CN106842244B - Testing system based on space application type satellite navigation receiver - Google Patents
Testing system based on space application type satellite navigation receiver Download PDFInfo
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- CN106842244B CN106842244B CN201611241215.8A CN201611241215A CN106842244B CN 106842244 B CN106842244 B CN 106842244B CN 201611241215 A CN201611241215 A CN 201611241215A CN 106842244 B CN106842244 B CN 106842244B
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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
Abstract
The invention discloses a test system based on a space application type satellite navigation receiver, which comprises the following components: the system comprises a test PC, an automatic hardware test platform, a satellite navigation receiver to be tested and a signal generating device; the test PC is connected with the automatic hardware test platform through a communication cable; the satellite navigation receiver to be tested is arranged on an automatic hardware test platform; the automatic hardware test platform is connected with the satellite navigation receiver to be tested through a test cable; the satellite navigation receiver to be tested is connected with the signal generating device through a radio frequency cable; and the automatic hardware test platform is used for testing the satellite navigation receiver to be tested according to the test items determined by the test PC to obtain a test result and outputting the test result. The invention solves the defect that the universal receiver test system can not test the performance indexes such as telemetering data, remote control instructions, long-term stability of the system and the like.
Description
Technical Field
The invention belongs to the technical field of satellite navigation receiver testing, and particularly relates to a testing system based on a space application type satellite navigation receiver.
Background
A satellite navigation system is a navigation system that performs positioning based on radio navigation signals broadcast by navigation satellites. The current Global satellite navigation System includes a Global Positioning System (GPS) in the united states, a beidou navigation System in China, a guroney satellite navigation System in Russia, and a galileo satellite navigation System developed by Europe. With the continuous development and improvement of the Beidou navigation system in China, the dual-system satellite navigation receiver based on the GPS and the Beidou navigation system is developed rapidly. At present, the application field of the dual-system satellite navigation receiver is expanded from the traditional ground application to the space application field. The carrier positioning navigation is realized by adopting a dual-system satellite navigation receiver in intelligent cannonballs, various aircrafts and pico-nano satellites, and the receiver is generally called as a satellite navigation receiver for space application.
Compared with a common application type receiver, the space application type receiver is in a worse environment, so that the requirement on the stability of the receiver is higher. The control of the space type satellite navigation receiver is generally completed by remote control commands, and the navigation information output by the space type satellite navigation receiver and the state information of the receiver are in the form of telemetering data instead of a conventional navigation protocol. General receiver test systems generally have low automation degree, cannot complete long-term stability tests, and cannot complete the tests on telemetering data and remote control instructions. Therefore, the general navigation receiver testing method is not suitable for the space application type satellite navigation receiver. The testing work of the receiver has important significance for the research and development and production of the receiver, the test in the research and development stage can search for bugs in software and hardware design, and the testing work before delivery can confirm the working state of the receiver.
Disclosure of Invention
The technical problem of the invention is solved: the testing system based on the space application type satellite navigation receiver overcomes the defects of the prior art, and solves the problem that a general receiver testing system cannot test performance indexes such as telemetering data, remote control instructions and long-term stability of the system.
In order to solve the technical problem, the invention discloses a test system based on a space application type satellite navigation receiver, which comprises: the system comprises a test PC, an automatic hardware test platform, a satellite navigation receiver to be tested and a signal generating device;
the test PC is connected with the automatic hardware test platform through a communication cable; the satellite navigation receiver to be tested is arranged on an automatic hardware test platform; the automatic hardware test platform is connected with the satellite navigation receiver to be tested through a test cable; the satellite navigation receiver to be tested is connected with the signal generating device through a radio frequency cable;
and the automatic hardware test platform is used for testing the satellite navigation receiver to be tested according to the test items determined by the test PC to obtain a test result and outputting the test result.
In the above test system based on the satellite navigation receiver for space application, the test item includes at least one of the following test indexes: the method comprises the following steps of testing indexes of power supply voltage, working temperature, carrier-to-noise ratio, time precision, positioning precision, track parameter precision, original observed quantity precision, long-term stability and real-time working state.
In the above test system based on a satellite navigation receiver with space application, the automated hardware test platform includes: the device comprises a power interface, a communication interface and a signal interface;
the power interface is connected with the satellite navigation receiver to be tested through a power interface circuit;
the communication interface is connected with the satellite navigation receiver to be tested through a communication interface circuit;
the signal interface is connected with the satellite navigation receiver to be tested through a signal interface circuit.
In the test system based on the space application type satellite navigation receiver, the power interface circuit is used for supplying power to the satellite navigation receiver to be tested and peripheral circuits of the automatic hardware test platform; wherein the power interface circuit comprises: the device comprises a power input connector, a current limiting circuit, a voltage conversion circuit and a voltage and current monitoring circuit.
In the test system based on the space application type satellite navigation receiver, the communication interface circuit is used for establishing communication between an automatic hardware test platform and the satellite navigation receiver to be tested and between the automatic hardware test platform and a test PC; the automatic hardware test platform is communicated with the satellite navigation receiver to be tested through an RS-422 interface, and the automatic hardware test platform is communicated with the test PC through an RS-232 interface.
In the test system based on the space application type satellite navigation receiver, the signal interface circuit is used for controlling an input/output channel of radio frequency signals, establishing communication between the satellite navigation receiver to be tested and the radio frequency navigation signals, and converting different radio frequency interfaces.
In the test system based on the space application type satellite navigation receiver, the test PC is used for generating a test program according to the test items of the satellite navigation receiver to be tested;
the automatic hardware test platform is used for testing the remote control instructions one by one according to a test program and an instruction test sequence specified by a standard test specification; after all the remote control instruction tests are completed, the satellite navigation receiver to be tested is configured to be in a conventional mode, the telemetering data is tested according to a data test sequence specified by a standard test specification, and a test result is obtained and output.
In the above test system based on a satellite navigation receiver for space application, the signal generating device includes: an antenna or a satellite navigation signal simulation signal source.
The invention has the following advantages:
the test system based on the space application type satellite navigation receiver can complete the test of performance indexes such as telemetering data, remote control instructions, positioning precision, receiver working state, receiver stability and the like, and solves the defect that a universal receiver test system cannot test the performance indexes such as telemetering data, remote control instructions, system long-term stability and the like.
Furthermore, the invention also solves the problems of complex construction of the test system, complex test steps, poor visibility of test results, lag generation of test conclusions and the like, improves the automation degree of the test system and improves the test coverage.
Drawings
FIG. 1 is a schematic structural diagram of a test system for a satellite navigation receiver based on space application in an embodiment of the present invention;
fig. 2 is a schematic diagram of a connection structure between an automated hardware testing platform and a satellite navigation receiver under test according to an embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, common embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.
The test system based on the space application type satellite navigation receiver can be used for performance test, system stability test and pre-delivery performance confirmation in the research and development process of the satellite navigation receiver.
Referring to fig. 1, a schematic structural diagram of a test system based on a satellite navigation receiver for space application in an embodiment of the present invention is shown. In this embodiment, the test system for a satellite navigation receiver based on a space application type includes: a test PC 100(Personal Computer), an automated hardware test platform 200, a satellite navigation receiver 300 to be tested, and a signal generating device 400. The to-be-tested satellite navigation receiver 300 is mainly a satellite navigation receiver based on space application, and the signal generating device 400 may be an antenna or a satellite navigation signal simulation signal source.
As shown in fig. 1, the test PC 100 is connected to the automated hardware test platform 200 via a communication cable; the satellite navigation receiver 300 to be tested is arranged on the automatic hardware test platform 200; the automated hardware test platform 200 is connected with the satellite navigation receiver 300 to be tested through a test cable; the satellite navigation receiver 300 to be tested is connected with the signal generating device 400 through a radio frequency cable.
In this embodiment, the automated hardware testing platform 200 is configured to test the satellite navigation receiver 300 to be tested according to the test items determined by the testing PC 100, obtain a test result, and output the test result.
In a preferred embodiment of the present invention, referring to fig. 2, a schematic diagram of a connection structure between an automated hardware testing platform and a satellite navigation receiver under test in an embodiment of the present invention is shown. In this embodiment, the specific circuit structure of the automated hardware testing platform 200 may be determined according to the test items to be tested, the specification of the standard test specification, and the hardware interface of the satellite navigation receiver 300 to be tested. As shown in fig. 2, the automated hardware testing platform 200 mainly includes: power source interface, communication interface and signal interface.
Wherein, the power interface is connected with the satellite navigation receiver 300 to be tested through a power interface circuit; the communication interface is connected with the satellite navigation receiver 300 to be tested through a communication interface circuit; the signal interface is connected with the satellite navigation receiver 300 to be tested through a signal interface circuit.
Preferably, the power interface circuit is used for supplying power to the satellite navigation receiver 300 to be tested and peripheral circuits of the automated hardware testing platform 200. Wherein the power interface circuit comprises: the device comprises a power input connector, a current limiting circuit, a voltage conversion circuit and a voltage and current monitoring circuit. Preferably, in practical applications, the power interface circuit may be designed according to the input voltage requirement of the automated hardware testing platform 200, the power supply voltage requirement of the satellite navigation receiver 300 to be tested, and the quality requirement of the power supply of the satellite navigation receiver 300 to be tested, which is not limited in this embodiment.
And the communication interface circuit is used for establishing communication between the automatic hardware test platform 200 and the satellite navigation receiver 300 to be tested and communication between the automatic hardware test platform 300 and the test PC 100. The automated hardware test platform 200 and the satellite navigation receiver 300 to be tested generally adopt an RS-422 interface for communication, and the automated hardware test platform 200 and the test PC 100 generally adopt an RS-232 interface for communication. In this embodiment, the automated hardware testing platform 200 is to implement a conversion function between different communication interfaces.
The signal interface circuit is used for controlling an input/output path of the radio frequency signal, establishing communication between the satellite navigation receiver 300 to be tested and the radio frequency navigation signal, and converting different radio frequency interfaces. The radio frequency signal mainly refers to a radio frequency signal generated by a signal generating device. In this embodiment, the signal generator 400 generally uses an N-type or ultra-small a-type (SMA) interface to input the RF signal to the automated hardware testing platform 200, and the types of the RF input interfaces of the satellite navigation receiver 300 to be tested are many, and the selectable interfaces include a Screw Connector (TNC), a Bayonet Connector (Bayonet Connector, BNC), an ultra-small a-type (SMA), a Micro RF Coaxial Connector (MCX), a Micro RF Coaxial Connector (MMCX), and the like, so the signal interface circuit is to complete the conversion function between different RF interfaces.
In a preferred embodiment of the present invention, the test PC 100 can be specifically configured to generate a test program according to a test item of the satellite navigation receiver 100 to be tested. The automatic hardware testing platform 200 is used for testing the remote control instructions one by one according to a testing program and an instruction testing sequence specified by a standard testing specification; after all the remote control instruction tests are completed, the satellite navigation receiver 300 to be tested is configured to be in a conventional mode, the telemetry data is tested according to the data test sequence specified by the standard test specification, and a test result is obtained and output. The test system according to the embodiment of the invention can test at least one of the following test indexes of the satellite navigation receiver 300 to be tested: the method comprises the following steps of testing indexes of power supply voltage, working temperature, carrier-to-noise ratio, time precision, positioning precision, track parameter precision, original observed quantity precision, long-term stability and real-time working state.
Preferably, after receiving the test result, the test PC 100 may analyze the test result and display the analysis result in an interface format in real time.
Based on the above embodiments, the present embodiment describes the test system based on the space application type satellite navigation receiver in detail through a specific test procedure.
This embodiment takes a dual-mode four-frequency point satellite navigation receiver of a pico-nano satellite platform as an example, that is, the dual-mode four-frequency point satellite navigation receiver of the pico-nano satellite platform is taken as a satellite navigation receiver to be measured, and the method includes: the system comprises a GPS navigation module, a Beidou navigation module and a backup navigation module. By the test system based on the space application type satellite navigation receiver, the performance of the receiver under various working modes of all navigation modules can be tested.
In this embodiment, the satellite navigation receiver to be tested may be mounted on an automated hardware testing platform, and the testing PC, the automated hardware testing platform, the satellite navigation receiver to be tested, and the signal generating device may be connected by a cable.
In this embodiment, the automated hardware testing platform may be composed of a 1-way RS422 to RS232 interface, a 2-way TTL (Transistor Logic, TLL) to RS232 interface, a 2-way 5V power output, a 1-way 3.3V power output, and a 1-way rf signal input/output interface. According to the test specification, the automatic hardware test platform works at the temperature of minus 40 ℃ to plus 85 ℃. DC stabilized power supply for providing 5V @2A power supply for automatic test hardware platform
In this embodiment, the automated test program may be run on a test PC, send remote control instructions, receive telemetry data via a communication cable, and analyze the received test results. The satellite navigation receiver to be tested receives the remote control command sent by the test PC and the automatic hardware test platform, switches the working state and returns the telemetering data to the test PC. And the test PC analyzes the telemetering data returned by the satellite navigation receiver to be tested in real time through an automatic test program and displays the telemetering data in a test interface of the test PC, and records all sent and received data.
The power interface circuit adopts a single path of 5V input, 2 paths of 5V output and 1 path of 3.3V output. The current limiting threshold of the current limiting circuit is 2.0A. The communication interface circuit comprises an RS422/RS232 data conversion circuit and a TLL/RS232 data conversion circuit. The signal interface circuit realizes the conversion function from the radio frequency input SMA interface to the output MMCX interface.
In this embodiment, the test system completes the remote control instruction test and the telemetry data test of the GPS navigation module in sequence; and after the whole test of the GPS navigation module is completed, the Beidou navigation module and the backup navigation module are sequentially tested.
Specifically, the method comprises the following steps:
the method comprises the following steps that a satellite navigation receiver to be tested is installed on an automatic hardware testing platform and is connected with a testing cable between the satellite navigation receiver and the testing hardware platform;
connecting a radio frequency cable between the satellite navigation receiver to be tested and an antenna or a satellite navigation signal simulation signal source;
running an automatic test program on a test PC and powering up an automatic test hardware platform;
selecting a communication serial port connected with a communication cable on a lateral PC, and filling information such as a tester, a test satellite navigation receiver number, a test record storage path, a file name and the like;
selecting a 'GPS navigation module starting instruction', starting to test a remote control instruction of the GPS navigation module, wherein the remote control instruction comprises 'allowing to send GPS positioning telemetering', 'forbidding to send GPS positioning telemetering', 'allowing to send GPS original measuring data', 'forbidding to send GPS original measuring data', 'GPS navigation module processing software injection permission', 'GPS navigation module processing software injection end' and 'starting GPS navigation module processing software injection program', and the like. The test system simulates the housekeeping host and sequentially sends the commands to complete the test of the remote control command. In the remote control instruction testing process, the instruction execution condition can be output in real time through the test display interface, for example, if the instruction test passes, "Command xx is OK" is output; otherwise, the "Command xx is failed" is output.
After all the instructions are tested, the test system outputs 'GPS command test is ok'. And then, carrying out telemetry data test, and setting a telemetry data frame to be tested, a telemetry polling period and test time. In the test process, the test system simulates the satellite host to start data polling according to the set requirements, and displays the analyzed telemetering result in real time. After the test is finished, the test system can analyze the telemetering data according to the user request, and a test report is generated and displayed.
And selecting a command of closing the GPS navigation module and a command of opening the Beidou navigation module, closing the GPS navigation module and opening the Beidou navigation module, referring to the test flow of the GPS navigation module, and testing the Beidou navigation module until the test of the backup navigation module is completed.
In summary, the test system based on the space application type satellite navigation receiver of the present invention can complete the test of the performance indexes such as the telemetry data, the remote control command, the positioning accuracy, the receiver operating state, the receiver stability, etc., and solves the disadvantage that the general receiver test system cannot test the performance indexes such as the telemetry data, the remote control command, the system long-term stability, etc.
Furthermore, the invention also solves the problems of complex construction of the test system, complex test steps, poor visibility of test results, lag generation of test conclusions and the like, improves the automation degree of the test system and improves the test coverage.
The test system based on the space application type satellite navigation receiver is applied to the research, development, delivery and test process of a pico-nano satellite-borne satellite navigation receiver, hundreds of tests are carried out by using the test system at present, and the system runs stably and normally. The test period of the satellite-borne satellite navigation receiver is shortened from the original 48 hours to the current 8 hours, so that the test efficiency is greatly improved, the test complexity is reduced, and a good effect is achieved.
The above description is only for the best mode of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention.
Those skilled in the art will appreciate that the invention may be practiced without these specific details.
Claims (6)
1. A test system for a satellite navigation receiver based on space application, comprising: the system comprises a test PC, an automatic hardware test platform, a satellite navigation receiver to be tested and a signal generating device; wherein, the satellite navigation receiver that awaits measuring includes: the system comprises a GPS navigation module, a Beidou navigation module and a backup navigation module;
the test PC is connected with the automatic hardware test platform through a communication cable; the satellite navigation receiver to be tested is arranged on an automatic hardware test platform; the automatic hardware test platform is connected with the satellite navigation receiver to be tested through a test cable; the satellite navigation receiver to be tested is connected with the signal generating device through a radio frequency cable;
the test PC is used for generating a test program according to the test items of the satellite navigation receiver to be tested; wherein the test item comprises at least one of the following test indexes: the method comprises the following steps of testing indexes of power supply voltage, working temperature, carrier-to-noise ratio, time precision, positioning precision, track parameter precision, original observed quantity precision, long-term stability and real-time working state;
an automated hardware testing platform to:
and (3) testing the remote control commands one by one according to a test program and a command test sequence specified by a standard test specification: selecting an instruction for starting the GPS navigation module, and starting to test the remote control instruction of the GPS navigation module; selecting a command of turning off the GPS navigation module and a command of turning on the Beidou navigation module, and starting to test the remote control command of the Beidou navigation module; the remote control instruction comprises a plurality of remote control instructions, wherein the remote control instructions comprise a plurality of remote control instructions, namely 'permission to send GPS positioning telemetering', 'prohibition to send GPS positioning telemetering', 'permission to send GPS raw measurement data', 'prohibition to send GPS raw measurement data', 'GPS navigation module processing software injection permission', 'GPS navigation module processing software injection end' and 'start GPS navigation module processing software injection program', and 'permission to send Beidou navigation positioning telemetering', 'prohibition to send Beidou navigation positioning telemetering', 'permission to send Beidou raw measurement data', 'prohibition to send Beidou navigation raw measurement data', 'Beidou navigation module processing software injection permission', 'Beidou navigation module processing software injection end' and 'start Beidou navigation module processing software injection program';
after all the remote control instruction tests are completed, the satellite navigation receiver to be tested is configured to be in a conventional mode, a telemetry data frame to be tested, a telemetry polling period and test time are set, telemetry data are tested according to a data test sequence specified by a standard test specification, a test result is obtained, and the test result is output.
2. The test system of claim 1, wherein the automated hardware test platform comprises: the device comprises a power interface, a communication interface and a signal interface;
the power interface is connected with the satellite navigation receiver to be tested through a power interface circuit;
the communication interface is connected with the satellite navigation receiver to be tested through a communication interface circuit;
the signal interface is connected with the satellite navigation receiver to be tested through a signal interface circuit.
3. The test system of claim 2,
the power interface circuit is used for supplying power to the satellite navigation receiver to be tested and a peripheral circuit of the automatic hardware test platform; wherein the power interface circuit comprises: the device comprises a power input connector, a current limiting circuit, a voltage conversion circuit and a voltage and current monitoring circuit.
4. The test system of claim 2,
the communication interface circuit is used for establishing communication between the automatic hardware test platform and the satellite navigation receiver to be tested and between the automatic hardware test platform and the test PC; the automatic hardware test platform is communicated with the satellite navigation receiver to be tested through an RS-422 interface, and the automatic hardware test platform is communicated with the test PC through an RS-232 interface.
5. The test system of claim 2,
and the signal interface circuit is used for controlling an input/output channel of the radio frequency signal, establishing communication between the satellite navigation receiver to be tested and the radio frequency navigation signal, and converting different radio frequency interfaces.
6. The test system of claim 1, wherein the signal generating device comprises: the antenna or satellite navigation signal simulates a signal source.
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| CN107167822B (en) * | 2017-07-13 | 2019-12-10 | 北京理工大学 | method for simulating satellite navigation positioning of four-axis aircraft |
| CN109143277A (en) * | 2017-11-02 | 2019-01-04 | 上海华测导航技术股份有限公司 | A kind of GNSS receiver automatic software test method |
| CN108761499A (en) * | 2017-12-27 | 2018-11-06 | 北京时代民芯科技有限公司 | A kind of test system and method for the spaceborne GNSS receiver operation on orbit of simulation |
| CN111880201B (en) * | 2020-09-28 | 2021-01-22 | 蘑菇车联信息科技有限公司 | Beidou terminal testing system, testing method and testing device |
| CN115248052B (en) * | 2022-09-22 | 2022-11-25 | 中国民航大学 | Self-checking system of automatic testing device of airborne VHF navigation system receiver |
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