CN110002005B - A reconfigurable micro-nano satellite system architecture and satellite system reconstruction method - Google Patents

Abstract

The embodiment of the present invention discloses a reconfigurable micro-nano satellite system architecture and a satellite system reconstruction method; the reconfigurable micro-nano satellite system includes: a general module, including a plurality of modules to achieve all functional requirements of the satellite system A common module that needs to be used; special modules, including a plurality of special modules corresponding to the single function requirements of the satellite system and only required to realize the corresponding single function requirements; standardized bus, used to connect the general module The shared modules in and the dedicated modules in the dedicated modules.

Description

A reconfigurable micro-nano satellite system architecture and satellite system reconstruction method

technical field

The invention relates to the field of aerospace technology, in particular to a reconfigurable micro-nano satellite system architecture and a satellite system reconstruction method.

Background technique

With the diversified development of satellite functions, satellites carry more and more functions. In the field of traditional satellite design, a specific system in the satellite only undertakes a predefined function. If the system corresponding to a specific function is damaged, the entire satellite will lose this function. Although the reliability of the satellite can be improved by adding redundant backups to the satellite, for each functional system in the satellite, a corresponding backup system needs to be added accordingly, which increases the design complexity of the satellite system and increases the overall The volume mass of the satellite increases the cost of satellite manufacturing. In addition, to improve the reliability of satellites by means of function backup, additional support from ground supporting equipment is required. Therefore, it is necessary to upgrade the existing ground station equipment, which increases the complexity of the system.

In order to avoid the above situation, there have been satellite systems that reconstruct some functions within a specific functional range. That is to say, for several systems with similar functions, by adding a small number of functional modules, each system can be By injecting the software of the corresponding function, it can realize one of several functions. For the star service computer, the program can switch between functions such as star service management, attitude and orbit control calculation, and simple processing of payload data by adding software on-orbit modification functions. The limited function backup cannot realize the backup function for different loads. For example, the function backup of the signal processor of the measurement and control system cannot be realized. It is not helpful to improve the overall reliability of the satellite system. It is still necessary to increase the corresponding function backup.

A cold backup switching method of a homogeneous star service system that has appeared at present can control the switching of two sets of cold backup state star service computers through an external control circuit, and save the current state through the external control circuit. This method not only requires two sets of computers and peripheral supporting circuits, but also needs to increase the external control circuit, thereby increasing the complexity of the system and the possible failure points.

For micro-nano satellites, due to the small size of the satellite and the very limited energy and space inside the satellite, there is usually no space to add additional backup systems, which greatly reduces the reliability of the satellite. Based on this, it can only pass the test at the time of manufacture. Screening is used to ensure reliability, which results in that satellite life is usually short, and it is difficult to meet the requirements of long life and high reliability.

SUMMARY OF THE INVENTION

In view of this, the embodiments of the present invention are expected to provide a reconfigurable micro-nano satellite system architecture and a satellite system reconstruction method, which can not only improve the reliability of the satellite system, but also reduce the backup circuits and devices required for reconstruction The number of satellites saves space and reduces the energy requirements of satellites.

The technical scheme of the present invention is realized as follows:

In a first aspect, an embodiment of the present invention provides a reconfigurable micro-nano satellite system, where the satellite system includes:

A general module, including a plurality of shared modules required to realize all functional requirements of the satellite system;

Special modules, including a plurality of special modules corresponding to the single function requirements of the satellite system and only required to realize the corresponding single function requirements;

The standardized bus is used to connect the common module in the general module and the special module in the special module.

In a second aspect, an embodiment of the present invention provides a satellite system reconstruction method. The method is applied to the satellite system described in the first aspect, and the method includes:

Each computing processing module in the general module injects different functional requirements on the rail through software, so that each computing processing module controls the dedicated module corresponding to the functional requirements injected by itself;

When the first calculation and processing module fails, the first calculation and processing module is turned off, and a second calculation and processing module is determined from other calculation and processing modules except the first calculation and processing module;

Modify the special module corresponding to the second calculation processing module by means of software annotation; wherein, the special module corresponding to the second calculation processing module after modification includes the special module corresponding to the second calculation processing module before the modification and the first calculation processing module. The special module corresponding to the calculation processing module before the failure.

The embodiments of the present invention provide a reconfigurable micro-nano satellite system architecture and a satellite system reconstruction method; in the traditional satellite system, common modules that can be used for all functional requirements are formed into a general module, and only a certain A dedicated module used for a single functional requirement forms a dedicated module. Compared with the traditional satellite system, when the functional requirements of the satellite system are realized, the coupling between the general module and the special module is reduced, and in the process of improving the reliability of the satellite system, only the general module or special module is required. The components in the module are backed up, and the granularity of reliability backup is reduced from the system level to the component level, which reduces the system complexity for realizing the functional requirements of the satellite system, reduces the waste of resources of the satellite system, reduces the power consumption and the quality of the satellite system. .

Description of drawings

1 is a schematic diagram of the architecture of a satellite platform in an existing satellite system;

2 is a schematic diagram of the architecture of a reconfigurable micro-nano satellite system proposed by an embodiment of the present invention;

3 is a schematic diagram of the composition of a general module proposed in an embodiment of the present invention;

4 is a schematic diagram of the composition of a standardized bus proposed in an embodiment of the present invention;

FIG. 5 is a schematic diagram of the composition of a computing processing module proposed by an embodiment of the present invention;

6 is a schematic diagram of the composition of a special module proposed by an embodiment of the present invention;

7 is a schematic diagram of the composition of a star sensor proposed in an embodiment of the present invention;

8A is a schematic diagram of the composition of a data transmission and distribution system proposed by an embodiment of the present invention;

FIG. 8B is a schematic diagram of the composition of a camera subsystem according to an embodiment of the present invention;

8C is a schematic diagram of the composition of a storage subsystem proposed by an embodiment of the present invention;

9 is a schematic flowchart of a method for reconstructing a satellite system proposed by an embodiment of the present invention;

FIG. 10 is a schematic diagram of a satellite system architecture according to an embodiment of the present invention.

Detailed ways

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.

For a complete satellite system, it can include a satellite platform and a satellite payload, and the satellite payload is carried on the satellite platform. Referring to FIG. 1, it shows a schematic diagram of the architecture of a satellite platform in an existing satellite system. In the current existing satellite system, a plurality of subsystems are included. Taking the architecture shown in FIG. 1 as an example, the satellite system 1 may include The measurement and control subsystem 11 , the integrated electronic subsystem 12 , the attitude and flight trajectory control (hereinafter referred to as the attitude and trajectory control) subsystem 13 and the power supply and distribution subsystem 14 . Each subsystem includes the following components: CPU, communication interface circuit, and power supply interface circuit. The internal communication of the satellite system is realized between the sub-systems through the system communication bus 15, and the power supply and distribution sub-system 14 supplies power to the power supply circuit interfaces of the remaining sub-systems through the system power distribution bus 16, thereby providing electrical energy for the functions of the remaining sub-systems. As can be seen from Figure 1, in the satellite system architecture, each sub-system is tightly coupled, and the CPUs of each sub-system are independent of each other, that is, the CPU of each system is only responsible for implementing the functions of its own system. For example, the integrated electronic CPU in the integrated electronic sub-system 12 is responsible for the whole satellite telemetry acquisition and forwarding, remote control reception and execution, attitude and orbit control calculation and other functions; The power control CPU in the power sub-system 14 realizes functions such as state acquisition and monitoring, windsurfing shunt control, battery charging control, voltage conversion and power distribution control. In addition, each subsystem requires an independent CPU and supporting peripheral circuits (such as power supply interface circuit and communication interface circuit). To improve reliability, it can only be achieved through subsystem-level backup, that is, in the process of backing up a subsystem, all components in the subsystem need to be backed up. Usually, each subsystem will have a set of backup subsystems, so that the entire satellite platform system needs 5 to 6 sets of CPUs and corresponding peripheral circuits. In addition, if it is necessary to further improve the reliability, it can only be achieved by adding sub-system-level backup, which further increases the waste of resources and is not conducive to the optimization of the weight, power consumption and volume of the satellite system.

For the architecture of Figure 1, it should be noted that the computing power of the CPU usually has a large redundancy, and the capacity of the supporting peripheral circuits also has a large margin, but the architecture shown in Figure 1 limits each The CPU can only realize the functions of the system in which it is located, and the excess computing power and peripheral circuit capabilities cannot be used to realize the functions of other subsystems, nor can they be used for backup purposes.

In the face of the above problems, based on the CPU's ability to realize function reconfiguration through software programming and the relatively simple functions of the power supply interface circuit and the communication interface circuit, which can be used in different systems, the embodiment of the present invention proposes a method that can The reconfigured micro/nano satellite system architecture, see FIG. 2, which shows that the reconfigurable micro/nano satellite system 2 architecture may include:

The general module 21 includes a plurality of shared modules required to realize all functional requirements of the satellite system 2;

The dedicated module 22 includes a plurality of dedicated modules corresponding to the single functional requirements of the satellite system 2 and only required to realize the corresponding single functional requirements;

The standardized bus 23 is used to connect the common module in the general module 21 and the special module in the special module 22 .

Through the micro-nano satellite system 2 provided in FIG. 2, a common module 21 that can be used for all functional requirements in the traditional satellite system, including satellite platforms and satellite loads, is formed into a general module 21, which will only be used for a single functional requirement. The dedicated modules form dedicated modules 22 . Compared with the traditional satellite system, when the functional requirements of the satellite system are realized, the coupling degree between the general module 21 and the special module 22 is reduced, and in the process of improving the reliability of the satellite system, only the general module is required. 21 or the components in the special module 22 are backed up, and the granularity of reliability backup is reduced from the system level to the component level, which reduces the system complexity of realizing the functional requirements of the satellite system, reduces the waste of resources of the satellite system, reduces power consumption and quality of the satellite system.

For the satellite system shown in FIG. 2, in a possible implementation manner, referring to FIG. 3, the types of the general module 21 include: a computing processing module 211 and an interface expansion module 212; wherein,

The calculation processing module 211 is configured to perform data calculation, signal processing and generation of control instructions according to various functional requirements of the satellite system 2; , measurement and control, navigation, data transmission and power management capabilities, and can also perform signal processing on the acquired signals;

The interface expansion module 212 is configured to convert the non-standard interfaces in the general module 21 and the special module 22 into standardized interfaces;

Referring to FIG. 4 , the standardized bus 23 includes a standardized module communication bus 231 and a standardized power distribution bus 232 .

For this implementation, preferably, referring to FIG. 5 , the computing processing module 211 may include a general-purpose CPU 2111 and a CPU interface circuit 2112; wherein,

The general-purpose CPU 2111 can be specifically configured for the collection and forwarding of telemetry data of the whole satellite, the reception and execution of ground remote control commands, and the calculation of attitude and flight trajectory;

And, receiving payload signals and processing payload signals, including satellite management, attitude and orbit control, measurement and control, navigation and data transmission;

And the modulation and demodulation processing of radio frequency signals;

As well as the collection and detection of power supply and distribution status, windsurfing shunt control, battery charging control, voltage conversion, and power distribution control;

The CPU interface circuit 2112 is configured to receive data and signals sent by the dedicated module 22 through the standardized module communication bus;

and sending corresponding control instructions to the dedicated module 22 through the standardized module communication bus.

With respect to the general-purpose CPU 2111 described above, during specific implementation, each general-purpose CPU 2111 can access all the special-purpose modules 22; each general-purpose CPU 2111 injects different functional requirements on the rail through software, so that each general-purpose CPU 2111 can Controls the dedicated modules corresponding to the functional requirements injected by itself; each general-purpose CPU 2111 can be turned off.

It is understandable that, in the traditional satellite architecture, the software configuration inside the satellite is implemented by the CPU of each sub-system. Generally speaking, one CPU is accompanied by at least one software configuration item. By reducing the total number of CPUs in the satellite system, repeated software configuration items can be reduced. For example, in the traditional satellite architecture, both the platform and the payload have temperature, voltage and current acquisition software for temperature control and status monitoring. However, with the satellite system proposed in the embodiment of the present invention, the internal software configuration is implemented by a general-purpose CPU, that is, the general-purpose CPU is used to simultaneously collect telemetry parameters such as the temperature, voltage and current of the platform and the load, thereby reducing the number of satellite systems. Software configuration items to simplify program complexity.

It should be noted that the above-mentioned general-purpose CPU is a general term for devices with logic control functions, which may include CPU (Central Processing Unit), DSP (Digital Signal Processor), FPGA (Field Programmable Logic Gate Array), and other programmable logic gate arrays. A device, module or system that realizes functions such as control, operation, and processing.

It should be noted that, for a single functional requirement, the computing power of each general-purpose CPU 2111 is redundant. Therefore, each general-purpose CPU 2111 can be made to control a plurality of dedicated modules correspondingly, thereby saving the number of general-purpose CPUs 2111 to set. Therefore, the number of peripheral circuits required by the general-purpose CPU 2111 is reduced, thereby reducing the resource consumption of the satellite system, saving the satellite space, and reducing the quality of the satellite system. Under normal working conditions, each general-purpose CPU 2111 is only responsible for its own corresponding dedicated module. When a general-purpose CPU 2111 fails, the general-purpose CPU 2111 in failure is turned off, and a non-faulty general-purpose CPU 2111 is turned off by means of software modification. While the general-purpose CPU 2111 is responsible for its own corresponding special-purpose module, it is also responsible for the corresponding special-purpose module that the faulty general-purpose CPU 2111 is responsible for. The specific method of selecting a non-faulty general-purpose CPU 2111 can obtain the remaining computing power of all the non-faulty general-purpose CPUs 2111 when they are responsible for their corresponding dedicated modules, and select the non-faulty general-purpose CPU 2111 with the most remaining computing power to be additionally responsible for the faulty general-purpose CPU 2111. The corresponding special-purpose module that the general-purpose CPU 2111 is responsible for. Therefore, in the event of a failure, there is no need to perform system-level backup, and the reliability of the satellite system can be improved only through switching and backup between components such as a general-purpose CPU.

Further, both the calculation processing module 211 and the dedicated module are connected to the standardized bus through a bus isolator, so that when the calculation processing module 211 or the dedicated module is closed due to a fault, the closed calculation processing module 211 or special modules do not affect the normal communication of the standardized bus.

For the satellite system shown in FIG. 2, in a possible implementation manner, in the standardized bus, the standardized module communication bus has a backup communication bus, the common module in the general module and the dedicated communication bus The dedicated modules in the module are connected with the standardized module communication bus and the backup communication bus through independent interface circuits respectively;

When the standardized module communication bus fails, the common module in the general module and the special module in the special module are switched to the backup communication bus for communication; or, the special module in the The dedicated module receives the selection instruction transmitted by the computing processing module, and selects the standardized module communication bus or the backup communication bus for communication based on the instruction of the selection instruction.

Understandably, in order to improve communication reliability, the standardized module communication bus can be designed as a backup. At this time, each shared module or dedicated module can provide two mutually independent communication bus interfaces, which are respectively connected to two mutually backup communication bus interfaces. Standardized module communication bus, two mutually backup communication buses have the same function, and each standardized module communication bus can fully realize the communication function between modules. Therefore, when there is a problem with one standardized module communication bus, either the shared module or the dedicated module can automatically switch to another standardized module communication bus to realize the communication work, or after receiving the selection instruction sent by the computing unit module, based on the The indication of the selection command selects the standardized modular communication bus used to implement the communication function.

For the satellite system shown in FIG. 2 , in a possible implementation manner, referring to FIG. 6 , the types of the dedicated modules 22 include a measurement and control function module 221 , a power supply and distribution module 222 , an attitude and orbit control module 223 and a load function module 224;

The measurement and control function module 221 is configured to, after receiving the remote control signal through the antenna, decode the received remote control signal through baseband to obtain a remote control command, and send the remote control command to the calculation processing module 211;

And, receive the telemetry data transmitted by the calculation processing module 211 through the standardized module communication bus 231, synthesize the telemetry data into a telemetry signal through the baseband, and transmit the telemetry signal to the outside through the antenna;

The power supply and distribution module 222 is configured to transmit the working state of the power supply assembly to the calculation processing module through the standardized module communication bus 231;

And, receive the control command transmitted by the computing processing module 211 through the standardized module communication bus 231, and execute the instruction of the control command;

and, providing power to the common module and the dedicated module through the standardized power distribution bus 232;

The attitude and orbit control module 223 is configured to collect the attitude and flight orbit parameters of the satellite system, and transmit the parameters to the calculation processing module 211 through the standardized module communication bus 231;

The load function module 224 is configured to implement the corresponding satellite load function through the control command transmitted by the calculation processing module 211 .

For the above four special modules, in a specific implementation process, the measurement and control function module 221 includes an antenna, a measurement and control radio frequency device, a measurement and control baseband, and a measurement and control interface circuit. Therefore, the function of the above-mentioned measurement and control function module 211 can be specifically described as: after the measurement and control radio frequency device receives the remote control signal through the antenna, the measurement and control baseband decodes the received remote control signal through the baseband to obtain a remote control command, and the measurement and control interface circuit decodes the remote control command. Send to the calculation processing module 211 through the standardized module communication bus 231; and the measurement and control interface circuit receives the telemetry data transmitted by the calculation processing module 211 through the standardized module communication bus 231, The data is synthesized into a telemetry signal, and the measurement and control radio frequency device transmits the telemetry signal to the outside through an antenna.

The power supply and distribution module 222 includes a shunt, a charge controller and a standardized voltage regulation and power distribution unit. Therefore, the function of the above-mentioned power supply and distribution module 222 can be specifically described as: transmitting the working state of the power supply assembly to the computing processing module through the standardized module communication bus 231 ; and receiving through the standardized module communication bus 231 The control command transmitted by the calculation processing module 211, the shunt, the charging controller and the standardized voltage regulation unit execute the instruction of the control command; Dedicated modules provide power. In detail, the power supply component may include a photovoltaic module, such as a solar panel. After the photovoltaic module converts light energy into electrical energy, it is transmitted to a charge controller through a shunt, and the battery is supplied with power through the charge controller.

The attitude and orbit control module 223 includes a flywheel, a star sensor, a gyroscope and a magnetic torquer. Its function can be specifically described as: collecting the attitude and flight orbit parameters of the satellite system 2 through the flywheel, star sensor, gyroscope and magnetic torque device, and transmitting the parameters to the calculation processing module 211 .

In the traditional satellite system, since the attitude and orbit control components such as star sensors, gyroscopes, and flywheels all include CPU, interface circuit, power supply circuit and corresponding special modules, such as motors, image sensors, etc., for the implementation of the present invention In the example, the attitude and orbit control components can also be divided into general components and proprietary components, so that common circuit components such as CPU, interface circuit, power supply circuit, etc. are shared between the satellite platform and the single payload, so as to achieve full system reconfiguration. The satellite architecture greatly reduces the number of components and circuit complexity on the satellite without reducing reliability. Taking the star sensor as an example, Fig. 7 is a schematic diagram of the internal circuit function modules of the star sensor in the traditional satellite system, including an image sensor, a CPU, an interface circuit, a power supply circuit, and the like. By designing the common components in the star sensor as a general module, only the internal image sensor and interface circuit of the star sensor are retained, and the functions of the CPU and power supply circuit are replaced by the common module in the general module, thereby reducing the number of The circuit complexity of the star sensor.

The load function module 224 corresponds to the satellite load carried on the satellite platform. In the traditional satellite system, the satellite load also has circuit function modules similar to those of the subsystems in the traditional satellite platform. In the satellite platform, the specific satellite payload may include a data transmission sub-system, a camera sub-system and a storage sub-system. Taking the data transmission sub-system as an example, as shown in FIG. 8A , a traditional data transmission sub-system may include a broadband radio frequency channel, a data transmission radio frequency baseband, a CPU, an FPGA for signal processing, an interface circuit, and a power supply circuit. In this embodiment, the CPU, the interface circuit, and the power supply circuit are separated from the system into a common module, and the digital radio frequency baseband interface is converted into a standardized interface through the FPGA, and the signal processing, modulation and demodulation functions are completed in the FPGA. Therefore, in the load function module 224, the data transmission module is used to implement the corresponding load function of the data transmission sub-system, and the data transmission module may include a broadband radio frequency channel, a data transmission radio frequency baseband and an interface circuit. Taking a camera subsystem as an example, referring to FIG. 8B , a traditional camera subsystem may include a lens assembly, an image sensor, a CPU, an FPGA for signal processing, an interface circuit, and a power supply circuit. In this embodiment, the CPU, the interface circuit, and the power supply circuit are also separated from the system into a shared module, and the digital radio frequency baseband interface is converted into a standardized interface through the FPGA, and signal processing, modulation and demodulation are completed in the FPGA. Therefore, in the payload function module 224, the camera module is used to implement the payload function corresponding to the camera subsystem, and the camera module may include a lens assembly, an image sensor and an interface circuit. Taking the storage subsystem as an example, referring to FIG. 8C , a traditional storage subsystem includes a flash memory array, a CPU, an FPGA for signal processing, an interface circuit, a power supply circuit, and the like. Also for the storage subsystem, according to the shared module separation process performed by the data transmission module and the camera module, in the load function module 224, a storage module is obtained to realize the load function corresponding to the camera subsystem, and the storage module A flash memory array and interface circuitry may be included. After the satellite payload subsystem is separated from the shared modules according to the above scheme, the circuit complexity of the payload function module can be reduced, thereby reducing the quality and power consumption of the satellite payload subsystem.

In addition, since the amount of communication data between the payload subsystems is usually large, in order to avoid the influence of the amount of communication data between the satellite payloads on the communication of the satellite platform, preferably, the standardized bus further includes a standardized high-speed communication bus. In order to transmit the payload data between the payload function modules;

Correspondingly, the interface circuits in the data transmission module, the camera module and the storage module include a high-speed communication interface circuit and a low-speed communication interface circuit; wherein, the high-speed communication interface circuit is connected with the standardized high-speed communication bus, and the low-speed communication interface circuit is connected to the standard high-speed communication bus. A communication interface circuit is connected to the standardized modular communication bus.

It should be noted that a standardized high-speed communication bus is added between the satellite payload function modules to realize communication between different satellite payloads. Therefore, the satellite payload function module has both a standardized modular communication bus and a standardized high-speed communication bus. The standardized modular communication bus is used to transmit control data and telemetry data, and the standardized high-speed communication bus is used to transmit payload data. Correspondingly, in various satellite load function modules, the communication interface circuit can also be correspondingly divided into a high-speed communication interface circuit and a low-speed communication interface circuit; the high-speed communication interface circuit is connected with the standardized high-speed communication bus, and the low-speed communication interface circuit is The communication interface circuit is connected with the standardized module communication bus, so as to avoid the mutual influence between high and low speed data.

For the above four special modules, through the joint design of the satellite platform and the satellite load, the common module of the satellite platform and the satellite load is universally designed, which can minimize the use of satellites without affecting the function and reliability. The number of components reduces the overall design complexity of the satellite.

For the above four special modules, in the specific implementation process, each special module may include a backup special module correspondingly. Therefore, when a certain special module in a certain special module fails, the fault special module can be turned off, and the function of the fault special module can be switched to the backup special module. It should be noted that since the backup between the dedicated modules does not involve the shared modules, the coupling between the dedicated modules and the shared modules is reduced, a low-cost and low-complexity method for improving reliability can be provided, and an all-satellite system can be realized. Reconfigurable satellite architecture.

Through the above technical solutions, it can be seen that when a certain functional requirement fails, there is no need to perform backup switching for all components that meet the functional requirement of the fault, but only the shared module or dedicated module needs to be switched, thereby reducing the circuit complexity of the system. It reduces the waste of resources and improves the utilization rate of resources.

Based on the same inventive concept as the foregoing technical solutions, see FIG. 9 , which shows a method for reconstructing a satellite system provided by an embodiment of the present invention. The method can be applied to the satellite system described in any of the foregoing technical solutions. The methods described include:

S901: Each computing processing module in the general module injects different functional requirements on the rail through software, so that each computing processing module controls a dedicated module corresponding to the functional requirements injected by itself;

S902: when the first computing and processing module fails, turn off the first computing and processing module, and determine a second computing and processing module from other computing and processing modules except the first computing and processing module;

S903: Modify the special module corresponding to the second calculation processing module by means of software annotation; wherein, the special module corresponding to the second calculation processing module after modification includes the special module corresponding to the second calculation processing module before modification and the special module corresponding to the second calculation processing module before modification. A dedicated module corresponding to the first calculation processing module before the failure.

For the technical solution shown in FIG. 9 , in a possible implementation manner, the method may further include: in a dedicated module, when a dedicated module in a dedicated module fails, shutting down the faulty dedicated module , and replace the faulty dedicated module with the backup dedicated module in this type of dedicated module.

For the technical solution shown in FIG. 9 , in a possible implementation manner, both the computing processing module and the dedicated module are connected to the standardized bus through a bus isolator, so that the computing processing module or the dedicated module can be shut down due to a fault At the time, the closed computing processing module or special-purpose module does not affect the normal communication of the standardized bus.

The following specific examples are provided in conjunction with any of the above-mentioned embodiments. It can be understood that the following specific examples are only illustrative for the specific implementation of any of the above-mentioned embodiments, and do not limit the technical solutions of any of the above-mentioned embodiments.

Referring to the schematic diagram of the satellite system architecture shown in FIG. 10, in the following specific example, the number of calculation processing modules 11 is 2, namely 11a and 11b, and each calculation processing module 11 includes a general CPU and a CPU interface circuit; an interface expansion module The number of 12 is 2, which are 12a and 12b respectively, and each interface expansion module 12 includes an interface expansion circuit; the number of measurement and control function modules 21 is 2, which are respectively 21a and 21b, and each measurement and control function module 21 includes an antenna, a measurement and control function module 21. Radio frequency device, measurement and control baseband, and measurement and control interface circuit; the number of power supply and distribution modules 22 and attitude and track control modules 23 is 1; The orbit control module 23 includes special components in the flywheel, star sensor, gyroscope and magnetic torquer, such as motor components and voltage and current sampling circuits in the flywheel, image sensors and interface circuits in the star sensor, and angular velocity in the gyroscope. Sensors and interface circuits, solenoid coils and interface circuits in magnetic torquers. The satellite payload takes the data transmission module 24, the camera module 25 and the storage module 26 as examples. The data transmission module 24 includes a broadband radio frequency communication circuit, a data transmission radio frequency baseband and an interface circuit; the camera module 25 includes a lens assembly, an image sensor and an interface circuit. ; The storage module 26 includes a flash memory array and an interface circuit.

The satellite payload and the modules of the satellite platform are connected and communicate with each other through the standardized module communication bus, and each module can be connected to the standardized module communication bus through the bus isolator; and the modules of the satellite payload are also communicated with each other through standardized high-speed communication. The bus is connected to realize the transmission of payload data. Therefore, for each module of the satellite payload, such as the data transmission module 24, the camera module 25, and the storage module 26, the interface circuit may include high-speed communication interface circuit and low-speed communication interface circuit. A communication interface circuit; wherein the high-speed communication interface circuit is connected with the standardized high-speed communication bus, and the low-speed communication interface circuit is connected with the standardized module communication bus.

The power distribution module 22 supplies power to other modules through a standardized power distribution bus. It should be noted that, in the following specific examples, the standardized module communication bus and the standardized power distribution bus may specifically be a Controller Area Network (CAN, Controller Area Network) bus, and the topology structure connected between the modules may be a bus structure, The star structure, etc., will not be repeated in the following specific examples.

Specific example one

Taking the satellite system architecture shown in FIG. 10 as an example, since the computing power of the general-purpose CPU can control the measurement and control function module 21, the power supply and distribution module 22, the attitude and orbit control module 23, the data transmission module 24, the camera module 25 and the storage module 26, Therefore, when realizing the functional requirements of the satellite system, the measurement and control function module 21 , the power supply and distribution module 22 , the attitude and orbit control module 23 , the data transmission module 24 , the camera module 25 and the storage module can be controlled only by a single calculation processing module 11 26. In this specific example, first, the functional requirements of the satellite system are injected into the calculation processing module 11a by means of software on-orbit injection, and then the calculation processing module 11a can monitor and control the function module 21a, power supply and distribution module according to the injected functional requirements. 22 and the attitude and orbit control module 23 to control; then, when the calculation processing module 11a breaks down, the calculation processing module 11a can be closed, and the functional requirements of the satellite system are injected into the calculation processing module by means of software on-orbit injection. 11b, at this time, the measurement and control function module 21a, the power supply and distribution module 22, and the attitude and orbit control module 23 can be controlled by the calculation processing module 11b.

In addition, since the calculation processing module 11a is closed, the bus isolator ensures that the closed calculation processing module 11a will not affect the normal communication of the standardized module communication bus.

Specific example two

Taking the satellite system architecture shown in FIG. 10 as an example, under normal working conditions, the calculation processing module 11a can monitor and control the measurement and control function module 21a, the power supply and distribution module 22, the attitude and orbit control module 23, and the data transmission module 24 according to the injected functional requirements. , the camera module 25 and the storage module 26 for control. When the computing power of the computing processing module 11a decreases and cannot control the measurement and control function module 21, the power supply and distribution module 22, the attitude and orbit control module 23, the data transmission module 24, the camera module 25 and the storage module 26, the software can also be used on the track. Part of the functional requirements of the satellite system are injected into the calculation processing module 11b in the way of Note. Taking the measurement and control function module 21a as an example, the calculation processing module 11a can control the power supply and distribution module 22 and the attitude and orbit control module 23; and the calculation processing module 11b controls Measurement and control function module 21 .

Specific example three

Taking the satellite system architecture shown in FIG. 10 as an example, in a normal working state, the calculation processing module 11a controls the power supply and distribution module 22, the attitude and orbit control module 23, the data transmission module 24, the camera module 25, and the storage module 26. The module 11b controls the measurement and control function module 21 . When the calculation processing module 11a is shut down due to a fault, it is also possible to inject part of the functional requirements corresponding to the calculation processing module 11a into the calculation processing module 11b by means of software on-track injection, so that the calculation processing module 11b can control the measurement and control function module 21a. , the power supply and distribution module 22 and the attitude and orbit control module 23 are controlled.

In addition, since the calculation processing module 11a is closed, the bus isolator ensures that the closed calculation processing module 11a will not affect the normal communication of the standardized module communication bus.

For the traditional satellite platform system, in the process of realizing the functional requirements, when the CPU fails, because it is a backup at the system-level granularity, the functional subsystem where the faulty CPU is located is usually switched to the backup function. sub-system.

In the above specific example, since it is a component-level granular backup, when a CPU fails, it only needs to switch to the backup general-purpose CPU, thereby reducing the resources consumed by the satellite function backup.

It should be noted that the technical solutions described in the embodiments of the present invention may be combined arbitrarily unless there is a conflict.

The above are only specific embodiments of the present invention, but the protection scope of the present invention is not limited to this. Any person skilled in the art can easily think of changes or substitutions within the technical scope disclosed by the present invention. should be included within the protection scope of the present invention. Therefore, the protection scope of the present invention should be based on the protection scope of the claims.

Claims (12)

1. a reconfigurable micro-nano satellite system, is characterized in that, described satellite system comprises: A general module, including a plurality of shared modules required to realize all functional requirements of the satellite system; Special modules, including a plurality of special modules corresponding to the single function requirements of the satellite system and only required to realize the corresponding single function requirements; a standardized bus for connecting the common module in the general module and the special module in the special module; Wherein, the type of the general module includes more than one computing processing module, and the computing processing module is configured as: Each computing processing module injects different functional requirements on the rail through software, so that each computing processing module controls the dedicated module corresponding to the functional requirements injected by itself; When a first calculation processing module in the one or more calculation processing modules fails, the first calculation processing module is turned off, and a second calculation processing module is determined from other calculation processing modules except the first calculation processing module. calculation processing module; Modify the special module corresponding to the second calculation processing module by means of software annotation; wherein, the special module corresponding to the second calculation processing module after modification includes the special module corresponding to the second calculation processing module before the modification and the first calculation processing module. The special module corresponding to the calculation processing module before the failure. 2. The satellite system according to claim 1, wherein the type of the general module further comprises: an interface expansion module; wherein, The calculation processing module is further configured to perform data calculation, signal processing and generation of control instructions according to various functional requirements of the satellite system; The interface expansion module is configured to convert the non-standard interfaces in the general module and the special module into standardized interfaces; The standardized bus includes standardized module communication bus and standardized power distribution bus. 3. The satellite system according to claim 2, wherein the calculation processing module comprises a general-purpose CPU and a CPU interface circuit; wherein, The general-purpose CPU is configured for collection and forwarding of satellite telemetry data, reception and execution of ground remote control commands, and attitude and flight trajectory calculation; And, receiving payload signals and processing payload signals, including satellite management, attitude and orbit control, measurement and control, navigation and data transmission; And the modulation and demodulation processing of radio frequency signals; As well as the collection and detection of power supply and distribution status, windsurfing shunt control, battery charging control, voltage conversion, and power distribution control; The CPU interface circuit is configured to receive data and signals sent by the dedicated module through the standardized module communication bus; and sending corresponding control instructions to the dedicated module through the standardized module communication bus. 4. The satellite system according to claim 3, wherein each of the general-purpose CPUs can access all dedicated modules; each general-purpose CPU injects different functional requirements on-orbit by software, so that each general-purpose CPU can The CPU can control specialized modules corresponding to the functional requirements it injects; each general-purpose CPU can be turned off. 5. The satellite system according to claim 4, wherein the computing processing module and the special purpose module are both connected to the standardized bus through a bus isolator, so that the computing processing module or the special purpose module is When turned off, the turned off computing processing module or special module does not affect the normal communication of the standardized bus. 6. satellite system according to claim 2 is characterized in that, in described standardized bus, described standardized module communication bus has backup communication bus, in the shared module in described general module and described special module The dedicated modules in are connected with the standardized module communication bus and the backup communication bus respectively through independent interface circuits; When the standardized module communication bus fails, the common module in the general module and the special module in the special module are switched to the backup communication bus for communication; or, the special module in the The dedicated module receives the selection instruction transmitted by the computing processing module, and selects the standardized module communication bus or the backup communication bus for communication based on the instruction of the selection instruction. 7. satellite system according to claim 2, is characterized in that, the kind of described special module, comprises measurement and control function module, power supply and distribution module, attitude and orbit control module and load function module; Wherein, the measurement and control function module is configured to, after receiving the remote control signal through the antenna, decode the received remote control signal through baseband to obtain a remote control command, and send the remote control command to the calculation processing through the standardized module communication bus module; And, receiving the telemetry data transmitted by the computing processing module through the standardized module communication bus, synthesizing the telemetry data into a telemetry signal through the baseband, and transmitting the telemetry signal to the outside through an antenna; The power supply and distribution module is configured to transmit the working state of the power supply assembly to the computing processing module through the standardized module communication bus; And, receiving the control command transmitted by the computing processing module through the standardized module communication bus, and executing the instruction of the control command; and, providing power to the common module and the dedicated module through the standardized power distribution bus; The attitude and orbit control module is configured to collect the attitude and flight orbit parameters of the satellite system, and transmit the parameters to the calculation processing module through the standardized module communication bus; The load function module is configured to implement the corresponding satellite load function through the control command transmitted by the calculation processing module. 8. The satellite system according to claim 7, wherein, The measurement and control function module includes an antenna, a measurement and control radio frequency device, a measurement and control baseband, and a measurement and control interface circuit; The power supply and distribution module includes a shunt, a charge controller and a standardized voltage regulation and power distribution unit; The attitude and orbit control module includes a flywheel, a star sensor, a gyroscope and a magnetic torque device; The load function module includes at least one of a data transmission module, a camera module and a storage module, wherein the data transmission module includes a broadband radio frequency channel, a data transmission radio frequency baseband and an interface circuit; the camera module includes a lens assembly , an image sensor and an interface circuit; the storage module includes a flash memory array and an interface circuit. 9. The satellite system according to claim 8, wherein the standardized bus further comprises a standardized high-speed communication bus configured to transmit load data between the load function modules; Correspondingly, the interface circuits in the data transmission module, the camera module and the storage module include a high-speed communication interface circuit and a low-speed communication interface circuit; wherein, the high-speed communication interface circuit is connected with the standardized high-speed communication bus, and the low-speed communication interface circuit is connected to the standard high-speed communication bus. A communication interface circuit is connected to the standardized modular communication bus. 10 . The satellite system according to claim 7 , wherein each dedicated module includes a backup dedicated module correspondingly. 11 . 11. A method for reconstructing a satellite system, wherein the method is applied to the satellite system according to any one of claims 1 to 10, and the method comprises: Each computing processing module in the general module injects different functional requirements on the rail through software, so that each computing processing module controls the dedicated module corresponding to the functional requirements injected by itself; When the first calculation and processing module fails, the first calculation and processing module is turned off, and a second calculation and processing module is determined from other calculation and processing modules except the first calculation and processing module; Modify the special module corresponding to the second calculation processing module by means of software annotation; wherein, the special module corresponding to the second calculation processing module after modification includes the special module corresponding to the second calculation processing module before the modification and the first calculation processing module. The special module corresponding to the calculation processing module before the failure. 12. The method according to claim 11, wherein the method further comprises: in the special module, when a special module in a special module is faulty, shutting down the fault special module, and turning off the fault. A backup dedicated module of this kind of dedicated module takes over the faulty dedicated module.

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