CN104122459A - Airplane airborne radome test control system - Google Patents
Airplane airborne radome test control system Download PDFInfo
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- CN104122459A CN104122459A CN201310152935.7A CN201310152935A CN104122459A CN 104122459 A CN104122459 A CN 104122459A CN 201310152935 A CN201310152935 A CN 201310152935A CN 104122459 A CN104122459 A CN 104122459A
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Abstract
The invention belongs to the technical field of an aviation test and especially relates to an airborne radome test control system. The test control system comprises an instruction system, a GPIB communication module, a signal source and a spectrum analyzer, wherein the instruction system is connected with the communication module; and the communication module is connected with the signal source and the spectrum analyzer through a control bus. The system helps to meet the electric performance test requirements of multiple frequency points, wide broadband and multiple azimuths of an airplane airborne radome.
Description
Technical field
The invention belongs to aeronautic measurement technical field, particularly relate to a kind of Airborne Radome test control system.
Background technology
Along with the frequency bandwidth of aircraft airborne radar increases, frequency increases, sweep limit increases, the electric performance test of radome is had higher requirement.Traditional manual detection, the guarantee requirement that maintenance service cannot meet radome of fighter electric performance test.Auto-Test System progressively becomes the necessary guarantee of radome of fighter electric performance test reliability service.The develop rapidly of the modern science and technology such as microelectric technique, computer technology, sensor technology and the information processing technology, become and promote the constantly very strong driving force of progress of its architecture, method of testing, measuring technology, provide very favourable condition to the exploitation of radome electrical property automatic measuring and controlling system.
At present, the domestic advanced radome test macro that we purchase, the radome electrical performance indexes that can only carry out single-frequency point, folk prescription position detects, and test period is long, easily operating personnel is caused to hazards of electromagnetic radiation.
Summary of the invention
(1) object of the present invention
For overcome in above-mentioned technology, exist problem, the invention provides a kind of can realize radome electrical performance indexes detect in the test of single-frequency point, folk prescription position, can realize again the radome test control system of multifrequency point, multi-faceted test.Can improve testing efficiency, avoid operating personnel to cause hazards of electromagnetic radiation.
(2) technical scheme
In order to solve the problems of the technologies described above, the present invention is achieved through the following technical solutions:
A kind of aircraft airborne radome test control system, this test control system comprises order set, GPIB communication module, signal source and frequency spectrograph, and wherein order set is connected with communication module, and communication module is connected with signal source and frequency spectrograph by control bus.
Described order set use control signal source and the duty of frequency spectrograph, acquisition process and the demonstration of data; Signal source sends radiofrequency signal by airborne radar emitting antenna to tested radome in the time of test; Frequency spectrograph receives the radiofrequency signal of transmission antennas transmit in the time of test by airborne radar receiving antenna.
Order set comprises display module, block of state, frequency module, signal modulation module, channel selecting module and power model.Wherein display module is for display source signal and frequency spectrograph running status, user test flow setting; Block of state is for setting and the monitoring of signal source and frequency spectrograph running status; Frequency module adopts frequency of operation and the frequency transformation mode of stepless control pattern for signalization source and frequency spectrograph; Channel selecting module is for signalization source and frequency spectrograph communication channel and address setting; Power model is for the monitoring of signalization source emissive power and emission state.
The step-lengths such as described frequency change mode is conversion and discrete frequency point transformation.
Described communication module adopts multi-channel parallel communication modes.
In native system, signal residence time Δ t when signal source transmitting
1, Δ t time delay existing when frequency spectrograph gathers
2, frequency spectrograph acquisition time t, it should meet Δ t
1=Δ t
2+ t.
Δ t time delay existing when frequency spectrograph gathers
2more than 2ms.
(3) the present invention has following beneficial effect compared with prior art:
Native system has met aircraft airborne radome multifrequency point, large bandwidth, multi-faceted electric performance test requirement.Native system principle design and parameter are selected with strong points, and from cost, cheap, performance is better than domestic similar test macro.Native system meets man-machine work efficiency principle, simple to operate, easy to maintenance, has greatly improved in actual use work efficiency, has saved the working time.Native system selection suitable apparatus control bus and the bus interface card that price quality ratio is high, compatibility is good.Native system is realized the Long-distance Control to signal source and frequency spectrograph, avoids operating personnel's radiation area work.Native system measuring accuracy is high, test condition high conformity, and test speed is fast.
Brief description of the drawings
Fig. 1 is a kind of block scheme of aircraft airborne radome test control system.
Embodiment
Hyperchannel, long test have proposed very high requirement to system, require to ensure real-time, authenticity, the continuity of data, in the hope of reflecting really the real-time status of test process.Native system has adopted stepless control pattern (continuous mode), and each passage moves by data block (block) instruction, and consistent to ensure each controlled device mode of operation, test channel has enough sampling rates.Bus card transmits with local pci bus, has both ensured the high transfer rate of each channel data, has ensured again the consistance of data simultaneously.
In system, consider the extensibility of system and redevelopment property, we have adopted modularization programming.This system has comprised frequency module, power model, signal modulation module, channel selecting module and block of state.
Below in conjunction with Fig. 1, the present invention is described in further detail: based on advanced technology and the design concept of being convenient to safeguard, taking software as core, the method of testing of structuring, modularization, robotization is basis, has designed aircraft airborne radome test control system block scheme (see figure 1).Native system is selected Labview software environment, makes it better realize structuring, the modular design in system development.GPIB communication module completes physical connection, the transmission of steering order and the real-time detection of instrument state to signal source, frequency spectrograph.Order set comprises display module, block of state, frequency module, signal modulation module, channel selecting module and power model.Frequency module has realized single-point continuous wave mode, frequency sweep mode, initial/setting, sweep parameters of stopping frequency arranges function; Power model, except realizing control, the power stage of radio-frequency (RF) switch arrange, has also increased power scan function; Signal modulation module is realized the setting of signal modulation system (as AM, FM etc.) and modulation parameter; Channel selecting module and block of state are realized the selection of control channel and Instrument working state, signalling formula (cw, single etc.), these modules can better be carried out choice and operation according to testing requirement, can better remind operating personnel to avoid entering signal emitting area to the Real-Time Monitoring of Instrument working state simultaneously, reduce radiation hazard.This software testing system has used modular design simultaneously, has possessed better maintainability and extensibility.
The test request test macro of data possesses higher accuracy and readability.Native system can, according to different choice single-spot testing or the multi-point sampler of test event, can arrange continuously multiple test points in multi-point sampler.After test starts, test macro can send instruction to signal source and frequency spectrograph successively makes it carry out the test of set frequency by controlling requirement.Acquisition system gathers the data of frequency spectrograph and is imported in memory module by reading in real time.It is too high that this acquisition system has solved frequency spectrograph sampling rate, causes the inaccurate problem of image data.
Deng the test of step frequency point
In the time waiting test event of step frequency point, realize and select to arrange single-point continuous wave mode, frequency sweep mode, initial/to stop the parameter such as setting, frequency sweep step-length, signal waveform of frequency at this display module upper frequency Xiang Zhongke; In display module power entry, select definite value power mode and power scan pattern are set, control and the emission state instruction of power stage value and signal source radio-frequency (RF) switch can also be set; In display module Frequency And Amplitude Modulation options, can open and close according to demand modulation system, corresponding modulation system and parameter are set; In display module Condition Detection item, can idsplay order system whether be normally connected with controlled device, can show failure cause simultaneously, whether the timely checkout facility of alert is working properly.
The test of discrete point in frequency
In the time of the test event of discrete point in frequency such as carrying out, realize the setting of discrete point in frequency, user can arrange multiple Frequency points according to testing requirement, and test macro will carry out the test event of each frequency successively.
In the process that realizes this function, focus on the rapport of caution signal source radio-frequency transmissions time and frequency spectrograph acquisition time, because of the sampling rate of frequency spectrograph higher, in the time that signal source is carried out frequency shift, the data that frequency spectrograph gathers are instantaneous value, often there is larger error in this value, for addressing this problem, in native system, signal residence time Δ t when signal source transmitting
1, Δ t time delay existing when frequency spectrograph gathers
2, frequency spectrograph acquisition time t, it should meet Δ t
1=Δ t
2+ t.Δ t time delay existing when frequency spectrograph gathers
2more than 2ms.
Claims (5)
1. an aircraft airborne radome test control system, is characterized in that, this test control system comprises order set, GPIB communication module, signal source and frequency spectrograph, wherein order set is connected with communication module, communication module is connected with signal source and frequency spectrograph by control bus, wherein
Described order set use control signal source and the duty of frequency spectrograph, acquisition process and the demonstration of data; Signal source sends radiofrequency signal by airborne radar emitting antenna to tested radome in the time of test; Frequency spectrograph receives the radiofrequency signal of transmission antennas transmit in the time of test by airborne radar receiving antenna,
Order set comprises display module, block of state, frequency module, signal modulation module, channel selecting module and power model, and wherein display module is for display source signal and frequency spectrograph running status, user test flow setting; Block of state is for setting and the monitoring of signal source and frequency spectrograph running status; Frequency module adopts frequency of operation and the frequency transformation mode of stepless control pattern for signalization source and frequency spectrograph; Channel selecting module is for signalization source and frequency spectrograph communication channel and address setting; Power model is for the monitoring of signalization source emissive power and emission state.
2. a kind of aircraft airborne radome test control system as claimed in claim 1, is characterized in that, described frequency change mode such as is at step-length conversion and the discrete frequency point transformation.
3. a kind of aircraft airborne radome test control system as claimed in claim 1, is characterized in that, described communication module adopts multi-channel parallel communication modes.
4. a kind of aircraft airborne radome test control system as described in one of claim 1-3, is characterized in that, in native system, and signal residence time Δ t when signal source transmitting
1, Δ t time delay existing when frequency spectrograph gathers
2, frequency spectrograph acquisition time t, it should meet Δ t
1=Δ t
2+ t.
5. a kind of aircraft airborne radome test control system as claimed in claim 4, is characterized in that, frequency spectrograph gather time exist time delay Δ t2 more than 2ms.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201310152935.7A CN104122459A (en) | 2013-04-27 | 2013-04-27 | Airplane airborne radome test control system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310152935.7A CN104122459A (en) | 2013-04-27 | 2013-04-27 | Airplane airborne radome test control system |
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| CN104122459A true CN104122459A (en) | 2014-10-29 |
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| CN201310152935.7A Pending CN104122459A (en) | 2013-04-27 | 2013-04-27 | Airplane airborne radome test control system |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106254009A (en) * | 2016-07-21 | 2016-12-21 | 北京航空航天大学 | A kind of Unmanned Aerial Vehicle Data Link test electromagnetic interference signal recurrence system and reproducing method |
| CN106526551A (en) * | 2016-10-31 | 2017-03-22 | 西安坤蓝电子技术有限公司 | Radar antenna dynamic performance testing system and method |
| CN107544062A (en) * | 2016-06-23 | 2018-01-05 | 陕西飞机工业（集团）有限公司 | A kind of Airborne Radome orientation wide-angle testing auxiliary device |
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Patent Citations (4)
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| US4468669A (en) * | 1982-06-10 | 1984-08-28 | The United States Of America As Represented By The Secretary Of The Army | Self contained antenna test device |
| CN101492750A (en) * | 2008-12-30 | 2009-07-29 | 北京科技大学 | High furnace burden face measurement and control system based on industrial phased array radar |
| US8179138B2 (en) * | 2009-05-20 | 2012-05-15 | Wistron Corporation | CRT test system |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107544062A (en) * | 2016-06-23 | 2018-01-05 | 陕西飞机工业（集团）有限公司 | A kind of Airborne Radome orientation wide-angle testing auxiliary device |
| CN107544062B (en) * | 2016-06-23 | 2019-08-02 | 陕西飞机工业（集团）有限公司 | A kind of Airborne Radome orientation wide-angle testing auxiliary device |
| CN106254009A (en) * | 2016-07-21 | 2016-12-21 | 北京航空航天大学 | A kind of Unmanned Aerial Vehicle Data Link test electromagnetic interference signal recurrence system and reproducing method |
| CN106254009B (en) * | 2016-07-21 | 2018-08-03 | 北京航空航天大学 | A kind of Unmanned Aerial Vehicle Data Link test electromagnetic interference signal recurrence system and reproducing method |
| CN106526551A (en) * | 2016-10-31 | 2017-03-22 | 西安坤蓝电子技术有限公司 | Radar antenna dynamic performance testing system and method |
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Application publication date: 20141029 |