CN112859687A - Integrated satellite integrated electronic system - Google Patents
Integrated satellite integrated electronic system Download PDFInfo
- Publication number
- CN112859687A CN112859687A CN202110039918.7A CN202110039918A CN112859687A CN 112859687 A CN112859687 A CN 112859687A CN 202110039918 A CN202110039918 A CN 202110039918A CN 112859687 A CN112859687 A CN 112859687A
- Authority
- CN
- China
- Prior art keywords
- module
- data
- central processing
- processing module
- satellite
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
- G05B19/042—Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
- G05B19/0423—Input/output
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B2219/00—Program-control systems
- G05B2219/20—Pc systems
- G05B2219/25—Pc structure of the system
- G05B2219/25257—Microcontroller
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Position Fixing By Use Of Radio Waves (AREA)
Abstract
The invention discloses an integrated satellite integrated electronic system, comprising: the core plate card, the integration is provided with on the core plate card: the analog quantity acquisition module is used for acquiring environmental data of the environment where the satellite is located and running state data of an external module mounted on the satellite; the measurement and control module is used for receiving and processing the uplink remote control signal to obtain uplink remote control data; the navigation information processing module is used for receiving and processing the original navigation signal to obtain effective navigation data; the central processing module is used for processing environmental data, running state data, uplink remote control data and effective navigation data; and sending a drive control signal to the drive module; the central processing module is also used for providing downlink telemetering data to the measurement and control module so that the measurement and control module processes the downlink telemetering data to obtain a downlink telemetering signal; the driving module is used for driving the corresponding peripheral module to execute corresponding action according to the driving control signal; the mass production degree of the satellite is effectively improved, and the weight and the volume of the satellite are effectively reduced.
Description
Technical Field
The invention belongs to the technical field of artificial satellites, and particularly relates to an integrated satellite integrated electronic system.
Background
The satellite integrated electronic system adopts a highly integrated interconnection technology, and an information management and transmission system for comprehensively utilizing electronic equipment in the satellite has a core effect in the whole satellite information flow management control, is a system for implementing autonomous management and control by the satellite, performs modular design on the electronic equipment in the satellite, performs high integration according to the functions of the equipment, reduces the number, volume and weight of the electronic equipment, and simplifies a cable network between the equipment.
The manufactured commercial small satellite basically adopts an integrated design for having the characteristics of low cost, multiple functions, short period, light weight, small volume and the like, but the design of the current commercial small satellite always adopts the design idea of the traditional satellite, and only the satellite single machine is simply subjected to structural system modularization, and each single machine component is separately designed and produced and needs to be customized, so that the integration level is not high, the universality, the expansibility, the maintainability and the batch production degree of each single machine component are low, and the defects of prolonged life cycle, increased process files, large communication and coordination workload, dispersed technical state and the like in the satellite development process are overcome.
Disclosure of Invention
The embodiment of the invention provides an integrated satellite integrated electronic system, which at least solves the technical problems of low universality, poor expansibility, poor batch production degree, poor maintainability and poor batch production degree of each single unit component of a satellite in the prior art.
In a first aspect, the present invention provides an integrated satellite integrated electronic system according to an embodiment of the present invention, including: the core integrated circuit board, be provided with on the core integrated circuit board: the analog quantity acquisition module is used for acquiring environmental data of the environment where the satellite is located and running state data of an external module mounted on the satellite; the measurement and control module is used for receiving and processing the uplink remote control signal to obtain uplink remote control data; the navigation information processing module is used for receiving and processing the original navigation signal to obtain effective navigation data; the central processing module is used for processing the environment data, the running state data, the uplink remote control data and the effective navigation data; and sending a drive control signal to the drive module; the central processing module is further used for providing downlink telemetering data to the measurement and control module so that the measurement and control module processes the downlink telemetering data to obtain a downlink telemetering signal; and the driving module is used for driving the corresponding peripheral module to execute corresponding action according to the driving control signal.
Preferably, the measurement and control module is further configured to: and controlling the corresponding peripheral module based on the uplink remote control data.
Preferably, the central processing module includes: each group of processing units is used for processing the same target data to obtain a corresponding processing result, determining whether the processing result meets a preset check condition based on redundancy calculation, and if so, outputting the processing result; wherein the target data comprises one or more of the following data: the environmental data, the operational state data, the uplink remote control command, and the effective navigation data.
Preferably, each set of the processing units includes a flash memory, a DDR (Double Data Rate) operation memory, an FPGA logic processor, and two ARM (Advanced RISC Machine) processors; the flash memory is used for providing an operating program storage space for the group of processing units; the DDR is used for providing data cache for the group of processing units; the FPGA logic processor is used for expanding interface resources; one ARM processor is used for star management, and the other ARM processor is used for attitude and orbit calculation.
Preferably, the integrated satellite integrated electronic system further includes: the data storage module is connected with the central processing module and used for storing the target data; the central processing module is further configured to store the target data into the data storage module and read the target data from the data storage module.
Preferably, the integrated satellite integrated electronic system further includes: the interface module is used for electrically connecting the peripheral module and the load; and the data exchange module is used for establishing communication connection between the central processing module and the measurement and control module, between the multiple groups of processing units of the central processing module and between the central processing module and the interface module.
Preferably, the central processing module is further configured to: and configuring and initializing a switching chipset of the data switching module through an RGMII (Reduced Gigabit Media Independent Interface).
Preferably, the integrated satellite integrated electronic system further includes: the power supply and distribution module is connected with a power supply through the interface module, and is electrically connected with the central processing module and the measurement and control module, and the power supply and distribution module is used for supplying power to the peripheral module correspondingly and feeding back the electric data of the peripheral module which is currently supplied with power to the central processing module according to the control of the central processing module and/or the measurement and control module.
Preferably, the analog quantity acquisition module includes: the satellite sensitive acquisition unit is electrically connected with the central processing module and is used for providing satellite sensitive data to the central processing module; the solar sensitive acquisition unit is electrically connected with the central processing module and is used for providing solar sensitive data for the central processing module; the gyro acquisition unit is electrically connected with the central processing module and is used for providing angular motion induction quantity for the central processing module; the magnetic strength acquisition unit is electrically connected with the central processing module and is used for providing magnetic field induction quantity for the central processing module; the satellite and rocket separation monitoring unit is electrically connected with the central processing module and is used for providing state data of connection between a satellite and a carrier rocket for the central processing module; and the peripheral monitoring unit is electrically connected with the central processing module and is used for providing the running state data of the peripheral module for the central processing module.
Preferably, the driving module includes: the solar panel mechanism is electrically connected with the central processing module and is used for driving the solar panel to move according to the driving control signal; the magnetic torque mechanism is electrically connected with the central processing module and is used for controlling the movement of the magnetic torquer according to the driving control signal; the wheel disc mechanism is electrically connected with the central processing module and is used for controlling the wheel disc assembly to move according to the driving control signal and collecting rotation induction quantity; and the propelling mechanism is electrically connected with the central processing module and is used for controlling the propeller to execute corresponding actions according to the driving control signal.
One or more technical solutions provided in the embodiments of the present invention have at least the following technical effects or advantages:
in the integrated satellite integrated electronic system disclosed in the embodiment of the invention, a core board card is integrally provided with: the system comprises an analog quantity acquisition module, a measurement and control module, a navigation information processing module, a central processing module and a driving module; then, acquiring environmental data of the environment where the satellite is located and running state data of a peripheral module mounted on the satellite through an analog quantity acquisition module; receiving and processing the uplink remote control signal through the measurement and control module to obtain uplink remote control data; receiving and processing an original navigation signal through a navigation information processing module to obtain effective navigation data; the central processing module processes the environmental data, the running state data, the uplink remote control data and the effective navigation data, and sends a driving control signal to the driving module, even provides downlink telemetering data to the measurement and control module, so that the measurement and control module processes the downlink telemetering data to obtain a downlink telemetering signal; finally, the driving module is used for driving the corresponding peripheral module to execute corresponding action according to the driving control signal; on the premise of ensuring that all functions of the satellite are available, all functional modules of the satellite are integrated in one core board card to form an integrated satellite integrated electronic system, so that the central processing module can comprehensively control and manage the electronic system. Therefore, the universality is higher, the expansion of the functional modules in the system is facilitated, the mass production degree of the satellite is facilitated to be improved, and the weight and the volume of the satellite are effectively reduced.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on the drawings without creative efforts.
FIG. 1 is a diagram illustrating an integrated satellite integrated electronic system according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of the CPU module of FIG. 1;
FIG. 3 is a schematic diagram of each group of processing units according to an embodiment of the present invention;
fig. 4 is a schematic diagram of an optimal structure of an integrated satellite integrated electronic system according to an embodiment of the present invention.
Detailed Description
The embodiment of the invention provides an integrated satellite integrated electronic system, which is used for solving the technical problem that the weight and the volume of a satellite cannot be further reduced due to the fact that the batch production degree of the satellite is reduced because of low universality and poor expansibility of each single unit component of the satellite in the prior art.
In order to solve the technical problems, the embodiment of the invention provides the following general ideas:
an integrated satellite integrated electronic system comprising: the core plate card, the integration is provided with on the core plate card: the analog quantity acquisition module is used for acquiring environmental data of the environment where the satellite is located and running state data of an external module mounted on the satellite; the measurement and control module is used for receiving and processing the uplink remote control signal to obtain uplink remote control data; the navigation information processing module is used for receiving and processing the original navigation signal to obtain effective navigation data; the central processing module is used for processing environmental data, running state data, uplink remote control data and effective navigation data; and sending a drive control signal to the drive module; the central processing module is also used for providing downlink telemetering data to the measurement and control module so that the measurement and control module processes the downlink telemetering data to obtain a downlink telemetering signal; and the driving module is used for driving the corresponding peripheral module to execute the corresponding action according to the driving control signal.
By integrating settings on the core board card: the analog quantity acquisition module, the measurement and control module, the navigation information processing module, the central processing module and the driving module are integrated on the core board card on the premise of ensuring that all functions of the satellite are available, so that the mass production degree of the satellite is improved, and the weight and the volume of the satellite are effectively reduced.
First, it is stated that the term "and/or" appearing herein is merely one type of associative relationship that describes an associated object, meaning that three types of relationships may exist, e.g., a and/or B may mean: a exists alone, A and B exist simultaneously, and B exists alone. In addition, the character "/" herein generally indicates that the former and latter related objects are in an "or" relationship.
Referring to fig. 1, an integrated satellite integrated electronic system according to an embodiment of the present invention includes:
the core integrated circuit board 100, the integrated being provided with on the core integrated circuit board 100: the analog quantity acquisition module 101 is used for acquiring environmental data of the environment where the satellite is located and running state data of the peripheral module 102 mounted on the satellite; the measurement and control module 103 is used for receiving and processing the uplink remote control signal to obtain uplink remote control data; the navigation information processing module 104 is used for receiving and processing the original navigation signal to obtain effective navigation data; a central processing module 105 for processing environmental data, operational status data, uplink remote control data and effective navigation data; and sending a drive control signal to the drive module 106; the central processing module 105 is further configured to provide the downlink telemetry data to the measurement and control module 103, so that the measurement and control module 103 processes the downlink telemetry data to obtain a downlink telemetry signal; the driving module 106 is configured to drive the corresponding peripheral module 102 to execute the corresponding action according to the driving control signal.
In the embodiment of the present invention, the analog quantity acquisition module 101 is configured to acquire environmental data of an environment where a satellite is located and operation state data of the peripheral module 102 mounted on the satellite; the measurement and control module 103 is used for receiving and processing the uplink remote control signal to obtain uplink remote control data; the navigation information processing module 104 is used for receiving and processing the original navigation signal to obtain effective navigation data; the central processing module 105 is used for processing environmental data, running state data, uplink remote control data and effective navigation data; and sending a drive control signal to the drive module 106; the central processing module 105 is further configured to provide the downlink telemetry data to the measurement and control module 103, so that the measurement and control module 103 processes the downlink telemetry data to obtain a downlink telemetry signal; the driving module 106 is configured to drive the corresponding peripheral module 102 to execute the corresponding action according to the driving control signal.
Specifically, the analog acquisition module 101 includes, electrically connected to the central processing module 105: a satellite-sensitive acquisition unit (not shown) for providing satellite-sensitive data to the central processing module 105, a solar-sensitive acquisition unit (not shown) for providing solar-sensitive data to the central processing module 105, a gyro acquisition unit (not shown) for providing angular motion induction to the central processing module 105, a magnetic strength acquisition unit (not shown) for providing magnetic field induction to the central processing module 105, a satellite-rocket separation monitoring unit (not shown) for providing satellite-rocket connection status data to the central processing module 105, and a peripheral monitoring unit (not shown) for providing operating status data of the peripheral module 102 to the central processing module 105.
In the specific implementation process, the satellite sensitive acquisition unit can be a satellite sensitive acquisition circuit, the satellite sensitive acquisition circuit converts the imaging result of the satellite sensitive optical assembly into a digital image through photoelectric conversion and analog-to-digital conversion, then provides the digital image to the central processing module 105, and finally realizes the calculation of satellite judgment, single satellite positioning, satellite identification, attitude angle and the like through the central processing module 105; the solar sensitive acquisition unit can be a digital solar sensitive acquisition circuit, the digital solar sensitive acquisition circuit converts an input signal of the solar sensitive optical assembly into a digital solar sensitive signal through photoelectric conversion and analog-to-digital conversion, then the digital solar sensitive signal is provided to the central processing module 105, and finally the central processing module 105 completes the gray scale centroid calculation of the solar facula; the gyro acquisition unit can be a gyro acquisition circuit which is divided into an optical part and an electrical part, the optical part generates a light source and processes the light path, and the electrical part converts a received optical signal into a digital signal through photoelectric conversion, analog-to-digital conversion and inverse modulation digital-to-analog conversion and provides the digital signal for the central processing module 105 to perform three-axis rotation calculation; the magnetic strength acquisition unit can be a magnetometer acquisition circuit which converts signals input by the magnetoresistive sensor component into magnetic strength digital signals through high-precision analog-to-digital conversion and provides the magnetic strength digital signals to the central processing module 105 for magnetic strength calculation; the satellite and rocket separation monitoring unit provides satellite and rocket separation switch signals to the central processing module 105 in real time, so that the central processing module 105 can monitor the state information of the connection between the satellite and the carrier rocket in real time; the peripheral monitoring unit comprises: the sensors include a whole satellite temperature sensor, a pressure sensor, a photosensitive sensor, a power distribution switch state, a power distribution voltage, a power distribution current and the like, and the sensors convert acquired analog quantity signals into digital signals through analog-to-digital conversion, and send the digital signals obtained through respective processing to the central processing module 105.
In the embodiment of the invention, the measurement and control module 103 and the central processing module 105 carry out bidirectional communication through an Ethernet port, and mainly measure and control local machine remote measurement and control data and whole satellite remote measurement and control information. The uplink remote control signal is sent from the ground, enters the measurement and control module 103 through an external measurement and control receiving antenna and a filter, specifically, converts a radio frequency signal into an intermediate frequency signal, enters a baseband of the measurement and control module 103 for processing after the intermediate frequency signal is demodulated and converted, frames the remote control data and sends the remote control data to the central processing module or the load 107; downlink telemetry signals are sent to a baseband processor of the measurement and control module 103 from the central processing module 105 or the load 107, and are modulated, converted and converted to radio frequency signals, and then amplified and sent to the ground through a filter and a measurement and control transmitting antenna, in addition, the measurement and control module 103 can also send direct control instructions to devices on the satellite, such as the peripheral module 102 or the driving module 106, through a network port, an Open Collector (OC) mode, and the like, and further, when the central processing module 105 fails, or when a remote control signal only contains some simple control commands, the devices on the satellite can be directly controlled, the reliability of controlling the devices on the satellite is improved, and the calculation amount of the central processing module 105 is reduced.
In the embodiment of the present invention, the Navigation information processing module 104 may be a GNSS (Global Navigation Satellite System) receiving processing module, and the GNSS receiving processing module includes a radio frequency front end processing (not shown), a Navigation module (not shown), and the like, and amplifies an input GNSS radio frequency signal, converts the radio frequency signal into an intermediate frequency signal by using the radio frequency front end, and provides the intermediate frequency signal to the central processing module 105 through the Navigation module after obtaining effective Navigation data through processing such as filtering, and the central processing module 105 performs positioning and orbit determination calculation to obtain time data, positioning, orbit determination, and extrapolation data, so that the Satellite can obtain Navigation information, time synchronization data, and original observation data.
In an embodiment of the present invention, the central processing module 105 includes: and each group of processing units is used for processing the same target data to obtain a corresponding processing result, determining whether the processing result meets a preset check condition based on redundancy calculation, and if so, outputting the processing result.
Wherein the target data comprises one or more of the following data: environmental data, operating state data, uplink remote control commands and effective navigation data.
Specifically, each group of processing units comprises a flash memory, a DDR (double data rate) run-in memory, an FPGA (field programmable gate array) logic processor and two ARM processors; a flash memory for providing an operating program storage space for the set of processing units; the DDR is used for providing data cache for the group of processing units; the FPGA logic processor is used for expanding interface resources; one ARM processor is used for star management, and the other ARM processor is used for attitude and orbit calculation.
It should be noted that, in an actual implementation process, the number of the processing units 200 of the central processing module 105 may be adjusted according to usage requirements, for example, the central processing module 105 may include one group of the processing units 200, three groups of the processing units 200, five groups of the processing units 200, or even ten groups of the processing units 200; therefore, the embodiments of the present specification are not limited. Referring to fig. 2, the following description is made only by way of example when the central processing module 105 includes three sets of processing units 200:
the three groups of processing units 200 adopt an SOC (System on Chip) as a main processor, the processing units 200 perform data interaction with the other processing units 200 through an ethernet or a bus, each group of processing units 200 is responsible for calculating data received from the central processing module 105 to obtain a processing result in advance, and the processing results obtained by each group of processing units 200 are backed up by using a hot backup, and then the processing results are calculated by adopting triple modular redundancy data to determine whether the processing results meet preset verification conditions, the processing results of each group of processing units 200 and the processing results of the other processing units 200 are compared, the processing results with the same number and the largest number in the comparison results are retained, and the remaining processing results are deleted; or the processing result with the highest total similarity in the comparison results is reserved, and the rest processing results are deleted.
In the following, the processing results of comparing A, B, C three groups of processing units 200 are taken as an example:
if the processing results of the B group and the C group are the same, but the processing results of the A group are different from the processing results of the B group and the C group, only the processing results of the B group and the C group are retained, and the processing results of the A group are deleted; if the three groups of processing results are different, the similarity between the processing result of the group A and the processing result of the group B is 90%, the similarity between the processing result of the group A and the processing result of the group C is 85%, and the similarity between the processing result of the group B and the processing result of the group C is 84%, the processing result of the group A with the highest similarity of the processing results is reserved, the processing results of the group B and the group C are deleted, and the central processing module 105 finally sends a control instruction and access data according to the reserved processing results, so that the input and output reliability of the central processing module 105 is improved.
In addition, referring to the schematic structural diagram of each group of processing units 200 shown in fig. 3, each group of processing units 200 uses one SOC, each SOC includes two ARM processors and an FPGA (Field Programmable Gate Array), one of the ARM processors of each SOC is used for housekeeping management, including flight timing management, flight mission management, thermal control management, power management, data access management, load data management, and the like, and the other ARM processor is used for attitude and orbit control calculation; the FPGA of each SOC is used for hardware interface expansion, load application management, analog quantity acquisition and the like; the DDR memory electrically connected to the SOC provides a high-speed data cache for the processing unit 200, and can load an embedded real-time operating system, so that the application program and the system can run quickly, and the high-capacity and high-reliability Flash memory electrically connected to the SOC provides a running program storage space for the SOC, so that running software can be stored in multiple copies and reliably.
In the embodiment of the present invention, the driving module 106 includes, electrically connected to the central processing module 105: the driving module 106 may further include a solar sailboard mechanism (not shown) for driving the solar sailboard to move according to the driving control signal, a magnetic torquer mechanism (not shown) for controlling the magnetic torquer to move according to the driving control signal, a wheel disc mechanism (not shown) for controlling the wheel disc assembly to move according to the driving control signal, and a propulsion mechanism (not shown) for controlling the propeller to perform a corresponding action according to the driving control signal, and in addition, the driving module 106 may also provide a time synchronization function for the related load 107.
Specifically, the Solar panel mechanism changes the rotational speed of the SADA (Solar Array Drive Assembly) member and the direction of the Solar panel according to the received Drive control signal; according to the received drive control signal, the magnetic moment mechanism changes the direction of the magnetic torquer without delay; according to the received drive control signal, the wheel disc mechanism drives a motor of the wheel disc assembly and changes the direction, and meanwhile, the rotation angle value of the wheel disc is collected; according to the received drive control signal, the propulsion mechanism changes the switch of the electromagnetic valve and the self-locking valve of the propeller without time delay.
In order to ensure the safety of the data on the satellite, a backup needs to be established on the satellite, please refer to fig. 4, the satellite integrated electronic system further includes a data storage module 401 connected to the central processing module 105 for storing the target data; the central processing module 105 is further configured to store the target data in the data storage module 401, and read the target data from the data storage module 401.
In a specific implementation process, the central processing module 105 controls the data storage module 401, specifically, the control of the large-capacity storage chipset is used to realize that the whole satellite telemetry data and the service data of the load 107 are stored as required, and the central processing module 105 reads and processes corresponding data through control modes such as program automatic control or receiving control signals sent by the ground, and then sends the corresponding data to the corresponding load 107, the data transmission module, the measurement and control module 103, and the like for further processing. In addition, the central processing module 105 stores key parameters of satellite affair management, power control, thermal control calculation, attitude control calculation, orbit control calculation, load data and the like into a small-capacity high-reliability storage chip, and reads the parameters on the satellite orbit as required.
In order to facilitate data transmission between the modules of the satellite integrated electronic system and improve the scalability of the satellite integrated electronic system, referring to fig. 4, the satellite integrated electronic system further includes an interface module 402 for electrically connecting the peripheral module 102 and the load; the data exchange module 403 is configured to establish a communication connection between the central processing module 105 and the measurement and control module 103, a communication connection between the groups of processing units 200 of the central processing module 105, and a communication connection between the central processing module 105 and the interface module 402.
In a specific implementation process, the interface module 402 provides a hardware interface for communicating with all the peripheral modules 102, the power supply 108, and the load 107 for the satellite integrated electronic system, where the peripheral modules 102 are related shelf products around the satellite integrated electronic system, and include: the device comprises a star-sensitive optical component, a solar-sensitive optical component, a gyro optical fiber ring component, a magnetic resistance sensor component, a wheel disk component, a magnetic torquer, a propeller, a filter, an antenna, a pressure point switch, an initiating explosive device, a SADA (synthetic aperture radar), a heating band, a temperature sensor and the like.
As an optional implementation manner, the central processing module 105 is further configured to configure and initialize the switching chipset of the data switching module 403 through the RGMII interface, specifically, the central processing module 105 performs data interaction with the data switching module 403 through the ethernet port and configures and initializes the switching chipset through the RGMII interface, where the data switching module 403 provides a multi-channel ethernet interface and adopts a cold backup design, and each device on the satellite performs ethernet data transmission with the measurement and control module 103 and the load through the data switching module 403.
In order to ensure that each device on the satellite can work normally and can control the connection and disconnection of the power supply of each device, referring to fig. 4, the satellite integrated electronic system further includes a power supply and distribution module 404, which is connected to the power supply 108 through an interface module 402 and is electrically connected to the central processing module 105 and the measurement and control module 103, wherein the power supply and distribution module 404 is configured to supply power to the corresponding peripheral module 102 and feed back the electrical data of the peripheral module 102 currently supplying power to the central processing module 105 according to the control of the central processing module 105 and/or the measurement and control module 103.
In the specific implementation process, the power supply and distribution module 404 is composed of a power supply module 4041 and a power distribution module 4042, the power supply module receives power supplies input from the ground, the solar cell array and the storage battery pack, and realizes the functions of reverse current cut-off of the three power supplies, shunt control of the solar cell array, charge and discharge of the storage battery, over-discharge protection of the storage battery pack, a bus voltage and current sampling circuit, bus voltage stabilizing filtering, secondary power supply conversion and the like; the power distribution module is controlled by the central processing module 105 and the measurement and control module 103, provides a primary power supply and a secondary power supply power distribution path for each device on the satellite, and feeds back sampling circuit data such as the switching state, voltage, current and the like of each power distribution path to the central processing module 105.
The technical scheme in the embodiment of the invention at least has the following technical effects or advantages:
1. the integrated satellite integrated electronic system disclosed by the embodiment of the invention is characterized in that the integrated satellite integrated electronic system is integrated on a core board card and comprises the following components: the analog quantity acquisition module, the measurement and control module, the navigation information processing module, the central processing module and the driving module are integrated on the core board card on the premise of ensuring that all functions of the satellite are available, so that the mass production degree of the satellite is improved, and the weight and the volume of the satellite are effectively reduced.
2. Because the measurement and control module 103 can send a direct control instruction to a device on the satellite, for example, the peripheral module 102 or the driving module 106, through a network port, an OC, and the like, when the central processing module 105 fails, or when the remote control signal only contains some simple control commands, the device on the satellite can be directly controlled, the reliability of controlling the device on the satellite is improved, and the calculation amount of the central processing module 105 is reduced.
3. Because each group of processing units 200 is responsible for calculating the data received from the central processing module 105 to obtain a processing result in advance, and the processing result obtained by each group of processing units 200 is backed up by using a hot backup, and then the triple modular redundancy data calculation is adopted to determine whether the processing result meets the preset check condition, the central processing module 105 finally sends a control instruction and accesses data according to the reserved processing result, and the input and output reliability of the central processing module 105 is improved.
While preferred embodiments of the present invention have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the appended claims be interpreted as including preferred embodiments and all such alterations and modifications as fall within the scope of the invention.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present invention without departing from the spirit and scope of the invention. Thus, if such modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include such modifications and variations.
Claims (10)
1. An integrated satellite integrated electronic system, comprising: the core integrated circuit board, the integration is provided with on the core integrated circuit board:
the analog quantity acquisition module is used for acquiring environmental data of the environment where the satellite is located and running state data of an external module mounted on the satellite;
the measurement and control module is used for receiving and processing the uplink remote control signal to obtain uplink remote control data;
the navigation information processing module is used for receiving and processing the original navigation signal to obtain effective navigation data;
the central processing module is used for processing the environment data, the running state data, the uplink remote control data and the effective navigation data; and sending a drive control signal to the drive module; the central processing module is further used for providing downlink telemetering data to the measurement and control module so that the measurement and control module processes the downlink telemetering data to obtain a downlink telemetering signal;
and the driving module is used for driving the corresponding peripheral module to execute corresponding action according to the driving control signal.
2. The system of claim 1, wherein the instrumentation module is further to: and controlling the corresponding peripheral module based on the uplink remote control data.
3. The system of claim 1, wherein the central processing module comprises:
each group of processing units is used for processing the same target data to obtain a corresponding processing result, determining whether the processing result meets a preset check condition based on redundancy calculation, and if so, outputting the processing result;
wherein the target data comprises one or more of the following data: the environmental data, the operational state data, the uplink remote control command, and the effective navigation data.
4. The system of claim 3, wherein each set of the processing units comprises a flash memory, a DDR runtime memory, an FPGA logic processor, and two ARM processors;
the flash memory is used for providing an operating program storage space for the group of processing units;
the DDR is used for providing data cache for the group of processing units;
the FPGA logic processor is used for expanding interface resources;
one ARM processor is used for star management, and the other ARM processor is used for attitude and orbit calculation.
5. The system of claim 3, further comprising:
the data storage module is connected with the central processing module and used for storing the target data;
the central processing module is further configured to store the target data into the data storage module and read the target data from the data storage module.
6. The system of claim 3, further comprising:
the interface module is used for electrically connecting the peripheral module and the load;
and the data exchange module is used for establishing communication connection between the central processing module and the measurement and control module, between the multiple groups of processing units of the central processing module and between the central processing module and the interface module.
7. The system of claim 6, wherein the central processing module is further configured to:
the switching chipset of the data switching module is configured and initialized via the RGMII interface.
8. The system of claim 6, further comprising:
the power supply and distribution module is connected with a power supply through the interface module, and is electrically connected with the central processing module and the measurement and control module, and the power supply and distribution module is used for supplying power to the peripheral module correspondingly and feeding back the electric data of the peripheral module which is currently supplied with power to the central processing module according to the control of the central processing module and/or the measurement and control module.
9. The system of claim 1, wherein the analog acquisition module comprises:
the satellite sensitive acquisition unit is electrically connected with the central processing module and is used for providing satellite sensitive data to the central processing module;
the solar sensitive acquisition unit is electrically connected with the central processing module and is used for providing solar sensitive data for the central processing module;
the gyro acquisition unit is electrically connected with the central processing module and is used for providing angular motion induction quantity for the central processing module;
the magnetic strength acquisition unit is electrically connected with the central processing module and is used for providing magnetic field induction quantity for the central processing module;
the satellite and rocket separation monitoring unit is electrically connected with the central processing module and is used for providing state data of connection between a satellite and a carrier rocket for the central processing module;
and the peripheral monitoring unit is electrically connected with the central processing module and is used for providing the running state data of the peripheral module for the central processing module.
10. The system of claim 1, wherein the drive module comprises:
the solar panel mechanism is electrically connected with the central processing module and is used for driving the solar panel to move according to the driving control signal;
the magnetic torque mechanism is electrically connected with the central processing module and is used for controlling the movement of the magnetic torquer according to the driving control signal;
the wheel disc mechanism is electrically connected with the central processing module and is used for controlling the wheel disc assembly to move according to the driving control signal and collecting rotation induction quantity;
and the propelling mechanism is electrically connected with the central processing module and is used for controlling the propeller to execute corresponding actions according to the driving control signal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110039918.7A CN112859687A (en) | 2021-01-13 | 2021-01-13 | Integrated satellite integrated electronic system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110039918.7A CN112859687A (en) | 2021-01-13 | 2021-01-13 | Integrated satellite integrated electronic system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112859687A true CN112859687A (en) | 2021-05-28 |
Family
ID=76003118
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110039918.7A Pending CN112859687A (en) | 2021-01-13 | 2021-01-13 | Integrated satellite integrated electronic system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112859687A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116400580A (en) * | 2023-06-08 | 2023-07-07 | 上海航天空间技术有限公司 | Multi-redundancy control integrated electronic system and implementation method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102062645A (en) * | 2010-11-01 | 2011-05-18 | 航天东方红卫星有限公司 | Matrix multi-path temperature detection circuit for small satellite platform |
| CN102364908A (en) * | 2011-10-21 | 2012-02-29 | 深圳航天东方红海特卫星有限公司 | Information transmission system and method based on satellite-borne electronic equipment |
| CN103064392A (en) * | 2012-12-28 | 2013-04-24 | 中国人民解放军国防科学技术大学 | Satellite borne integrated electronic system |
| CN104182305A (en) * | 2014-08-28 | 2014-12-03 | 上海航天电子通讯设备研究所 | Triple modular redundancy control and data management computer and using method thereof |
| CN205910547U (en) * | 2016-08-03 | 2017-01-25 | 深圳航天东方红海特卫星有限公司 | Star of integration carries integration electronic system |
| CN111268174A (en) * | 2020-02-27 | 2020-06-12 | 上海利正卫星应用技术有限公司 | Integrated micro-nano satellite electronic system |
-
2021
- 2021-01-13 CN CN202110039918.7A patent/CN112859687A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102062645A (en) * | 2010-11-01 | 2011-05-18 | 航天东方红卫星有限公司 | Matrix multi-path temperature detection circuit for small satellite platform |
| CN102364908A (en) * | 2011-10-21 | 2012-02-29 | 深圳航天东方红海特卫星有限公司 | Information transmission system and method based on satellite-borne electronic equipment |
| CN103064392A (en) * | 2012-12-28 | 2013-04-24 | 中国人民解放军国防科学技术大学 | Satellite borne integrated electronic system |
| CN104182305A (en) * | 2014-08-28 | 2014-12-03 | 上海航天电子通讯设备研究所 | Triple modular redundancy control and data management computer and using method thereof |
| CN205910547U (en) * | 2016-08-03 | 2017-01-25 | 深圳航天东方红海特卫星有限公司 | Star of integration carries integration electronic system |
| CN111268174A (en) * | 2020-02-27 | 2020-06-12 | 上海利正卫星应用技术有限公司 | Integrated micro-nano satellite electronic system |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116400580A (en) * | 2023-06-08 | 2023-07-07 | 上海航天空间技术有限公司 | Multi-redundancy control integrated electronic system and implementation method |
| CN116400580B (en) * | 2023-06-08 | 2023-08-08 | 上海航天空间技术有限公司 | Multi-redundancy control integrated electronic system and implementation method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110040263B (en) | Micro satellite information system based on CAN bus | |
| CN103064392B (en) | Satellite borne integrated electronic system | |
| CN201000576Y (en) | Flight control system for unmanned plane | |
| CN104460427A (en) | Integrated electronic system for modular microsatellite platform | |
| CN111306997A (en) | Electric system and electric control method of carrier rocket | |
| CN110544328A (en) | embedded high-energy-efficiency computing platform and method for airborne fault prediction and health management | |
| CN108100308B (en) | Reconfigurable veneer skin satellite system | |
| CN102096657B (en) | System-on-chip (SOC)-based micro information processing module | |
| CN112859687A (en) | Integrated satellite integrated electronic system | |
| CN106248051B (en) | missile flying parameter recording device | |
| CN112596799A (en) | Extensible universal airborne task management system | |
| CN102514736B (en) | Swing mechanism controller | |
| CN110030883A (en) | A kind of highly reliable carrier rocket final stage stays rail application system framework | |
| CN110487260A (en) | A kind of spacecraft attitude determines intelligent star sensor and its attitude determination method | |
| CN110837093A (en) | Remote sensing micro-nano satellite integrated information processing platform | |
| CN211041964U (en) | Rocket-borne integrated electronic system | |
| CN209230638U (en) | A kind of navigation control system based on multi-core processor | |
| CN112384444B (en) | Unmanned aerial vehicle with automatic renewable energy charging system | |
| CN208459852U (en) | A kind of unmanned aerial vehicle control system | |
| Kayal et al. | BEESAT: a pico satellite for the on orbit verification of micro wheels | |
| CN111490804A (en) | Integrated communication device and communication method for unmanned ship | |
| CN109976221A (en) | Final stage stays the processing method of rail application system perfect form integrated electronics framework | |
| CN112711214A (en) | Flight navigation data loader based on FPGA | |
| CN113359863A (en) | Unmanned aerial vehicle remote control system that takes off | |
| CN113467506A (en) | Core board design-based domestic flight controller and design method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20210528 |