CN106713197B - A kind of airborne instrument landing system data processing method based on software radio - Google Patents
A kind of airborne instrument landing system data processing method based on software radio Download PDFInfo
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- CN106713197B CN106713197B CN201611140729.4A CN201611140729A CN106713197B CN 106713197 B CN106713197 B CN 106713197B CN 201611140729 A CN201611140729 A CN 201611140729A CN 106713197 B CN106713197 B CN 106713197B
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L27/00—Modulated-carrier systems
- H04L27/02—Amplitude-modulated carrier systems, e.g. using on-off keying; Single sideband or vestigial sideband modulation
- H04L27/06—Demodulator circuits; Receiver circuits
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L27/00—Modulated-carrier systems
- H04L27/02—Amplitude-modulated carrier systems, e.g. using on-off keying; Single sideband or vestigial sideband modulation
- H04L27/08—Amplitude regulation arrangements
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Abstract
The airborne instrument landing system data processing method based on software radio that the present invention relates to a kind of, comprising: AM demodulation module is to in-phase component sequence XI(n), quadrature component sequence XQ(n) two-way digital baseband signal is handled, and obtains envelope signal A (n)；A (n) signal is divided into four tunnels, all the way by 90Hz filter, obtains 90Hz signal；All the way by 150Hz filter, 150Hz signal is obtained；All the way by 300~3000Hz filter, voice signal is obtained；DC component is obtained by DC component estimation module all the way；Amplitude measurement is carried out to X (n) signal and Z (n) signal, rear 1/10 sampled point of amplitude measurement intercept signal sequence carries out；The signal of signal and 150Hz for 90Hz respectively multiplied byCoefficient carry out amplitude amplification, it is 90Hz signal amplitude that X (n), which obtains corresponding amplitude output X ',；Z (n) obtains corresponding amplitude output Z ', is the amplitude of 150Hz signal；According to X ', Y, Z ', modulation degree needed for instrument landing is calculated is poor.
Description
Technical field
The invention belongs to aircraft navigation communication scheme fields, are related to a kind of instrument on board landing system based on software radio
System data processing method.
Background technique
Type aircraft navigation communication system is made of various airborne radio installations, including VOR, VHF, ILS etc..Due to passing
The design of system wireless device has a single function using hardware as core and poor expandability, the equipment of different function needs difference
Hardware design, research and develop with high costs, and be difficult to extend upgrading.Numerous discrete nav-com installations, lead to airborne equipment
Volume weight and power consumption are larger, and lack versatility and flexibility, and airborne nav-com installation needs a kind of integrated, one
The solution of change.
Integrative solution based on software and radio technique has upgrading easy to maintain, and scalability, flexibility is high, at
This low, a series of feature such as light-weight.On the basis of having built unitized hardware platform, various navigational communications functions
The design focal point of realization has just turned to software design by hardware design, is just become by the design requirement of advanced circuit to succinct height
Imitate the requirement of algorithm.
Summary of the invention
The invention proposes a kind of airborne instrument landing system software processing method based on software radio, traditional
Improvement is made that on the basis of instrument-landing-system modulation degree difference calculation method, sufficiently combines the theory of software radio
And design philosophy, have the characteristics that succinct efficiently and accurately is general.
Following skill can be used in a kind of airborne instrument landing system software processing method based on software radio of the present invention
Art scheme:
Include:
(1) AM demodulation module is to in-phase component sequence XI(n), quadrature component sequence XQ(n) two-way digital baseband signal carries out
Processing obtains envelope signal A (n), handles formula are as follows:
The A (n) is envelope signal, contains 90Hz signal, 150Hz signal, voice signal and DC component；
(2) A (n) signal is divided into four tunnels, all the way by 90Hz filter, obtains 90Hz signal；It is filtered all the way by 150Hz
Wave device obtains 150Hz signal；All the way by 300~3000Hz filter, voice signal is obtained；Estimated all the way by DC component
Meter module obtains DC component；
If the 90Hz signal is X (n), DC component signal is Y, and 150Hz signal is Z (n)；
(3) amplitude measurement carried out to X (n) signal and Z (n) signal, rear the 1/10 of amplitude measurement intercept signal sequence is adopted
Sampling point carries out；
(4) for the signal of 90Hz and 150Hz signal respectively multiplied byCoefficient carry out amplitude amplification, X (n) obtains
Corresponding amplitude exports X ', is 90Hz signal amplitude；Z (n) obtains corresponding amplitude output Z ', is the amplitude of 150Hz signal；
(5) according to X ', Y, Z ', modulation degree needed for instrument landing can be calculated according to following formula is poor:
DDM=(X '-Z ')/Y,
Wherein DDM is that modulation degree needed for instrument-landing-system is poor.
The process of A (n) into the extraction of DC component estimation module progress DC component includes: in step (2)
DC component estimation module carries out multiplying window to input signal A (n) first, its calculation formula is:
yi=ai* [1-cos (ω)], wherein intermediate parameters
Wherein n is the element number of sequence A (n), aiFor i-th of element of A (n), yiFor aiIt is defeated after corresponding adding window
Out；If the yi, i=1,2, the 3...n-1 sequences constituted are Y (n), carry out taking mean operation to Y (n), can get direct current
Component signal Y.
Filter design parameter is respectively as follows: in step (2)
90Hz filter: type is Butterworth bandpass filter, and passband initial frequency is 80Hz, cut-off frequecy of passband
90Hz, filter order 10；
150Hz filter: type is Butterworth bandpass filter, and passband initial frequency is 140Hz, cut-off frequecy of passband
150Hz, filter order 10；
300~3000Hz filter: Butterworth type is bandpass filter, and passband initial frequency is 300Hz, and passband is cut
Only frequency 3000Hz, filter order 3.
The present invention has the advantages that algorithm is simple, module design has versatility, AM demodulation module, filter module
It can be used for the software realization of other navigation communication systems, this method is general for localizer and glide-path localizer receive capabilities
, it is not influenced by localizer is different with glide-path localizer modulation degree.The more traditional calculation method of the algorithm is efficient, accuracy
It is high.
Detailed description of the invention
Fig. 1 is module composition schematic diagram of the invention.
Fig. 2 is that modulation degree of the invention resolves module frame chart.
Fig. 3 is the schematic diagram for the DC component estimating part that modulation degree difference resolves inside modules.
Specific embodiment
The present invention is described in further details with reference to the accompanying drawing, a kind of instrument on board landing based on software radio
System software processing method is on general software radio hardware platform, and use is reusable, the design of modularized design thought
The data processing method for airborne instrument landing system course and glide-path localizer function.This method applies the device based on Fig. 1,
Steps are as follows:
(1) AM demodulation module is to in-phase component sequence XI(n), quadrature component sequence XQ(n) two-way digital baseband signal carries out
Processing obtains envelope signal A (n), handles formula are as follows:
The A (n) is envelope signal, contains 90Hz signal, 150Hz signal, voice signal and DC component；
(2) A (n) signal is divided into four tunnels, passes through 90Hz filter, 150Hz filter, 300~3000Hz filtering respectively
Device, DC component estimation module are handled；
The design of filter module is based on considered below: unlimited impact can be used to the phase of signal and insensitive in system
Response filter, i.e. I IR digital filter are designed using mature Design of Analog Filter method, adopt in this method
With Butterworth filter, it is fabricated to general software module, order and frequency parameter are adjustable；By theory analysis and test
Verifying, one group of good design parameter of test effect that this method uses are respectively as follows:
90Hz filter: type is bandpass filter, and passband initial frequency is 80Hz, cut-off frequecy of passband 90Hz, filtering
Device order is 10；
150Hz filter: type is bandpass filter, and passband initial frequency is 140Hz, cut-off frequecy of passband 150Hz, filter
Wave device order is 10；
300~3000Hz filter: type is bandpass filter, and passband initial frequency is 300Hz, cut-off frequecy of passband
3000Hz, filter order 3；
Butterworth filter design method is mature, and it is auxiliary that the progress of the softwares such as Matlab can be used when designing with upper filter
It helps, repeats no more.
Pass through 90Hz signal needed for the available Processing Algorithm of above-mentioned filter, 150Hz signal, in addition, voice
Signal is needed for localizer system, and rear after filtering to export as audio digital signals, the subsequent algorithm be not related to.If institute
Stating 90Hz signal is X (n), and DC component amplitude Y, 150Hz signal is Z (n)；
(3) as shown in Fig. 2, having carried out amplitude measurement, amplitude measurement intercept signal sequence to X (n) signal and Z (n) signal
Rear 1/10 sampled point carry out, in this way it is possible to prevente effectively from signal passes through mistake caused by amplitude fading caused by filter
The sampling duration of 0.1s-1s can be used in laboratory for difference；
(4) it in order to make up the amplitude loss generated in filtering, needs to amplify signal.In the filtering of (2) step
In device design, the cut-off frequecy of passband of the first two filter has been set as 90Hz and 150Hz, such 90Hz and 150Hz letter by us
Number amplitude fading be 3dB, i.e., amplitude fading is originalTimes, therefore, the letter of signal and 150Hz for 90Hz
Number respectively multiplied byCoefficient carry out amplitude amplification, to guarantee that amplitude does not decay.It is defeated to obtain corresponding amplitude by X (n) as a result,
X ' out is 90Hz signal amplitude；Z (n) obtains corresponding amplitude output Z ', is the amplitude of 150Hz signal.
(5) A (n) enters the process of the extraction of DC component estimation module progress DC component as shown in figure 3, DC component
Estimation module carries out multiplying window to input signal A (n) first, its calculation formula is:
yi=ai* [1-cos (ω)], wherein intermediate parameters
Wherein n is the element number of sequence A (n), aiFor i-th of element of A (n), yiFor aiIt is defeated after corresponding adding window
Out.
Next signal is carried out taking mean operation, can get DC component and exports Y.
Wherein DDM is that modulation degree needed for instrument-landing-system is poor.
This method be for localizer and glide-path localizer receive capabilities it is general, not by localizer and glide-path localizer tune
The different influence of system.
A kind of airborne instrument landing system data processing method based on software radio is established with open hardware
On the basis of general-purpose platform, using the thought with object-oriented, reusable, modular software module is constructed, is realized succinct, high
Effect accurately calculates.
The method Computer Simulation verifying is subjected to, the absolute error of obtained modulation degree difference data is no more than
0.000004DDM；
The method administration has been carried out the two-shipper antenna transmitting-receiving under laboratory environment to test on Hardware Platform of Software Radio
Card, modulation degree difference absolute error are less than 0.001DDM.
Claims (2)
1. a kind of airborne instrument landing system software processing method based on software radio characterized by comprising
(1) AM demodulation module is to in-phase component sequence XI(n), quadrature component sequence XQ(n) at two-way digital baseband signal
Reason obtains envelope signal A (n), handles formula are as follows:
The A (n) is envelope signal, contains 90Hz signal, 150Hz signal, voice signal and DC component；
(2) A (n) signal is divided into four tunnels, all the way by 90Hz filter, obtains 90Hz signal；It is filtered all the way by 150Hz
Device obtains 150Hz signal；All the way by 300~3000Hz filter, voice signal is obtained；Estimated all the way by DC component
Module obtains DC component；
If the 90Hz signal is X (n), DC component signal is Y, and 150Hz signal is Z (n)；
(3) amplitude measurement, rear 1/10 sampled point of amplitude measurement intercept signal sequence are carried out to X (n) signal and Z (n) signal
It carries out；
(4) for the signal of 90Hz and 150Hz signal respectively multiplied byCoefficient carry out amplitude amplification, X (n) obtains corresponding
Amplitude exports X ', is 90Hz signal amplitude；Z (n) obtains corresponding amplitude output Z ', is the amplitude of 150Hz signal；
(5) according to X ', Y, Z ', modulation degree needed for instrument landing can be calculated according to following formula is poor:
DDM=(X '-Z ')/Y,
Wherein DDM is that modulation degree needed for instrument-landing-system is poor；
The process of A (n) into the extraction of DC component estimation module progress DC component includes: in step (2)
DC component estimation module carries out multiplying window to input signal A (n) first, its calculation formula is:
yi=ai* [1-cos (ω)], wherein intermediate parameters
Wherein n is the element number of sequence A (n), aiFor i-th of element of A (n), yiFor aiOutput after corresponding adding window；If
The yi, i=1,2, the 3...n-1 sequences constituted are Y (n), carry out taking mean operation to Y (n), can get DC component letter
Number Y.
2. a kind of airborne instrument landing system software processing method based on software radio as described in claim 1, special
Sign is,
Filter design parameter is respectively as follows: in step (2)
90Hz filter: type be Butterworth bandpass filter, passband initial frequency be 80Hz, cut-off frequecy of passband 90Hz,
Filter order is 10；
150Hz filter: type is Butterworth bandpass filter, and passband initial frequency is 140Hz, cut-off frequecy of passband
150Hz, filter order 10；
300~3000Hz filter: Butterworth type is bandpass filter, and passband initial frequency is 300Hz, passband cutoff frequency
Rate 3000Hz, filter order 3.
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| CN112073347B (en) * | 2020-08-19 | 2023-02-28 | 中国民用航空总局第二研究所 | Analysis system of DVOR signal based on software defined radio technology |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103645458A (en) * | 2013-12-16 | 2014-03-19 | 天津七六四通信导航技术有限公司 | Course far field monitoring equipment for instrument landing system |
| CN105466453A (en) * | 2015-11-19 | 2016-04-06 | 中国民用航空总局第二研究所 | On-line monitoring system of navigation equipment and method thereof |
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| US9098999B2 (en) * | 2013-09-13 | 2015-08-04 | The Boeing Company | Systems and methods for assuring the accuracy of a synthetic runway presentation |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103645458A (en) * | 2013-12-16 | 2014-03-19 | 天津七六四通信导航技术有限公司 | Course far field monitoring equipment for instrument landing system |
| CN105466453A (en) * | 2015-11-19 | 2016-04-06 | 中国民用航空总局第二研究所 | On-line monitoring system of navigation equipment and method thereof |
Non-Patent Citations (1)
| Title |
|---|
| 一种ＩＬＳ接收机数字中频处理方法的研究与实现;李辉等;《舰船电子对抗》;20150430;第38卷(第2期);第82-84页 * |
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