CN111209219B - Satellite navigation simulation model consistency verification method and system - Google Patents
Satellite navigation simulation model consistency verification method and system Download PDFInfo
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Abstract
The invention provides a satellite navigation simulation model consistency verification method, which comprises the following steps: establishing a test task classification model; establishing a test task verification target system according to different attributes of the test tasks; defining a checking object of the test task; defining and covering comprehensive task evaluation content; and designing various test tasks according to the models and contents related to the evaluation contents. The system comprises a satellite model, an application model, a master control station model, a measurement and control station model, a monitoring station model, an injection station model, a combined model management module, a basic module model parameter and attribute configuration module and a test task parameter configuration module. According to the scheme, a top-down simulation verification method can be provided for a satellite navigation simulation model, the comprehensiveness of a test task is guaranteed to the maximum extent, and a verification result can be directly used for optimizing and upgrading a Beidou engineering system.
Description
Technical Field
The invention mainly relates to the technical field of satellite navigation, in particular to a method and a system for verifying consistency of a satellite navigation simulation model.
Background
The large complex satellite network has large scale, more entities and wide services, and in order to reduce the operation risk of a real system, the operation condition of the real satellite system is simulated by constructing a digital twin software simulation system before the construction of the large complex satellite system. The software simulation system has the advantages of flexibility, openness, foresight and the like which cannot be compared with a hardware system, but the software simulation system firstly needs to pay attention to the equivalence of the simulation system to a real system, and the correctness of a simulation model directly relates to the effectiveness of the whole simulation system. The Beidou global navigation system also needs to build a software simulation system for a core key technology of a verification system which is flexible on the ground, the software simulation of the Beidou system relates to a plurality of equivalent models such as a satellite system model, an operation control system model, a measurement and control system model, an inter-satellite link operation management system model and an application system model, and how to carry out consistency verification on the simulation model and a real model ensures the effectiveness of the simulation system, and becomes the most important part for building the software simulation system.
Through the search of the prior art, the invention of Chinese patent application (application publication number: CN 201710609081.9) is named as a credibility verification method of a high-fidelity simulation model of a satellite navigation system, and mainly aims to solve the problem of credibility of the satellite navigation simulation model. The credibility verification method described by the invention comprises four aspects: the method comprises the steps of establishing a systematized and hierarchical model verification standard tool library, establishing a space-time reference frame, establishing bottom-to-top layer-by-layer progressive weighting inspection, and establishing combination of error separation and back-stepping calculation based on measured data.
However, the invention of the chinese patent application (application publication No. CN 201710609081.9), entitled as a method for verifying the credibility of a high-fidelity simulation model of a satellite navigation system, provides a method only for comparing the refined modeling and model layering results of a single model to verify the credibility of the model, the refined modeling and verification of the simulation model in the ground test verification system of the beidou global navigation system are completed by the corresponding engineering system constructor, thereby ensuring the consistency between the simulation model and the real model, but the real satellite system is service and user-oriented, and the service of the navigation system has its particularity, one service needs to be completed by linking a plurality of models, and the correctness of the single model cannot ensure that it is effective when it participates in the linkage, so the method cannot be used for the consistency verification of the model of the whole satellite navigation system.
The invention relates to a Chinese patent (application publication number: CN 201710608895.0) named as a method for establishing a satellite navigation system test verification and test evaluation mathematical model, and mainly aims to solve the problem of system-level simulation test verification of a satellite navigation system. The method for establishing the test verification and test evaluation mathematical model described by the invention comprises four contents: testing the item to be tested by taking verification, design, construction and application processes as driving; forming a system-level simulation model according to the driving data; and forming a self-closing verification model.
However, the invention is named as a method for establishing a satellite navigation system test verification and test evaluation mathematical model in the Chinese invention patent (application publication number: CN 201710608895.0), and the invention focuses on how to divide the system into a first level, a second level and a third level of granularity to respectively carry out evaluation verification, and similarly, how to carry out test verification on the whole simulation system based on the satellite navigation system service is not mentioned.
In summary, the existing satellite navigation system model verification method and system are either a high-fidelity modeling and verification method for describing models simply or a test evaluation system verification for describing a satellite navigation system systematically, and a method for performing consistency verification on a satellite navigation system software simulation model from a real service perspective is lacked.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides a satellite navigation simulation model consistency verification method for solving the problem of correctness verification of each model in Beidou system ground software simulation, and also provides a satellite navigation simulation model consistency verification system.
The consistency verification method for the satellite navigation simulation model comprises the following steps:
s1: according to the main functions of the satellite navigation system, task classification is carried out from three aspects of functional requirements, test attributes and implementation modes to form task classification models, and each type of model can adopt the same or similar test method.
S2: and (3) checking a task target: and defining the task target content of each type of task according to the test task division classification model to form a fully covered task target system.
S3: explicitly checking the object: and (4) enumerating all covered checking elements in the target task link according to the task target by combining the refined functional requirements of the satellite navigation system.
S4: defining task evaluation content: the main body and the target of task evaluation are made clear through the two steps, and the task evaluation content defines whether the specific behavior content of the inspection object to be evaluated meets the task target.
S5: task design: detailed definition is carried out on the test configuration, the test process and the test result of each task according to the task evaluation content;
s6: putting the model into a simulation platform, and evaluating simulation operation; if the behavior of the model in the evaluation process is in accordance with the expectation, namely the performance of various detection points in the evaluation meets the expectation, the consistency of the satellite navigation simulation model is expected.
As a further improvement of the present invention, in the step S1, the task classification model divides the satellite navigation system test tasks into measurement-class test tasks and information-class test tasks.
As a further improvement of the present invention, in the step S2, the information-based test task is targeted for correctness evaluation, consistency evaluation, completeness evaluation, and timeliness evaluation; the test task target of the measurement-like task is a system orbit determination and time synchronization index and a difference and integrity evaluation index.
As a further improvement of the present invention, in step S3, the object to be checked in the information type test is information content and information execution carrier; the checking object of the measurement type test is a system key system.
As a further improvement of the present invention, in step S4, in combination with the functional requirements of the satellite navigation system, the task evaluation content of the information-based test includes: the method comprises an L satellite ground downlink loop information flow test, an L uplink S remote measurement downlink loop information flow test, a multi-satellite inter-satellite link information flow test and an inter-satellite ground information flow test. The measurement-class task content comprises: the method comprises the following steps of carrying out system measurement test under the conventional condition of networking constellation inter-satellite ground, carrying out system measurement test under the fault condition of networking constellation inter-satellite ground, carrying out system measurement test under the networking condition of networking constellation inter-satellite ground, carrying out system measurement test under the conventional condition of networking constellation autonomous operation, and carrying out system measurement test under the fault condition of networking constellation autonomous operation.
As a further improvement of the present invention, in step S5, the task design includes a scene configuration design, a test method design, a probe point design, and the like, the test method involves a complicated internal processing flow, and the present invention focuses on the scene configuration design and the probe point design. The detection point design covers the monitoring content of each node in the task test link, and the test result of each node can be traced.
The consistency verification system for the satellite navigation simulation model comprises the following steps: the system comprises a satellite model, an application model, a master control station model, a measurement and control station model, a monitoring station model, an injection station model, a combined model management module, a basic module model parameter and attribute configuration module and a test task parameter configuration module;
the receiving end of the satellite model is connected with an injection station model, and the sending end of the satellite model is respectively connected with an application model, a monitoring station model and a measurement and control station model, so as to be used for downloading navigation messages, generating telemetering downlink information, grouping solution frame inter-satellite transmission information and resolving satellite orbit and clock error under an autonomous navigation mode;
the receiving end of the application model is connected with the satellite model and used for completing user navigation calculation according to the navigation signal observation value and the navigation message information;
the receiving end of the monitoring station model is connected with the satellite model and used for receiving and analyzing the downlink navigation message; the sending end of the monitoring station model is connected with the main control station model and used for transmitting the navigation message frame format information back to the main control station model;
the receiving end of the measurement and control station model is connected with the satellite model, and the sending end of the measurement and control station model is connected with the main control station model so as to be used for uploading remote control instructions and inter-satellite control and management information and receiving the uploading receipt information of operation and control;
the receiving end of the master control station model is connected with the monitoring station model and the measurement and control station model, and the transmitting end is connected with the injection station model so as to realize precise orbit determination, time synchronization, message parameter generation, upper-injection message editing, navigation message upper injection and receiving of navigation messages returned by the monitoring station;
the receiving end of the injection station model is connected with the master control station and used for receiving an upper injection message data frame sent by a master control station communication system, and the output end of the injection station model is connected with the satellite model and used for injecting a navigation message frame format;
the combined model management module is used for carrying out combined configuration on each model;
the basic module model parameter and attribute setting module is used for configuring parameters for each model;
the test task parameter configuration is used for configuring system time, system working modes and system scenes.
As a further improvement of the invention, the test task parameter configuration module is used for carrying out combined calling on each model aiming at different test tasks according to scene configuration, the configuration of the model is imported from the model parameter and attribute setting of the basic module, and each node connected with the model is transparent and is used as a detection point for carrying out data monitoring.
Compared with the prior art, the invention has the advantages that:
1. compared with the traditional method, the verification method and the verification system from task classification to task design provided by the invention provide a top-down simulation verification design idea, and the comprehensiveness of the test task is ensured to the maximum extent.
2. The task target system comprises a general information type checking target system and a specific measurement type checking target system of the navigation system, and compared with the traditional method, the target system covers the test target of the navigation system more comprehensively, wherein the information type checking target system can also be generally used in other systems.
3. The checking object and the task evaluation content in the invention correspond to the operation participation elements and behaviors of the engineering system one by one, and the verification result is directly used for optimizing and upgrading the Beidou engineering system.
4. The detection point design in the task design covers each node in the task link, and the problem node can be effectively traced.
Drawings
Fig. 1 is a schematic flow chart of a method for verifying consistency of a satellite navigation simulation model according to an embodiment of the present invention.
Fig. 2 is a schematic structural diagram of a system for verifying consistency of a satellite navigation simulation model according to an embodiment of the present invention.
FIG. 3 is a schematic diagram of a design of a classification model of a test task of a satellite navigation system according to an embodiment of the present invention.
Fig. 4 is a schematic design diagram of a test verification target system of the satellite navigation system in the embodiment of the present invention.
Fig. 5 is a schematic diagram illustrating experimental content design of a satellite navigation system according to an embodiment of the present invention.
Detailed Description
Fig. 1 is a schematic flow chart of a method for verifying consistency of a satellite navigation simulation model according to an embodiment of the present invention, which includes the following steps.
And S1, establishing a classification model of the Beidou navigation system test task according to the functional requirements of the navigation system.
Specifically, the classification model of the Beidou navigation system test task comprises the following steps:
1) the time and space unified driving test task is as follows: a test task based on a time-frequency unified signal;
2) signal layer test tasks: testing tasks based on signal sending, transmission and receiving;
3) communication layer test tasks: and a test task based on the transmission, transmission and reception of the information carried on the signal. The method comprises the steps of whole network connectivity, communication time delay between any nodes, communication capacity, communication quality and the like;
4) testing tasks of a measuring layer: the test tasks based on the measurement performance of the navigation system comprise orbit determination performance, time synchronization performance, ephemeris clock prediction performance, difference performance and integrity performance;
5) service layer test tasks: the test task based on the service performance of the navigation system comprises the PVT precision, integrity, continuity and availability of a user;
6) the satellite model based on software simulation can not directly verify a system signal layer, and a simulation test task mainly verifies a communication layer, a measurement layer and a service layer of the system;
7) the measurement layer and the service layer both take the measurement performance index as a verification target, and the communication layer takes the correctness of the information flow as a verification target, so the measurement layer and the service layer are divided into an information verification task and a measurement verification task according to the verification targets of the communication layer, the measurement layer and the service layer.
And S2, according to the classification of the classification model, verifying targets of the information class verification task and the measurement class verification task are determined.
Specifically, validating the verification target includes:
1) the verification target of the information verification task is as follows: correctness, consistency, completeness, timeliness. Wherein the correctness verification target comprises the correctness of the information format and the correctness of the information dissemination. The consistency verification target comprises information constraint consistency, information transmission consistency, instruction response consistency and exception handling strategy consistency. The completeness verification index comprises complete file system, complete information elements and consistent information constraint and system requirement. The timeliness verification target comprises timely information updating frequency, reasonable node information processing and propagation delay and reasonable system overall delay of information propagation;
2) the measurement type test target is a fixed orbit and time synchronization system, a difference and integrity system of the verification system under a specific inter-satellite link system and a working mode. a) The system orbit determination and time synchronization evaluation system contains inter-satellite time synchronization precision, satellite-ground combined orbit determination precision, autonomous orbit determination precision and system equivalent measurement error. b) The difference and integrity evaluation system contains integrity alarm time, integrity alarm threshold, integrity risk probability, spatial signal correction precision and ionospheric grid correction precision.
And S3, defining the checking objects of the information type test task and the measurement type test task.
Specifically, the verification object includes:
1) the checking object of the information class shall include but not be limited to information content and information execution carrier: the information content, namely each content defined in the air interface control file between systems, is mainly divided into three types, namely navigation service parameters, upper note management control instructions and inter-satellite control and management instruction parameters. The information execution carrier is a carrier in a system such as a satellite model, an operation control model, a measurement and control model, a user model and the like, mainly comprises a navigation task processing unit of a satellite, a management and control system of operation control, a communication system and the like, and checks the correctness of the information execution carrier in information processing or execution (such as information framing, information analysis, information format rearrangement, control instruction information response and the like);
2) the checking object of the measurement type test is a key system of the Beidou navigation system: the system comprises an inter-satellite link system, a satellite-ground combined orbit determination and time synchronization system, an autonomous orbit determination and time synchronization system and a difference and integrity monitoring system.
And S4, defining the evaluation content of the information type test task and the measurement type test task.
Specifically, the evaluation content includes:
1) the information flow checking and verifying test follows the principle of staged, hierarchical and progressive expansion. According to the information link, the information flow verification test of the Beidou navigation system comprises but is not limited to: local loop tests such as an L-satellite ground downlink loop, an L-uplink S telemetering downlink loop and a multi-satellite-to-satellite forwarding loop and an inter-satellite-to-ground information flow test extended to a full link;
2) the evaluation content of the measurement type test task of the Beidou navigation system comprises but is not limited to: the method comprises the following steps of carrying out system measurement test under the conventional condition of networking constellation inter-satellite ground, carrying out system measurement test under the fault condition of networking constellation inter-satellite ground, carrying out system measurement test under the networking condition of networking constellation inter-satellite ground, carrying out system measurement test under the conventional condition of networking constellation autonomous operation, and carrying out system measurement test under the fault condition of networking constellation autonomous operation.
S5, the content of task design comprises scene design and probe point design.
Specifically, the scene design and detection points include:
1) l star uplink and downlink loop information flow test: the scene configuration is 1 network star (namely satellite model) and 1 master control station (including the survey system model, the management and control system model and the downlink monitoring receiving model of the operation and control system). Designing a detection point: the system comprises a management and control system inlet and outlet, a communication system outlet, a satellite model inlet and outlet and a downlink signal monitoring system inlet and outlet;
2) l downlink S telemetry loop information flow test: the scene configuration is 1 network star (namely satellite model), 1 master control station (including a communication system model and a control system model of an operation control system) and 1 measurement and control station model. Designing a detection point: an inlet of the control system, an outlet of the satellite model and an inlet of the measurement and control station;
3) testing the information flow of the multi-satellite link: the scene is configured as 5 sets of satellites (i.e., satellite models). Designing a detection point: the inlet and outlet of each satellite;
4) inter-satellite and inter-satellite information flow test: the inter-satellite and inter-ground test comprises a satellite-ground combined mode operation and an autonomous navigation mode operation, wherein a scene of the satellite-ground combined operation is configured into 5 networking satellites (namely a satellite model), 2 operation and control ground stations (a participation model comprises a control model, a communication measurement model, a downlink signal monitoring and receiving model, an inter-station model, a network management center model and a remote monitoring station model of a measurement and control system) and 1 measurement and control station model, and a scene of the autonomous navigation is configured into 5 networking satellites (namely a satellite model) and a plurality of anchoring stations. Designing a detection point: the system comprises a management and control system inlet and outlet, a communication system outlet, a satellite inlet and outlet, a downlink signal monitoring system inlet and outlet, a measurement and control network management center outlet, a measurement and control station outlet, a satellite inlet and outlet and an anchoring station outlet;
5) systematic measurement test under the conventional condition of the satellite-to-satellite ground: scene configuration: the system comprises a networking satellite constellation (satellite model), a ground test support system full operation and control station type (a master control station, an injection station, a monitoring station and a parallel address anchoring station), an inter-satellite link task management center and a measurement and control station of the operation and control system. Designing a detection point: a master control station information processing system;
6) the system measurement test under the condition of inter-satellite and inter-ground faults: scene configuration: the difference from the 5 th test is that the scene sets fault scenes such as satellite or detection station node failure, partial measurement data loss, partial link fault, abnormal measurement data input time sequence and the like. Designing a detection point: a master control station information processing system;
7) and (3) performing system measurement test under the condition of inter-satellite and inter-ground networking: scene configuration: the difference from the 5 th test is that the constellation configuration is different networking constellations which are accessed to the network one by one according to the networking sequence of all networking satellite models. Designing a detection point: a master control station information processing system;
8) and (3) carrying out system measurement test under the conventional conditions by self-operation: scene configuration: the difference from the 5 th test is that the system is in an autonomous operation state or a semi-autonomous operation state without a ground monitoring station or only a ground anchoring station. Designing a detection point: a master control station information processing system;
9) and (3) performing system measurement test under the condition of autonomous operation fault: scene configuration: the method is different from the 8 th test in fault scenes of failure of a satellite or a detection station node, loss of partial measurement data, partial link failure, abnormal input time sequence of the measurement data and the like. Designing a detection point: and the master control station information processing system.
S6: putting the model into a simulation platform, and evaluating simulation operation; if the behavior of the model in the evaluation process is in accordance with the expectation, namely the performance of various detection points in the evaluation meets the expectation, the consistency of the satellite navigation simulation model is expected.
Fig. 2 is a schematic structural diagram of a system for implementing a satellite navigation simulation model consistency verification according to an embodiment of the present invention.
The system according to the embodiment comprises a combined model management module 1, basic module model parameters and attribute setting 2, test task parameter configuration 3, a satellite model 4, an application model 5, a measurement and control station model 6, a monitoring station model 7, a master control station model 8 and an injection station model 9.
Specifically, the combined model management module 1 supports the user to perform combined configuration on each model. The basic module model parameters and properties settings 2 configure the individual models with their respective required parameters. The test task parameter configuration 3 is the configuration of the system time, the system working mode, the system scene and the like in the test task. The satellite model 4 is a simulation model developed according to engineering requirements, and can receive an upper power message, a lower power message, generate telemetering downlink information, assemble and disassemble inter-satellite transmission information, and resolve satellite orbits and clock errors in an autonomous navigation mode. The application model 5 is a user application model, can receive downlink navigation messages, analyzes message parameters, and completes user navigation calculation according to the navigation signal observation value and the navigation message information. The measurement and control station model 6 can upload remote control instructions and inter-satellite control and management information, receive upload receipt information of operation and control, and the like. The monitoring station model 7 mainly receives and analyzes the downlink navigation message, and transmits the frame format information of the navigation message back to the master control station communication system. The master control station model 8 comprises a signal processing system, a control system and a communication system, and mainly completes precision orbit determination, time synchronization, message parameter generation, upper note message editing, navigation message upper note and navigation message return receiving of the monitoring station. The injection station model 9 receives an upper note text data frame sent by the master control station communication system, and the upper note navigation text frame format.
FIG. 3 is a schematic diagram of a design of a classification model of a test task for a satellite navigation system according to an embodiment of the present invention.
Specifically, a test task classification model of the satellite navigation system is pyramid-shaped, a time-space unified drive mode and a signal layer are used as a basis, a communication layer and a measurement layer are main functions of the navigation system, the communication layer is related to information flow, the measurement layer is related to calculation and analysis of navigation signals, the uppermost layer is a service layer, and performance indexes of the service layer are mainly positioning time service precision, integrity, availability, continuity and the like of a user.
Fig. 4 is a schematic design diagram of a test verification target system for a satellite navigation system according to an embodiment of the present invention.
Specifically, the invention describes a test verification target system established by the invention, and the information flow verification stage solves the verification problem of system information transmission and operation control response. The information content among satellite systems is various and complex, and the comprehensiveness of verification is ensured by comparing the index system after the division according to the information type and the information hierarchy. The verification target of the information verification task, namely an information verification target system, comprises correctness, consistency, completeness and timeliness. The correctness comprises information format correctness and information broadcasting correctness, the consistency comprises information constraint consistency, information transmission consistency, instruction response consistency and exception handling strategy consistency, the completeness comprises file system completeness, information element completeness, information constraint consistency and system requirements, and the timeliness comprises timely information updating frequency, reasonable node information processing and propagation delay and reasonable system overall delay of information propagation.
And (3) the verification targets of the measurement verification tasks, namely all indexes of orbit determination and time synchronization evaluation, difference and integrity evaluation of the measurement verification target system coverage system. The system orbit determination and time synchronization evaluation comprises satellite-ground time synchronization precision, inter-satellite time synchronization precision, satellite-ground combined orbit determination precision, autonomous orbit determination precision and system equivalent measurement errors; the difference and integrity assessment include integrity alarm time, integrity alarm threshold, integrity risk probability, spatial signal correction accuracy, and ionospheric grid correction accuracy.
As shown in fig. 5, which is a system architecture for designing test contents, the test contents of the satellite navigation system in the embodiment of the present invention are an information flow type test task and a measurement type test task. The information flow test covers information flow tests of L and S links of the satellite and links among satellites, and specifically comprises local loop tests of L satellite uplink and downlink loops, L uplink and S remote measurement downlink loops, multi-satellite-to-satellite forwarding loops and the like, and inter-satellite-to-ground information flow tests extending to a full link. The measurement type test covers all index measurement contents under the normal and fault modes of inter-satellite space and autonomous operation, and specifically comprises a system measurement test under the normal condition of the networking satellite constellation inter-satellite space, a system measurement test under the fault condition of the networking satellite constellation inter-satellite space, a system measurement test under the networking condition of the networking satellite constellation inter-satellite space, a system measurement test under the normal condition of the networking satellite constellation autonomous operation and a system measurement test under the fault condition of the networking satellite constellation autonomous operation.
It should be noted that: the present invention may be implemented in software and/or in a combination of software and hardware, for example, the various means of the invention may be implemented using Application Specific Integrated Circuits (ASICs) or any other similar hardware devices. In one embodiment, the software program of the present invention may be executed by a processor to implement the steps or functions described above. Also, the software programs (including associated data structures) of the present invention can be stored in a computer readable recording medium, such as RAM memory, magnetic or optical drive or diskette and the like. Further, some of the steps or functions of the present invention may be implemented in hardware, for example, as circuitry that cooperates with the processor to perform various steps or functions.
It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned. Furthermore, it is obvious that the word "comprising" does not exclude other elements or steps, and the singular does not exclude the plural. A plurality of units or means recited in the system claims may also be implemented by one unit or means in software or hardware. The terms first, second, etc. are used to denote names, but not any particular order.
Claims (7)
1. A satellite navigation simulation model consistency verification method is characterized by comprising the following steps:
s1: establishing a test task classification model, wherein the test task comprises an information verification task and a measurement verification task;
s2: determining the verification targets of the information verification task and the measurement verification task;
s3: determining the checking objects of the information verification task and the measurement verification task, wherein the checking objects of the information verification task comprise information content and an information execution carrier, and the checking object of the measurement verification task is a key system of the Beidou navigation system;
s4: defining and covering comprehensive task evaluation content according to the behavior of the participation of the checking object, wherein the task evaluation content comprises the evaluation content of the information verification task and the evaluation content of the measurement verification task;
s5: according to the satellite navigation simulation model and the content related to the task evaluation content, carrying out scene configuration design, test method design and detection point design on various test tasks;
s6: putting the satellite navigation simulation model into a simulation platform, and evaluating simulation operation; and if the behavior of the satellite navigation simulation model in the evaluation process is in accordance with expectation, indicating that the satellite navigation simulation model is consistent with the real satellite navigation system.
2. The method for verifying the consistency of the satellite navigation simulation model according to claim 1, wherein: the test task classification model in the step S1 comprises a time-space unified driving test task, a communication layer test task, a measurement layer test task and a service layer test task; the time and space unified driving test task, the measurement layer test task and the service layer test task belong to a measurement type verification task, and the communication layer test task belongs to an information type verification task.
3. The method for verifying the consistency of the satellite navigation simulation model according to claim 2, wherein: the verification targets of the information verification task in the step S2 are correctness assessment, consistency assessment, completeness assessment and timeliness assessment; the verification target of the measurement verification task is system orbit determination and time synchronization evaluation and difference and integrity evaluation.
4. The method for verifying the consistency of the satellite navigation simulation model according to claim 1, wherein: in the step S3, the information content is defined in the air interface control file between systems, and the information execution carrier includes a satellite model, an operation control model, a measurement and control model, and a user model; the checking objects of the measurement verification task comprise an inter-satellite link system, a satellite-ground joint orbit determination and time synchronization system, an autonomous orbit determination and time synchronization system and a difference and integrity monitoring system.
5. The method for verifying the consistency of the satellite navigation simulation model according to claim 1, wherein: the evaluation content of the information verification task in the step S4 covers the local loop link and the full link, and includes an L-constellation uplink and downlink loop information flow test, an L-uplink S-telemetry downlink loop information flow test, a multi-constellation inter-satellite link information flow test, and an inter-constellation inter-satellite information flow test; the evaluation content of the measurement verification task covers all index measurement contents of an inter-satellite space, an autonomous operation normal mode and a fault mode, and comprises a system measurement test under a normal condition of the inter-satellite space of a networking satellite constellation, a system measurement test under a fault condition of the inter-satellite space of the networking satellite constellation, a system measurement test under a networking condition of the inter-satellite space of the networking satellite constellation, a system measurement test under a normal condition of the autonomous operation and a system measurement test under a fault condition of the autonomous operation.
6. The method for verifying the consistency of the satellite navigation simulation model according to claim 1, wherein: the scene configuration design in the step S5 is designed around a simulation model of the satellite navigation system, and different simulation models are configured for different test tasks, where the simulation models are selected from a satellite model, a communication measurement system model of an operation and control system, a management and control system model, a downlink monitoring receiving model, an inter-station model, a measurement and control system model, a telemetry station model, and an anchoring station model.
7. The method for verifying the consistency of the satellite navigation simulation model according to claim 6, wherein: in the step S5, the probe point is designed to cover the entrance and exit of each simulation model.
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| CN112434436B (en) * | 2020-12-01 | 2022-05-20 | 中国人民解放军国防科技大学 | Inter-satellite link scheduling method and system for Beidou navigation satellite system |
| CN112600611A (en) * | 2020-12-09 | 2021-04-02 | 中国科学院国家空间科学中心 | Scene configuration system for spatial internet constellation compatibility analysis simulation system |
| CN112803993B (en) * | 2021-04-13 | 2021-07-16 | 北京理工大学 | Short message system-oriented uplink signal system verification method and device |
| CN113296126B (en) * | 2021-04-25 | 2023-06-30 | 中国空间技术研究院 | Reliability verification and evaluation method for autonomous navigation software |
| CN113452430B (en) * | 2021-06-16 | 2023-03-10 | 中国电子科技集团公司第五十四研究所 | Ground agent system for testing navigation satellite and navigation satellite testing method |
| CN113484881B (en) * | 2021-06-30 | 2024-04-26 | 中国科学院微小卫星创新研究院 | Autonomous judging system and method for correctness of navigation message |
| CN113703009B (en) * | 2021-07-30 | 2022-03-25 | 中国人民解放军91977部队 | Satellite detection offshore target capability evaluation system and method |
| CN113688039B (en) * | 2021-08-20 | 2023-10-31 | 成都天奥测控技术有限公司 | Digital twinning-based simulation verification method for automatic test system |
| CN114325765B (en) * | 2022-03-14 | 2022-07-29 | 浙江时空道宇科技有限公司 | Integrity detection optimization method and computer-readable storage medium |
| CN115356952B (en) * | 2022-10-20 | 2023-01-31 | 中国人民解放军国防科技大学 | Self-closed loop checking method for digital model of aerospace system |
| CN115494525B (en) * | 2022-10-28 | 2023-03-10 | 中国人民解放军国防科技大学 | White box type ground parallel diagnosis system and method for satellite on-orbit fault |
| CN115575982B (en) * | 2022-11-24 | 2023-03-28 | 中汽研软件测评(天津)有限公司 | Method, apparatus and storage medium for determining robustness of vehicle-mounted satellite positioning system |
| CN115904333B (en) * | 2023-01-09 | 2023-10-13 | 中国人民解放军国防科技大学 | Design method and system of extensible satellite ground integrated test system |
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| CN102736520B (en) * | 2011-04-13 | 2015-08-12 | 北京邮电大学 | A kind of satellite navigation system principles simulation method and satellite signal simulator |
| CN103278822B (en) * | 2013-05-23 | 2015-09-30 | 桂林电子科技大学 | Based on satellite navigation and location system performance evaluation system and the method for HLA platform |
| CN103617332B (en) * | 2013-12-11 | 2016-10-05 | 北京北斗星通导航技术股份有限公司 | A kind of emulation platform measuring satellite navigation algorithm performance and method |
| CN106383357A (en) * | 2016-11-18 | 2017-02-08 | 中国航天标准化研究所 | Navigation information flow system simulating operation of satellite navigation system |
| CN107203683B (en) * | 2017-07-24 | 2018-04-06 | 中国人民解放军国防科学技术大学 | Satellite navigation system level is increased income the method for building up of analogue system |
| CN107423508B (en) * | 2017-07-24 | 2018-06-01 | 中国人民解放军国防科学技术大学 | Satellite navigation system verification experimental verification and the method for building up of test assessment mathematical model |
| CN107368659B (en) * | 2017-07-24 | 2018-06-01 | 中国人民解放军国防科学技术大学 | The reliability verification method of satellite navigation system high-fidelity simulation model |
| CN109542084B (en) * | 2018-11-19 | 2020-06-12 | 北京航空航天大学 | Integrity fault simulation method for satellite-based augmentation system |
| CN111221271B (en) * | 2020-04-22 | 2020-07-28 | 中国人民解放军国防科技大学 | Beidou satellite autonomous navigation parallel simulation method and system |
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Application publication date: 20200529 Assignee: Hunan Institute of advanced technology Assignor: National University of Defense Technology Contract record no.: X2022430000005 Denomination of invention: A method and system for verifying the consistency of satellite navigation simulation model Granted publication date: 20200901 License type: Common License Record date: 20220628 |