CN114660632A - Test method of navigation enhancement system - Google Patents
Test method of navigation enhancement system Download PDFInfo
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- CN114660632A CN114660632A CN202210145507.0A CN202210145507A CN114660632A CN 114660632 A CN114660632 A CN 114660632A CN 202210145507 A CN202210145507 A CN 202210145507A CN 114660632 A CN114660632 A CN 114660632A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/13—Receivers
- G01S19/23—Testing, monitoring, correcting or calibrating of receiver elements
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Abstract
One embodiment of the invention discloses a test method of a navigation enhancement system, which is characterized by comprising the following steps: s10: the method comprises the following steps that a navigation enhanced load device, a satellite-borne navigation monitoring receiver and a satellite-borne rubidium clock are used for carrying out interface matching test and function and performance index test; s20: testing the navigation enhancement terminal; s30: the time of the navigation enhancement load device, the satellite-borne navigation monitoring receiver, the navigation enhancement terminal, the channel simulator and the navigation data center is synchronized; s40: and performing interface, function, performance and full-flow test on the navigation enhancement load device, the ground navigation enhancement terminal, the navigation data center, the navigation signal simulator and the channel simulator to verify the correctness of the design of the navigation enhancement system signal and information link, the signal generation and the data processing.
Description
Technical Field
The present invention relates to the field of low earth orbit satellites. And more particularly, to a method of testing a navigation enhancement system.
Background
With the rapid development of the internet constellation of low-earth orbit satellites, the enhancement of navigation based on low-earth orbit satellites (LEO) becomes a research hotspot. The low-orbit navigation enhancement system can enhance the positioning accuracy of a high-orbit navigation satellite, can be used as a space-based monitoring station to monitor the integrity of signals of a medium-orbit navigation satellite, and can improve the estimation accuracy of orbit determination and clock error of the satellite; the low-orbit satellite has low orbit height, is easy to form a signal enhancement effect on the ground, and can enhance the positioning effect under interference, shielding and complex environments. The low-orbit navigation enhancement system can also be used as a standby navigation positioning and time service means under the condition that the navigation signals of the medium and high orbit satellites are interfered or rejected.
The simulation verification system is a key link for verifying the design rationality of the low-orbit navigation enhancement system, but the problems that how to verify the correctness of signals and information flow between low-orbit navigation enhancement satellite-ground equipment, test verification of the function and performance of a load on a satellite, and closed-loop simulation verification of the positioning precision, the backup navigation capability and the like which can be realized by the whole low-orbit navigation enhancement system still need to be solved.
Disclosure of Invention
In view of the above, a first embodiment of the present invention provides a method for testing a navigation enhancement system, including:
s10: the method comprises the following steps that a navigation enhanced load device, a satellite-borne navigation monitoring receiver and a satellite-borne rubidium clock are used for carrying out interface matching test and function and performance index test;
s20: testing the navigation enhancement terminal;
s30: the time of the navigation enhancement load device, the satellite-borne navigation monitoring receiver, the navigation enhancement terminal, the channel simulator and the navigation data center is synchronized;
s40: and performing interface, function, performance and full-flow test on the navigation enhancement load device, the ground navigation enhancement terminal, the navigation data center, the navigation signal simulator and the channel simulator to verify the correctness of the design of the navigation enhancement system signal and information link, the signal generation and the data processing.
In a specific embodiment, the S10 includes:
said satellite-borne rubidium clock providing a reference frequency signal for said navigation enhancing load device and said navigation monitoring receiver,
the navigation monitoring receiver receives the navigation signal simulator signal for positioning and time service,
and the navigation enhanced load device carries out time synchronization with the time information through the 1PPS output by the satellite-borne navigation monitoring receiver.
In a specific embodiment, the S20 includes:
the navigation data center generates low-orbit satellite simulation ephemeris,
the navigation signal simulator generates low orbit satellite simulation signals according to the ephemeris data and sends the signals to the navigation enhancement terminal,
and testing the function and performance indexes of the navigation enhancement terminal according to the low-orbit satellite simulation signal.
In a specific embodiment, in step S30, the navigation signal simulator sends a GNSS signal simulating a low earth orbit satellite trajectory to the on-board monitoring receiver, and sends a GNSS signal simulating a ground user trajectory to the navigation enhancement terminal and the channel simulator.
In a specific embodiment, the method further comprises:
s50: and connecting the navigation enhancement load device with load interface matching equipment, and controlling and receiving data of the navigation enhancement load device.
In one embodiment, the transmitting antenna of the navigation enhancement loading device and the receiving antenna of the navigation enhancement terminal are placed in a microwave dark box.
In a specific embodiment, the navigation enhancement load device, the satellite-borne navigation monitoring receiver, the navigation signal simulator and the satellite-borne rubidium clock are placed in a microwave camera obscura.
The invention has the following beneficial effects:
the invention provides a test method of a navigation enhancement system, which synchronously simulates a satellite-borne track and a ground user track through a navigation signal simulator, thereby not only ensuring the consistency with an in-orbit scene of a real satellite, but also ensuring the signal and time uniformity between the satellite and the ground; through simulated ground station observation data and observation data resolved by a navigation monitoring receiver in real time, the most real system working condition of the simulated satellite in orbit can be simulated, signals transmitted to the received signals and information transmission can be processed in a closed loop in real time, and the functions and the performances of equipment in the system can be tested to the greatest extent; the system can perform closed-loop simulation test on the precision of the navigation enhancement system, generate navigation enhancement information through data processing, broadcast the navigation enhancement information through the load device, perform high-precision positioning processing after receiving the navigation enhancement information by the ground terminal, and test the service precision of the navigation enhancement system.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 shows a flow diagram of a method of testing a navigation enhancement system according to one embodiment of the invention;
FIG. 2 shows a block diagram of an on-board load subsystem test according to an embodiment of the invention;
FIG. 3 illustrates a navigation enhanced terminal test block diagram according to one embodiment of the present invention;
FIG. 4 illustrates a system connection diagram in accordance with one embodiment of the present invention;
FIG. 5 illustrates testing of a navigation enhancement system according to one embodiment of the present invention;
FIG. 6 illustrates a navigation enhancement payload device peripheral interface schematic according to one embodiment of the invention;
FIG. 7 illustrates a low-earth-orbit satellite-enhanced GNSS mode in accordance with an embodiment of the present invention;
FIG. 8 illustrates a low earth orbit satellite standby navigation positioning mode according to one embodiment of the present invention;
FIG. 9 illustrates an autonomous generation of low-orbit satellite ephemeris pattern by a satellite-borne receiver according to one embodiment of the invention.
Detailed Description
In order to make the technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail with reference to the accompanying drawings.
As shown in fig. 1, an embodiment of the present invention provides a method for testing a navigation enhancement system, including:
s10: the method comprises the following steps that a navigation enhanced load device, a satellite-borne navigation monitoring receiver and a satellite-borne rubidium clock are used for carrying out interface matching test and function and performance index test;
as shown in FIG. 2, at this stage, the navigation enhancement load, the satellite-borne navigation monitoring receiver and the miniaturized satellite-borne rubidium clock are subjected to an integrated test. And completing interface matching tests among components/single units of an on-satellite load subsystem consisting of a navigation enhanced load, a satellite-borne navigation monitoring receiver and a miniaturized satellite-borne rubidium clock, and testing functions and performance indexes of the subsystem.
Specifically, the S10 includes: said satellite-borne rubidium clock providing a reference frequency signal for said navigation enhancing load device and said navigation monitoring receiver,
the navigation monitoring receiver receives the navigation signal simulator signal for positioning and time service,
and the navigation enhanced load device carries out time synchronization with the time information through the 1PPS output by the satellite-borne navigation monitoring receiver.
S20: testing the navigation enhancement terminal;
as shown in fig. 3, this stage is independent simulation and test, and is mainly used for terminal test, simulation analysis, demonstration verification, and the like. Specifically, the S20 includes: the navigation data center is responsible for data simulation of the system and generating low-orbit satellite simulation ephemeris, almanac, error model data and the like.
The navigation signal simulator generates low earth orbit satellite simulation signals according to ephemeris data and sends the low earth orbit satellite simulation signals to the navigation enhancement terminal, before the low earth orbit satellite simulation signals are in butt joint with a load, the functions and performance indexes of the navigation enhancement terminal are verified in advance, and the low earth orbit satellite simulation signals can be used for verifying the single-satellite and multi-satellite independent navigation and positioning capabilities of the low earth orbit satellite.
And testing the function and performance indexes of the navigation enhancement terminal according to the low-orbit satellite simulation signal.
S30: the time of the navigation enhancement load device, the satellite-borne navigation monitoring receiver, the navigation enhancement terminal, the channel simulator and the navigation data center is synchronized;
as shown in fig. 4, the joint debugging test of the navigation enhancement system needs to ensure time synchronization of the navigation enhancement load, the satellite-borne navigation monitoring receiver, the navigation enhancement terminal (ground monitoring station), the channel simulator and the navigation data center, wherein the satellite-borne navigation monitoring receiver, the navigation enhancement terminal (ground monitoring station) and the channel simulator interface matching device can receive a simulated GNSS satellite navigation signal in a line feed manner or receive a signal output by the multi-carrier navigation signal simulator in an air feed manner, thereby ensuring time synchronization of the system.
Because the satellite-borne navigation monitoring receiver and the ground equipment (a navigation enhancement terminal and a channel simulator) respectively need different carrier tracks, the invention utilizes one navigation signal simulator to send GNSS signals simulating low-orbit satellite tracks to the satellite-borne navigation monitoring receiver and send GNSS signals simulating ground user tracks to the navigation enhancement terminal and the channel simulator, thereby not only meeting the simulation conditions of the equipment, but also ensuring the time synchronization of the system;
a fixed scene can be simulated before the test, the simulation starting time, the ephemeris, the satellite trajectory and the ground station position are all fixed, the test has repeatability, and before each test, the time of the navigation signal simulator only needs to be adjusted to a certain time earlier than the simulation starting time.
S40: and performing interface, function, performance and full-flow test on the navigation enhancement load device, the ground navigation enhancement terminal, the navigation data center, the navigation signal simulator and the channel simulator to verify the correctness of the design of the navigation enhancement system signal and information link, the signal generation and the data processing.
This stage is performed indoors, as shown in fig. 5, a system level joint debugging test is performed, test devices such as a navigation enhanced load, a ground navigation enhanced terminal, a navigation data center, a navigation signal simulator, and a channel simulator are accessed into the test system, a system interface, a device function and performance, and a system overall flow are tested, the correctness of the design of a navigation enhanced system signal and an information link is verified, the correctness of signal generation and data processing is verified, and the verification of the function and performance index of the navigation enhanced system is tested and verified.
Wherein, in an optional embodiment, the transmitting antenna of the navigation enhancement loading device and the receiving antenna of the navigation enhancement terminal are placed in a microwave dark box.
In another alternative embodiment, all equipment is tested in a microwave anechoic chamber, for example, the navigation enhancement load device, the satellite navigation monitoring receiver, the navigation signal simulator and the satellite rubidium clock are placed in a microwave anechoic chamber.
The navigation data center can adopt an upper computer simulation mode, orbit determination, clock estimation and low orbit satellite ephemeris data are simulated well in advance, synchronization with the simulation time of the navigation signal simulator is kept, the data are sent to a load according to a fixed period, the data center simulation equipment manually synchronizes with the simulator time, and the starting time is delayed within 2 s.
The GNSS navigation signal simulator adopts dual-user output, one path of signal simulates a GNSS navigation signal received by the ground terminal (and simultaneously outputs the GNSS navigation signal to the channel simulator), and the other path of signal simulates the GNSS navigation signal received by the satellite-borne navigation receiver.
The low orbit satellite navigation signal output by the load transmitter is sent to the channel simulator after passing through the attenuator, and the output end controls the signal size through the adjustable attenuator.
And the load interface matching equipment is used for simulating a satellite platform, is connected with the load interface, and performs operations such as control, data transceiving and the like on the load.
In a specific embodiment, the method further comprises:
s50: and connecting the navigation enhancement load device with load interface matching equipment, and controlling and receiving data of the navigation enhancement load device.
As shown in fig. 6, the satellite only participates in the navigation enhancement load during the joint test of the navigation enhancement system, and the navigation enhancement load interface matching device, the power supply system and necessary tools thereof need to be developed to simulate the satellite platform and the navigation enhancement load interface, so that the navigation enhancement load can be ensured to work safely and normally during the joint debugging of the system.
The testing method provided by the implementation can be verified in a low-earth-orbit satellite enhanced GNSS mode, a low-earth-orbit satellite standby navigation positioning mode and a low-earth-orbit satellite ephemeris mode which is autonomously generated by a satellite-borne receiver, the first type is the low-earth-orbit satellite enhanced GNSS service mode shown in figure 7, the satellite-borne navigation monitoring receiver downloads GNSS observation data to a ground gateway station through a satellite communication link, a navigation data center combines data of the ground monitoring station to process data such as precise orbits, clock errors, pseudo ranges and carrier corrections, the data are injected to a low-earth-orbit satellite navigation enhanced load through the gateway station to generate a navigation enhanced signal to be broadcasted to the ground, the navigation enhanced terminal carries out high-precision single-point positioning after receiving the GNSS signal and the low-earth-orbit satellite navigation signal, and meanwhile, the ground navigation monitoring receiver monitors the quality of the low-earth-orbit broadcast navigation signal.
The second type is a low orbit satellite standby navigation positioning service mode as shown in fig. 8, the low orbit satellite and the ground support system use a satellite-ground link and an inter-satellite link to realize time synchronization, the low orbit satellite uses an inter-satellite link to realize orbit determination, the ground support system collects low orbit satellite navigation signal data through a ground monitoring station to generate navigation information such as low orbit satellite prediction ephemeris and time deviation, the navigation information is injected into the low orbit satellite in an uplink mode, the satellite generates and broadcasts navigation signals, and a user receiver receives the low orbit satellite navigation signals and provides PVT information for a user.
The third type is that the satellite-borne navigation monitoring receiver autonomously generates a low-orbit satellite ephemeris mode as shown in fig. 9. In the mode, the navigation enhancement data and the low-orbit ephemeris data are not generated through a ground navigation data center, but the satellite-borne navigation monitoring receiver autonomously generates the ephemeris data of the low-orbit satellite through on-satellite real-time orbit determination and orbit extrapolation.
The invention provides a test method of a navigation enhancement system, which synchronously simulates a satellite-borne track and a ground user track through a navigation signal simulator, thereby not only ensuring the consistency with an in-orbit scene of a real satellite, but also ensuring the signal and time uniformity between the satellite and the ground; through simulated ground station observation data and observation data resolved by a navigation monitoring receiver in real time, the most real system working condition of the simulated satellite in orbit can be simulated, signals transmitted to the received signals and information transmission can be processed in a closed loop in real time, and the functions and the performances of equipment in the system can be tested to the greatest extent; the system can perform closed-loop simulation test on the precision of the navigation enhancement system, generate navigation enhancement information through data processing, broadcast the navigation enhancement information through the load device, perform high-precision positioning processing after receiving the navigation enhancement information by the ground terminal, and test the service precision of the navigation enhancement system.
It should be understood that the above-mentioned embodiments of the present invention are only examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention, and it will be obvious to those skilled in the art that other variations or modifications may be made on the basis of the above description, and all embodiments may not be exhaustive, and all obvious variations or modifications may be included within the scope of the present invention.
Claims (7)
1. A test method of a navigation enhancement system is characterized by comprising the following steps:
s10: the method comprises the following steps that a navigation enhanced load device, a satellite-borne navigation monitoring receiver and a satellite-borne rubidium clock are used for carrying out interface matching test and function and performance index test;
s20: testing the navigation enhancement terminal;
s30: the time of the navigation enhancement load device, the satellite-borne navigation monitoring receiver, the navigation enhancement terminal, the channel simulator and the navigation data center is synchronized;
s40: and performing interface, function, performance and full-flow test on the navigation enhancement load device, the ground navigation enhancement terminal, the navigation data center, the navigation signal simulator and the channel simulator to verify the correctness of the design of the navigation enhancement system signal and information link, the signal generation and the data processing.
2. The method according to claim 1, wherein the S10 includes:
said satellite-borne rubidium clock providing a reference frequency signal for said navigation enhancing load device and said navigation monitoring receiver,
the navigation monitoring receiver receives the navigation signal simulator signal for positioning and time service,
and the navigation enhanced load device carries out time synchronization with the time information through the 1PPS output by the satellite-borne navigation monitoring receiver.
3. The method according to claim 1, wherein the S20 includes:
the navigation data center generates low-orbit satellite simulation ephemeris,
the navigation signal simulator generates low orbit satellite simulation signals according to the ephemeris data and sends the signals to the navigation enhancement terminal,
and testing the function and performance indexes of the navigation enhancement terminal according to the low-orbit satellite simulation signal.
4. The method as claimed in claim 1, wherein in performing S30, the navigation signal simulator sends GNSS signals simulating low earth orbit satellite trajectories to the on-board monitoring receiver, and sends GNSS signals simulating terrestrial user trajectories to a navigation enhancement terminal and a channel simulator.
5. The method of claim 1, further comprising:
s50: and connecting the navigation enhancement load device with load interface matching equipment, and controlling and receiving data of the navigation enhancement load device.
6. The method of claim 1, wherein the transmitting antenna of the navigation enhancement payload device and the receiving antenna of the navigation enhancement terminal are placed within a microwave anechoic chamber.
7. The method of claim 1, wherein said navigation enhancement load device, satellite borne navigation monitoring receiver, navigation signal simulator, and satellite borne rubidium clock are disposed within a microwave anechoic box.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115144876A (en) * | 2022-09-05 | 2022-10-04 | 湖南矩阵电子科技有限公司 | Low-earth-orbit satellite navigation enhancement terminal test evaluation method and system |
| CN115575982A (en) * | 2022-11-24 | 2023-01-06 | 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 |
| CN115657089A (en) * | 2022-11-15 | 2023-01-31 | 湖南矩阵电子科技有限公司 | Low-earth-orbit satellite navigation enhancement load calibration method and system |
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- 2022-02-17 CN CN202210145507.0A patent/CN114660632A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115144876A (en) * | 2022-09-05 | 2022-10-04 | 湖南矩阵电子科技有限公司 | Low-earth-orbit satellite navigation enhancement terminal test evaluation method and system |
| CN115657089A (en) * | 2022-11-15 | 2023-01-31 | 湖南矩阵电子科技有限公司 | Low-earth-orbit satellite navigation enhancement load calibration method and system |
| CN115575982A (en) * | 2022-11-24 | 2023-01-06 | 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 |
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