CN103308930A - Pseudo-range precision measurement method of satellite navigation signal simulator - Google Patents
Pseudo-range precision measurement method of satellite navigation signal simulator Download PDFInfo
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- CN103308930A CN103308930A CN2013101964692A CN201310196469A CN103308930A CN 103308930 A CN103308930 A CN 103308930A CN 2013101964692 A CN2013101964692 A CN 2013101964692A CN 201310196469 A CN201310196469 A CN 201310196469A CN 103308930 A CN103308930 A CN 103308930A
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Abstract
The invention provides a pseudo-range precision measurement method of a satellite navigation signal simulator, which can meet the measurement requirement of any pseudo-range value range, has high accuracy of measurement, and meets the calibration and verification requirements of the pseudo-range precision index of the satellite navigation signal simulator. The measurement method comprises the following steps: setting the satellite navigation signal simulator to output a radio frequency simulation signal of which the pseudo-range nominal value is p; converting the measurement of the pseudo-range p to the measurement of delay time corresponding to the pseudo-range p; and decomposing the time measurement into the measurement of a whole cycle part and the measurement of a decimal part. The measurement of the whole period part means that a periodic calibration signal is used for counting the whole cycles of the delay time of the radio frequency simulation signal from a pseudo-range start point, and the cycle of the calibration signal is measured. The measurement of the decimal part means that the time interval part smaller than one cycle of the calibration signal of the delay time of the radio frequency simulation signal from the pseudo-range start point is measured.
Description
Technical field
The present invention relates to the Satellite Navigation Technique field, particularly relate to a kind of satellite navigation signal simulator pseudorange accuracy measurement method.
Background technology
Satellite Navigation Technique is based on GLONASS (Global Navigation Satellite System) (GNSS, Global Navigation Satellite System) and to the technology of user-provided location, navigation and Time Service, has been widely used at present the military and civilian field.The user is based on satellite navigation equipment for user, and such as chip, module and end product etc. obtained related service.
In the processes such as the development of satellite navigation equipment for user and inspection, need to customize the navigation signal under the conditions such as different satellite constellations, error model, user trajectory, signal power, verify or check the technical indicator of product whether to satisfy related request, therefore, the manufacturer of satellite navigation equipment for user and testing agency extensively adopt satellite navigation signal simulator to generate as required the navigation simulation signal.
Pseudorange is the original observed quantity that satellite navigation equipment for user carries out location compute, also is the crucial emulated data that satellite navigation signal simulator produces, and the error size of simulator emulation pseudorange is directly connected to the confidence level of tested receiver testing result.At present, the measuring method of satellite navigation signal simulator pseudorange precision index is: by the time-domain analysis to simulator radio frequency simulation signal of output under particular dummy scene (the pseudorange nominal value is zero), identify the pseudo range signals starting point and measure its delay (transmission delay of simulation satellite signal) on time shaft, and carry out the measurement of time delay, again it be multiply by the light velocity and be converted to the pseudorange value.The limitation of the method shows as:
1. judge the pseudo range signals starting point by the display waveform of time-domain analysis instrument (such as oscillograph), can identify this point for some signal, such as Big Dipper area navigation simulating signal, with the Barker code overturn point as its unique point, navigation signal for other types then is difficult for maybe can not identifying, so this measuring method is only applicable to the simulator of particular type.
2. be subjected to time-domain analysis instrument time interval measurement precision index and the double constraints that satisfies the longest sampling time index of this measuring accuracy, this measuring method can only be measured the error of pseudorange null value or less pseudorange value, and can not measure the error of any pseudorange.For example: the pseudorange precision index of simulator is 0.05m, being transformed into the transmission time to be about 167ps(be electromagnetic signal should be apart from required time with light velocity propagation), for satisfying the alignment requirements of this index, the time interval measurement precision of time-domain analysis instrument must can reach 167ps, if satisfy more strict calibrating requirement, then need to reach the 55ps magnitude.High-end oscillograph can in the longest certain acquisition time (generally under the highest real-time sampling rate), in 2.5ms, satisfy this measuring accuracy requirement.But this acquisition time can not satisfy 20000km(at least is converted to about 67ms of propagation delay time) the measurement requirement of pseudorange output value scope.
Summary of the invention
The defective that the present invention exists according to prior art, a kind of measuring method of satellite navigation signal simulator pseudorange precision is provided, can satisfy the measurement requirement of any pseudorange value scope, accuracy of measurement is high, satisfies calibration and the calibrating requirement of satellite navigation signal simulator pseudorange precision index.
Technical scheme of the present invention is:
A kind of satellite navigation signal simulator pseudorange accuracy measurement method, it is characterized in that, it is the radio frequency simulation signal of p that satellite navigation signal simulator output pseudorange nominal value is set, to be converted to the measurement of pseudorange p the measurement of corresponding time delay to pseudorange p, described time measurement is decomposed into the measurement of part complete cycle and the measurement of fraction part, described complete cycle, the measurement of part referred to the periodic calibration signal radio frequency simulate signal be carried out from the delay in time of pseudorange starting point that cycle of counting and the Measurement and calibration signal of complete cycle issue, the measurement of described fraction part refer to measure radio frequency simulation signal pseudorange starting point time delay less than the time interval part of calibrating signal one-period; The actual measured value p ' that obtains thus simulator output pseudorange nominal value p is:
p′=c×(NT+d)?（1）
Wherein:
The actual measured value of p '-simulator output pseudorange
C-electromagnetic wave velocity of propagation in a vacuum
N-calibrating signal complete cycle issue, N is since 0 counting
The T-calibrating signal cycle
The fraction part of d-time delay, i.e. in time delay less than the time interval part in a calibrating signal cycle; Then the error delta p of simulator output pseudorange is:
Δp=p-p′?（2）。
The radio frequency simulation signal of described simulator output adds in the pseudorange initial point position and to be easy to arbitrarily the signature identified, and described signature can be used to the time-domain analysis instrument identification of time interval measurement.
Described periodic calibration signal and described radio frequency simulation signal are exported synchronously, and the cycle of described periodic calibration signal is not more than the time-domain analysis instrument in the longest sampling time of satisfying under the simulator pseudorange precision measure requirement condition.
Described periodic calibration signal is used as the external trigger signal of time-domain analysis instrument simultaneously, N-1 periodic signal of described periodic calibration signal has the feature that can trigger the time-domain analysis instrument, wherein N is the complete cycle issue of calibrating signal, is calculated according to formula (1) by simulator.
Described periodic calibration signal is the calibration pulse signal, and the high level of N-1 pulse signal raising is used for triggering the time-domain analysis instrument, and wherein N is the complete cycle issue of calibration pulse, is calculated according to formula (1) by simulator.
Technique effect of the present invention:
The measuring method of a kind of satellite navigation signal simulator pseudorange precision provided by the invention can satisfy the measurement requirement of any pseudorange value scope, and accuracy of measurement is high, satisfies calibration and the calibrating requirement of satellite navigation signal simulator pseudorange precision index.
By measuring method of the present invention, can realize tracing to the source of simulator pseudorange value: 1. for the simulator that can export the needed radio frequency simulation signal of measuring method of the present invention and periodic calibration signal, can use described measuring method and calibrate, realize pseudorange value tracing to the source to the time frequency parameter.2. for the simulator that can not export the needed radio frequency simulation signal of measuring method of the present invention and periodic calibration signal, can at first calibrate the satellite navigation receiver of high-precision stable performance with the used calibrated simulator of the inventive method, and then with other universal simulators of this receiver calibration, realize all kinds of satellite navigation signal simulator pseudorange values tracing to the source to the time frequency parameter.
Description of drawings
Fig. 1 is the schematic diagram of implementing measuring method of the present invention.
Fig. 2 implements the radio frequency simulation signal of measuring method of the present invention and the waveform schematic diagram of periodic calibration signal.
Embodiment
Below in conjunction with accompanying drawing embodiments of the invention are described in further detail.
A kind of satellite navigation signal simulator pseudorange accuracy measurement method, it is the radio frequency simulation signal of p that satellite navigation signal simulator output pseudorange nominal value is set, to be converted to the measurement of pseudorange p the measurement of corresponding time delay to pseudorange p, described time measurement is decomposed into the measurement of part complete cycle and the measurement of fraction part, described complete cycle, measurement partly referred to the periodic calibration signal radio frequency simulate signal be carried out from the delay in time of pseudorange starting point the cycle of counting and the Measurement and calibration signal of complete cycle issue, the measurement of described fraction part refers to measure radio frequency simulation signal pseudorange starting point time delay less than the time interval part of calibrating signal one-period, and the actual measured value p ' that obtains thus simulator output pseudorange nominal value p is:
p′=c×(NT+d)?（1）
Wherein:
The actual measured value of p '-simulator output pseudorange
C-electromagnetic wave velocity of propagation in a vacuum
N-calibrating signal complete cycle issue, N is since 0 counting
The T-calibrating signal cycle
The fraction part of d-time delay, i.e. in time delay less than the time interval part in a calibrating signal cycle;
Then the error delta p of simulator output pseudorange is:
Δp=p-p′?（2）。
For realizing above-mentioned measuring method, periodic calibration signal and the radio frequency simulation signal of the present invention's structure are as follows:
1. the radio frequency simulation signal of simulator output is used for identifying the pseudorange starting point to measure time delay corresponding to any pseudorange value.Add in the pseudo range signals initial point position and to be easy to arbitrarily the signature that identifies, spiking for example is so that can accurately identify this point on the time-domain analysis instrument.
2. the periodic calibration signal is used for the counting that time delay carry out complete cycle issue corresponding to any pseudorange value by simulator output or by the output of periodic calibration signal generator.Calibrating signal and radio frequency simulation signal are exported synchronously, and its cycle is not more than the time-domain analysis instrument in the longest sampling time (generally under high sampling rate) of satisfying under the simulator pseudorange precision measure requirement condition.For example: simulator pseudorange precision index is 0.05m, wish satisfies its alignment requirements, the time resolution of time-domain analysis instrument needs to reach 167ps at least, suppose the time-domain analysis instrument for certain model, the longest sampling time of satisfying this accuracy requirement is 2.5ms, then requires the cycle T of calibrating signal to be not more than 2.5ms.
3. the periodic calibration signal is used as the external trigger signal of time-domain analysis instrument simultaneously, N-1 periodic signal of periodic calibration signal has the feature that can trigger the time-domain analysis instrument, for example raise the high level of N-1 periodic signal, wherein N is the complete cycle issue of calibrating signal.For any pseudorange nominal value p to be measured, simulator calculates N according to formula (1), when the pseudo range signals of this value of output, exports synchronously calibrating signal and is used for triggering the time-domain analysis instrument.
As shown in Figure 1, for implementing the embodiment schematic diagram of measuring method of the present invention.In the present embodiment, satellite navigation signal simulator output pseudorange nominal value is the radio frequency simulation signal of p, exports synchronously the periodic calibration pulse signal by simulator simultaneously.The time-domain analysis instrument that is used for time interval measurement is oscillograph, and frequency counter is used for calibrating signal is carried out counting number and cycle of Measurement and calibration signal complete cycle.The output terminal of radio frequency simulation signal (being called for short " radio frequency output " among Fig. 1) connects oscillographic first passage, the output terminal of calibration pulse signal (being called for short " calibrating signal output " among Fig. 1) connects oscillographic second channel and oscillographic external trigger port, and the output terminal of simultaneously calibration pulse signal is the rate of connections counter also; Wherein, the radio frequency simulation signal of output is included in the signature of the time-domain analysis instrument identification that can be used to time interval measurement that has on the pseudorange starting point, the cycle of the calibration pulse signal of output is not more than the time-domain analysis instrument in the longest sampling time of satisfying under the simulator pseudorange precision measure requirement condition, the pulse signal that the high level of N-1 pulse of calibration pulse signal is elevated is as oscillographic external trigger signal, and wherein N is the complete cycle issue of calibration pulse.
Fig. 2 is the radio frequency simulation signal of the simulator output of enforcement measuring method of the present invention and the waveform schematic diagram of calibration pulse signal.Wherein the radio frequency simulation signal is illustrated with sinusoidal wave, does not draw actual modulation waveform (the actual modulated waveform does not present periodically).The radio frequency simulation signal of output adds spike as signature in the pseudorange initial point position, and the high level of N-1 pulse of the calibration pulse signal of output is elevated as oscillographic external trigger signal.
Measuring process is as follows:
1. connect tested simulator and oscillograph and frequency counter by Fig. 1, the radio frequency simulation signal output part connects oscillographic passage 1; The output terminal access channel oscilloscope 2 of calibration pulse signal accesses oscillograph external trigger input port simultaneously; The output terminal access frequency counter input end of calibration pulse signal.
2. simulator operation pseudorange nominal value is the test simulating scenes of p, p can arrange arbitrarily in the pseudorange value output area that simulator is supported, simulator is exported calibration pulse signal and radio frequency simulation signal synchronously, when output calibration pulse signal, simulator will calculate complete cycle issue N according to formula (1), and the high level of raising N-1 pulse be used for to trigger oscillograph.
3. after oscillograph triggers, passage 1 demonstrates the waveform of stable radio frequency output signal fraction part, passage 2 demonstrates the waveform of stable N pulse of calibration pulse signal, go out the rising edge of N calibration pulse and the time interval between radio frequency simulation signal pseudorange starting point with oscilloscope measurement, can obtain the measured value of the fraction part d in the formula (1).
4. with cycle and the pulse number of frequency counter Measurement and calibration pulse signal, obtain the measured value that N is counted in calibration pulse cycle T in the formula (1) and calibration pulse.
5. according to formula (1), calculate the actual measured value p ' of simulator output pseudorange nominal value p, according to the error delta p of formula (2) compute simulator output pseudorange.
Should be pointed out that the above embodiment can make the invention of those skilled in the art's comprehend, but do not limit the present invention in any way creation.Therefore, although this instructions and embodiment have been described in detail to the invention,, it will be appreciated by those skilled in the art that still and can make amendment or be equal to replacement the invention; And all do not break away from technical scheme and the improvement thereof of the spirit and scope of the present invention, and it all is encompassed in the middle of the protection domain of the invention patent.
Claims (5)
1. satellite navigation signal simulator pseudorange accuracy measurement method, it is characterized in that, it is the radio frequency simulation signal of p that satellite navigation signal simulator output pseudorange nominal value is set, p is the arbitrary value in the simulator pseudorange value output area, to be converted to the measurement of pseudorange p the measurement of corresponding time delay to pseudorange p, described time measurement is decomposed into the measurement of part complete cycle and the measurement of fraction part, described complete cycle, measurement partly referred to the periodic calibration signal radio frequency simulate signal be carried out from the delay in time of pseudorange starting point the cycle of counting and the Measurement and calibration signal of complete cycle issue, the measurement of described fraction part refers to measure radio frequency simulation signal pseudorange starting point time delay less than the time interval part of calibrating signal one-period, and the actual measured value p ' that obtains thus simulator output pseudorange nominal value p is:
p′=c×(NT+d)?（1）
Wherein:
The actual measured value of p '-simulator output pseudorange
C-electromagnetic wave velocity of propagation in a vacuum
N-calibrating signal complete cycle issue, N is since 0 counting
The T-calibrating signal cycle
The fraction part of d-time delay, i.e. in time delay less than the time interval part in a calibrating signal cycle;
Then the error delta p of simulator output pseudorange is:
Δp=p-p′?（2）。
2. satellite navigation signal simulator pseudorange accuracy measurement method according to claim 1, it is characterized in that, the radio frequency simulation signal of described simulator output, add in the pseudorange initial point position and to be easy to arbitrarily the signature identified, described signature can be used to the time-domain analysis instrument identification of time interval measurement.
3. satellite navigation signal simulator pseudorange accuracy measurement method according to claim 1, it is characterized in that, described periodic calibration signal and described radio frequency simulation signal are exported synchronously, and the cycle of described periodic calibration signal is not more than the time-domain analysis instrument in the longest sampling time of satisfying under the simulator pseudorange precision measure requirement condition.
4. satellite navigation signal simulator pseudorange accuracy measurement method according to claim 3, it is characterized in that, described periodic calibration signal is used as the external trigger signal of time-domain analysis instrument simultaneously, N-1 periodic signal of described periodic calibration signal has the feature that can trigger the time-domain analysis instrument, wherein N is the complete cycle issue of calibrating signal, is calculated according to formula (1) by simulator.
5. satellite navigation signal simulator pseudorange accuracy measurement method according to claim 4, it is characterized in that, described periodic calibration signal is the calibration pulse signal, the high level of N-1 pulse signal raising is used for triggering the time-domain analysis instrument, wherein N is the complete cycle issue of calibration pulse, is calculated according to formula (1) by simulator.
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Cited By (3)
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| CN104765044A (en) * | 2015-03-30 | 2015-07-08 | 北京华云智联科技有限公司 | Navigation satellite signal generator and implementation method |
| CN110658536A (en) * | 2018-06-29 | 2020-01-07 | 北京自动化控制设备研究所 | Satellite receiver navigation output signal time sequence testing method |
| CN107566061B (en) * | 2017-08-23 | 2021-04-09 | 成都天奥技术发展有限公司 | Microwave second-level time delay calibration system |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104765044A (en) * | 2015-03-30 | 2015-07-08 | 北京华云智联科技有限公司 | Navigation satellite signal generator and implementation method |
| CN107566061B (en) * | 2017-08-23 | 2021-04-09 | 成都天奥技术发展有限公司 | Microwave second-level time delay calibration system |
| CN110658536A (en) * | 2018-06-29 | 2020-01-07 | 北京自动化控制设备研究所 | Satellite receiver navigation output signal time sequence testing method |
| CN110658536B (en) * | 2018-06-29 | 2023-02-10 | 北京自动化控制设备研究所 | Satellite receiver navigation output signal time sequence testing method |
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