CN117194233A - Satellite simulator system with on-loop satellite-borne operating system and closed-loop simulation test method - Google Patents
Satellite simulator system with on-loop satellite-borne operating system and closed-loop simulation test method Download PDFInfo
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Abstract
The application provides a satellite simulator system with a satellite-borne operating system in a ring and a closed-loop simulation test method, which comprises the following steps: virtual spaceborne computer, system model and co-simulation bus; the virtual spaceborne computer is used for simulating software and hardware of a real spaceborne computer and running a real spaceborne operating system and application software; the system model is used for simulating each system function of the satellite; the collaborative simulation bus is used for information interaction and synchronous simulation of the virtual spaceborne computer and the system model. The application constructs a satellite simulator system with a real satellite-borne operating system and application software in the ring, is in seamless connection with a ground test system, performs closed-loop test like testing a real satellite, and has good engineering application value.
Description
Technical Field
The application relates to the technical field of satellite simulator simulation test, in particular to a satellite simulator system with a satellite-borne operating system in a ring and a closed-loop simulation test method.
Background
Satellite simulator systems can be used for virtual simulation verification of satellite functions, however simulation fidelity, convenience and effectiveness of test verification are important challenges for satellite simulators. And when a plurality of satellites exist in a constellation, on-ground installation test verification cannot be performed, and on-orbit test verification and modification have high cost.
Patent document CN104834226a discloses a digital satellite simulation system and a digital satellite state fast switching method, and focuses on the digital simulation state setting and switching method, which is different from the present application; the North navigation Dong Yunfeng issues a series of digital artificial intelligence program patents 201810393137:6, namely a method for executing source codes of a motion coupled digital satellite power subsystem, 201810037008.3, a method for executing source codes of an artificial intelligence programmer writing digital aircraft, 201810394612.1, a method for measuring and controlling an artificial intelligence writing satellite and a device for simulating force and heat coupling, 201810036677.9, a method for decomposing decisions of the artificial intelligence programmer writing the source codes of the digital aircraft, 201810284818.9, a method for writing a three-dimensional demonstration source program of a satellite passing system by the artificial intelligence programmer, 201810392553.4, a method for intelligently writing source codes of a gesture control and heat coupling digital satellite propulsion subsystem and the like, and focuses on software automation on writing model programs, which are different from the application; the analysis attitude control system model verification method of the satellite Internet digital twin system simulation verification research of the north-order ministry of China is different from the method; the Chinese space technical institute Li Xuan 'communication satellite simulator general basic platform design study' is mainly used for measurement and control equivalent verification and is different from the application; the north navigation Dong Yunfeng digital satellite concept research analyzes the modeling thought of the digital satellite point flow surface, and is different from the application; through investigation and analysis, the prior patent and paper mainly relate to multi-model coupling simulation, model verification, simulation training and the like, and are different from the satellite simulator system with the satellite-borne operating system in the loop and the simulated test closed-loop test method.
Disclosure of Invention
Aiming at the defects in the prior art, the application aims to provide a satellite simulator system with a satellite-borne operating system in the ring and a closed-loop simulation test method.
The satellite simulator system of the present application comprises: virtual spaceborne computer, system model and co-simulation bus;
the virtual spaceborne computer is used for simulating software and hardware of a real spaceborne computer and running a real spaceborne operating system and application software;
the system model is used for simulating each system function of the satellite;
the collaborative simulation bus is used for information interaction and synchronous simulation of the virtual spaceborne computer and the system model.
Preferably, the virtual on-board computer comprises a hardware simulation; the hardware simulation comprises a CPU core board of the spaceborne computer, a channel gateway peripheral, an inter-satellite communication peripheral, a serial time base peripheral, a bus peripheral, a comprehensive interface peripheral and a time management module simulation unit.
Preferably, the virtual on-board computer comprises software emulation; the software simulation is realized by adding a shipping planet carrier operating system on a virtual CPU core board, and a planet carrier App comprising a planet software, a gesture control software and a task planning software is operated on the planet carrier operating system, so that the digital simulation of the software and the hardware of a planet carrier computer is realized.
Preferably, the system model completes the function simulation of each system, and a standardized interface is adopted, wherein the model interface comprises a virtual spaceborne computer interaction interface, a model electrical load interface, an inter-model information interface, a model parameter setting interface and a model working state output interface;
the virtual spaceborne computer interaction interface is divided into a direct measurement and control interface, a serial port, a bus interface, a time unification interface, a channel gateway and an inter-spaceborne communication interface according to the interface design of a real spaceborne computer product;
the model electrical load interface simulates the power supply and distribution information simulation of a product, including load power consumption and heat consumption parameters;
the information interface between the models simulates information transfer between systems, including remote sensing data quantity and navigation information;
the model parameter setting interface is used for setting model initial state parameters, adjusting model process parameters and injecting model faults, and the channel gateway peripheral of the virtual spaceborne computer is set uniformly;
the model working state output interface is used for reporting parameters of the model, including dynamic simulation parameters and load data transmission working parameters.
Preferably, the virtual spaceborne computer runs a real spaceborne operating system and an application App, virtual bus interfaces, direct telemetry and remote control interfaces, serial interfaces, time unified interfaces, model electrical load interfaces, inter-model information interfaces, model parameter setting interfaces and model working state output interfaces are carried out between the system models and the virtual spaceborne computer through a collaborative simulation bus, information interaction between the virtual spaceborne computer and each system model is achieved, and simulation operation of the spaceborne operating system in a satellite simulator of a ring is completed.
Preferably, the satellite simulator is in seamless connection with the ground comprehensive test system to form a set of satellite-ground closed loop simulation test system, the sending of remote control instructions and the monitoring of telemetry data are consistent with the real satellite test flow, namely, like the real satellite test, the ground test system sends the software to send remote control instruction excitation, and the ground test system monitors the software to monitor telemetry response to perform the closed loop test of the satellite simulator.
According to the closed-loop simulation test method of the satellite simulator system with the on-board operating system in the ring, the following steps are executed:
step 1: the channel gateway of the virtual spaceborne computer and the external interface of the inter-satellite communication interface are network interfaces, the interface protocol is consistent with the network interface protocol of the ground measurement and control baseband equipment, for a ground test system, the channel gateway of the satellite simulator and the inter-satellite communication interface are equivalent to the measurement and control baseband equipment, and are in seamless connection with ground forwarding software to carry out remote control instruction, telemetry frame and inter-satellite information transceiving so as to form a simulation test environment of a satellite-ground closed loop;
step 2: the tester operates ground command software and sends satellite commands, inter-satellite communication information and model parameter setting commands;
step 3: the satellite instruction and the model parameter setting instruction are sent to the channel gateway peripheral equipment of the virtual spaceborne computer through the comprehensive testing server and the forwarding software;
step 4: the channel gateway is provided with an instruction classification function, and the received ground remote control data is divided into a satellite instruction and a model parameter setting instruction;
step 5: the satellite instruction is transmitted to a CPU core board of the virtual spaceborne computer, is interpreted and executed in a spaceborne operating system, and is distributed to a related system model through a peripheral interface of the virtual spaceborne computer;
step 6: the model parameter setting instruction is sent to a corresponding system model to carry out model parameter setting and fault parameter injection;
step 7: the inter-satellite uplink communication information is sent to an inter-satellite communication peripheral of the virtual spaceborne computer through the comprehensive testing server and the forwarding software;
step 8: the inter-satellite uplink information is transmitted to a CPU core board of the virtual spaceborne computer, and analyzed and processed by a spaceborne operating system and application software on the CPU core board;
step 9: according to the satellite instructions and the inter-satellite uplink communication information which are uploaded in the steps 1-8, the method uses the satellite instructions and the inter-satellite uplink communication information as test excitation input of the virtual spaceborne computer, drives the spaceborne operating system and application software to analyze and process the instructions, and distributes the instructions to each system model through a collaborative simulation bus by the virtual spaceborne computer to serve as the test excitation input of the system model;
step 10: each system model responds to instruction excitation input of the virtual computer, simulation output response feedback, and then information interaction is carried out between the system model and the virtual spaceborne computer through a collaborative simulation bus, so that task instruction scheduling, processing and information collection are completed;
step 11: the operation system and the application software on the virtual spaceborne computer organize the collected satellite information into telemetry frames, telemetry is sent to ground forwarding software through the channel gateway peripheral equipment according to a standard measurement and control baseband interface protocol, and the ground forwarding software converts the format of the telemetry frames and then sends the telemetry frames to a comprehensive measurement server for analysis;
step 12: similarly, the inter-satellite downlink communication information generated by the virtual spaceborne computer is sent to ground forwarding software through the inter-satellite communication interface peripheral equipment and is sent to the comprehensive testing server for processing;
step 13: the working state of the system model is used as a type of ground equipment telemetry through a model working state output interface and is sent to a comprehensive testing server for data analysis processing;
step 14: the comprehensive measurement service completes centralized processing of on-board telemetry, inter-board information and model working state information, and transmits the analyzed on-board telemetry, inter-board information and model working state information to a ground monitoring terminal for presentation;
step 15: and on the ground monitoring terminal, the satellite simulator command excitation and the closed-loop monitoring interpretation of the telemetry response are carried out in combination with the remote control command excitation.
Preferably, a plurality of satellite simulators form a satellite constellation simulation system, and each satellite simulator transmits cooperation information through an inter-satellite communication model to perform satellite constellation joint simulation of a satellite-borne operating system and application software in a ring.
Preferably, the constructed constellation simulation system and the ground test system simulate a test closed loop, so that the cooperation of a real satellite-borne operating system and an application software in the constellation system of the loop and intelligent management test verification are realized.
Compared with the prior art, the application has the following beneficial effects:
the application provides a satellite simulator system with a satellite-borne operating system in a ring and a closed-loop simulation test method, wherein the satellite simulator system with the real satellite-borne operating system in the ring and application software in the ring is constructed, and is in seamless connection with a ground test system, so that closed-loop test is performed like real satellite test; meanwhile, a plurality of satellite simulators form a satellite constellation simulation system, a closed loop is simulated by the satellite simulator and a ground test system, the coordination and intelligent management test verification of a satellite-borne operating system and application software in the constellation system of the loop are realized, the function relates to a plurality of satellites in the constellation, the on-ground installation test verification cannot be realized, the cost of on-orbit test verification and modification is high, short plates with insufficient ground test verification can be supplemented by the application, and good innovation and engineering application value are realized.
Drawings
Other features, objects and advantages of the present application will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:
FIG. 1 is a flow chart of a satellite simulator system with a satellite-borne operating system in the loop and a closed-loop simulation test method according to the present application;
fig. 2 is a flowchart of a method for simulating and verifying the constellation cooperation and intelligent management of the satellite-borne operating system and the application software in the ring.
Detailed Description
The present application will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the present application, but are not intended to limit the application in any way. It should be noted that variations and modifications could be made by those skilled in the art without departing from the inventive concept. These are all within the scope of the present application.
Examples
Referring to FIG. 2, the present application provides a satellite simulator system with a satellite-borne operating system in the loop, comprising: virtual spaceborne computer, system model and co-simulation bus;
the virtual spaceborne computer is used for simulating software and hardware of a real spaceborne computer and running a real spaceborne operating system and application software;
the system model is used for simulating each system function of the satellite;
the collaborative simulation bus is used for information interaction and synchronous simulation of the virtual spaceborne computer and the system model.
The virtual spaceborne computer comprises hardware simulation; the hardware simulation comprises a CPU core board of the spaceborne computer, a channel gateway peripheral, an inter-satellite communication peripheral, a serial time base peripheral, a bus peripheral, a comprehensive interface peripheral and a time management module simulation unit.
The virtual spaceborne computer comprises software simulation; the software simulation is realized by adding a shipping planet carrier operating system on a virtual CPU core board, and a planet carrier App comprising a planet software, a gesture control software and a task planning software is operated on the planet carrier operating system, so that the digital simulation of the software and the hardware of a planet carrier computer is realized.
The system model completes the function simulation of each system, a standardized interface is adopted, and the model interface comprises a virtual spaceborne computer interaction interface, a model electrical load interface, an inter-model information interface, a model parameter setting interface and a model working state output interface;
the virtual spaceborne computer interaction interface is divided into a direct measurement and control interface, a serial port, a bus interface, a time unification interface, a channel gateway and an inter-spaceborne communication interface according to the interface design of a real spaceborne computer product;
the model electrical load interface simulates the power supply and distribution information simulation of a product, including load power consumption and heat consumption parameters;
the information interface between the models simulates information transfer between systems, including remote sensing data quantity and navigation information;
the model parameter setting interface is used for setting model initial state parameters, adjusting model process parameters and injecting model faults, and the channel gateway peripheral of the virtual spaceborne computer is set uniformly;
the model working state output interface is used for reporting parameters of the model, including dynamic simulation parameters and load data transmission working parameters.
The virtual spaceborne computer runs a real spaceborne operating system and an application App, a virtual bus interface, a direct telemetry and remote control interface, a serial port, a time unified interface, a model electrical load interface, an inter-model information interface, a model parameter setting interface and a model working state output interface are carried out between the system model and the virtual spaceborne computer through a collaborative simulation bus, information interaction between the virtual spaceborne computer and each system model is achieved, and simulation operation of the spaceborne operating system in a satellite simulator of the ring is completed.
The satellite simulator is in seamless connection with the ground comprehensive test system to form a set of satellite-ground closed loop simulation test system, the transmission of remote control instructions and the monitoring of telemetry data are consistent with the real satellite test flow, namely, like the real satellite test, the ground test system transmits remote control instruction excitation through the command software, and the ground test system monitors the telemetry response through the monitoring software to perform the closed loop test of the satellite simulator.
Referring to fig. 1, the application provides a closed loop simulation method of a satellite simulator system with a satellite-borne operating system in a loop, which comprises the following steps:
step 101: the channel gateway of the virtual spaceborne computer and the external interface of the inter-satellite communication interface are network interfaces, the interface protocol is consistent with the network interface protocol of the ground measurement and control baseband equipment, for a ground test system, the channel gateway of the satellite simulator and the inter-satellite communication interface are equivalent to the measurement and control baseband equipment, and are in seamless connection with ground forwarding software to carry out remote control instruction, telemetry frame and inter-satellite information transceiving so as to form a simulation test environment of a satellite-ground closed loop;
step 102: the tester operates ground command software and sends satellite commands, inter-satellite communication information and model parameter setting commands;
step 103: the satellite instruction and the model parameter setting instruction are sent to the channel gateway peripheral equipment of the virtual spaceborne computer through the comprehensive testing server and the forwarding software;
step 104: the channel gateway is provided with an instruction classification function, and the received ground remote control data is divided into a satellite instruction and a model parameter setting instruction;
step 105: the satellite instruction is transmitted to a CPU core board of the virtual spaceborne computer, is interpreted and executed in a spaceborne operating system, and is distributed to a related system model through a peripheral interface of the virtual spaceborne computer;
step 106: the model parameter setting instruction is sent to a corresponding system model to carry out model parameter setting and fault parameter injection;
step 107: the inter-satellite uplink communication information is sent to an inter-satellite communication peripheral of the virtual spaceborne computer through the comprehensive testing server and the forwarding software;
step 108: the inter-satellite uplink information is transmitted to a CPU core board of the virtual spaceborne computer, and analyzed and processed by a spaceborne operating system and application software on the CPU core board;
step 109: and (3) driving a satellite-borne operating system and application software to analyze and process the instructions according to the satellite instructions and the inter-satellite uplink communication information which are uploaded in the steps (1-8) as test excitation input of the virtual satellite-borne computer, and distributing the instructions to each system model by the virtual satellite-borne computer through a collaborative simulation bus to serve as the test excitation input of the system model.
Step 201: each system model responds to instruction excitation input of the virtual computer, simulation output response feedback, and then information interaction is carried out between the system model and the virtual spaceborne computer through a collaborative simulation bus, so that task instruction scheduling, processing and information collection are completed;
step 202: the operation system and the application software on the virtual spaceborne computer organize the collected satellite information into telemetry frames, telemetry is sent to ground forwarding software through the channel gateway peripheral equipment according to a standard measurement and control baseband interface protocol, and the ground forwarding software converts the format of the telemetry frames and then sends the telemetry frames to a comprehensive measurement server for analysis;
step 203: similarly, the inter-satellite downlink communication information generated by the virtual spaceborne computer is sent to ground forwarding software through the inter-satellite communication interface peripheral equipment and is sent to the comprehensive testing server for processing;
step 204: the working state of the system model is used as a type of ground equipment telemetry through a model working state output interface and is sent to a comprehensive testing server for data analysis processing;
step 205: the comprehensive measurement service completes centralized processing of on-board telemetry, inter-board information and model working state information, and transmits the analyzed on-board telemetry, inter-board information and model working state information to a ground monitoring terminal for presentation;
step 206: and on the ground monitoring terminal, the satellite simulator command excitation and the closed-loop monitoring interpretation of the telemetry response are carried out in combination with the remote control command excitation.
And the satellite simulators form a satellite constellation simulation system, and each satellite simulator transmits cooperative information through an inter-satellite communication model to perform satellite constellation joint simulation of a satellite-borne operating system and application software in a ring.
The constructed constellation simulation system and the ground test system simulate a test closed loop, so that the cooperation of a real satellite-borne operating system and a constellation system of application software in the loop and intelligent management test verification are realized.
In conclusion, the satellite simulator with the real satellite-borne operating system and the application software in the loop is constructed, the satellite simulator is in seamless connection with the ground test system, a closed loop is simulated, virtual test is carried out like the test of a real satellite, and the efficiency and the capability of satellite design test and operation and maintenance treatment verification are improved. Meanwhile, a plurality of satellite simulators form a satellite constellation simulation system, a closed loop is simulated by the satellite simulator and a ground test system, the coordination and intelligent management test verification of a satellite-borne operating system and application software in the constellation system of the loop are realized, the function relates to a plurality of satellites in the constellation, the on-ground installation test verification cannot be realized, the cost of on-orbit test verification and modification is high, short plates with insufficient ground test verification can be supplemented by the application, and good innovation and engineering application value are realized.
Those skilled in the art will appreciate that the systems, apparatus, and their respective modules provided herein may be implemented entirely by logic programming of method steps such that the systems, apparatus, and their respective modules are implemented as logic gates, switches, application specific integrated circuits, programmable logic controllers, embedded microcontrollers, etc., in addition to the systems, apparatus, and their respective modules being implemented as pure computer readable program code. Therefore, the system, the apparatus, and the respective modules thereof provided by the present application may be regarded as one hardware component, and the modules included therein for implementing various programs may also be regarded as structures within the hardware component; modules for implementing various functions may also be regarded as being either software programs for implementing the methods or structures within hardware components.
The foregoing describes specific embodiments of the present application. It is to be understood that the application is not limited to the particular embodiments described above, and that various changes or modifications may be made by those skilled in the art within the scope of the appended claims without affecting the spirit of the application. The embodiments of the application and the features of the embodiments may be combined with each other arbitrarily without conflict.
Claims (10)
1. A satellite simulator system with a satellite-borne operating system in the loop, comprising: virtual spaceborne computer, system model and co-simulation bus;
the virtual spaceborne computer is used for simulating software and hardware of a real spaceborne computer and running a real spaceborne operating system and application software;
the system model is used for simulating each system function of the satellite;
the collaborative simulation bus is used for information interaction and synchronous simulation of the virtual spaceborne computer and the system model.
2. The on-board operating system in-loop satellite simulator system of claim 1, wherein the virtual on-board computer comprises a hardware simulation; the hardware simulation comprises a CPU core board of the spaceborne computer, a channel gateway peripheral, an inter-satellite communication peripheral, a serial time base peripheral, a bus peripheral, a comprehensive interface peripheral and a time management module simulation unit.
3. The on-board operating system in-loop satellite simulator system of claim 1 wherein the virtual on-board computer comprises software simulations; the software simulation is realized by adding a shipping planet carrier operating system on a virtual CPU core board, and a planet carrier App comprising a planet software, a gesture control software and a task planning software is operated on the planet carrier operating system, so that the digital simulation of the software and the hardware of a planet carrier computer is realized.
4. The on-loop satellite simulator system of claim 1, wherein the system model performs each system function simulation by adopting a standardized interface, and the model interface comprises a virtual on-satellite computer interaction interface, a model electrical load interface, an inter-model information interface, a model parameter setting interface and a model working state output interface;
the virtual spaceborne computer interaction interface is divided into a direct measurement and control interface, a serial port, a bus interface, a time unification interface, a channel gateway and an inter-spaceborne communication interface according to the interface design of a real spaceborne computer product;
the model electrical load interface simulates the power supply and distribution information simulation of a product, including load power consumption and heat consumption parameters;
the information interface between the models simulates information transfer between systems, including remote sensing data quantity and navigation information;
the model parameter setting interface is used for setting model initial state parameters, adjusting model process parameters and injecting model faults, and the channel gateway peripheral of the virtual spaceborne computer is set uniformly;
the model working state output interface is used for reporting parameters of the model, including dynamic simulation parameters and load data transmission working parameters.
5. The on-loop satellite simulator system of the on-loop satellite operating system according to claim 1, wherein the virtual on-loop computer runs the real on-loop satellite operating system and an application App, and the system model and the virtual on-loop satellite simulator of the on-loop satellite operating system are simulated and run through a co-simulation bus by means of communication of a virtual bus interface, a direct telemetry remote control interface, a serial port, a time unified interface, a model electrical load interface, an inter-model information interface, a model parameter setting interface and a model working state output interface.
6. The satellite simulator system of the on-loop satellite operating system of claim 1, wherein the satellite simulator is in seamless connection with the ground comprehensive test system to form a set of satellite-ground closed loop simulation test system, the sending of the remote control command and the monitoring of the telemetry data are consistent with the real satellite test flow, namely, like the real satellite test, the ground test system sends the remote control command excitation through the software to send the remote control command excitation, and the ground test system monitors the software to monitor the telemetry response to carry out the closed loop test of the satellite simulator.
7. A closed loop simulation method for a satellite simulator system with a satellite-borne operating system in a loop, which is characterized in that the satellite simulator system with the satellite-borne operating system in the loop as claimed in any one of claims 1 to 6 is adopted to execute the following steps:
step 1: the channel gateway of the virtual spaceborne computer and the external interface of the inter-satellite communication interface are network interfaces, the interface protocol is consistent with the network interface protocol of the ground measurement and control baseband equipment, for a ground test system, the channel gateway of the satellite simulator and the inter-satellite communication interface are equivalent to the measurement and control baseband equipment, and are in seamless connection with ground forwarding software to carry out remote control instruction, telemetry frame and inter-satellite information transceiving so as to form a simulation test environment of a satellite-ground closed loop;
step 2: the tester operates ground command software and sends satellite commands, inter-satellite communication information and model parameter setting commands;
step 3: the satellite instruction and the model parameter setting instruction are sent to the channel gateway peripheral equipment of the virtual spaceborne computer through the comprehensive testing server and the forwarding software;
step 4: the channel gateway is provided with an instruction classification function, and the received ground remote control data is divided into a satellite instruction and a model parameter setting instruction;
step 5: the satellite instruction is transmitted to a CPU core board of the virtual spaceborne computer, is interpreted and executed in a spaceborne operating system, and is distributed to a related system model through a peripheral interface of the virtual spaceborne computer;
step 6: the model parameter setting instruction is sent to a corresponding system model to carry out model parameter setting and fault parameter injection;
step 7: the inter-satellite uplink communication information is sent to an inter-satellite communication peripheral of the virtual spaceborne computer through the comprehensive testing server and the forwarding software;
step 8: the inter-satellite uplink information is transmitted to a CPU core board of the virtual spaceborne computer, and analyzed and processed by a spaceborne operating system and application software on the CPU core board;
step 9: and (3) driving a satellite-borne operating system and application software to analyze and process the instructions according to the satellite instructions and the inter-satellite uplink communication information which are uploaded in the steps (1-8) as test excitation input of the virtual satellite-borne computer, and distributing the instructions to each system model by the virtual satellite-borne computer through a collaborative simulation bus to serve as the test excitation input of the system model.
8. The method for closed-loop simulation of a satellite simulator system with an on-board operating system in the loop of claim 7, further comprising:
step 10: each system model responds to instruction excitation input of the virtual computer, simulation output response feedback, and then information interaction is carried out between the system model and the virtual spaceborne computer through a collaborative simulation bus, so that task instruction scheduling, processing and information collection are completed;
step 11: the operation system and the application software on the virtual spaceborne computer organize the collected satellite information into telemetry frames, telemetry is sent to ground forwarding software through the channel gateway peripheral equipment according to a standard measurement and control baseband interface protocol, and the ground forwarding software converts the format of the telemetry frames and then sends the telemetry frames to a comprehensive measurement server for analysis;
step 12: similarly, the inter-satellite downlink communication information generated by the virtual spaceborne computer is sent to ground forwarding software through the inter-satellite communication interface peripheral equipment and is sent to the comprehensive testing server for processing;
step 13: the working state of the system model is used as a type of ground equipment telemetry through a model working state output interface and is sent to a comprehensive testing server for data analysis processing;
step 14: the comprehensive measurement service completes centralized processing of on-board telemetry, inter-board information and model working state information, and transmits the analyzed on-board telemetry, inter-board information and model working state information to a ground monitoring terminal for presentation;
step 15: and on the ground monitoring terminal, the satellite simulator command excitation and the closed-loop monitoring interpretation of the telemetry response are carried out in combination with the remote control command excitation.
9. The closed-loop simulation method of the satellite simulator system in the ring of the satellite-borne operating system according to claim 7, wherein a plurality of satellite simulators form a satellite constellation simulation system, and each satellite simulator transmits cooperation information through an inter-satellite communication model to perform satellite constellation joint simulation of the satellite-borne operating system and application software in the ring.
10. The method for simulating the closed loop of the satellite simulator system with the on-loop satellite operation system according to claim 7, wherein the constructed constellation simulation system and the ground test system simulate a closed loop to realize the constellation system coordination and intelligent management test verification of the real on-loop satellite operation system and the application software.
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| CN202311070165.1A CN117194233A (en) | 2023-08-23 | 2023-08-23 | Satellite simulator system with on-loop satellite-borne operating system and closed-loop simulation test method |
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| CN202311070165.1A CN117194233A (en) | 2023-08-23 | 2023-08-23 | Satellite simulator system with on-loop satellite-borne operating system and closed-loop simulation test method |
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