CN104655149A - Test system of inertial navigation system - Google Patents
Test system of inertial navigation system Download PDFInfo
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- CN104655149A CN104655149A CN201310582516.7A CN201310582516A CN104655149A CN 104655149 A CN104655149 A CN 104655149A CN 201310582516 A CN201310582516 A CN 201310582516A CN 104655149 A CN104655149 A CN 104655149A
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- inertial navigation
- navigation system
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- computer
- usb
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C25/00—Manufacturing, calibrating, cleaning, or repairing instruments or devices referred to in the other groups of this subclass
Abstract
A test system of an inertial navigation system comprises an upper computer (1), a USB/RS422 convertor (2), a to-be-test inertial navigation system (3) and a standard inertial navigation system (4). Both the to-be-test inertial navigation system and the standard inertial navigation system are arranged on a rotary bench. In the test system, with a computer as a core, all the external devices are connected to computer ports and the computer sends control signals through the computer ports to achieve measurement of the inertial navigation system through command specified in an agreement. The test system is composed of the upper computer (1), a USB/RS422 convertor (2), a to-be-test inertial navigation system (3) and a standard inertial navigation system (4). The computer is a control center of the test system and achieve control of the whole system through the ports, thereby accomplishing acquisition, communication, process, storage and the like of data and displaying a measurement result and measurement information on a display screen. The to-be-test inertial navigation system and the standard inertial navigation system are mainly used for data acquisition, wherein the data is converted through the USB/RS422 convertor and then is sent to the computer, so that detection of the to-be-test inertial navigation system is achieved through data processing.
Description
Technical field
What the present invention relates to is a kind of software systems, particularly be a kind of inertial navigation system test macro.
Background technology
Inertial navigation system is as a kind of modernization navigator, and for the attitude measurement of movable body and location provide reliable guarantee, at aviation, land, oceanic navigational, tracing control, the aspects such as platform stable are widely used.Its principle of work is from known starting point, by follow the tracks of and calculate oneself displacement each time thus when by determining oneself position when the not exhibition and clue in other any outsides.In the past due to the restriction of technology, by measuring oneself displacement thus accurate Calculation navigation is very difficult.And after having had inertial navigation system, utilizing inertial navigation system, various platform can calculate oneself displacement by real―time precision measurment, realizes navigating accurately.
Inertial navigation system before being taken into use, needs to test its performance, and this is a requisite link.By the test to inertial navigation system performance, verify that can tested inertial navigation system satisfy the demands.Therefore, soon a set of and inertial navigation test macro accurately must be needed.
Along with inertial navigation technique constantly develops, function is constantly perfect, going deep into of test, has occurred a lot of new performance requirement.And at inertial navigation system before being taken into use, the performance new to these is needed to test, continuous electrical testing as inertial navigation system requires it is that requirement system can image data incessantly for a long time, the power-off test request of inertial navigation system is that requirement system can auto-breaking and can automatic recovery of power supply under certain condition, the calibration factor test request of inertial navigation system is the rotation that requirement system can control turntable, and strictly can control frequency and the amplitude of turntable rotation, the temperature property test of inertial navigation system requires it is the heating work that requirement system can control incubator, and control the heating rate etc. of incubator.Along with the appearance of new performance requirement, testing apparatus originally, testing software have been difficult to satisfied new performance test requirement, thus need to explore to develop new inertial navigation system test macro, can meet new performance test requirement.And by new test macro, the performance test efficiency of inertial navigation system should be able to be improved, the performance parameter of inertial navigation system can be demarcated exactly by various performance test and estimate their precision, thus judge whether inertial navigation system meets designing requirement.
Summary of the invention
The object of this invention is to provide the high precision measurement equipment of a set of inertial navigation system parameter acquisition and test.
A kind of inertial navigation system test macro, its composition comprises: host computer 1, USB/RS422 converter 2, tested inertial navigation system 3 and benchmark inertial navigation system 4 form, and it is characterized in that in hardware system, tested inertial navigation system 3 and benchmark inertial navigation system) be all connected on turntable.
Described a kind of inertial navigation system test macro, it is characterized in that described external unit all hangs on computer port, computing machine sends various control signal by port, realizes the measurement to inertial navigation system with the order specified in agreement.
The object of the present invention is achieved like this:
Inertial navigation test macro can be divided into hardware system and software systems two parts.In hardware system, tested inertial navigation system and benchmark inertial navigation system are all placed on turntable, inertial navigation test macro take computing machine as core, all external units all hang on computer port, computing machine sends various control signal by port, realizes the measurement to inertial navigation system with the order specified in agreement.Testing apparatus is made up of computing machine, USB/RS422 converter, tested inertial navigation system and benchmark inertial navigation system.Computing machine is the control center of test platform, and he realizes control to whole system by port, thus completes the function such as collection, communication, process, storage of data, by test result and information displaying on a display screen.What produce due to tested inertial navigation system and benchmark inertial navigation system is all RS422 signal, what computing machine received and sent is usb signal, therefore, need to adopt USB/RS422 converter to realize the mutual conversion of usb signal and RS422 signal, thus realize the information communication between computing machine and tested inertial navigation system and benchmark inertial navigation system.The Main Function of tested inertial navigation system and benchmark inertial navigation system is image data, and data by sending to computing machine after the conversion of RS422/USB converter, realize detection to tested inertial navigation system by data processing.
The workflow of system software is after program starts, and serial ports carried out initialization before this, after completing, judges whether to send setting instruction to inertial navigation.Determine to send setting instruction to inertial navigation, then inertial navigation sends data, and computer receiving data, processes and show; Otherwise computing machine directly receives data.Data processing also, after display, judges whether data preserve, if preserve, then preserves data and then judges whether to receive, receive rear closedown serial ports, quit a program, if do not receive, then return and continue to receive, until receive, close serial ports, quit a program.
Accompanying drawing explanation
Fig. 1 is inertial navigation system test structure figure;
In figure: 1, host computer, 2, USB/RS422 converter, 3, tested inertial navigation system, 4, benchmark inertial navigation system.
Embodiment
Below in conjunction with accompanying drawing citing, the present invention is described in more detail:
Composition graphs 1, Fig. 1 is inertial navigation system test structure figure.In hardware system, tested inertial navigation system and benchmark inertial navigation system are all placed on turntable, inertial navigation test macro take computing machine as core, all external units all hang on computer port, computing machine sends various control signal by port, realizes the measurement to inertial navigation system with the order specified in agreement.As shown in Figure 1, testing apparatus is made up of computing machine, USB/RS422 converter, tested inertial navigation system and benchmark inertial navigation system system hardware pie graph.Computing machine is the control center of test platform, and he realizes control to whole system by port, thus completes the function such as collection, communication, process, storage of data, by test result and information displaying on a display screen.What produce due to tested inertial navigation system and benchmark inertial navigation system is all RS422 signal, what computing machine received and sent is usb signal, therefore, need to adopt USB/RS422 converter to realize the mutual conversion of usb signal and RS422 signal, thus realize the information communication between computing machine and tested inertial navigation system and benchmark inertial navigation system.The Main Function of tested inertial navigation system and benchmark inertial navigation system is image data, and data by sending to computing machine after the conversion of RS422/USB converter, realize detection to tested inertial navigation system by data processing.In inertial navigation system testing software signal wiring figure, USB/RS422 converter is the bridge connecting inertial navigation system and computing machine.Due to the continual development of electronic equipment, USB interface is replacing various interface, but in some current industrial environments, much important equipment still makes
Be RS422 interface, therefore in order to realize the data communication between computer and RS422 equipment, just need to use USB/RS422 converter.In the equipment connection of this inertial navigation system testing software design, the RS422 signal that inertial navigation system sends, converts usb signal to by USB/RS422 converter, sends computing machine to; The usb signal that computing machine produces, converts RS422 signal to by USB/RS422 converter, inertial navigation system can be received.
After program starts, serial ports carried out initialization before this, after completing, judged whether to send setting instruction to inertial navigation.Determine to send setting instruction to inertial navigation, then inertial navigation sends data, and computer receiving data, processes and show; Otherwise computing machine directly receives data.Data processing also, after display, judges whether data preserve, if preserve, then preserves data and then judges whether to receive, receive rear closedown serial ports, quit a program, if do not receive, then return and continue to receive, until receive, close serial ports, quit a program.
Claims (2)
1. an inertial navigation system test macro, its composition comprises: host computer (1), USB/RS422 converter (2), tested inertial navigation system (3) and benchmark inertial navigation system (4) form, it is characterized in that in hardware system, tested inertial navigation system (3) and benchmark inertial navigation system (4) are all connected on turntable.
2. a kind of inertial navigation system test macro according to claim 1, it is characterized in that described external unit all hangs on computer port, computing machine sends various control signal by port, realizes the measurement to inertial navigation system with the order specified in agreement.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310582516.7A CN104655149A (en) | 2013-11-19 | 2013-11-19 | Test system of inertial navigation system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310582516.7A CN104655149A (en) | 2013-11-19 | 2013-11-19 | Test system of inertial navigation system |
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| CN104655149A true CN104655149A (en) | 2015-05-27 |
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| CN201310582516.7A Pending CN104655149A (en) | 2013-11-19 | 2013-11-19 | Test system of inertial navigation system |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105115520A (en) * | 2015-08-25 | 2015-12-02 | 北京航天时代光电科技有限公司 | Fiber-optic gyroscope and inertial measurement unit automated multi-channel test system |
| CN110411442A (en) * | 2018-04-27 | 2019-11-05 | 致伸科技股份有限公司 | Sensor test macro and the method being applied thereon |
| CN110514223A (en) * | 2019-08-22 | 2019-11-29 | 中国航空工业集团公司西安飞行自动控制研究所 | A kind of vehicle-mounted inertial guidance data acquisition system |
| CN113411410A (en) * | 2021-08-19 | 2021-09-17 | 北京中天星控科技开发有限公司 | Inertial navigation equipment testing method, communication server, communication device and storage medium |
-
2013
- 2013-11-19 CN CN201310582516.7A patent/CN104655149A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105115520A (en) * | 2015-08-25 | 2015-12-02 | 北京航天时代光电科技有限公司 | Fiber-optic gyroscope and inertial measurement unit automated multi-channel test system |
| CN105115520B (en) * | 2015-08-25 | 2018-02-09 | 北京航天时代光电科技有限公司 | A kind of optical fibre gyro and used group automation multiple channel test system |
| CN110411442A (en) * | 2018-04-27 | 2019-11-05 | 致伸科技股份有限公司 | Sensor test macro and the method being applied thereon |
| CN110514223A (en) * | 2019-08-22 | 2019-11-29 | 中国航空工业集团公司西安飞行自动控制研究所 | A kind of vehicle-mounted inertial guidance data acquisition system |
| CN113411410A (en) * | 2021-08-19 | 2021-09-17 | 北京中天星控科技开发有限公司 | Inertial navigation equipment testing method, communication server, communication device and storage medium |
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Legal Events
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| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20150527 |
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| WD01 | Invention patent application deemed withdrawn after publication |