CN110002005B - Reconfigurable micro-nano satellite system architecture and satellite system reconfiguration method - Google Patents
Reconfigurable micro-nano satellite system architecture and satellite system reconfiguration method Download PDFInfo
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- CN110002005B CN110002005B CN201910161273.7A CN201910161273A CN110002005B CN 110002005 B CN110002005 B CN 110002005B CN 201910161273 A CN201910161273 A CN 201910161273A CN 110002005 B CN110002005 B CN 110002005B
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Abstract
The embodiment of the invention discloses a reconfigurable micro-nano satellite system architecture and a satellite system reconfiguration method; the reconfigurable micro-nano satellite system comprises: the universal module comprises a plurality of common modules which are required to be used for realizing all functional requirements of the satellite system; the special module comprises a plurality of special modules which correspond to the single function requirements of the satellite system and are only used for realizing the corresponding single function requirements; and the standardized bus is used for connecting the shared module in the general module and the special module in the special module.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a reconfigurable micro-nano satellite system architecture and a satellite system reconfiguration method.
Background
With the development of the diversification of the functions of the satellite, the functions carried by the satellite are more and more. In the field of traditional satellite design, a specific system in a satellite only undertakes a predefined function, and if the system corresponding to the specific function is damaged, the whole satellite loses the function. Although the reliability of the satellite can be improved by adding redundant backup in the satellite, for each functional system in the satellite, a corresponding backup system needs to be added, so that the design complexity of the satellite system is increased, the volume and mass of the whole satellite are also increased, and the manufacturing cost of the satellite is increased. And the reliability of the satellite is improved through a function backup mode, and extra support of ground corollary equipment is needed, so that the existing ground station equipment needs to be upgraded and modified, and the complexity of the system is increased.
In order to avoid the above situation, a satellite system that reconstructs a part of functions within a specific function range has appeared, that is, for a plurality of systems with similar functions, a small number of function modules are added, so that each system can implement one of a plurality of functions by injecting software of the corresponding function. For the housekeeping computer, the on-orbit modification function can be realized by the way of injecting software, and the switching among the functions of housekeeping, attitude and orbit control calculation, simple processing of load data and the like can be realized; however, due to the limitation of hardware architecture, the scheme can only realize limited function backup, and cannot realize backup functions for different loads, for example, function backup of a signal processor of a measurement and control system cannot be realized.
The existing cold backup switching method for the isomorphic housekeeping system can control the switching of two sets of cold backup state housekeeping computers through an external control circuit and save the current state through the external control circuit. This method requires not only two sets of computers and peripheral support circuits but also an additional external control circuit, thereby increasing the complexity of the system and the possible points of failure.
For the micro-nano satellite, because the satellite is small in volume and the energy and space in the satellite are very limited, an extra backup system is not added in the space, so that the reliability of the satellite is greatly reduced; based on this, reliability can only be guaranteed through test screening during manufacturing, so that the service life of the satellite is generally short, and the requirements of long service life and high reliability are difficult to meet.
Disclosure of Invention
In view of this, embodiments of the present invention are expected to provide a reconfigurable micro/nano satellite system architecture and a satellite system reconfiguration method, which not only can improve the reliability of a satellite system, but also reduce the number of backup circuits and devices required for reconfiguration, save satellite space, and reduce the energy requirement of a satellite.
The technical scheme of the 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:
the universal module comprises a plurality of common modules which are required to be used for realizing all functional requirements of the satellite system;
the special module comprises a plurality of special modules which correspond to the single function requirements of the satellite system and are only used for realizing the corresponding single function requirements;
and the standardized bus is used for connecting the shared module in the general module and the special module in the special module.
In a second aspect, a method for reconstructing a satellite system according to an embodiment of the present invention is applied to the satellite system according to the first aspect, and the method includes:
each calculation processing module in the general module injects different function requirements on the track through software so that each calculation processing module controls a special module corresponding to the injected function requirements;
when a first computing processing module fails, shutting down the first computing processing module, and determining a second computing processing module from other computing processing modules except the first computing processing module;
modifying the special module corresponding to the second computing processing module in a software uploading mode; the modified special modules corresponding to the second computing processing module comprise the special modules corresponding to the second computing processing module before modification and the special modules corresponding to the first computing processing module before failure.
The embodiment of the invention provides a reconfigurable micro-nano satellite system architecture and a satellite system reconfiguration method; in a traditional satellite system, a common module which can be used for all function requirements forms a universal module, and a special module which can be used for only one single function requirement forms a special module. Compared with the traditional satellite system, when the functional requirement of the satellite system is realized, the coupling degree between the general module and the special module is reduced, only the components in the general module or the special module need to be backed up in the process of improving the reliability of the satellite system, the granularity of the reliability backup is reduced from the system level to the component level, the system complexity for realizing the functional requirement of the satellite system is reduced, the resource waste of the satellite system is reduced, and the power consumption and the quality of the satellite system are reduced.
Drawings
FIG. 1 is a schematic diagram of a satellite platform in a conventional satellite system;
fig. 2 is a schematic diagram of a reconfigurable micro/nano satellite system architecture according to an embodiment of the present invention;
fig. 3 is a schematic diagram illustrating a general module according to an embodiment of the present invention;
FIG. 4 is a block diagram of a standardized bus according to an embodiment of the present invention;
fig. 5 is a schematic diagram illustrating a computing processing module according to an embodiment of the present invention;
fig. 6 is a schematic diagram illustrating a dedicated module according to an embodiment of the present invention;
fig. 7 is a schematic diagram of a star sensor according to an embodiment of the present invention;
FIG. 8A is a schematic diagram of a digital transmission subsystem according to an embodiment of the present invention;
fig. 8B is a schematic diagram illustrating a camera subsystem according to an embodiment of the present invention;
FIG. 8C is a schematic diagram of a memory subsystem according to an embodiment of the present invention;
fig. 9 is a schematic flowchart of a method for reconstructing a satellite system according to 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 Description
The technical solution 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, a satellite platform and a satellite load may be included, and the satellite load is carried on the satellite platform. Referring to fig. 1, which shows a schematic of a satellite platform architecture in a conventional satellite system, the conventional satellite system includes a plurality of subsystems, and taking the architecture shown in fig. 1 as an example, the satellite system 1 may include a measurement and control subsystem 11, an integrated electronic subsystem 12, an attitude and flight orbit control (hereinafter referred to as attitude and orbit control) subsystem 13, and a power supply and distribution subsystem 14. Each subsystem comprises the following components: CPU, communication interface circuit and power supply interface circuit. The satellite system internal communication is realized among all subsystems through a system communication bus 15, and a power supply and distribution subsystem 14 supplies power to power supply circuit interfaces of other subsystems through a system power distribution bus 16, so that electric energy is supplied for realizing the functions of the other subsystems. As can be seen from fig. 1, in the satellite system architecture, the subsystems are tightly coupled, and the CPUs of the subsystems are independent of each other, that is, the CPU of each subsystem is only responsible for implementing the functions of the system in which it is located. For example, the integrated electronic CPU in the integrated electronic subsystem 12 is responsible for functions such as whole satellite telemetry acquisition and forwarding, remote control reception and execution, attitude and orbit control calculation, and the like; the measurement and control CPU in the measurement and control subsystem 11 realizes the modulation and demodulation function of the radio frequency signal; the power control CPU in the power supply and distribution subsystem 14 implements functions such as state acquisition and monitoring, sailboard shunt control, battery charging control, voltage conversion, and power distribution control. In addition, each subsystem requires a separate CPU and associated peripheral circuitry (e.g., power interface circuitry and communication interface circuitry). If the reliability needs to be improved, the method can only be realized through subsystem-level backup, that is, all components in a subsystem need to be backed up in the process of backing up the subsystem. Usually, each subsystem has a backup subsystem, so that the whole satellite platform system needs 5 to 6 sets of CPUs and corresponding peripheral circuits. In addition, if the reliability needs to be further improved, the method can be realized only by adding subsystem-level backup, which further increases the resource waste and is not beneficial to the optimization of the weight, the power consumption and the volume of the satellite system.
It should be noted that, for the architecture shown in fig. 1, there is usually a large redundancy in the computing power of the CPU, and there is a large margin in the capability of the peripheral circuit, but because the architecture shown in fig. 1 limits that each CPU can only implement the function of its own system, the excess computing power and the peripheral circuit capability cannot be used for implementing the functions of other subsystems, and cannot be used for backup.
In order to solve the above problems, based on the two characteristics that a CPU has the capability of implementing function reconfiguration through software programming and the functions of a power supply interface circuit and a communication interface circuit are single so as to be commonly used among different systems, an embodiment of the present invention provides a reconfigurable micro-nano satellite system architecture, which is shown in fig. 2 and shows that the reconfigurable micro-nano satellite system 2 architecture may include:
a general module 21, including a plurality of common modules, which are required to be used for realizing all functional requirements of the satellite system 2;
a dedicated module 22, including a plurality of dedicated modules, for corresponding to the single functional requirements of the satellite system 2 and for being used only for realizing the corresponding single functional requirements;
a standardized bus 23 for connecting the common modules in the general module 21 and the dedicated modules in the dedicated module 22.
Through the micro-nano satellite system 2 provided in fig. 2, a common module, which can be used for all functional requirements in a conventional satellite system, including a satellite platform and a satellite load, forms a general module 21, and a special module, which can be used for only a single functional requirement, forms a special module 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, in the process of improving the reliability of the satellite system, only the components in the general module 21 or the special module 22 need to be backed up, the granularity of the reliability backup is reduced from a system level to a component level, the system complexity for realizing the functional requirements of the satellite system is reduced, the resource waste of the satellite system is reduced, and the power consumption and the quality of the satellite system are reduced.
For the satellite system shown in fig. 2, in one possible implementation, referring to fig. 3, the types of the general modules 21 include: a calculation processing module 211 and an interface expansion module 212; wherein the content of the first and second substances,
the computation processing module 211 is configured to perform data computation, signal processing and generation of control instructions for various functional requirements of the satellite system 2; that is to say, the calculation processing module 211 has the capabilities of star management, attitude and orbit control, measurement and control, navigation, data transmission, power management and the like, 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 calculation processing module 211 may include a general-purpose CPU2111 and a CPU interface circuit 2112; wherein the content of the first and second substances,
the general CPU2111 may be specifically configured to collect and forward whole satellite telemetry data, receive and execute ground remote control commands, and calculate attitude and flight trajectory;
receiving and processing the load signal, including satellite affair management, attitude and orbit control, measurement and control, navigation and data transmission of the satellite;
modulating and demodulating the radio frequency signal;
collecting and detecting power supply and distribution states, controlling the flow distribution of the sailboards, controlling the charging of the storage battery, converting the voltage and controlling the power distribution;
the CPU interface circuit 2112 is configured to receive data and signals sent by the special module 22 through the standardized module communication bus;
and sends a corresponding control command to the dedicated module 22 through the standardized module communication bus.
For the general-purpose CPUs 2111, in a specific implementation, each of the general-purpose CPUs 2111 can access all the dedicated modules 22; each general-purpose CPU2111 injects different functional requirements on the track through software, so that each general-purpose CPU2111 can control a dedicated module corresponding to the functional requirement injected by itself; each general-purpose CPU2111 can be turned off.
It is understood that, in the conventional satellite architecture, the software configuration inside the satellite is implemented by the CPUs of the subsystems, and generally speaking, one CPU accompanies 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 a traditional satellite architecture, a platform and a load both have temperature, voltage and current acquisition software for realizing temperature control and state monitoring. By adopting the satellite system provided by the embodiment of the invention, the internal software configuration is realized by the general CPU, namely, the general CPU is used for simultaneously realizing acquisition of telemetering parameters such as temperature, voltage and current of the platform and the load, so that the software configuration items of the satellite system are reduced, and the program complexity is simplified.
It should be noted that the general-purpose CPU is a generic term for a device having a logic control function, and may include a CPU (central processing unit), a DSP (digital signal processor), an FPGA (field programmable gate array), and other devices, modules, or systems capable of implementing functions such as control, operation, and processing through programming.
It should be noted that, for a single function requirement, the computing power of each general-purpose CPU2111 is redundant, so that each general-purpose CPU2111 can correspondingly control a plurality of dedicated modules, thereby saving the number of general-purpose CPUs 2111, and thus reducing the number of peripheral circuits required by the general-purpose CPU2111, thereby reducing the resource consumption of the satellite system, saving the satellite space, and reducing the quality of the satellite system. In a normal working state, each general CPU2111 is only responsible for its corresponding dedicated module, and when a certain general CPU2111 fails, the failed general CPU2111 is turned off, and a non-failed general CPU2111 is made to be responsible for its corresponding dedicated module and simultaneously also for the corresponding dedicated module that the failed general CPU2111 is responsible for by a software note-up modification manner. Specifically, the method of selecting the non-faulty general-purpose CPU2111 may obtain the remaining computing power of all the non-faulty general-purpose CPUs 2111 in charge of the respective corresponding dedicated modules, and select the non-faulty general-purpose CPU2111 with the most remaining computing power to additionally take charge of the corresponding dedicated module in charge of the faulty general-purpose CPU 2111. Therefore, when a fault occurs, system-level backup is not needed, and the reliability of the satellite system is improved only by switching and backing up the components such as the general CPU.
Further, for both the computing processing module 211 and the application specific module are connected to the standardized bus through bus isolators, so that when the computing processing module 211 or application specific module is shut down due to a fault, the shut down computing processing module 211 or application specific module does 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, and the shared module in the general module and the dedicated module in the dedicated module are connected to the standardized module communication bus and the backup communication bus respectively through independent interface circuits;
when the standardized module communication bus is in fault, the shared module in the general module and the special module in the special module are switched to the backup communication bus for communication; or a special module in the special module receives a selection instruction transmitted by the calculation processing module, and selects the standardized module communication bus or the backup communication bus to communicate based on the instruction of the selection instruction.
It can be understood that, in order to improve the communication reliability, the standardized module communication bus may be designed to be backed up, at this time, each shared module or dedicated module may provide two independent communication bus interfaces, which are respectively connected to the two mutually backed up standardized module communication buses, the two mutually backed up communication buses have the same function, and each standardized module communication bus may completely implement the communication function between the modules. Therefore, when a problem occurs in one standardized module communication bus, the shared module or the dedicated module can be automatically switched to the other standardized module communication bus to realize communication work, and the standardized module communication bus used for realizing the communication function can be selected based on the instruction of the selection instruction after the selection instruction sent by the computing unit module is received.
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 receive a remote control signal through an antenna, decode the received remote control signal through a baseband to obtain a remote control command, and send the remote control command to the calculation processing module 211 through the standardized module communication bus 231;
and receiving the telemetry data transmitted by the calculation processing module 211 through the standardized module communication bus 231, synthesizing the telemetry data into a telemetry signal through a baseband, and transmitting the telemetry signal to the outside through an antenna;
the power supply and distribution module 222 is configured to transmit the operating state of a power supply component to the computing processing module through the standardized module communication bus 231;
and an instruction to receive the control command transmitted by the calculation processing module 211 through the standardized module communication bus 231 and to execute the control command;
and, providing power to the shared modules and the dedicated modules through the standardized power distribution bus 232;
the attitude and orbit control module 223 is configured to acquire 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 payload function module 224 is configured to implement a corresponding satellite payload 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 rf device, a measurement and control baseband, and a measurement and control interface circuit. Therefore, for the functions of the measurement and control function module 211, the following may be specifically described: after receiving the remote control signal through the antenna, the measurement and control baseband decodes the received remote control signal to obtain a remote control command, and the measurement and control interface circuit sends the remote control command to the calculation processing module 211 through the standardized module communication bus 231; and the measurement and control interface circuit receives the telemetering data transmitted by the calculation processing module 211 through the standardized module communication bus 231, synthesizes the telemetering data into a telemetering signal through a measurement and control baseband, and transmits the telemetering signal to the outside through an antenna by the measurement and control radio frequency device.
The power supply and distribution module 222 includes a shunt, a charge controller, and a standardized voltage regulation and distribution unit. Therefore, the functions of the power supply and distribution module 222 can be described as follows: transmitting the operating state of a power supply component to the computing processing module via 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 diverter, the charge controller and the standardized voltage adjustment unit executing an instruction of the control command; and, the power distribution unit provides power to the shared modules as well as to the dedicated modules through the standardized power distribution bus 232. In detail, the power supply module may include a photovoltaic module, such as a solar panel, and the photovoltaic module converts light energy into electric energy, transmits the electric energy to the charge controller through the shunt, and supplies power to the storage battery through the charge controller.
The attitude and orbit control module 223 comprises a flywheel, a star sensor, a gyroscope and a magnetic torquer. Its function can be described specifically as: the attitude and flight orbit parameters of the satellite system 2 are collected by the flywheel, the star sensor, the gyroscope and the magnetic torquer, and the parameters are transmitted to the calculation processing module 211.
In the traditional satellite system, because attitude and orbit control components such as a satellite sensor, a gyroscope, a flywheel and the like all comprise a CPU, an interface circuit, a power supply circuit and corresponding special modules such as a motor, an image sensor and the like, the attitude and orbit control components can be divided into general components and special components in the embodiment of the invention, so that the general circuit components such as the CPU, the interface circuit, the power supply circuit and the like are shared between a satellite platform and a load single machine, the whole system reconfigurable satellite architecture is realized, and the number of components on the satellite and the circuit complexity are greatly reduced while the reliability is not reduced. Taking a satellite sensor as an example, fig. 7 is a schematic diagram of an internal circuit function module of the satellite sensor in a conventional satellite system, wherein the internal circuit function module includes an image sensor, a CPU, an interface circuit, a power supply circuit, and the like. The universal assembly in the star sensor is designed into a universal module, only the image sensor and the interface circuit in the star sensor are reserved, and the functions of the CPU and the power supply circuit are replaced by a shared module in the universal module, so that the circuit complexity of the star sensor is reduced.
The load function module 224 corresponds to a satellite load carried by a satellite platform, and in a conventional satellite system, the satellite load also has circuit function modules similar to those of each subsystem in the conventional satellite platform. In a satellite platform, the specific satellite loads may include a data transmission subsystem, a camera subsystem, and a storage subsystem. Taking the data transmission subsystem as an example, referring to fig. 8A, the conventional data transmission subsystem 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 to form a common module, the FPGA converts the data transmission rf baseband interface into a standardized interface, and completes signal processing, modulation, and demodulation functions in the FPGA, so that in the load function module 224, the data transmission module is used to implement a load function corresponding to the data transmission subsystem, and the data transmission module may include a broadband rf channel, a data transmission rf baseband, and an interface circuit. Taking the camera subsystem as an example, referring to fig. 8B, the conventional 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 to form a common module, and the FPGA converts the digital radio frequency baseband interface into a standardized interface, and completes the signal processing, modulating, and demodulating functions in the FPGA, so that in the load function module 224, the camera module is used to implement the load 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, the conventional storage subsystem includes a flash memory array, a CPU, an FPGA for signal processing, an interface circuit, and a power supply circuit. Also for the storage subsystem, according to the common module separation process performed by the data transmission module and the camera module, a storage module is obtained in the load function module 224 to implement the load function corresponding to the camera subsystem, and the storage module may include a flash memory array and an interface circuit. After the satellite load subsystem is separated from the shared modules according to the scheme, the circuit complexity of the load function module can be reduced, and the quality and the power consumption of the satellite load subsystem are further reduced.
In addition, since the communication data volume between the load subsystems is usually large, in order to avoid the influence of the communication data volume between the satellite loads on the communication of the satellite platform, preferably, the standardized bus further comprises a standardized high-speed communication bus configured to transmit the load data between the load function modules;
correspondingly, the interface circuits in the data transmission module, the camera module and the storage module comprise 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 connected with the standardized module communication bus.
It should be noted that, a standardized high-speed communication bus is added between the satellite load function modules to implement communication between different satellite loads. Therefore, the satellite load function module is provided with a standardized module communication bus and a standardized high-speed communication bus, wherein the standardized module communication bus is used for transmitting control data and telemetering data, and the standardized high-speed communication bus is used for transmitting load data. Correspondingly, in various satellite load functional modules, the communication interface circuit can 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 connected with the standardized module communication bus, so that mutual influence between high-speed data and low-speed data is avoided.
Aiming at the four special modules, the satellite platform and the satellite load are jointly designed, the common module of the satellite platform and the satellite load is universally designed, the number of components used by the satellite can be reduced to the maximum extent under the condition of not influencing functions and reliability, and the complexity of the overall design of the satellite is reduced.
For the above four special modules, in the specific implementation process, each special module may include a corresponding backup special module. Therefore, when a certain special module in a certain special module fails, the special module with the failure can be closed, and the function of the special module with the failure is switched to the backup special module. It should be noted that, because the backup between the dedicated modules does not involve the shared module, the coupling between the dedicated modules and the shared module is reduced, a method for improving reliability with low cost and low complexity can be provided, and a full satellite system reconfigurable satellite architecture is realized.
Through the technical scheme, when a certain functional requirement breaks down, backup switching is not needed for all components for realizing the functional requirement of the fault, and only a shared module or a special module is needed to be switched, so that the circuit complexity of the system is reduced, the resource waste is reduced, and the resource utilization rate is improved.
Based on the same inventive concept in the foregoing technical solution, referring to fig. 9, a method for reconstructing a satellite system, which may be applied to the satellite system in any example of the foregoing technical solution, is shown in an embodiment of the present invention, and the method includes:
s901: each calculation processing module in the general module injects different function requirements on the track through software so that each calculation processing module controls a special module corresponding to the injected function requirements;
s902: when a first computing processing module fails, shutting down the first computing processing module, and determining a second computing processing module from other computing processing modules except the first computing processing module;
s903: modifying the special module corresponding to the second computing processing module in a software uploading mode; the modified special modules corresponding to the second computing processing module comprise the special modules corresponding to the second computing processing module before modification and the special modules corresponding to the first computing processing module before failure.
For the technical solution shown in fig. 9, in a possible implementation manner, the method may further include: in the special module, when one special module in one special module fails, the special module with the failure is closed, and the backup special module in the special module of the kind takes over the special module with the failure.
With respect to the solution shown in fig. 9, in a possible implementation manner, the computing processing module and the dedicated module are both connected to the standardized bus through a bus isolator, so that when the computing processing module or the dedicated module is turned off due to a fault, the turned-off computing processing module or dedicated module does not affect the normal communication of the standardized bus.
The following specific examples are provided in combination with any one of the above embodiments, and it should be understood that the following specific examples are only illustrative of specific implementations of any one of the above embodiments, and do not limit the technical solutions of any one of the above embodiments.
Referring to the satellite system architecture schematic shown in fig. 10, in the following specific example, the number of computing processing modules 11 is 2, 11a and 11b, respectively, and each computing processing module 11 includes a general-purpose CPU and a CPU interface circuit; the number of the interface expansion modules 12 is 2, 12a and 12b, respectively, and each interface expansion module 12 includes an interface expansion circuit; the number of the measurement and control functional modules 21 is 2, 21a and 21b, and each measurement and control functional module 21 comprises an antenna, a measurement and control radio frequency device, a measurement and control baseband and a measurement and control interface circuit; the number of the power supply and distribution modules 22 and the attitude and orbit control modules 23 is 1; a power supply and distribution module 22 including a shunt, a charge controller and a standardized voltage regulation and distribution unit; the attitude and orbit control module 23 includes a flywheel, a satellite sensor, a gyroscope, and dedicated components in the magnetic torquer, such as a motor assembly and a voltage and current sampling circuit in the flywheel, an image sensor and an interface circuit in the satellite sensor, an angular velocity sensor and an interface circuit in the gyroscope, and an electromagnetic coil and an interface circuit in the magnetic torquer. The satellite load is exemplified by a data transmission module 24, a camera module 25 and a storage module 26, wherein 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 memory module 26 includes a flash memory array and interface circuitry.
The satellite load and each module of the satellite platform are connected and communicated with each other through a standardized module communication bus, and each module can be connected to the standardized module communication bus through a bus isolator; the modules of the satellite load are also connected through a standardized high-speed communication bus to realize transmission of load data, so that for the modules of the satellite load, such as the data transmission module 24, the camera module 25 and the storage module 26, the interface circuits therein may include 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 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 example, the standardized module communication bus and the standardized power distribution bus may specifically be a Controller Area Network (CAN) bus, and the topology structures connected between the modules may be a bus structure, a star structure, and the like, which are not described in the following specific example.
Specific example 1
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, when the functional requirements of the satellite system are met, 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 may be controlled by only a single computing and processing module 11. In this specific example, first, functional requirements of the satellite system are injected into the calculation processing module 11a in an on-orbit software injection manner, so that the calculation processing module 11a can control the measurement and control functional module 21a, the power supply and distribution module 22, and the attitude and orbit control module 23 according to the injected functional requirements; then, when the computing processing module 11a fails, the computing processing module 11a may be turned off, and the functional requirements of the satellite system are also injected into the computing processing module 11b by way of on-orbit injection of software, so that the measurement and control functional module 21a, the power supply and distribution module 22, and the attitude and orbit control module 23 can be controlled by the computing processing module 11 b.
In addition, because the computing processing module 11a is closed, the bus isolator ensures that the closed computing processing module 11a does not affect the normal communication of the communication bus of the standardized module.
Specific example 2
Taking the satellite system architecture shown in fig. 10 as an example, in a normal operating state, the computing processing module 11a can control the measurement and control function module 21a, 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 according to the injected function requirements. When the computing capability of the computing processing module 11a is reduced and 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 cannot be controlled, part of the functional requirements of the satellite system can be injected into the computing processing module 11b in an on-orbit injection manner by software, and taking the measurement and control function module 21a as an example, the computing 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 the measurement and control function module 21.
Specific example III
Taking the satellite system architecture shown in fig. 10 as an example, in a normal operating state, the computing 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, and the computing processing module 11b controls the measurement and control function module 21. When the computing processing module 11a is turned off due to a fault, part of the function requirements corresponding to the computing processing module 11a may also be injected into the computing processing module 11b in an on-orbit software injection manner, so that the computing processing module 11b controls the measurement and control function module 21a, the power supply and distribution module 22, and the attitude and orbit control module 23.
In addition, because the computing processing module 11a is closed, the bus isolator ensures that the closed computing processing module 11a does not affect the normal communication of the communication bus of the standardized module.
For a conventional satellite platform system, in a function requirement implementation process, when a CPU fails, a functional subsystem where the failed CPU is located is usually switched to a backup functional subsystem because of a backup in a system-level granularity.
In the above specific example, because the backup is performed at a component level granularity, when the CPU fails, only the general CPU needs to be switched to the backup, thereby reducing the resources consumed by the backup of the satellite functions.
It should be noted that: the technical schemes described in the embodiments of the present invention can be combined arbitrarily without conflict.
The above description is only for the specific embodiments of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present invention, and all the changes or substitutions should be covered within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (12)
1. A reconfigurable micro-nano satellite system is characterized in that the satellite system comprises:
the universal module comprises a plurality of common modules which are required to be used for realizing all functional requirements of the satellite system;
the special module comprises a plurality of special modules which correspond to the single function requirements of the satellite system and are only used for realizing the corresponding single function requirements;
the standardized bus is used for connecting the common module in the general module and the special module in the special module;
wherein the generic module class includes one or more computation processing modules configured to:
each calculation processing module injects different function requirements on the track through software, so that each calculation processing module controls a special module corresponding to the injected function requirements;
when a first computing processing module of the more than one computing processing modules fails, closing the first computing processing module, and determining a second computing processing module from other computing processing modules except the first computing processing module;
modifying the special module corresponding to the second computing processing module in a software uploading mode; the modified special modules corresponding to the second computing processing module comprise the special modules corresponding to the second computing processing module before modification and the special modules corresponding to the first computing processing module before failure.
2. The satellite system according to claim 1, wherein the generic module further comprises: an interface extension module; wherein the content of the first and second substances,
the computing processing module is also configured to perform data computation, signal processing and control instruction generation according to various functional requirements of the satellite system;
the interface extension module is configured to convert the non-standard interfaces in the general module and the special module into standard interfaces;
the standardized bus comprises a standardized module communication bus and a standardized power distribution bus.
3. The satellite system according to claim 2, wherein the computation processing module includes a general purpose CPU and a CPU interface circuit; wherein the content of the first and second substances,
the general CPU is configured for acquiring and forwarding whole satellite telemetry data, receiving and executing ground remote control commands and calculating attitude and flight orbit;
receiving and processing the load signal, including satellite affair management, attitude and orbit control, measurement and control, navigation and data transmission of the satellite;
modulating and demodulating the radio frequency signal;
collecting and detecting power supply and distribution states, controlling the flow distribution of the sailboards, controlling the charging of the storage battery, converting the voltage and controlling the power distribution;
the CPU interface circuit is configured to receive data and signals sent by the special module through the standardized module communication bus;
and sending a corresponding control instruction to the special module through the standardized module communication bus.
4. The satellite system of claim 3, wherein each of the general purpose CPUs has access to all of the application specific modules; each general CPU injects different function requirements on the rail through software, so that each general CPU can control a special module corresponding to the injected function requirements; each general purpose CPU can be turned off.
5. The satellite system according to claim 4, wherein the computing processing module and the application specific module are each connected to the standardized bus by a bus isolator such that when the computing processing module or application specific module is shut down due to a fault, the shut down computing processing module or application specific module does not affect the normal communication of the standardized bus.
6. The satellite system according to claim 2, wherein the standardized module communication bus has a backup communication bus in the standardized bus, and the standardized module communication bus and the backup communication bus are connected to the common module in the general-purpose module and the dedicated module in the dedicated module respectively through independent interface circuits;
when the standardized module communication bus is in fault, the shared module in the general module and the special module in the special module are switched to the backup communication bus for communication; or a special module in the special module receives a selection instruction transmitted by the calculation processing module, and selects the standardized module communication bus or the backup communication bus to communicate based on the instruction of the selection instruction.
7. The satellite system according to claim 2, wherein the types of the dedicated modules include a measurement and control function module, a power supply and distribution module, an attitude and orbit control module and a load function module;
the measurement and control functional module is configured to receive a remote control signal through an antenna, decode the received remote control signal through a baseband to obtain a remote control command, and send the remote control command to the calculation processing module through the standardized module communication bus;
receiving the telemetering data transmitted by the computing processing module through the standardized module communication bus, synthesizing the telemetering data into a telemetering signal through a baseband, and transmitting the telemetering signal to the outside through an antenna;
the power supply and distribution module is configured to transmit the working state of a power supply component to the computing processing module through the standardized module communication bus;
receiving a control command transmitted by the computing processing module through the standardized module communication bus, and executing an instruction of the control command;
and providing electrical energy to the shared modules and the dedicated modules through the standardized power distribution bus;
the attitude and orbit control module is configured to acquire attitude and flight orbit parameters of the satellite system and transmit the parameters to the calculation processing module through the standardized module communication bus;
and the load function module is configured to realize a corresponding satellite load function through the control command transmitted by the calculation processing module.
8. The satellite system of claim 7,
the measurement and control functional module comprises 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 comprises a shunt, a charging controller and a standardized voltage regulation and distribution unit;
the attitude and orbit control module comprises a flywheel, a star sensor, a gyroscope and a magnetic torquer;
the load function module comprises at least one of a data transmission module, a camera module and a storage module, wherein the data transmission module comprises a broadband radio frequency channel, a data transmission radio frequency baseband and an interface circuit; the camera module comprises a lens assembly, an image sensor and an interface circuit; the memory module includes a flash memory array and an interface circuit.
9. The satellite system of claim 8, wherein the standardized bus further comprises a standardized high-speed communication bus configured to transmit payload data between the payload function modules;
correspondingly, the interface circuits in the data transmission module, the camera module and the storage module comprise 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 connected with the standardized module communication bus.
10. The satellite system of claim 7, wherein each of the plurality of application specific modules includes a backup application specific module.
11. A method for reconstructing a satellite system, the method being applied to the satellite system according to any one of claims 1 to 10, the method comprising:
each calculation processing module in the general module injects different function requirements on the track through software so that each calculation processing module controls a special module corresponding to the injected function requirements;
when a first computing processing module fails, shutting down the first computing processing module, and determining a second computing processing module from other computing processing modules except the first computing processing module;
modifying the special module corresponding to the second computing processing module in a software uploading mode; the modified special modules corresponding to the second computing processing module comprise the special modules corresponding to the second computing processing module before modification and the special modules corresponding to the first computing processing module before failure.
12. The method of claim 11, further comprising: in the special module, when one special module in one special module fails, the special module with the failure is closed, and the backup special module in the special module of the kind takes over the special module with the failure.
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| CN110426721B (en) * | 2019-08-05 | 2021-06-15 | 哈尔滨工业大学 | Modular reconfigurable satellite in-orbit self-reconfiguration method based on graph theory and A-x algorithm |
| CN110920935A (en) * | 2019-12-18 | 2020-03-27 | 哈尔滨工业大学 | Plug-and-play intelligent core system |
| CN111224728B (en) * | 2020-01-13 | 2020-09-18 | 北京空间飞行器总体设计部 | Health time estimation method suitable for satellite reconfigurable stand-alone equipment |
| CN111891398B (en) * | 2020-08-13 | 2022-03-11 | 中国人民解放军国防科技大学 | Elastic universal intelligent satellite hardware system architecture |
| CN112350764B (en) * | 2020-09-30 | 2021-09-24 | 军事科学院系统工程研究院网络信息研究所 | Comprehensive communication system suitable for stratospheric lift-off platform |
| BG67584B1 (en) * | 2020-10-22 | 2023-10-31 | "Ендуросат" Ад | Unifying platform for nanosatellite systems |
| CN112614325B (en) * | 2020-12-07 | 2022-03-29 | 上海卫星工程研究所 | Separated microsatellite measurement and control system, method and medium |
| CN113204188B (en) * | 2021-04-26 | 2022-07-19 | 中国人民解放军国防科技大学 | Multimode-driven quick-response satellite switching instruction system and design and application method thereof |
| CN113434292A (en) * | 2021-06-25 | 2021-09-24 | 山东航天电子技术研究所 | Intelligent micro-nano satellite system architecture and system reconstruction method |
| CN113815904B (en) * | 2021-09-06 | 2023-11-10 | 中国科学院微小卫星创新研究院 | Modularized energy system capable of being maintained and replaced on orbit |
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