reaction flywheels, moment gyroscopes, etc. The attitude and orbit control application software receives attitude data from star sensors and high-precision gyroscopes, and sends command data to the reaction flywheels and moment gyroscopes to realize the measurement and control of on-board attitude.

[0047] The CAN bus utilizes a dual-bus backup connection. During data transmission, the BC uses the dual bus for transmission and reception, while the RT uses the default bus (A bus) for all data except multicast and RT-to-RT interaction. The CAN bus transmission types used by the attitude and orbit control system include remote control transmission, system command transmission, vector word transmission, and broadcast transmission. In particular, the RT is forced to use the following three commands during system command transmission: CAN controller reset, RT default use of the A bus, and RT default use of the B bus. For extended frames, the CAN dual filter configuration consists of a first filter and a second filter, each with an acceptance code and a mask code. For the BC, the filter setting is disabled, allowing all communication data to be monitored. For the RT, dual filtering is used during power-up / reset: the first filter receives its own nID data, and the second filter receives broadcast or multicast data. For RTs that need to receive multicast information (ephemeris, positioning, and orbit determination data), the second filter must be configured to receive both broadcast and multicast data.

[0048] The bus communication process in the multi-node communication process of the CAN bus is as follows Figure 2 As shown, the communication process includes 1) BC-side broadcast transmission; 2) single-node vector word response bidirectional transmission communication in sequence; 3) remote control data transmission; 4) other multicast data transmission on the BC side and the RT side; 5) other data transmission organized according to the vector word bits.

[0049] Regarding vector word transmission, during the normal communication and transmission phase of the CAN bus, the BC end periodically (0.5s) queries the RT end for vector words and organizes data communication based on the vector words returned by the RT end. The definition of vector words is shown in Table 1:

[0050] Table 1 Definition of vector words

[0051] Position No. content definition b3~b15 reserve 1: data notification sent; 0: no data service request b2 Memory unloading 1: Memory unload data request sent; 0: No data service request b1 Slow transmission 1: Slow data request sent; 0: No data service request b0 Fast remote transmission 1: Fast remote data request sent; 0: No data service request

[0052] When the BC side queries the corresponding vector word, it sends the corresponding service notification and waits for the data to be returned. When the RT side receives the service notification, it sends the corresponding service data and clears the corresponding vector word bit.

[0053] The 1553B bus serves as the control bus for the entire satellite and is managed by the satellite service software running on an integrated electronic computer. The attitude and orbit control system unit included in the RT end only has a power controller. The power controller collects the thermosensitive current, magnetic torquer current, power supply unit voltage and the unit's own status information, and packages them into a fast telemetry package format and sends them to the attitude and orbit control application software on the BC end. After obtaining the data, the attitude and orbit control application software performs real-time attitude calculation and then sends it to the satellite service software through the soft bus. The satellite service software will uniformly organize and manage the attitude and orbit control control command information and send it to the RT end through the 1553B bus.

[0054] 1553B bus adopts dual bus backup connection mode. During data transmission, if Figure 3 As shown in the figure, data transfers initiated by the 1553B bus BC utilize a direct update mechanism, with the BC orchestrating bus data transfers. Data transfers requested by remote terminals (RTs) utilize a service request mechanism. Each RT responds to the BC's "Send Status Word" and "Send Vector Word" commands by returning a status word and a vector word, respectively. Each RT identifies a data transfer request using the service request bit in the bus status word and identifies the type of data being requested based on the vector word bits.

[0055] The attitude and orbit control application software and the satellite service software run together on the onboard integrated electronic computer. The satellite orbit, attitude and other information are transmitted from the attitude and orbit control application software to the satellite service software through the soft bus. The satellite service software then broadcasts the orbit, attitude and other data of the attitude and orbit control system on the 1553B bus for use by the entire satellite.

[0056] As one of the remote terminals, the attitude and rail power controller uses the following 1553B bus mode commands: Send Status Word, Start Self-Test, Send Vector Word, and Send Self-Test Word. Send Status Word requires the attitude and rail power controller to send a status word related to the last valid instruction word before executing this command. The attitude and rail power controller does not update its status word when executing this mode command. Start Self-Test initiates the attitude and rail power controller's internal self-test and returns the corresponding status word. Send Vector Word requires the attitude and rail power controller to send a status word and a data word containing service request information, allowing the bus controller to determine the attitude and rail power controller's specific service request. Send Self-Test Word requires the attitude and rail power controller to send a status word and a data word containing the self-test result, with no space between the status word and the data word. The self-test result should not be changed by executing other instructions.

[0057] The 1553B bus status word fields used by the attitude and orbit control power controller include: message error bit, service request bit, subsystem flag bit, and terminal flag bit. Service requests in the attitude and orbit control power controller's vector word include: request to send reconstructed data, request to send raw observations, request to send GNSS data, request to send memory data offload, request to send fast telemetry, request to send packed telemetry, request to send slow telemetry, and request to send working state change.

[0058] In order to enhance the reliability of bus transmission information and reduce the complexity of software writing, the attitude and orbit control broadcast data of CAN and 1553B buses are unified. The broadcast data information includes the current working mode of the satellite, satellite attitude, satellite orbit valid flag, satellite orbit recursion data, satellite time energy information, and satellite positioning and orbit determination data.

[0059] Furthermore, the integrated electronic computer in the present invention serves as the BC end of both the CAN bus and the 1553B bus. The CAN bus is managed by attitude and orbit control application software running in the integrated electronic computer. The RT end includes attitude and orbit control units such as the reaction flywheel, star sensor, and fiber optic gyroscope. The attitude and orbit control software collects telemetry data from the RT end and sends remote control commands and broadcast data. Units such as the reaction flywheel, star sensor, and fiber optic gyroscope that do not need to receive broadcast data can be shielded from broadcast data using a filter mechanism. The 1533B bus is managed by the satellite service software running in the integrated electronic computer. The RT end includes the power controller for the attitude and orbit control system and related units in other systems. The attitude and orbit control power controller uses a centralized star network topology to power the other units in the attitude and orbit control system. It also collects telemetry information returned by the analog sun sensor, 01 type sun sensor, magnetometer, and magnetorquer, packages it, and sends it to the integrated electronic computer. The information is then transmitted via the soft bus to the attitude and orbit control application software for closed-loop control.

[0060] Example 2

[0061] The present invention also provides a dual-bus-based attitude and orbit control system construction system. The dual-bus-based attitude and orbit control system construction system can be implemented by executing the process steps of the dual-bus-based attitude and orbit control system construction method. That is, those skilled in the art can understand the dual-bus-based attitude and orbit control system construction method as a preferred implementation method of the dual-bus-based attitude and orbit control system construction system.

[0062] The present invention provides a dual-bus-based attitude and orbit control system construction system, including: the attitude and orbit control system uses both a 1553B bus and a CAN bus for communication. The CAN bus is used for information exchange within individual units of the attitude and orbit control system. The 1553B bus is used for information exchange between the attitude and orbit control system's power controller and the platform. The attitude and orbit control system uses a unified power controller to power each unit within the system and simultaneously collect analog signals from the back-end units.

[0063] The CAN bus is managed by attitude and orbit control application software running on an integrated electronic computer. The RT side includes a star sensor, high-precision gyroscope, reaction flywheel, and moment gyroscope. The attitude and orbit control application software receives attitude data from the star sensor and high-precision gyroscope and sends command data to the reaction flywheel and moment gyroscope, enabling onboard attitude measurement and control. The CAN bus utilizes a dual-bus backup connection. During data transmission, the BC side uses the dual bus for transmission and reception, while the RT side uses the default bus for all data except multicast and RT-to-RT communication. For extended frames, the CAN dual filter consists of a first filter and a second filter, each with an acceptance code and a mask code. On the BC side, the filter setting is disabled, allowing all communication data to be monitored. On the RT side, dual filtering is used during power-up / reset: the first filter receives its own nID data, and the second filter receives broadcast or multicast data. For RTs that need to receive multicast information, the second filter should be configured to receive both broadcast and multicast data. The attitude and orbit control system uses the CAN bus for transmission types including remote control, system command, vector word, and broadcast.

[0064] The 1553B bus is managed by the satellite service software running on a comprehensive electronic computer. The attitude and orbit control system (ATC) unit on the remote (RT) side consists solely of a power controller. This controller collects information about the tachometer current, magnetic torquer current, power supply unit voltage, and its own status, packages it into a fast telemetry packet, and transmits it to the attitude and orbit control application software on the back-end (BC) side. The BC software then performs real-time attitude calculations and transmits these data via a soft bus to the satellite service software, which then centrally manages and sends attitude and orbit control control commands via the 1553B bus to the RT side. The 1553B bus utilizes a dual-bus backup connection. Data transfers initiated by the 1553B bus controller (BC) utilize a direct update mechanism, with the BC side managing the bus data transfers. Data transfers requested by the remote terminal (RT) utilize a service request mechanism.

[0065] The attitude and orbit control application software and the satellite service software run together on the onboard integrated electronic computer. The attitude and orbit control application software transmits information such as the satellite's orbit and attitude to the satellite service software via a soft bus. The satellite service software then broadcasts this data on the 1553B bus for use by the entire satellite. The attitude and orbit control broadcast data from the CAN and 1553B buses is unified. This broadcast data includes the satellite's current operating mode, satellite attitude, valid satellite orbit flag, satellite orbit recursion data, satellite time energy information, and satellite positioning and orbit determination data.

[0066] Those skilled in the art will appreciate that, in addition to implementing the system and its various devices, modules, and units provided by the present invention in purely computer-readable program code, it is entirely possible to implement the same functions of the system and its various devices, modules, and units provided by the present invention in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers by logically programming the method steps. Therefore, the system and its various devices, modules, and units provided by the present invention can be considered a hardware component, and the devices, modules, and units included therein for implementing various functions can also be considered as structures within the hardware component; the devices, modules, and units for implementing various functions can also be considered as both software modules implementing the method and structures within the hardware component.

[0067] The above describes specific embodiments of the present invention. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art may make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. The embodiments of this application and the features in the embodiments may be combined with each other in any manner unless there is a conflict.

Claims

1. A method for constructing an attitude and orbit control system based on a dual bus, characterized in that: include: The attitude and orbit control system uses both 1553B bus and CAN bus for communication; The CAN bus is used for information exchange within the attitude and orbit control system. The 1553B bus is used for information exchange between the power controller of the attitude and orbit control system and the platform; The attitude and orbit control system uses a unified power supply controller to power each unit in the system and collect analog quantities of the back-end units at the same time; The BC ends of the CAN bus and the 1553B bus are integrated electronic computers.

2. The method for constructing a dual-bus-based attitude and orbit control system according to claim 1, characterized in that: The CAN bus is managed by attitude and orbit control application software running in a comprehensive electronic computer, and the RT end includes a star sensor, a high-precision gyroscope, a reaction flywheel, and a moment gyroscope; The attitude and orbit control application software receives attitude data from star sensors and high-precision gyroscopes, sends command data to reaction flywheels and moment gyroscopes, and realizes on-board attitude measurement and control.

3. The method for constructing a dual-bus-based attitude and orbit control system according to claim 1, characterized in that: The CAN bus adopts a dual-bus backup connection mode. During data transmission, the BC end uses a dual bus for sending and receiving, and the RT end uses a default bus for sending and receiving data except for multicast and RT-end interactive transmission.

4. The method for constructing a dual-bus-based attitude and orbit control system according to claim 1, characterized in that: The CAN dual filter for the extended frame is provided with a first filter and a second filter, wherein each filter has an acceptance code and a masking code respectively; For the BC side, turn off the filter setting and monitor all communication data; For the RT side, dual filtering is used during power-on / reset. The first filter is used to receive its own nID data, and the second filter is used to receive broadcast or multicast data. For the RT end that needs to receive multicast information, the second filter needs to be set according to demand to be able to receive broadcast data and multicast data at the same time.

5. The method for constructing a dual-bus-based attitude and orbit control system according to claim 1, characterized in that: The transmission types used by the attitude and orbit control system in the CAN bus include remote control transmission, system command transmission, vector word transmission, and broadcast transmission.

6. The method for constructing a dual-bus-based attitude and orbit control system according to claim 1, characterized in that: The 1553B bus is managed by the satellite service software running in the integrated electronic computer. The attitude and orbit control system unit included in the RT end only has a power controller. The power controller collects the telemetry current, magnetic torquer current, power supply unit voltage and the unit's own status information, and packages them into a fast telemetry package format and sends them to the attitude and orbit control application software on the BC end. After obtaining the data, the attitude and orbit control application software performs real-time attitude calculation and then sends it to the satellite service software through the soft bus. The satellite service software uniformly organizes and manages the attitude and orbit control control command information to the RT end through the 1553B bus.

7. The method for constructing a dual-bus-based attitude and orbit control system according to claim 1, characterized in that: The 1553B bus uses a dual-bus backup connection mode. During data transmission, for the data transmission process initiated by the 1553B bus controller BC end, a direct update data transmission mechanism is adopted, and the BC end organizes bus data transmission; For the data transmission process required by the remote terminal RT, a service request mechanism is used.

8. The method for constructing a dual-bus-based attitude and orbit control system according to claim 1, characterized in that: The attitude and orbit control application software and the satellite service software run together on the integrated electronic computer on board. The satellite orbit, attitude and other information are transmitted from the attitude and orbit control application software to the satellite service software through the soft bus. The satellite service software then broadcasts the data of the attitude and orbit control system on the 1553B bus for use by the entire satellite.

9. The method for constructing a dual-bus-based attitude and orbit control system according to claim 1, characterized in that: The attitude and orbit control broadcast data of CAN and 1553B buses are unified. The broadcast data information includes the current working mode of the satellite, satellite attitude, satellite orbit valid flag, satellite orbit recursion data, satellite time energy information, and satellite positioning and orbit determination data.

10. A dual-bus-based attitude and orbit control system construction system, characterized in that: include: The attitude and orbit control system uses both 1553B bus and CAN bus for communication; The CAN bus is used for information exchange within the attitude and orbit control system. The 1553B bus is used for information exchange between the power controller of the attitude and orbit control system and the platform; The attitude and orbit control system uses a unified power supply controller to power each unit in the system and collect analog quantities of the back-end units at the same time; The BC ends of the CAN bus and the 1553B bus are integrated electronic computers.

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