CN113610424A - Satellite full-function modularized simulation system, simulation processing method and electronic equipment - Google Patents
Satellite full-function modularized simulation system, simulation processing method and electronic equipment Download PDFInfo
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Abstract
The application provides a satellite full-function modularized simulation system, a simulation processing method and electronic equipment, wherein the simulation system comprises a satellite basic module and a measurement and control data transmission ground detection module; the satellite basic module is in communication connection with the measurement and control data transmission ground detection module and is used for compressing state information of each single machine in the acquired satellite full-function modularized simulation system to obtain telemetering information and sending the telemetering information to the measurement and control data transmission ground detection module; the measurement and control data transmission ground detection module is in communication connection with the ground test system and used for decoding the received telemetering information and sending the state information obtained after decoding to the ground test system so that the ground test system can visually display the operation state information. Therefore, the simulation system has the data transmission test function, simulates the basic general function of a common satellite, and can change, expand and flexibly simulate different functions of the satellite.
Description
Technical Field
The present disclosure relates to the field of satellite simulation technologies, and in particular, to a satellite full-function modularized simulation system, a simulation processing method, and an electronic device.
Background
The satellite is a natural celestial body which surrounds a planetary orbit and periodically runs according to a closed orbit, an artificial satellite can also be a satellite generally, the artificial satellite has wide application range, and some artificial satellites are provided with photographic equipment for photographing and reconnaissance the ground, surveying resources and the like; some devices are provided with astronomical observation equipment for astronomical observation; some are equipped with communication relay equipment for relaying broadcasts, television, etc.
With the progress of satellite technology and the continuous expansion of satellite applications, the space task to be performed by satellite products is increasingly complex, which results in the increasing challenges in the design and implementation of satellite simulation systems. The existing satellite simulation processing system has incomplete functions, inflexible functions and no additional function simulation, so that the improvement of the comprehensiveness of the functions of the satellite simulation processing system is a technical problem to be solved urgently.
Disclosure of Invention
In view of this, an object of the present application is to provide a full-function modularized simulation system for a satellite, a simulation processing method and an electronic device, which can implement a simulation system of a full-function module for a satellite, so that the function of the satellite simulation system is generalized and modularized, and thus basic general functions of a general satellite, such as a transmission test function, can be simulated, and thus state information on the satellite is transmitted to the ground in the simulation system.
The embodiment of the application provides a satellite full-function modularized simulation system, which comprises a satellite basic module and a measurement and control data transmission ground detection module; wherein,
the satellite basic module is in communication connection with the measurement and control data transmission ground detection module and is used for compressing the acquired state information of each single machine in the satellite full-function modularized simulation system to obtain telemetering information and sending the telemetering information to the measurement and control data transmission ground detection module;
the measurement and control data transmission ground detection module is in communication connection with the ground test system and used for decoding the received telemetering information and sending the state information obtained after decoding to the ground test system so that the ground test system can visually display the operation state information.
Furthermore, the simulation system also comprises a satellite attitude dynamics module and a navigation simulation source module which are in communication connection with the satellite base module; the satellite infrastructure module includes an attitude calculation unit, wherein,
the navigation simulation source module is used for sending navigation information of a satellite to the satellite basic module;
the satellite attitude dynamics module is used for sending attitude dynamics motion information of the satellite in an external space environment to the attitude calculation unit;
the attitude calculation unit is used for determining the current attitude information of the satellite according to the received attitude dynamic motion information and adjusting the attitude of the satellite based on the current attitude information of the satellite and the received navigation information of the satellite.
Further, the satellite base module comprises a satellite calculation unit, a load unit and a data transmission unit, both of which are in communication connection with the satellite calculation unit, and the load unit is in communication connection with the data transmission unit, wherein,
the satellite calculation unit is used for receiving a task scheduling request of a satellite, performing parameter configuration on the satellite based on the task scheduling request and sending a task scheduling instruction to the load unit;
the load unit is used for carrying out task test on the satellite according to the received task scheduling instruction to obtain task test data and sending the task test data to the data transmission unit;
the data transmission unit is used for sending the received task test data to the measurement and control data transmission ground detection module;
the measurement and control data transmission ground detection module is used for sending the received task test data to the ground test system so that the ground test system can visually display the task test data.
Further, the satellite basic module comprises a measurement and control unit which is in communication connection with the satellite calculation unit, wherein,
the measurement and control data transmission ground detection module is used for receiving a task control instruction sent by the ground test system and sending the task control instruction to the measurement and control unit;
the measurement and control unit is used for receiving the task control instruction and sending the task control instruction to the star calculation unit;
the satellite calculation unit is used for receiving the task control instruction sent by the measurement and control unit, performing task control on the satellite based on the task control instruction, obtaining satellite task acquisition information data, and then sending the satellite work debugging information and the information acquired by the task to the ground test system, so that the ground test system can monitor the satellite state and the task result.
Furthermore, the simulation system comprises a power module, the power module is in communication connection with the satellite base module, and the power module is used for supplying power to the satellite base module.
The embodiment of the application also provides a satellite full-function modularized simulation processing method, which comprises the following steps:
compressing the acquired state information of each single machine in the satellite full-function modular simulation system to obtain telemetering information;
and decoding the telemetering information, and sending the state information obtained after decoding to the ground test system so as to be conveniently displayed visually by the ground test system.
Further, the simulation processing method further includes:
acquiring navigation information of a satellite;
acquiring attitude dynamic motion information of a satellite in an external space environment;
determining current attitude information of the satellite based on the attitude dynamic motion information of the satellite in the external space environment;
adjusting the attitude of the satellite based on the current attitude information of the satellite and the received navigation information of the satellite.
Further, the simulation processing method further includes:
receiving a task scheduling request of a satellite, performing parameter configuration on the satellite based on the task scheduling request, and sending a task scheduling instruction;
and performing task testing on the satellite based on the task scheduling instruction to obtain task testing data, and issuing the task testing data to the ground testing system so that the ground testing system can visually display the task testing data.
An embodiment of the present application further provides an electronic device, including: a processor, a memory and a bus, the memory storing machine readable instructions executable by the processor, the processor and the memory communicating via the bus when the electronic device is running, the machine readable instructions when executed by the processor performing the steps of the satellite full-function modular simulation processing method as described above.
Embodiments of the present application further provide a computer-readable storage medium, where a computer program is stored on the computer-readable storage medium, and when the computer program is executed by a processor, the computer program performs the steps of the simulation processing method for fully functional modularization of satellites as described above.
The application provides a satellite full-function modularized simulation system, a simulation processing method and electronic equipment, wherein the simulation system comprises a satellite basic module and a measurement and control data transmission ground detection module; the satellite basic module is in communication connection with the measurement and control data transmission ground detection module and is used for compressing the acquired state information of each single machine in the satellite full-function modular simulation system to obtain telemetering information and sending the telemetering information to the measurement and control data transmission ground detection module; the measurement and control data transmission ground detection module is in communication connection with the ground test system and used for decoding the received telemetering information and sending the state information obtained after decoding to the ground test system so that the ground test system can visually display the operation state information.
Therefore, the simulation system of the satellite full-function module can be realized, so that the satellite simulation system has comprehensive and modularized functions, can simulate basic general functions of a common satellite, including a housekeeping management function, an attitude control simulation function, a satellite-ground communication function, a navigation function, a load test function and a data transmission function, can test one or more modules in the simulation system, is convenient and flexible to build, and can be recombined to adapt to different simulation tasks.
In order to make the aforementioned objects, features and advantages of the present application more comprehensible, preferred embodiments accompanied with figures are described in detail below.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present application and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained from the drawings without inventive effort.
Fig. 1 is a schematic structural diagram of a fully functional modular satellite simulation system according to an embodiment of the present disclosure;
fig. 2 is a schematic structural diagram of a satellite infrastructure module in a fully functional modular simulation system for satellites according to an embodiment of the present disclosure;
fig. 3 is a schematic structural diagram of a wireless connection of a fully functional modular satellite simulation system according to an embodiment of the present disclosure;
fig. 4 is a schematic structural diagram of a cable connection of a fully functional modular satellite simulation system according to an embodiment of the present disclosure;
fig. 5 is a flowchart of a simulation processing method for fully functional modularization of a satellite according to an embodiment of the present application;
fig. 6 is a flowchart of another simulation processing method for fully functional modularization of a satellite according to an embodiment of the present application;
fig. 7 is a flowchart of another simulation processing method for fully functional modularization of a satellite according to an embodiment of the present application;
fig. 8 is a flowchart of another simulation processing method for fully functional modularization of a satellite according to an embodiment of the present application;
fig. 9 is a schematic structural diagram of an electronic device according to an embodiment of the present application.
Icon: 100-a simulation system; 110-a satellite base module; 111-attitude calculation unit; 112-a star calculation unit; 113-a load cell; 114-a data transmission unit; 115-a measurement and control unit; 116-a navigation unit; 120-measurement and control data transmission ground detection module; 130-satellite attitude dynamics module; 140-navigation simulation source module; 150-a power module; 900-an electronic device; 910-a processor; 920-a memory; 930-bus.
Detailed Description
To make the purpose, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it should be understood that the drawings in the present application are for illustrative and descriptive purposes only and are not used to limit the scope of protection of the present application. Additionally, it should be understood that the schematic drawings are not necessarily drawn to scale. The flowcharts used in this application illustrate operations implemented according to some embodiments of the present application. It should be understood that the operations of the flow diagrams may be performed out of order, and that steps without logical context may be performed in reverse order or concurrently. One skilled in the art, under the guidance of this application, may add one or more other operations to, or remove one or more operations from, the flowchart.
In addition, the described embodiments are only a part of the embodiments of the present application, and not all of the embodiments. The components of the embodiments of the present application, generally described and illustrated in the figures herein, can be arranged and designed in a wide variety of different configurations. Thus, the following detailed description of the embodiments of the present application, presented in the accompanying drawings, is not intended to limit the scope of the claimed application, but is merely representative of selected embodiments of the application. All other embodiments, which can be derived by a person skilled in the art from the embodiments of the present application without making any creative effort, shall fall within the protection scope of the present application.
To enable those skilled in the art to utilize the present disclosure, the following embodiments are presented in conjunction with a specific application scenario, "satellite simulation," which is intended to enable those skilled in the art to apply the general principles defined herein to other embodiments and application scenarios without departing from the spirit and scope of the present disclosure.
The method, system, electronic device or computer-readable storage medium described in the embodiments of the present application may be applied to any scenario in which satellite simulation is required, and the embodiments of the present application do not limit a specific application scenario, and any scheme that uses the simulation system and the simulation processing method of the satellite full-function modularization provided in the embodiments of the present application is within the scope of the present application.
It is noted that, with the progress of satellite technology and the continuous expansion of satellite applications, the space task to be performed by the satellite product is increasingly complex, which makes the challenges in designing and implementing the satellite simulation system more severe. The existing satellite simulation processing system has incomplete functions, inflexible functions and no additional function simulation, so that the improvement of the comprehensiveness of the functions of the satellite simulation processing system is a technical problem to be solved urgently.
Based on the above, the application provides a full-function modularized simulation system for a satellite, wherein the simulation system comprises a satellite basic module and a measurement and control data transmission ground detection module; the satellite basic module is in communication connection with the measurement and control data transmission ground detection module and is used for compressing the acquired state information of each single machine in the satellite full-function modular simulation system to obtain telemetering information and sending the telemetering information to the measurement and control data transmission ground detection module; the measurement and control data transmission ground detection module is in communication connection with the ground test system and used for decoding the received telemetering information and sending the state information obtained after decoding to the ground test system so that the ground test system can visually display the operation state information.
Therefore, the simulation system of the satellite full-function module can be realized, so that the satellite simulation system has comprehensive and modularized functions, can simulate basic general functions of a common satellite, including a housekeeping management function, an attitude control simulation function, a satellite-ground communication function, a navigation function, a load test function and a data transmission function, can test one or more modules in the simulation system, is convenient and flexible to build, and can be recombined to adapt to different simulation tasks. Further, a fully functional modular satellite simulation system 100 as disclosed herein is described.
Referring to fig. 1, fig. 1 is a schematic structural diagram of a full-function modularized simulation system for a satellite according to an embodiment of the present disclosure, as shown in fig. 1, a simulation system 100 includes a satellite base module 110 and a measurement and control data transmission ground inspection module 120; the satellite base module 110 is in communication connection with the measurement and control data transmission ground detection module 120, and is configured to compress the acquired state information of each single machine in the satellite full-function modular simulation system 100 to obtain telemetry information, and send the telemetry information to the measurement and control data transmission ground detection module 120; the measurement and control data transmission ground detection module 120 is in communication connection with the ground test system, and is configured to decode the received telemetry information and send the state information obtained after decoding to the ground test system, so that the ground test system can visually display the operation state information.
Specifically, the satellite infrastructure module 110 collects status information of all the single computers in the simulation system 100, compresses and packages the status information of each single computer to form telemetry information, and sends the telemetry information to the measurement and control data transmission ground inspection module 120, the measurement and control data transmission ground inspection module 120 decodes the received telemetry information to obtain the status information of each single computer, and sends the status information to the ground test system, so that the status information is visually displayed in the ground test system for operators to check in time.
Here, the state information of the single machine is the operation state information of all the modules in the simulation system 100.
Further, as shown in fig. 1, the simulation system 100 further includes a satellite attitude dynamics module 130 and a navigation simulation source module 140, both of which are communicatively connected to the satellite base module 110; the satellite infrastructure module comprises an attitude calculation unit, wherein the navigation simulation source module 140 is configured to send navigation information of a satellite to the satellite infrastructure module 110; the satellite attitude dynamics module 130 is configured to send attitude dynamics motion information of the satellite in the external space environment to the attitude calculation unit; the attitude calculation unit is used for determining the current attitude information of the satellite according to the received attitude dynamic motion information and adjusting the attitude of the satellite based on the current attitude information of the satellite and the received navigation information of the satellite.
Here, the navigation simulation source module 140 may provide simulation information of the GPS/BD navigation satellites for the navigation module of the satellite simulation platform.
Here, the satellite attitude dynamics module 130 transmits attitude dynamics motion information of the satellite in the external spatial environment to the attitude calculation unit.
Here, the attitude calculation unit is in communication interaction with the satellite attitude dynamics module 130 through an RS422 interface, and the attitude calculation unit calculates current attitude information of the satellite according to initial attitude dynamics motion information of the attitude dynamics motion information provided by the satellite attitude dynamics module 130 in the case where no attitude sensor (star sensor, sun sensor), attitude measurement component (magnetometer, gyroscope), and attitude adjustment component (reaction flywheel, magnetic torquer) are configured, and performs attitude simulation adjustment on the satellite according to the received positioning broadcast of the navigation information of the satellite and the current attitude information of the satellite, which can simulate the actual working state of the attitude calculation unit.
Further, as shown in fig. 1, the simulation system 100 includes a power module 150, the power module 150 is communicatively connected to the satellite base module 110, and the power module 150 is configured to supply power to the satellite base module 110.
Here, the power module 150 may provide a power supply capability of 100V, 4 kW.
Further, please refer to fig. 2 for a schematic structural diagram of a satellite infrastructure module in a fully functional modularized simulation system of a satellite according to an embodiment of the present disclosure, as shown in fig. 2, the satellite infrastructure module 110 includes a satellite calculation unit 112, a load unit 113, and a data transmission unit 114, both of which are communicatively connected to the satellite calculation unit 112, and the load unit 113 is communicatively connected to the data transmission unit 114, wherein the satellite calculation unit 112 is configured to receive a task scheduling request of a satellite, perform parameter configuration on the satellite based on the task scheduling request, and send a task scheduling instruction to the load unit 113; the load unit 113 is configured to perform a task test on the satellite according to the received task scheduling instruction, obtain task test data, and send the task test data to the data transmission unit 114; the data transmission unit 114 is configured to send the received task test data to the measurement and control data transmission ground inspection module 120; the measurement and control data transmission ground inspection module 120 is configured to send the received task test data to the ground test system, so that the ground test system can visually display the task test data.
Here, the housekeeping computing unit 112 includes Can, RS422, RS485, LVDS, pulse per second, GPIO interface, OC command interface, analog quantity acquisition interface, temperature control loop interface, and power interface.
Here, the star service calculating unit 112 is communicatively connected to the load unit 113 and the data transmission unit 114, and communicates via the CAN interface, and data transmission is performed between the data transmission unit 114 and the load unit 113 via LVDS. When the star computing unit 112 makes a task scheduling request, the load unit 113 sends task test data generated when working according to the task scheduling instruction to the data transmission unit 114 through LVDS, and the data transmission unit 114 sends the task test data of the load unit to the measurement and control data transmission ground inspection module 120.
Here, the task scheduling request is to execute a camera device, a communication device, or other devices.
Further, as shown in fig. 2, the satellite infrastructure module 110 includes a measurement and control unit 115, and the measurement and control unit 115 is in communication connection with the satellite calculation unit 112, wherein the measurement and control data transmission ground inspection module 120 is configured to receive a fault decision control instruction sent by the ground test system, and send the fault decision control instruction to the measurement and control unit 115; the measurement and control unit 115 is configured to receive the fault decision control instruction and send the fault decision control instruction to the house service computing unit 112; the satellite calculation unit 112 is configured to receive the fault decision control instruction sent by the measurement and control unit 115, maintain a fault of the satellite based on the fault decision control instruction, obtain operation information after satellite maintenance processing, and send the operation information after satellite maintenance processing to the ground test system, so that the ground test system monitors the fault maintenance of the satellite. Further, the satellite infrastructure module 110 includes a navigation unit 116, and the navigation unit 116 is communicatively connected to the star computing unit 112.
Here, the house keeping unit 112 is connected to the measurement and control unit 115 by wire, and communicates with the measurement and control unit 115 through the CAN interface and the RS422 interface.
The ground test system judges the working condition of the satellite according to the received running state information and task test data, judges whether the working condition of the satellite fails or not, determines a failed part of the satellite and determines a decision for solving the failure if the working condition of the satellite fails, sends a failure decision control instruction to the housekeeping computing unit 112 after the failed part and the failure decision are determined, the housekeeping computing unit 112 adjusts and maintains the failed part of the satellite according to the failure decision control instruction to obtain running information after the satellite maintenance, and the housekeeping computing unit 112 sends the running information after the satellite maintenance to the ground test system so as to realize that the ground test system monitors the failure maintenance of the satellite.
Here, the method further includes that the housekeeping computing unit 112 collects and packages state information of all the single machines on the simulation system 100 to form telemetry information, and sends the telemetry information to the measurement and control unit 115 through the RS422, and the measurement and control unit 115 is responsible for sending the received telemetry information of the housekeeping computing unit 112 to the measurement and control data transmission ground inspection module 120.
Further, as shown in fig. 2, the satellite infrastructure module 110 includes an attitude calculation unit 111, and the attitude calculation unit 111 is configured to determine current attitude information of the satellite according to the received attitude kinetic motion information, and adjust the attitude of the satellite based on the current attitude information of the satellite and the received navigation information of the satellite.
Further, please refer to fig. 3, as shown in fig. 3, which is a schematic structural diagram of a wireless connection of a satellite full-function modularized simulation system provided in an embodiment of the present application, in which, as shown in fig. 3, the data transmission unit 114 is connected to a first data transmission antenna by wire, and transmits task test data to a second data transmission antenna based on the first data transmission antenna, where the second data transmission antenna is connected to the measurement and control data transmission ground detection module 120 by wire, and the second data transmission antenna transmits the task test data to the measurement and control data transmission ground detection module 120; further, the first measurement and control antenna is connected to the measurement and control unit 115 by a wire, and the measurement and control unit 115 sends the telemetry information to the second measurement and control antenna based on the first measurement and control antenna, wherein the second measurement and control antenna is connected to the measurement and control data transmission ground detection module 120 by a wire, and the second measurement and control antenna transmits the telemetry information to the measurement and control data transmission ground detection module 120. Further, the navigation simulation source module is connected to the second navigation antenna via a wire, and sends out navigation information to the first navigation antenna via the second navigation antenna, and the first navigation antenna provides the navigation information to the navigation unit 116 of the satellite base module 110.
Here, the measurement and control data transmission ground inspection module 120 is connected to the second measurement and control antenna, the second measurement and control antenna and the ground test system by wire, the second measurement and control antenna can receive the telemetry information sent by the first measurement and control antenna, the measurement and control data transmission ground inspection module 120 decodes the telemetry information to obtain the state information after receiving the telemetry information, then sends the state information to the ground test system, the ground test system unpacks and analyzes the state information, and then can display the received telemetry information in a visual form. And the ground test system can send an instruction to the satellite base module 110, and the sent instruction is sent from the ground test system to the measurement and control data transmission ground inspection module 120 and then sent to the satellite base module 110 through the second measurement and control antenna.
Further, please refer to fig. 4, fig. 4 is a schematic structural diagram of a wired connection of a fully-functional modular satellite simulation system according to an embodiment of the present disclosure. As shown in fig. 4, the data transmission unit 114 and the measurement and control unit 115 are connected to the measurement and control data transmission ground inspection module 120 by wires, and the navigation unit 116 is connected to the navigation simulation source module 140 by wires, so as to realize fast data transmission in the simulation system 100.
The application provides a satellite full-function modularized simulation system, which comprises a satellite basic module and a measurement and control data transmission ground detection module; the satellite basic module is in communication connection with the measurement and control data transmission ground detection module and is used for compressing the acquired state information of each single machine in the satellite full-function modular simulation system to obtain telemetering information and sending the telemetering information to the measurement and control data transmission ground detection module; the measurement and control data transmission ground detection module is in communication connection with the ground test system and used for decoding the received telemetering information and sending the state information obtained after decoding to the ground test system so that the ground test system can visually display the operation state information.
Like this, can realize the analog system of satellite full function module for thereby the basic general function that can simulate general satellite of function universalization, modularization of satellite analog system, such as biography test function, gesture analog function, satellite-ground communication function, navigation function and load test function, and can test single or more modules by the different simulation task requirements of adaptation that can be quick.
Referring to fig. 5, fig. 5 is a flowchart of a simulation processing method of a full-function modularized satellite according to an embodiment of the present disclosure, as shown in fig. 5, the simulation processing method includes:
s501: and compressing the acquired state information of each single machine in the satellite full-function modular simulation system to obtain telemetering information.
In the step, the state information of each single computer in the satellite full-function modularized simulation system is collected, and the state information of each single computer is collected and then compressed to obtain the telemetering information.
The single machine is each module in the satellite full-function modularized simulation system, such as other modules or units in the measurement and control data transmission ground detection module, the measurement and control unit, and the like in the simulation system.
Here, the state information is state information of each module in the simulation system performing work operation, such as attitude information in the attitude calculation unit.
S502: and decoding the telemetering information, and sending the state information obtained after decoding to the ground test system so as to be conveniently displayed visually by the ground test system.
In the step, the received telemetering information is decoded to obtain the state information of each single machine after decoding, and the state information is sent to a ground test system so as to be displayed visually in the ground test system.
In the specific embodiment, the description is performed in combination with a full-function modularized simulation system of a satellite, a satellite basic module is controlled to receive state information of each single machine in the full-function modularized simulation system of the satellite, the state information of each single machine is compressed to obtain telemetering information, and the telemetering information is sent to a measurement and control data transmission ground detection module. And the control measurement and control data transmission ground detection module decodes the received telemetering information and sends the state information obtained after decoding to the ground test system so as to be convenient for the ground test system to carry out visual display.
In another embodiment, explained in connection with the satellite full-function modularized simulation system, the housekeeping computing unit in the control satellite basic module receives the state information of each stand-alone in the satellite full-function modularized simulation system and compresses the state information to obtain the telemetric information, then the communication connection with the measurement and control unit is transmitted to the measurement and control unit through the CAN interface and the RS422 interface, the measurement and control unit sends the measurement and control data transmission ground detection module based on the first measurement and control antenna and the measurement and control second antenna, the measurement and control data transmission ground detection module decodes the received remote measurement information to obtain the state information of each single machine, and the state information of each single machine is sent to a ground test system, the ground test system analyzes and processes the state information of each single machine, the status information of each single machine can be displayed in a visual form in the ground test system.
The application provides a satellite full-function modularized simulation processing method, which comprises the following steps: compressing the acquired state information of each single machine in the satellite full-function modular simulation system to obtain telemetering information; and decoding the telemetering information, and sending the state information obtained after decoding to the ground test system so as to be conveniently displayed visually by the ground test system. Therefore, the running state information of each single machine in the satellite full-function modularized simulation system can be comprehensively monitored, and the timeliness of obtaining the running state information of each single machine is effectively improved.
Referring to fig. 6, fig. 6 is a flowchart of another simulation processing method for fully functional modularization of a satellite according to an embodiment of the present application. As shown in fig. 6, the simulation processing method further includes:
s601: navigation information of the satellites is acquired.
In the step, the navigation information of the satellite is obtained by using the position information of the navigation satellite sent by the navigation simulation source module.
S602: attitude dynamic motion information of the satellite in an external space environment is acquired.
In this step, attitude dynamic motion information of the satellite in the external space environment is acquired.
S603: and determining current attitude information of the satellite based on the attitude dynamic motion information of the satellite in the external space environment.
In this step, the current attitude information of the satellite is calculated based on the initial attitude kinetic movement information of the attitude kinetic movement information without the configuration of the attitude sensor (star sensor, sun sensor), the attitude measurement component (magnetometer, gyroscope) and the attitude adjustment component (reaction flywheel, magnetotorquer).
S604: adjusting the attitude of the satellite based on the current attitude information of the satellite and the received navigation information of the satellite.
In the step, the attitude of the satellite is adjusted in a simulation mode according to the acquired current attitude information of the satellite and the navigation information of the satellite sent by the navigation simulation source module.
In a specific embodiment, the description is given by combining a full-function modularized simulation system of a satellite, a navigation simulation source module is controlled to send navigation information of the satellite to a satellite base module, and a satellite attitude dynamics module is controlled to send attitude dynamics motion information of the satellite in an external space environment to an attitude calculation unit; and the control attitude calculation unit determines the current attitude information of the satellite according to the received attitude dynamic motion information and adjusts the attitude of the satellite based on the current attitude information of the satellite and the received navigation information of the satellite.
The application provides a satellite full-function modularized simulation processing method, which comprises the following steps: acquiring navigation information of a satellite; acquiring attitude dynamic motion information of a satellite in an external space environment; determining current attitude information of the satellite based on the attitude dynamic motion information of the satellite in the external space environment; adjusting the attitude of the satellite based on the current attitude information of the satellite and the received navigation information of the satellite. Therefore, when the attitude information of the satellite deviates from the orbit, the attitude of the satellite can be quickly and accurately adjusted.
Referring to fig. 7, fig. 7 is a flowchart of another simulation processing method for fully functional modularization of a satellite according to an embodiment of the present application. As shown in fig. 7, the simulation processing method further includes:
s701: receiving a task scheduling request of a satellite, performing parameter configuration on the satellite based on the task scheduling request, and sending a task scheduling instruction.
In the step, a task scheduling request of the satellite is obtained, the task scheduling request is used for carrying out parameter configuration on the satellite, and a task scheduling instruction is sent.
Here, the task scheduling request requests the load on the satellite to perform the test of the instrument device, such as a camera device, a communication device or other devices.
S702: and performing task testing on the satellite based on the task scheduling instruction to obtain task testing data, and issuing the task testing data to the ground testing system so that the ground testing system can visually display the task testing data.
In the step, the satellite is subjected to task testing according to the task scheduling instruction, so that corresponding task testing data are obtained, and the task testing data are issued to the ground testing system, so that the ground testing system can visually display the task testing data.
Here, the task test is performed according to the task scheduling request, if the task scheduling request is to execute the camera device, the task test is to photograph the ground by using the camera device on the satellite, and the task test data is an image photographed by the camera.
In a specific embodiment, the description is performed by combining a full-function modularized simulation system of a satellite, a satellite computing unit is controlled to receive a task scheduling request of the satellite, the satellite is subjected to parameter configuration based on the task scheduling request, and a task scheduling instruction is sent to a load unit; the control load unit performs task testing on the satellite according to the received task scheduling instruction to obtain task testing data, and sends the task testing data to the data transmission unit; controlling the data transmission unit to compress the received task test data and send the compressed task test data to the measurement and control data transmission ground detection module; and controlling the measurement and control data transmission ground detection module to decode the received compressed task test data to obtain task test data, and sending the task test data to the ground test system so that the ground test system can visually display the task test data.
In another embodiment, the description is given by combining a satellite full-function modular simulation system, task test data is sent to a data transmission unit, the data transmission unit compresses the task test data and sends the compressed task test data by using a first data transmission antenna, a measurement and control data transmission ground inspection module receives the compressed task test data based on a second data transmission antenna, decompresses the compressed task test data to obtain task test data, and sends the task test data to a ground test system for visual display.
The application provides a satellite full-function modularized simulation processing method, which comprises the following steps: receiving a task scheduling request of a satellite, performing parameter configuration on the satellite based on the task scheduling request, and sending a task scheduling instruction; and performing task testing on the satellite based on the task scheduling instruction to obtain task testing data, and issuing the task testing data to the ground testing system so that the ground testing system can visually display the task testing data. Therefore, the satellite can be subjected to the load test, and the load test result is sent to the ground test system for visual display.
Referring to fig. 8, fig. 8 is a flowchart of another simulation processing method for fully functional modularization of satellites according to an embodiment of the present application. As shown in fig. 8, the simulation processing method further includes:
s801: and receiving a task control instruction sent by the ground test system.
In the step, a task control instruction sent by the ground test system is obtained.
Here, for example, the ground test system performs fault determination on the working condition of the satellite according to the received state information and the task test data, determines a fault location and a processing strategy for solving the fault if it is determined that the working condition of the satellite has the fault, and transmits a task control instruction to facilitate maintenance of the fault location of the satellite after determining the fault location and the processing strategy for solving the fault.
S802: and performing task control on the satellite based on the task control instruction, and after satellite task acquisition information data is obtained, sending the satellite work debugging information and the information acquired by the task to the ground test system so as to monitor the satellite state and the task result by the ground test system.
In the step, data are acquired for a task performed on the satellite according to a task control instruction, satellite work debugging information and information acquired by the task are obtained, and the information is sent to a ground test system, so that the ground test system can monitor the satellite state and a task result of the satellite.
Here, for example, if it is determined that the working condition of the payload of the satellite is abnormal, the operating parameters of the payload need to be adjusted so that the operating state of the satellite returns to normal.
In a specific embodiment, the description is given by combining a satellite full-function modular simulation system, and a control measurement and control data transmission ground detection module receives a task control instruction sent by a ground test system and sends the task instruction to a measurement and control unit; controlling the measurement and control unit to receive the task control instruction and send the task control instruction to the star computing unit; and controlling the satellite calculation unit to receive the task control instruction sent by the measurement and control unit, performing task control on the satellite based on the task control instruction, and sending the satellite work debugging information and the information acquired by the task to the ground test system after acquiring satellite task acquisition information data so that the ground test system can monitor the satellite state and the task result.
In another embodiment, the description is given by combining a full-function modularized simulation system of a satellite, a ground test system sends a task control instruction to a measurement and control data transmission ground inspection module, the control measurement and control data transmission ground inspection module sends the task control instruction to a first measurement and control antenna based on a second measurement and control antenna, the first measurement and control antenna then transmits the task control instruction to a measurement and control unit, the measurement and control unit transmits the task control instruction to a satellite calculation unit for instruction execution, the control satellite calculation unit performs task control on the satellite based on the task decision control instruction, and after satellite task acquisition information data is obtained, the satellite work setup information and information acquired by the task are sent to the ground test system, so that the ground test system can monitor the satellite state and the task result.
The application provides a satellite full-function modularized simulation processing method, which receives a task control instruction sent by a ground test system. And performing task control on the satellite based on the task control instruction, and after satellite task acquisition information data is obtained, sending the satellite work debugging information and the information acquired by the task to the ground test system so as to monitor the satellite state and the task result by the ground test system. Therefore, the satellite can be subjected to task control according to the task control instruction sent by the ground test system, and the satellite state and the task result can be monitored.
Referring to fig. 9, fig. 9 is a schematic structural diagram of an electronic device according to an embodiment of the present disclosure. As shown in fig. 9, the electronic device 900 includes a processor 910, a memory 920, and a bus 930.
The memory 920 stores machine-readable instructions executable by the processor 910, when the electronic device 900 runs, the processor 910 communicates with the memory 920 through the bus 930, and when the machine-readable instructions are executed by the processor 910, the steps of the satellite full-function modular simulation processing method in the method embodiments shown in fig. 5 to 8 may be executed.
An embodiment of the present application further provides a computer-readable storage medium, where a computer program is stored on the computer-readable storage medium, and when the computer program is executed by a processor, the computer program may perform the steps of the satellite full-function modular simulation processing method in the method embodiments shown in fig. 5 to fig. 8.
It is clear to those skilled in the art that, for convenience and brevity of description, the specific working processes of the above-described systems, apparatuses and units may refer to the corresponding processes in the foregoing method embodiments, and are not described herein again.
In the several embodiments provided in the present application, it should be understood that the disclosed system, apparatus and method may be implemented in other ways. The above-described embodiments of the apparatus are merely illustrative, and for example, the division of the units is only one logical division, and there may be other divisions when actually implemented, and for example, a plurality of units or components may be combined or integrated into another system, or some features may be omitted, or not executed. In addition, the shown or discussed mutual coupling or direct coupling or communication connection may be an indirect coupling or communication connection of devices or units through some communication interfaces, and may be in an electrical, mechanical or other form.
The units described as separate parts may or may not be physically separate, and parts displayed as units may or may not be physical units, may be located in one place, or may be distributed on a plurality of network units. Some or all of the units can be selected according to actual needs to achieve the purpose of the solution of the embodiment.
In addition, functional units in the embodiments of the present application may be integrated into one processing unit, or each unit may exist alone physically, or two or more units are integrated into one unit.
The functions, if implemented in the form of software functional units and sold or used as a stand-alone product, may be stored in a non-volatile computer-readable storage medium executable by a processor. Based on such understanding, the technical solution of the present application or portions thereof that substantially contribute to the prior art may be embodied in the form of a software product stored in a storage medium and including instructions for causing a computer device (which may be a personal computer, a server, or a network device) to execute all or part of the steps of the method according to the embodiments of the present application. And the aforementioned storage medium includes: various media capable of storing program codes, such as a usb disk, a removable hard disk, a Read-Only Memory (ROM), a Random Access Memory (RAM), a magnetic disk, or an optical disk.
Finally, it should be noted that: the above-mentioned embodiments are only specific embodiments of the present application, and are used for illustrating the technical solutions of the present application, but not limiting the same, and the scope of the present application is not limited thereto, and although the present application is described in detail with reference to the foregoing embodiments, those skilled in the art should understand that: any person skilled in the art can modify or easily conceive the technical solutions described in the foregoing embodiments or equivalent substitutes for some technical features within the technical scope disclosed in the present application; such modifications, changes or substitutions do not depart from the spirit and scope of the exemplary embodiments of the present application, and are intended to be covered by the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. A satellite full-function modularized simulation system is characterized by comprising a satellite basic module and a measurement and control data transmission ground detection module; wherein,
the satellite basic module is in communication connection with the measurement and control data transmission ground detection module and is used for compressing the acquired state information of each single machine in the satellite full-function modularized simulation system to obtain telemetering information and sending the telemetering information to the measurement and control data transmission ground detection module;
the measurement and control data transmission ground detection module is in communication connection with the ground test system and used for decoding the received telemetering information and sending the state information obtained after decoding to the ground test system so that the ground test system can visually display the state information.
2. The satellite full function modular simulation system of claim 1, further comprising a satellite attitude dynamics module and a navigation simulation source module, both communicatively coupled to the satellite base module; the satellite infrastructure module includes an attitude calculation unit, wherein,
the navigation simulation source module is used for sending navigation information of a satellite to the satellite basic module;
the satellite attitude dynamics module is used for sending attitude dynamics motion information of the satellite in an external space environment to the attitude calculation unit;
the attitude calculation unit is used for determining the current attitude information of the satellite according to the received attitude dynamic motion information and adjusting the attitude of the satellite based on the current attitude information of the satellite and the received navigation information of the satellite.
3. The satellite full function modular simulation system of claim 1, wherein the satellite infrastructure module comprises a satellite calculation unit, a load unit, and a data transfer unit, both communicatively coupled to the satellite calculation unit, the load unit and the data transfer unit communicatively coupled, wherein,
the satellite calculation unit is used for receiving a task scheduling request of a satellite, performing parameter configuration on the satellite based on the task scheduling request and sending a task scheduling instruction to the load unit;
the load unit is used for carrying out task test on the satellite according to the received task scheduling instruction to obtain task test data and sending the task test data to the data transmission unit;
the data transmission unit is used for sending the received task test data to the measurement and control data transmission ground detection module;
the measurement and control data transmission ground detection module is used for sending the received task test data to the ground test system so that the ground test system can visually display the task test data.
4. The fully functional modular satellite simulation system of claim 3, wherein the satellite infrastructure module comprises a measurement and control unit communicatively coupled to the satellite computing unit, wherein,
the measurement and control data transmission ground detection module is used for receiving a task control instruction sent by the ground test system and sending the control instruction to the measurement and control unit;
the measurement and control unit is used for receiving the control instruction and sending the control instruction to the star calculation unit;
the satellite calculation unit is used for receiving the task control instruction sent by the measurement and control unit, performing task control on the satellite based on the task control instruction, obtaining satellite task acquisition information data, and then sending the satellite work debugging information and the information acquired by the task to the ground test system, so that the ground test system can monitor the satellite state and the task result.
5. The satellite full function modular simulation system of claim 1, comprising a power module communicatively coupled to the satellite base module, the power module configured to provide power to the satellite base module.
6. A full-function modularized simulation processing method for a satellite, which is applied to the simulation system for a full-function modularized satellite according to any one of claims 1-5, the simulation processing method comprising:
compressing the acquired state information of each single machine in the satellite full-function modular simulation system to obtain telemetering information;
and decoding the telemetering information, and sending the state information obtained after decoding to the ground test system so as to be conveniently displayed visually by the ground test system.
7. The method of claim 6, further comprising:
acquiring navigation information of a satellite;
acquiring attitude dynamic motion information of a satellite in an external space environment;
determining current attitude information of the satellite based on the attitude dynamic motion information of the satellite in the external space environment;
adjusting the attitude of the satellite based on the current attitude information of the satellite and the received navigation information of the satellite.
8. The method of claim 6, further comprising:
receiving a task scheduling request of a satellite, performing parameter configuration on the satellite based on the task scheduling request, and sending a task scheduling instruction;
and performing task testing on the satellite based on the task scheduling instruction to obtain task testing data, and issuing the task testing data to the ground testing system so that the ground testing system can visually display the task testing data.
9. An electronic device, comprising: a processor, a memory and a bus, the memory storing machine readable instructions executable by the processor, the processor and the memory communicating over the bus when the electronic device is operating, the machine readable instructions when executed by the processor performing the steps of a satellite full function modular simulation processing method according to any of claims 6 to 8.
10. A computer-readable storage medium, characterized in that the computer-readable storage medium has stored thereon a computer program which, when being executed by a processor, carries out the steps of a satellite full-function modular simulation processing method according to any one of claims 6 to 8.
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Application publication date: 20211105 |