CN113610424A - Satellite full-function modularized simulation system, simulation processing method and electronic equipment - Google Patents

Abstract

The present application provides a satellite full-function modular simulation system, a simulation processing method and electronic equipment. The simulation system includes a satellite basic module and a measurement and control digital transmission and ground detection module; wherein, the satellite basic module is connected with the measurement and control digital transmission. The communication connection of the ground detection module is used for compressing the collected state information of each single machine in the satellite full-function modular simulation system to obtain telemetry information, and sending the telemetry information to the measurement and control digital ground detection module; the measurement and control data The ground detection module is connected in communication with the ground test system, and is used 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 will The running status information is displayed visually. In this way, the simulation system can have the function of data transmission test, simulate the basic general functions of ordinary satellites, and make the simulation system changeable, expandable, and flexible to simulate different functions of satellites.

Description

Satellite full-function modular simulation system, simulation processing method and electronic equipment

technical field

The present application relates to the technical field of satellite simulation, and in particular, to a satellite full-function modular simulation system, a simulation processing method and an electronic device.

Background technique

A satellite is a natural celestial body that orbits a planet and runs periodically in a closed orbit. Generally, artificial satellites can also become satellites. Artificial satellites have a wide range of uses. Some are equipped with photographic equipment for photographing and reconnaissance on the ground. , survey resources, etc.; some are equipped with astronomical observation equipment for astronomical observation; some are equipped with communication relay equipment to relay radio, television, etc.

With the advancement of satellite technology and the continuous expansion of satellite applications, the space tasks to be performed by satellite products have become increasingly complex, resulting in increasingly severe challenges in the design and implementation of satellite simulation systems. The functions of the existing satellite simulation processing system are one-sided and incomplete, the functions of the simulation system are fixed and inflexible, and other function simulations cannot be added. Therefore, improving the comprehensiveness of the functions of the satellite simulation system is an urgent technical problem to be solved.

SUMMARY OF THE INVENTION

In view of this, the purpose of this application is to provide a satellite full-function modular simulation system, simulation processing method and electronic equipment, which can realize the satellite full-function module simulation system, so that the functions of the satellite simulation system are comprehensive and modular, thereby It can simulate the basic general functions of ordinary satellites, such as the data transmission test function, so as to realize the transmission of the status information on the satellite to the ground in the simulation system.

The embodiment of the present application provides a satellite full-function modular simulation system, the simulation system includes a satellite basic module and a measurement and control digital transmission and ground detection module; wherein,

The satellite basic module is connected in communication with the measurement and control digital transmission and ground detection module, and is used for compressing the collected state information of each single machine in the satellite full-function modular simulation system to obtain telemetry information, and sending the telemetry information to the measurement and control digital ground detection module;

The measurement and control digital ground detection module is connected to the ground test system for decoding the received telemetry information, and sends the state information obtained after decoding to the ground test system, so that the The ground test system visually displays the operating status information.

Further, the simulation system further includes a satellite attitude dynamics module and a navigation simulation source module, both of which are connected in communication with the satellite basic module; the satellite basic module includes an attitude calculation unit, wherein,

The navigation simulation source module is used for sending satellite navigation information to the satellite base module;

The satellite attitude dynamics module is used to send the attitude dynamics motion information of the satellite in the external space environment to the attitude calculation unit;

The attitude calculation unit is configured to determine the current attitude information of the satellite according to the received attitude dynamics motion information, and determine the current attitude information of the satellite based on the current attitude information of the satellite and the received navigation information of the satellite. posture adjustment.

Further, the satellite basic module includes a satellite service computing unit, a load unit and a data transmission unit, both of which are connected in communication with the satellite service computing unit, and the load unit is in communication connection with the data transmission unit, wherein,

The satellite service computing unit is configured to receive a task scheduling request from a satellite, configure parameters for the satellite based on the task scheduling request, and send a task scheduling instruction to the load unit;

The load unit is configured to perform a mission test on the satellite according to the received mission scheduling instruction, obtain mission test data, and send the mission test data to the data transmission unit;

The data transmission unit is used to send the received task test data to the measurement and control data transmission and ground detection module;

The measurement and control digital ground detection module is used for sending the received mission test data to the ground test system, so that the ground test system can visualize the mission test data.

Further, the satellite basic module includes a measurement and control unit, and the measurement and control unit is connected in communication with the satellite service computing unit, wherein,

The measurement and control digital ground detection module is used for receiving mission control instructions sent by the ground test system, and sending the mission control instructions to the measurement and control unit;

The measurement and control unit is used to receive the mission control instruction and send it to the star service computing unit;

The satellite service computing unit is used to receive the mission control instruction sent by the measurement and control unit, perform mission control on the satellite based on the mission control instruction, and after obtaining the satellite mission acquisition information data, the satellite work configuration information and mission. The collected information is sent to the ground test system, so that the ground test system can monitor satellite status and mission results.

Further, the simulation system includes a power supply module, the power supply module is in communication connection with the satellite basic module, and the power supply module is used for supplying power to the satellite basic module.

The embodiment of the present application also provides a satellite full-function modular simulation processing method, the simulation processing method includes:

compressing the collected state information of each single machine in the satellite full-function modular simulation system to obtain telemetry information;

The telemetry information is decoded, and the state information obtained after decoding is sent to the ground test system, so that the ground test system can display it visually.

Further, the simulation processing method also includes:

Obtain satellite navigation information;

Obtain the attitude dynamics motion information of the satellite in the external space environment;

Determine the current attitude information of the satellite based on the attitude dynamics motion information of the satellite in the external space environment;

The attitude of the satellite is adjusted based on the current attitude information of the satellite and the received navigation information of the satellite.

Further, the simulation processing method also includes:

Receive a task scheduling request from a satellite, configure parameters for the satellite based on the task scheduling request, and send a task scheduling instruction;

The ground test system that performs mission test on the satellite based on the mission scheduling instruction, obtains mission test data, and distributes the mission test data, so that the ground test system can perform the mission test data on the ground test system. Visual display.

Embodiments of the present application further provide an electronic device, including: a processor, a memory, and a bus, where the memory stores machine-readable instructions executable by the processor, and when the electronic device runs, the processor and the The memories communicate with each other through a bus, and when the machine-readable instructions are executed by the processor, the steps of the above-mentioned satellite full-function modular simulation processing method are executed.

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 run by a processor, the steps of the above-mentioned satellite full-function modular simulation processing method are executed.

The application provides a satellite full-function modular simulation system, simulation processing method and electronic equipment, the simulation system includes a satellite basic module and a measurement and control digital ground detection module; wherein, the satellite basic module, and the measurement and control The communication connection of the data transmission ground detection module is used for compressing the collected state information of each single machine in the satellite full-function modular simulation system to obtain telemetry information, and sending the telemetry information to the measurement and control digital transmission ground detection module; The measurement and control digital ground detection module is connected to the ground test system for decoding the received telemetry information, and sends the state information obtained after decoding to the ground test system, so that the The ground test system visually displays the operating status information.

In this way, a simulation system of satellite full-function modules can be realized, so that the functions of the satellite simulation system can be comprehensive and modular, so that the basic general functions of ordinary satellites can be simulated, including satellite management functions, attitude control simulation functions, satellite-ground communication functions, and navigation functions. Function, load test function and data transmission function, and can test single or multiple modules in the simulation system, and the simulation system is convenient and flexible to set up, and can be reorganized to adapt to different simulation tasks.

In order to make the above-mentioned objects, features and advantages of the present application more obvious and easy to understand, the preferred embodiments are exemplified below, and are described in detail as follows in conjunction with the accompanying drawings.

Description of drawings

In order to illustrate the technical solutions of the embodiments of the present application more clearly, the following drawings will briefly introduce the drawings that need to be used in the embodiments. It should be understood that the following drawings only show some embodiments of the present application, and therefore do not It should be regarded as a limitation of the scope, and for those of ordinary skill in the art, other related drawings can also be obtained according to these drawings without any creative effort.

1 is a schematic structural diagram of a satellite full-function modular simulation system provided by an embodiment of the application;

2 is a schematic structural diagram of a satellite basic module in a satellite full-function modular simulation system provided by an embodiment of the application;

3 is a schematic structural diagram of a wireless connection of a satellite full-function modular analog system provided by an embodiment of the present application;

4 is a schematic structural diagram of a wired connection of a satellite full-function modular simulation system provided by an embodiment of the application;

5 is a flowchart of a satellite full-function modular simulation processing method provided by an embodiment of the present application;

6 is a flowchart of another satellite full-function modular simulation processing method provided by an embodiment of the present application;

7 is a flowchart of another satellite full-function modular simulation processing method provided by an embodiment of the present application;

8 is a flowchart of another satellite full-function modular simulation processing method provided by an embodiment of the present application;

FIG. 9 is a schematic structural diagram of an electronic device provided by an embodiment of the present application.

Icon: 100-simulation system; 110-satellite basic module; 111-attitude calculation unit; 112-star service calculation unit; 113-load unit; 114-data transmission unit; 115-measurement and control unit; 116-navigation unit; 120-measurement and control 130-satellite attitude dynamics module; 140-navigation simulation source module; 150-power module; 900-electronic equipment; 910-processor; 920-memory; 930-bus.

Detailed ways

In order to make the purposes, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the accompanying drawings in the embodiments of the present application. It should be understood that the The accompanying drawings are only for the purpose of illustration and description, and are not used to limit the protection scope of the present application. In addition, it should be understood that the schematic drawings are not drawn to scale. The flowcharts used in this application illustrate operations implemented in accordance with some embodiments of the application. It should be understood that the operations of the flowcharts may be performed out of order and that steps without logical context may be performed in reverse order or concurrently. In addition, those skilled in the art can add one or more other operations to the flowchart, and can also remove one or more operations from the flowchart under the guidance of the content of the present application.

In addition, the described embodiments are only some of the embodiments of the present application, but not all of the embodiments. The components of the embodiments of the present application generally described and illustrated in the drawings herein may be arranged and designed in a variety of different configurations. Thus, the following detailed description of the embodiments of the application provided in the accompanying drawings is not intended to limit the scope of the application as claimed, but is merely representative of selected embodiments of the application. Based on the embodiments of the present application, all other embodiments obtained by those skilled in the art without creative work fall within the protection scope of the present application.

In order to enable those skilled in the art to use the content of the present application, the following embodiments are given in combination with the specific application scenario "satellite simulation". For those skilled in the art, without departing from the spirit and scope of the present application, the The general principles defined herein apply to other embodiments and application scenarios.

The following methods, systems, electronic devices, or computer-readable storage media in the embodiments of the present application can be applied to any scenario that requires satellite simulation. The embodiments of the present application do not limit the specific application scenarios. The scheme of a satellite full-function modular simulation system and a simulation processing method are all within the protection scope of the present application.

It is worth noting that with the advancement of satellite technology and the continuous expansion of satellite applications, the space tasks to be performed by satellite products are increasingly complex, resulting in increasingly severe challenges in the design and implementation of satellite simulation systems. The functions of the existing satellite simulation processing system are one-sided and incomplete, the functions of the simulation system are fixed and inflexible, and other function simulations cannot be added. Therefore, improving the comprehensiveness of the functions of the satellite simulation system is an urgent technical problem to be solved.

Based on this, the present application provides a satellite full-function modular simulation system, the simulation system includes a satellite basic module and a measurement and control digital ground detection module; wherein, the satellite basic module is connected with the measurement and control digital ground detection module. The module communication connection is used to compress the collected state information of each unit in the satellite full-function modular simulation system to obtain telemetry information, and send the telemetry information to the measurement and control digital ground detection module; the measurement and control data The ground transmission detection module is connected to the ground test system for decoding the received telemetry information, and sends the state information obtained after decoding to the ground test system, so that the ground test system can The running status information is displayed visually.

In this way, a simulation system of satellite full-function modules can be realized, so that the functions of the satellite simulation system can be comprehensive and modular, so that the basic general functions of ordinary satellites can be simulated, including satellite management functions, attitude control simulation functions, satellite-ground communication functions, and navigation functions. Function, load test function and data transmission function, and can be tested for single or multiple modules in the simulation system. The simulation system is convenient and flexible to set up, and can be reorganized to adapt to different simulation tasks. Further, a satellite full-function modular simulation system 100 disclosed in this application will be introduced.

Please refer to FIG. 1 . FIG. 1 is a schematic structural diagram of a satellite full-function modular simulation system provided by an embodiment of the application. As shown in FIG. 1 , the simulation system 100 includes a satellite basic module 110 and a measurement and control digital transmission ground detector. Module 120; wherein, the satellite basic module 110 is connected in communication with the measurement and control digital transmission and ground detection module 120, and is used for compressing the collected 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 digital ground detection module 120; the measurement and control digital ground detection module 120 is connected to the ground test system for decoding the received telemetry information, and The state information obtained after decoding is sent to the ground test system, so that the ground test system can visually display the running state information.

Specifically, the satellite basic module 110 collects the state information of all the stand-alone machines in the simulation system 100, compresses and packs the state information of each stand-alone machine to form telemetry information, and sends the telemetry information to the measurement and control data transmission and ground detection module 120, and the measurement and control data The ground transmission detection module 120 decodes and processes the received telemetry information to obtain the status information of each stand-alone machine, and sends the status information to the ground test system, so that the status information can be visually displayed in the ground test system for the operator to view in time .

Here, the state information of the single machine is the running state information of all 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 connected in communication with the satellite base module 110; the satellite base module includes an attitude calculation unit, Wherein, the navigation simulation source module 140 is used for sending the navigation information of the satellite to the satellite basic module 110; the satellite attitude dynamics module 130 is used for sending the attitude dynamics motion information of the satellite in the external space environment sent to the attitude calculation unit; the attitude calculation unit is used to determine the current attitude information of the satellite according to the received attitude dynamics motion information, and based on the current attitude information of the satellite and the received The satellite's navigation information adjusts the attitude of the satellite.

Here, the navigation simulation source module 140 can provide simulation information of GPS/BD navigation satellites for use by the navigation module of the satellite simulation platform.

Here, the satellite attitude dynamics module 130 sends the attitude dynamics motion information of the satellite in the external space environment to the attitude calculation unit.

Here, the attitude calculation unit communicates and interacts with the satellite attitude dynamics module 130 through the RS422 interface, and the attitude calculation unit is based on the attitude dynamics motion information provided by the satellite attitude dynamics module 130. ), the attitude measurement component (magnetometer, gyroscope) and the attitude adjustment component (reaction flywheel, magnetic torquer) configuration of the initial attitude dynamics motion information, calculate the current attitude information of the satellite, and according to the received The positioning broadcast of the navigation information of the satellites and the current attitude information of the satellites, the attitude simulation adjustment of the satellites is carried out, and this process can simulate the actual working state of the attitude calculation unit.

Further, as shown in FIG. 1 , the simulation system 100 includes a power supply module 150 , the power supply module 150 is connected in communication with the satellite basic module 110 , and the power supply module 150 is used to supply power to the satellite basic module 110 .

Here, the power module 150 can provide a power supply capacity of 100V and 4kW.

Further, please refer to FIG. 2 for a schematic structural diagram of a satellite basic module in a satellite full-function modular simulation system provided by an embodiment of the application. As shown in FIG. 2 , the satellite basic module 110 includes a satellite service calculation. The unit 112, the load unit 113 and the data transmission unit 114 are all connected in communication with the star service calculation unit 112, the load unit 113 is in communication connection with the data transmission unit 114, wherein the star service calculation unit 112 , is used to receive the task scheduling request of the satellite, configure parameters for the satellite based on the task scheduling request, and send a task scheduling instruction to the load unit 113; the load unit 113 is used to The scheduling instruction performs a task test on the satellite, obtains task test data, and sends the task test data to the data transmission unit 114; the data transmission unit 114 is used to send the received mission test data. to the measurement and control digital ground detection module 120; the measurement and control digital ground detection module 120 is used to send the received task test data to the ground test system, so that the ground test system can detect the task Visual display of test data.

Here, the star computing unit 112 has Can, RS422, RS485, LVDS, second pulse, GPIO interface, OC command interface, analog quantity acquisition interface, temperature control loop interface and power supply interface.

Here, the star service computing unit 112 is communicatively connected to the load unit 113 and the data transmission unit 114, and communicates through the CAN interface, and the data transmission unit 114 and the load unit 113 perform data transmission through LVDS. When the star computing unit 112 makes a task scheduling request, the task test data generated when the load unit 113 works according to the task scheduling instruction is sent 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. In the digital ground detection 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 basic module 110 includes a measurement and control unit 115, and the measurement and control unit 115 is connected in communication with the satellite service calculation unit 112, wherein the measurement and control digital transmission and ground detection module 120 is used for Receive the fault decision control command sent by the ground test system, and send the fault decision control command to the measurement and control unit 115; the measurement and control unit 115 is used to receive the fault decision control command and send it to the star service The calculation unit 112; the satellite service calculation unit 112 is used to receive the fault decision control instruction sent by the measurement and control unit 115, repair the fault of the satellite based on the fault decision control instruction, and obtain the operation information after the satellite maintenance processing. , sending the operation information processed by the satellite maintenance to the ground test system, so that the ground test system can monitor the fault maintenance of the satellite. Further, the satellite basic module 110 includes a navigation unit 116, and the navigation unit 116 is connected to the satellite service computing unit 112 in communication.

Here, the star service computing unit 112 is wired to the measurement and control unit 115, and communicates with the measurement and control unit 115 through the CAN interface and the RS422 interface.

Here, the ground test system judges the working condition of the satellite according to the received operating status information and mission test data, and determines whether the working condition of the satellite is faulty. After determining the fault location and the fault decision, send a fault decision control instruction to the satellite service computing unit 112, and the satellite service computing unit 112 adjusts and maintains the faulty part of the satellite according to the fault decision control instruction, and obtains the satellite maintenance processing. For operation information, the satellite service computing unit 112 sends the operation information processed by the satellite maintenance to the ground test system, so that the ground test system can monitor the fault maintenance of the satellite.

Here, it also includes that the star service computing unit 112 collects the status information of all single machines on the simulation system 100 and packages them to form telemetry information, and sends it to the measurement and control unit 115 through RS422, and the measurement and control unit 115 is responsible for the received telemetry of the star service calculation unit 112. The information is sent to the measurement and control digital ground detection module 120 .

Further, as shown in FIG. 2 , the satellite basic module 110 includes an attitude calculation unit 111, and the attitude calculation unit 111 is configured to determine the current attitude information of the satellite according to the received attitude dynamics motion information, and based on The current attitude information of the satellite and the received navigation information of the satellite adjust the attitude of the satellite.

Further, please refer to FIG. 3 . FIG. 3 is a schematic structural diagram of a wireless connection of a satellite full-function modular analog system provided in an embodiment of the application. As shown in FIG. 3 , the data transmission unit 114 is wired to connect the first digital The transmission antenna, based on the first data transmission antenna, sends the task test data to the second data transmission antenna, wherein the second data transmission antenna is wired with the measurement and control digital transmission ground detection module 120, and the second data transmission antenna transmits the task test data to Measurement and control data transmission ground detection module 120; further, the first measurement and control antenna is wired to the measurement and control unit 115, and the measurement and control unit 115 sends 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 digital transmission. The ground detection module 120 is connected by wire, and the second measurement and control antenna transmits the telemetry information to the measurement and control digital transmission ground detection module 120 . Further, the navigation simulation source module is wired to the second navigation antenna, and sends out navigation information to the first navigation antenna through the second navigation antenna, and the first navigation antenna supplies the navigation information to the navigation unit 116 of the satellite base module 110 for use.

Here, the measurement and control data transmission ground detection module 120 is wired to connect the second measurement and control antenna, the second data transmission antenna and the ground test system, the second measurement and control antenna can receive the telemetry information sent by the first measurement and control antenna, and the measurement and control digital transmission ground detection module 120 receives After the telemetry information is decoded, the state information is obtained, and then the state information is sent to the ground test system. The ground test system unpacks and analyzes the state information, and then the received telemetry information can be displayed in a visual form. And through the ground test system, instructions can be sent to the satellite base module 110, and the sent instructions are sent from the ground test system to the measurement and control digital ground detection module 120, and then sent to the satellite base module 110 through the second measurement and control antenna.

Further, please refer to FIG. 4 , which is a schematic structural diagram of a wired connection of a satellite full-function modular analog system provided by an embodiment of the present application. As shown in FIG. 4 , the data transmission unit 114 and the measurement and control unit 115 are wired to the measurement and control data transmission and ground detection module 120 , and the navigation unit 116 is wired to the navigation simulation source module 140 , thereby realizing fast data transmission in the simulation system 100 .

The application provides a satellite full-function modular simulation system. The simulation system includes a satellite basic module and a measurement and control digital ground detection module; wherein, the satellite basic module is connected in communication with the measurement and control digital ground detection module, It is used for compressing the collected state information of each single machine in the satellite full-function modular simulation system to obtain telemetry information, and sending the telemetry information to the measurement and control digital ground detection module; the measurement and control digital ground detection module , communicated with the ground test system, used to decode the received telemetry information, and send the decoded state information to the ground test system, so that the ground test system can Information is displayed visually.

In this way, a simulation system of satellite full-function modules can be realized, so that the functions of the satellite simulation system are comprehensive and modular, so that the basic general functions of ordinary satellites can be simulated, such as data transmission test function, attitude simulation function, satellite-ground communication function, and navigation function. And load test function, and can quickly adapt to different simulation tasks to test single or multiple modules.

Please refer to FIG. 5. FIG. 5 is a flowchart of a satellite full-function modular simulation processing method provided by an embodiment of the application. As shown in FIG. 5, the simulation processing method includes:

S501: Compress the collected state information of each unit in the satellite full-function modular simulation system to obtain telemetry information.

In this step, the state information of each stand-alone machine in the satellite full-function modular simulation system is collected, and after the state information of each stand-alone machine is collected, compression processing is performed to obtain telemetry information.

Here, the single machine is each module in the satellite full-function modular simulation system, such as the measurement and control digital ground detection module, measurement and control unit and other modules or units in the above-mentioned simulation system.

Here, the state information is the state information of the working operation of each module in the simulation system, such as the attitude information in the attitude calculation unit.

S502: Decode the telemetry information, and send the state information obtained after decoding to the ground test system, so that the ground test system can display it visually.

In this step, the received telemetry information is decoded to obtain the decoded state information of each stand-alone machine, and the state information is sent to the ground test system, so that the state information can be visualized in the ground test system.

In a specific embodiment, the description will be given in conjunction with a satellite full-function modular simulation system. The satellite basic module is controlled to receive the state information of each individual machine in the satellite full-function modular simulation system, and the state information of each stand-alone machine is compressed to obtain telemetry. information, and send the telemetry information to the measurement and control digital ground detection module. The control measurement and control digital ground detection module decodes the received telemetry information, and sends the decoded state information to the ground test system, so that the ground test system can display it visually.

In another embodiment, the description is given in conjunction with a satellite full-function modular simulation system, and the satellite service computing unit in the satellite basic module is controlled to receive the status information of each single machine in the satellite full-function modular simulation system, and the status information Perform compression processing to obtain telemetry information, and then communicate with the measurement and control unit through the CAN interface and RS422 interface and send it to the measurement and control unit. The ground detection module decodes the received telemetry information to obtain the status information of each single machine, and sends the status information of each single machine to the ground test system. The ground test system parses and processes the status information of each single machine, which can make The test system displays the status information of each single machine in a visual form.

The present application provides a satellite full-function modular simulation processing method, the simulation processing method includes: compressing the collected state information of each single machine in the satellite full-function modular simulation system to obtain telemetry information; The telemetry information is decoded, and the state information obtained after decoding is sent to the ground test system, so that the ground test system can display it visually. In this way, it is possible to comprehensively monitor the operation state information of each single machine in the satellite full-function modular simulation system, and effectively improve the timeliness of obtaining the operation state information of each single machine.

Please refer to FIG. 6 , which is a flowchart of another satellite full-function modular simulation processing method provided by an embodiment of the present application. As shown in Figure 6, the simulation processing method further includes:

S601: Acquire satellite navigation information.

In this 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: Obtain the attitude dynamics motion information of the satellite in the external space environment.

In this step, the attitude dynamics motion information of the satellite in the external space environment is acquired.

S603: Determine the current attitude information of the satellite based on the attitude dynamics motion information of the satellite in the external space environment.

In this step, based on the attitude dynamics motion information, there is no attitude sensor (star sensor, sun sensor), attitude measurement component (magnetometer, gyroscope) and attitude adjustment component (reaction flywheel, magnetic moment). The current attitude information of the satellite is calculated from the initial attitude dynamic motion information in the case of the satellite) configuration.

S604: Adjust the attitude of the satellite based on the current attitude information of the satellite and the received navigation information of the satellite.

In this step, the attitude of the satellite is simulated and adjusted 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 in conjunction with a satellite full-function modular simulation system, the navigation simulation source module is controlled to send the navigation information of the satellite to the satellite basic module, and the satellite attitude dynamics module is controlled to transmit the attitude power of the satellite in the external space environment. The learning motion information is sent to the attitude calculation unit; the control attitude calculation unit determines the current attitude information of the satellite according to the received attitude dynamics motion information, and based on the current attitude information of the satellite and the received navigation of the satellite The information adjusts the attitude of the satellite.

The present application provides a full-featured modular simulation processing method for satellites, the simulation processing method includes: acquiring navigation information of satellites; acquiring attitude dynamics motion information of satellites in an external space environment; The current attitude information of the satellite is determined from the attitude dynamics motion information in the environment; the attitude of the satellite is adjusted based on the current attitude information of the satellite and the received navigation information of the satellite. In this way, when the attitude information of the satellite deviates from the orbit, the attitude of the satellite can be adjusted quickly and accurately.

Please refer to FIG. 7 , which is a flowchart of another satellite full-function modular simulation processing method provided by an embodiment of the present application. As shown in Figure 7, the simulation processing method further includes:

S701: Receive a task scheduling request from a satellite, configure parameters for the satellite based on the task scheduling request, and send a task scheduling instruction.

In this step, a task scheduling request of the satellite is acquired, parameters are configured for the satellite using the task scheduling request, and a task scheduling instruction is sent.

Here, the task scheduling request is to request the payload on the satellite to test the instrument equipment, such as camera equipment, communication equipment or other equipment.

S702: Perform a mission test on the satellite based on the mission scheduling instruction, obtain mission test data, and deliver the mission test data to the ground test system, so that the ground test system can test the mission Data is visualized.

In this step, mission testing is performed on the satellite according to the task scheduling instruction to obtain corresponding mission testing data, and the mission testing data is delivered to the ground testing system, so that the ground testing system can visually display the task testing and 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 use the camera device on the satellite to take pictures of the ground, and the task test data is the image taken by the camera.

In a specific embodiment, the description will be given in conjunction with a satellite full-featured modular simulation system. The satellite service computing unit is controlled to receive the task scheduling request of the satellite, configure the parameters of the satellite based on the task scheduling request, and send it to the load unit. Task scheduling instruction; control the load unit to perform task testing on the satellite according to the received task scheduling instruction, obtain task testing data, and send the task testing data to the data transmission unit; control the data transmission unit The received task test data is compressed and sent to the measurement and control digital ground detection module; the measurement and control digital ground detection module is controlled to decode the received compressed task test data to obtain the task test data, The mission test data is sent to the ground test system, so that the ground test system can visualize the mission test data.

In another embodiment, the description is given in conjunction with a satellite full-function modular simulation system, the mission test data is sent to the data transmission unit, and the data transmission unit compresses the mission test data and uses the first data transmission antenna to deliver it, The measurement and control digital ground detection module receives the compressed mission test data based on the second data transmission antenna, decompresses it to obtain mission test data, and sends the mission test data to the ground test system for visual display.

The present application provides a satellite full-function modular simulation processing method, the simulation processing method includes: receiving a task scheduling request of a satellite, configuring parameters for the satellite based on the task scheduling request, and sending a task scheduling instruction; The task scheduling instruction performs a task test on the satellite, obtains task test data, and issues the mission test data to the ground test system, so that the ground test system can visualize the mission test data. show. In this way, the load test of the satellite can be realized, and the load test result can be sent to the ground test system for visual display.

Please refer to FIG. 8 , which is a flowchart of another satellite full-function modular simulation processing method provided by an embodiment of the present application. As shown in Figure 8, the simulation processing method further includes:

S801: Receive a mission control instruction sent by the ground test system.

In this step, the mission control instructions sent by the ground test system are acquired.

Here, for example, the ground test system performs fault judgment on the working condition of the satellite according to the received status information and mission test data. If it is judged that the working condition of the satellite is faulty, it determines the fault location and the processing strategy to solve the fault. , after determining the fault location and the processing strategy for solving the fault, the mission control command is sent to facilitate the maintenance of the fault location of the satellite.

S802: Perform mission control on the satellite based on the mission control instruction, and after obtaining the satellite mission acquisition information data, send the satellite work setup information and mission acquired information to the ground test system, so that the ground test system Monitor satellite status and mission results.

In this step, according to the mission control instruction, the satellite is carried out to collect data for the mission, obtain the information on the installation and adjustment of the satellite and the information collected by the mission, and send the information to the ground test system, so that the ground test system can monitor the satellite's performance. Monitor satellite status and mission results.

Here, for example, if it is determined that the payload of the satellite has abnormal working conditions, it is necessary to adjust the operating parameters of the payload so that the operating state of the satellite returns to normal.

In a specific embodiment, described in conjunction with a satellite full-function modular simulation system, the control measurement and control digital ground detection module receives the mission control instructions sent by the ground test system, and sends the mission instructions to the measurement and control unit; control The measurement and control unit receives the mission control instruction and sends it to the satellite service calculation unit; controls the satellite service calculation unit to receive the mission control instruction sent by the measurement and control unit, and performs mission control on the satellite based on the mission control instruction , after obtaining the satellite task acquisition information data, the satellite work configuration information and the information collected by the task are sent to the ground test system, so that the ground test system can monitor the satellite status and task results.

In another embodiment, described in conjunction with the satellite full-function modular simulation system, the ground test system sends mission control instructions to the measurement and control digital ground detection module, which controls the measurement and control digital ground detection module to transmit the mission control instructions based on the second measurement and control antenna. It is sent to the first measurement and control antenna, and the first measurement and control antenna transmits the mission control instruction to the measurement and control unit, and the measurement and control unit transmits the mission control instruction to the star service computing unit for instruction execution, and controls the star service calculation unit based on the described task. The decision-making control command controls the mission of the satellite, and after obtaining the satellite mission acquisition information data, the satellite work configuration information and the information collected by the mission are sent to the ground test system, so that the ground test system can determine the satellite status and mission. The results are monitored.

The present application provides a full-function modular simulation processing method for satellites, which receives mission control instructions sent by the ground test system. Mission control is performed on the satellite based on the mission control instruction, and after the satellite mission acquisition information data is obtained, the satellite work configuration information and mission acquired information are sent to the ground test system, so that the ground test system can monitor the satellite Status and task results are monitored. In this way, the mission control of the satellite can be performed according to the mission control instruction sent by the ground test system, and the monitoring of the satellite state and the mission result can be realized.

Please refer to FIG. 9 , which is a schematic structural diagram of an electronic device provided by an embodiment of the present application. 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 is running, the processor 910 communicates with the memory 920 through the bus 930, and the machine-readable instructions are executed. When the processor 910 executes, it can execute the steps of the satellite full-function modular simulation processing method in the method embodiments shown in the above-mentioned FIG. .

Embodiments of the present application further provide a computer-readable storage medium, where a computer program is stored on the computer-readable storage medium. When the computer program is run by a processor, the computer program can execute the method embodiments shown in FIG. 5 to FIG. 8 above. For the steps of the satellite full-function modular simulation processing method, the specific implementation can refer to the method embodiment, which will not be repeated here.

Those skilled in the art can clearly understand that, for the convenience and brevity of description, the specific working process of the above-described systems, devices and units may refer to the corresponding processes in the foregoing method embodiments, which will not be repeated here.

In the several embodiments provided in this application, it should be understood that the disclosed system, apparatus and method may be implemented in other manners. The apparatus embodiments described above are only illustrative. For example, the division of the units is only a logical function division. In actual implementation, there may be other division methods. For example, multiple units or components may be combined or Can be integrated into another system, or some features can be ignored, or not implemented. On the other hand, the shown or discussed mutual coupling or direct coupling or communication connection may be through some communication interfaces, indirect coupling or communication connection of devices or units, which may be in electrical, mechanical or other forms.

The units described as separate components may or may not be physically separated, and components displayed as units may or may not be physical units, that is, may be located in one place, or may be distributed to multiple network units. Some or all of the units may be selected according to actual needs to achieve the purpose of the solution in this embodiment.

In addition, each functional unit in each embodiment of the present application may be integrated into one processing unit, or each unit may exist physically alone, or two or more units may be integrated into one unit.

The functions, if implemented in the form of software functional units and sold or used as stand-alone products, may be stored in a processor-executable non-volatile computer-readable storage medium. Based on this understanding, the technical solution of the present application can be embodied in the form of a software product in essence, or the part that contributes to the prior art or the part of the technical solution. The computer software product is stored in a storage medium, including Several instructions are used to cause a computer device (which may be a personal computer, a server, or a network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of the present application. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (Read-Only Memory, ROM), random access memory (Random Access Memory, RAM), magnetic disk or optical disk and other media that can store program codes.

Finally, it should be noted that the above-mentioned embodiments are only specific implementations of the present application, and are used to illustrate the technical solutions of the present application, rather than limit them. The embodiments describe the application in detail, and those of ordinary skill in the art should understand that: any person skilled in the art can still modify the technical solutions described in the foregoing embodiments within the technical scope disclosed in the application. Or can easily think of changes, or equivalently replace some of the technical features; and these modifications, changes or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions in the embodiments of the application, and should be covered in this application. within the scope of protection. 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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