CN106855643B - Based on the inverse method for realizing moon wheel measuring with beam interference measuring technique - Google Patents
Based on the inverse method for realizing moon wheel measuring with beam interference measuring technique Download PDFInfo
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Abstract
The present invention provide it is a kind of based on the inverse method for realizing moon wheel measuring with beam interference measuring technique, including：In two ground survey stations of the ground configuration within 50km；Two signal sources are arranged in moonscape；1st ground survey station GS1With the 2nd ground survey station GS2The 1st signal source S is received simultaneously1The downlink signal of forwarding, and signal phase estimation is carried out, obtain phase difference between the 1st station；1st ground survey station GS1With the 2nd ground survey station GS2The 2nd signal source S is received simultaneously2The downlink signal of forwarding, and signal phase estimation is carried out, obtain phase difference between the 2nd station；Establish the 1st signal source S1With the 2nd signal source S2The relationship of the baseline and differential delay value of composition；According to the relationship of baseline and differential delay value, resolves and arrive moon rotation information.Advantage is：The advantages of present invention has high certainty of measurement, measurement pattern very simple, and realization is relatively easy to, can be widely used to promote.
Description
Technical field
The invention belongs to uranometry technical fields, and in particular to one kind realizing the moon based on inverse with beam interference measuring technique
The method that ball rotation measures.
Background technology
Lunar LASER Ranging technology is most important method in current moon wheel measuring.By measuring moonscape
The distance of multiple laser cooperative targets realizes the measurement to moon ball rotation, and obtains the situation of change of the state of the moon itself.
On traditional very long baseline interferometry(VLBI (Very Long Baseline Interferometry, VLBI) basis
On derivative I-VLBI (Inverse VLBI, inverse VLBI) technology be also current moon wheel measuring a kind of effective means.
Its basic principle is as shown in Figure 1：Assuming that positioned at the surface of the moon, there are two signal sources, respectively the 1st signal source S1With the 2nd signal
Source S2.There is the 1st ground survey station GS in ground configuration1.1st ground survey station GS1The 1st signal source S is received respectively1With the 2nd signal source S2
The downlink signal of transmission, and relevant treatment is carried out, obtain the 1st signal source S1With the 2nd signal source S2Reach same 1st ground survey station
GS1Light time difference, also referred to as geometric delays.
The geometry site constituted according to signal source and ground survey station has Δ τg=Bgs1/c；Wherein, Δ τgFor geometry when
Prolong；B is the 1st signal source S1To the 2nd signal source S2Baseline length；s1For：From the 1st signal source S1Direction sees, the 1st ground survey station
GS1Direction vector；C is the light velocity.Thus the information of baseline B is contained in geometric delays observed quantity known to formula.Due to the moon
The 1st signal source S on surface1With the 2nd signal source S2It is with moon ball rotation, therefore, the state change of baseline contains the moon
Rotation information can measure moon rotation parameter by measure geometry time delay.
Since the rotation of the moon is very small, in order to measure a moon ball rotation, the required precision of measurement amount is very high.Mesh
Before, in centimetres, the measurement accuracy of improved equipment also can only achieve several millimeters the precision of Lunar LASER Ranging.However,
When carrying out moon wheel measuring using inverse VLBI technologies, since the medium error introduced in signal propagation path is difficult to disappear very well
It removes, measurement accuracy is poor, it is difficult to meet moon wheel measuring requirement.Under the conditions of current measurement accuracy, the moon information such as ball rotation
It will drown out in error signal and cannot be found.
Currently, the research of this technology is using Japan and European Space Agency as representative, the two is set out from different angles to I- respectively
VLBI technologies are improved.Japan proposes the method that I-VLBI is measured, complex in realization.First, which increase one
A orbiter, orbital vehicle around lunar flight, earth station send uplink signal to orbiter, orbital vehicle, and orbiter, orbital vehicle is to the 1st signal source S1With the 2nd letter
Number source S2Forward the ground station signals received；Secondly, orbiter, orbital vehicle, signal source are operated under Coherence Mode, are turned by relevant
Hair ensures that two signal source downlink signals are relevant with earth station's uplink signal.This method is related to two signal sources of lunar surface and orbiter, orbital vehicle
The synchronization of the frequency of signal, in addition this method need bidirectional ranging etc., realize that complex, technical difficulty is relatively large.Europe
Principle of the empty office based on same wave beam proposes a kind of new method, and identical deep space number is configured for two signal sources of lunar surface
Answering machine, the same survey station in ground send uplink signal, and two signal sources are forwarded after receiving uplink signal, last ground receiver
The downlink signal of forwarding is simultaneously handled.The more Japanese method for proposing that I-VLBI is measured of the realization difficulty of this method is realized more simple
It is single, but the disadvantages of this method is：Multiple identical deep space Digital transponders are needed to configure, and need the same of ground
Antenna measures.
Invention content
In view of the defects existing in the prior art, the present invention provides a kind of based on against with the beam interference measuring technique realization moon
The method of wheel measuring can effectively solve the above problems.
The technical solution adopted by the present invention is as follows：
The present invention provides a kind of based on the inverse method for realizing moon wheel measuring with beam interference measuring technique including following
Step：
Step 1, two ground survey stations in ground configuration within 50km, respectively the 1st ground survey station GS1With the 2nd
Ground survey station GS2；Two signal sources, respectively the 1st signal source S are arranged in moonscape1With the 2nd signal source S2；
Step 2, it is assumed that the 1st ground survey station GS1For main website, the 2nd ground survey station GS2For secondary station, skill is transmitted using optical fiber time-frequency
The time frequency signal of main website is transferred to secondary station by art, realizes the 1st ground survey station GS1With the 2nd ground survey station GS2Time and frequency it is total
It enjoys；
Step 3, the 1st signal source S is set1With the 2nd signal source S2It is operated under coherency states；1st ground survey station GS1Respectively
To the 1st signal source S1With the 2nd signal source S2Send uplink signal, the 1st signal source S1With the 2nd signal source S2Receive uplink signal
After carry out coherent forwarding；Meanwhile the 2nd ground survey station GS2Respectively to the 1st signal source S1With the 2nd signal source S2Uplink signal is sent,
1st signal source S1With the 2nd signal source S2Coherent forwarding is carried out after receiving uplink signal；
Step 4, the 1st ground survey station GS1With the 2nd ground survey station GS2The 1st signal source S is received simultaneously1The downlink signal of forwarding,
And signal phase estimation is carried out, obtain phase difference between the 1st station；
1st ground survey station GS1With the 2nd ground survey station GS2The 2nd signal source S is received simultaneously2The downlink signal of forwarding, and carry out
Signal phase is estimated, phase difference between the 2nd station is obtained；
Step 5, it is based between the 1st station phase difference between phase difference and the 2nd station, obtains the 1st signal source S1With the 2nd signal source S2It
Between difference station between phase difference, resolved to the 1st signal source S with beam interference measuring principle further according to multifrequency point1With the 2nd signal source
S2To the differential delay value of earth station；
Step 6, the 1st signal source S is established1With the 2nd signal source S2The relationship of the baseline and differential delay value of composition；
Step 7, it according to the relationship of baseline and differential delay value, resolves and arrives moon rotation information.
Preferably, in step 4, the 1st ground survey station GS1With the 2nd ground survey station GS2The 1st signal source S is received simultaneously1Forwarding
Downlink signal, and signal phase estimation is carried out, phase difference between the 1st station is obtained, specially：
For the 1st signal source S1, downlink signal includes a carrier signal and two pairs of DOR sound signals；Wherein, carrier wave is believed
Number it is denoted as C, two pairs of DOR sound signals are denoted as-D2 ,-D1, D1, D2 respectively；Carrier signal ,-D2 sound signals ,-D1 sound signals, D1 sounds
Signal, D2 sound signals the 1st station between phase difference be denoted as respectivelyWherein, i=C ,-D2 ,-D1, D1, D2；
Due to containing the corresponding phase of signal source time delay actual value, ionosphere, troposphere in phase difference result between the 1st station
And the phase error that instrument and equipment introduces, it is represented by：
Wherein：ForAs i=C ,-D2 ,-D1, D1, D2, the 1st signal source S is respectively represented1Corresponding carrier wave letter
Number, the signal frequency of-D2 sound signals ,-D1 sound signals, D1 sound signals, D2 sound signals, unit Hz；
It is the 1st signal source S1Corresponding passive space vehicle time delay actual value, unit s；
It is the 1st signal source S1The time delay error that corresponding ionosphere introduces, unit s；
It is the 1st signal source S1The time delay error that corresponding troposphere introduces, unit s；
It is the 1st signal source S1The time delay error that corresponding instrument and equipment introduces, unit s；
It is the 1st signal source S1The time delay error that the clock correction of corresponding two survey stations introduces, unit s；
It is the 1st signal source S1Corresponding system random error, unit s；
For the 2nd signal source S2, downlink signal equally includes a carrier signal and two pairs of DOR sound signals；Wherein, it carries
Wave signal is denoted as C, and two pairs of DOR sound signals are denoted as-D2 ,-D1, D1, D2 respectively；Carrier signal ,-D2 sound signals ,-D1 sound signals,
D1 sound signals, D2 sound signals the 2nd station between phase difference be denoted as respectivelyWherein, i=C ,-D2 ,-D1, D1, D2；
Due to containing the corresponding phase of signal source time delay actual value, ionosphere, troposphere in phase difference result between the 2nd station
And the phase error that instrument and equipment introduces, it is represented by：
Wherein：ForAs i=C ,-D2 ,-D1, D1, D2, carrier signal ,-D2 sound signals ,-D1 sounds are corresponded to respectively
The signal frequency of signal, D1 sound signals, D2 sound signals, unit Hz；
It is the 2nd signal source S2Corresponding passive space vehicle time delay actual value, unit s；
It is the 2nd signal source S2The time delay error that corresponding ionosphere introduces, unit s；
It is the 2nd signal source S2The time delay error that corresponding troposphere introduces, unit s；
It is the 2nd signal source S2The time delay error that corresponding instrument and equipment introduces, unit s；
It is the 2nd signal source S2The time delay error that the clock correction of corresponding two survey stations introduces, unit s；
It is the 2nd signal source S2Corresponding system random error, unit s.
Preferably, step 5 is specially：
1st signal source S1With the 2nd signal source S2Between difference station between phase meter be shown as
Wherein：I=C ,-D2 ,-D1, D1, D2；
For Δ φi, as i=C ,-D2 ,-D1, D1, D2, phase difference ,-D2 between the difference station of carrier signal are corresponded to respectively
Phase difference between the difference station of sound signal ,-D1 sound signals difference station between phase difference, D1 sound signals difference station between phase difference and D2
Phase difference between the difference station of sound signal；
For fi, as i=C ,-D2 ,-D1, D1, D2, carrier signal ,-D2 sound signals ,-D1 sound signals, D1 are corresponded to respectively
The signal frequency of sound signal, D2 sound signals, unit Hz；
Represent the 1st signal source S1, the 2nd signal source S2The difference of corresponding passive space vehicle time delay actual value,
Unit is s；
Represent the difference of the time delay error of ionosphere introducing, unit s；
Represent the difference of the time delay error of troposphere introducing, unit s；
Represent the difference of the time delay error of instrument and equipment introducing, unit s；
Represent the difference of the time delay error of the clock correction introducing of two survey stations, unit s；
Represent the difference of system random error, unit s.
Since two, ground survey station is very close, the difference of time delay error that ionosphere introduces, troposphere introduce when
The difference of delay difference is eliminated, and the difference of the time delay error of the clock correction introducing of the difference for the time delay error that instrument and equipment introduces and two survey stations is logical
It crosses difference to be also eliminated, i.e.,：Δτino=0, Δ τtro=0, Δ τins=0, Δ τcl=0, therefore, Δ φi=2 π fi(Δτg+
Δτσ)；
Then, the 1st signal source S1With the 2nd signal source S2Differential delay to earth station is expressed as：Δτg=Δ φi/(2π
fi)-Δτσ。
Preferably, step 6 is specially：
The principle for measuring the extraction of differential delay value according to same beam interference has：
Wherein：τ1It is signal from the 1st signal source S1To the 1st ground survey station GS1Light time；
τ2It is signal from the 1st signal source S1To the 2nd ground survey station GS2Light time；
τ3It is signal from the 2nd signal source S2To the 1st ground survey station GS1Light time；
τ4It is signal from the 2nd signal source S2To the 2nd ground survey station GS2Light time, unit s；
According to I-VLBI principles, the 1st signal source S1With the 2nd signal source S2The baseline of composition is B；For moon baseline B, the 1st
Ground survey station GS1Geometric delaysWith the 2nd ground survey station GS2Geometric delaysIt is expressed as：
Therefore, with wave beam differential delay valueIt is expressed as
In conjunction with formula 4 and formula 6 it is found that
And due to
Wherein：B is the 1st signal source S1With the 2nd signal source S2The baseline of composition；s1For the 1st ground survey station GS1Direction to
Amount；S2For the 2nd ground survey station GS2Direction vector；C is the light velocity；
Therefore, baseline and the relationship of differential delay value are：
Δτg=Bs1/c-B·s2/ c (formula 8).
Preferably, step 7 is specially：
By observing for a long time, multigroup differential delay measurement amount Δ τ is obtainedg、s1And S2Value；
Therefore, every group of differential delay measurement amount Δ τg、s1And S2Value, resolved according to formula 8 and obtain baseline letter
Breath；The variation of multigroup baseline information characterizes the rotation information of the moon.
It is provided by the invention to realize the method for moon wheel measuring with following excellent with beam interference measuring technique based on inverse
Point：
The advantages of present invention has high certainty of measurement, measurement pattern very simple, and realization is relatively easy to, can be widely popularized makes
With.
Description of the drawings
Fig. 1 is the schematic diagram of the method for the moon wheel measuring that the prior art provides；
Fig. 2 is the signal provided by the invention based on the inverse method for realizing moon wheel measuring with beam interference measuring technique
Figure.
Wherein：1 is the 1st signal source S1；2 be the 2nd signal source S2；3 be the 1st signal source S1With the 2nd signal source S2The moon of composition
Face baseline B；4 be the 1st ground survey station GS1；5 be the 1st ground survey station GS1The angle theta in direction and baseline B1；6 be the 1st signal source S1
With the 2nd signal source S2Reach the 1st ground survey station GS1Distance difference Δ l1；7 be the 2nd ground survey station GS2；8 be the 2nd ground survey station
GS2The angle theta in direction and baseline B2；9 be the 1st signal source S1With the 2nd signal source S2Reach the 2nd ground survey station GS2Distance difference
Δl2；10 be the 1st ground survey station GS1Direction and the 2nd ground survey station GS2The angle Δ θ in direction.
Specific implementation mode
In order to make the technical problems, technical solutions and beneficial effects solved by the present invention be more clearly understood, below in conjunction with
Accompanying drawings and embodiments, the present invention will be described in further detail.It should be appreciated that specific embodiment described herein only to
It explains the present invention, is not intended to limit the present invention.
The present invention is mainly characterized in that the ground survey station pair two months using two close proximities compared with traditional method
Ball signal source measured with beam interference, can effectively eliminate ionosphere, troposphere, instrument and equipment etc. by Double deference and draw
The error entered, significantly improves measurement accuracy.The observed quantity that differential delay is measured for the same beam interference of acquisition, equally contains
The information for the baseline that two signal sources of the moon are constituted arrives moon rotation amount to resolve.
Main thought of the present invention is：
Utilize two the 1st ground survey station GS within 50km1With the 2nd ground survey station GS2Reception is fixed on the two of lunar surface
A signal source, i.e.,：1st signal source S1With the 2nd signal source S2The radio signal sent out carries out measuring (Same with beam interference
Beam Interferometry, SBI), the observed quantity of difference geometric delays is obtained, on this basis according to the principle of I-VLBI,
The 1st signal source S of moonscape is resolved using difference geometric delays observed result1With the 2nd signal source S2The basic lineal vector of composition changes
Situation, it is as inverse to measure (I-SBI) measurement method with beam interference to finally measure moon ball rotation.Its basic principle such as Fig. 2
It is shown.
The 1st signal source S of moonscape1With the 2nd signal source S2Downlink signal by reaching the earth after spatial, the 1st
Ground survey station GS1With the 2nd ground survey station GS2The downlink signal that the two is sent is received simultaneously.Distance about 40 of the signal source to earth station
Ten thousand kilometers, and the position of two survey stations, within 50km, therefore, the signal path of two signal sources to earth stations is almost the same,
Error on signal path is eliminated well, and measurement accuracy significantly improves, eliminate in traditional VLBI observation when be delayed
The larger problem of difference.
Relative to the method that ESA is proposed, the present invention does not need specific answering machine and carries out signal forwarding, and be commonly concerned with response
Machine can be met the requirements；In signal processing level, after the downlink signal that ground station reception signal source is sent, you can carry out analysis and
Processing obtains time delay observed result, and measurement pattern is very simple, and realization is relatively easy to.
Specifically, provided by the invention based on the inverse method for realizing moon wheel measuring with beam interference measuring technique, packet
Include following steps：
Step 1, two ground survey stations in ground configuration within 50km, respectively the 1st ground survey station GS1With the 2nd
Ground survey station GS2；Two signal sources, respectively the 1st signal source S are arranged in moonscape1With the 2nd signal source S2；
Specifically, after ground survey station receives the downlink signal that signal source is sent, the signal typically received is radiofrequency signal,
Therefore, it is necessary to carry out the signal to downconvert to intermediate frequency handling, in the present invention, downlink is received simultaneously using two ground survey stations
Signal measured with beam interference, and two ground survey stations are required to carry out down-converted.In order to ensure two ground survey stations
Frequency source influences consistent during down-converted, needs the 1st ground survey station GS1Time and frequency signal be transferred to the 2nd
Ground survey station GS2(it is assumed herein that the 1st ground survey station GS1For main website, the 2nd ground survey station GS2For secondary station), realize the 1st ground survey station
GS1With the 2nd ground survey station GS2Time and frequency sharing.Due to the 1st ground survey station GS1Configured with hydrogen clock, hydrogen clock frequency at present
Stability is 10-13The magnitude of/s is transmitted, it is ensured that two ground survey station down coversion local frequency stabilitys using optical fiber time-frequency
10 can be reached-13The magnitude of/s.
Step 2, it is assumed that the 1st ground survey station GS1For main website, the 2nd ground survey station GS2For secondary station, skill is transmitted using optical fiber time-frequency
The time frequency signal of main website is transferred to secondary station by art, realizes the 1st ground survey station GS1With the 2nd ground survey station GS2Time and frequency it is total
It enjoys；
Step 3, the 1st signal source S is set1With the 2nd signal source S2It is operated under coherency states；1st ground survey station GS1Respectively
To the 1st signal source S1With the 2nd signal source S2Send uplink signal, the 1st signal source S1With the 2nd signal source S2Receive uplink signal
After carry out coherent forwarding；Meanwhile the 2nd ground survey station GS2Respectively to the 1st signal source S1With the 2nd signal source S2Uplink signal is sent,
1st signal source S1With the 2nd signal source S2Coherent forwarding is carried out after receiving uplink signal；
Currently, the frequency stability of common spaceborne crystal oscillator is 10-10The magnitude of/s, the frequency stability of high stability crystal oscillator is 10-12The magnitude of/s.In order to eliminate influence of the spaceborne crystal oscillator of different signal source to measurement, the present invention proposes the survey under coherency states
The answering machine of amount method, setting signal source is operated under coherency states, and two, ground survey station respectively sends two signal sources
Row signal, signal source receive signal and carry out coherent forwarding.Since signal source is operated in coherency states, the frequency of downlink signal with
Uplink signal frequency coherence, the frequency source of two ground survey stations is identical in addition, comprehensive it is found that signal source downlink signal uses ground
The frequency source of face hydrogen clock, frequency stability can reach 10-13The magnitude of/s.
Step 4, the 1st ground survey station GS1With the 2nd ground survey station GS2The 1st signal source S is received simultaneously1The downlink signal of forwarding,
And signal phase estimation is carried out, obtain phase difference between the 1st station；
1st ground survey station GS1With the 2nd ground survey station GS2The 2nd signal source S is received simultaneously2The downlink signal of forwarding, and carry out
Signal phase is estimated, phase difference between the 2nd station is obtained；
In this step, the 1st ground survey station GS1With the 2nd ground survey station GS2The 1st signal source S is received simultaneously1The downlink of forwarding is believed
Number, and signal phase estimation is carried out, phase difference between the 1st station is obtained, specially：
For the 1st signal source S1, downlink signal includes a carrier signal and two pairs of DOR sound signals；Wherein, carrier wave is believed
Number it is denoted as C, two pairs of DOR sound signals are denoted as-D2 ,-D1, D1, D2 respectively；Carrier signal ,-D2 sound signals ,-D1 sound signals, D1 sounds
Signal, D2 sound signals the 1st station between phase difference be denoted as respectivelyWherein, i=C ,-D2 ,-D1, D1, D2；
Due to containing the corresponding phase of signal source time delay actual value, ionosphere, troposphere in phase difference result between the 1st station
And the phase error that instrument and equipment introduces, it is represented by：
Wherein：ForAs i=C ,-D2 ,-D1, D1, D2, the 1st signal source S is respectively represented1Corresponding carrier wave letter
Number, the signal frequency of-D2 sound signals ,-D1 sound signals, D1 sound signals, D2 sound signals, unit Hz；
It is the 1st signal source S1Corresponding passive space vehicle time delay actual value, unit s；
It is the 1st signal source S1The time delay error that corresponding ionosphere introduces, unit s；
It is the 1st signal source S1The time delay error that corresponding troposphere introduces, unit s；
It is the 1st signal source S1The time delay error that corresponding instrument and equipment introduces, unit s；
It is the 1st signal source S1The time delay error that the clock correction of corresponding two survey stations introduces, unit s；
It is the 1st signal source S1Corresponding system random error, unit s；
For the 2nd signal source S2, downlink signal equally includes a carrier signal and two pairs of DOR sound signals；Wherein, it carries
Wave signal is denoted as C, and two pairs of DOR sound signals are denoted as-D2 ,-D1, D1, D2 respectively；Carrier signal ,-D2 sound signals ,-D1 sound signals,
D1 sound signals, D2 sound signals the 2nd station between phase difference be denoted as respectivelyWherein, i=C ,-D2 ,-D1, D1, D2；
Due to containing the corresponding phase of signal source time delay actual value, ionosphere, troposphere in phase difference result between the 2nd station
And the phase error that instrument and equipment introduces, it is represented by：
Wherein：ForAs i=C ,-D2 ,-D1, D1, D2, carrier signal ,-D2 sound signals ,-D1 sounds are corresponded to respectively
The signal frequency of signal, D1 sound signals, D2 sound signals, unit Hz；
It is the 2nd signal source S2Corresponding passive space vehicle time delay actual value, unit s；
It is the 2nd signal source S2The time delay error that corresponding ionosphere introduces, unit s；
It is the 2nd signal source S2The time delay error that corresponding troposphere introduces, unit s；
It is the 2nd signal source S2The time delay error that corresponding instrument and equipment introduces, unit s；
It is the 2nd signal source S2The time delay error that the clock correction of corresponding two survey stations introduces, unit s；
It is the 2nd signal source S2Corresponding system random error, unit s.
Step 5, it is based between the 1st station phase difference between phase difference and the 2nd station, obtains the 1st signal source S1With the 2nd signal source S2It
Between difference station between phase difference, resolved to the 1st signal source S with beam interference measuring principle further according to multifrequency point1With the 2nd signal source
S2To the differential delay value of earth station；
This step is specially：
Assuming that the 1st signal source S1With the 2nd signal source S2Signal frequency it is very close, might as well assume two signal sources
Frequency is consistent, i.e.,：1st signal source S1With the 2nd signal source S2Between difference station between phase meter be shown as
Wherein：I=C ,-D2 ,-D1, D1, D2；
For Δ φi, as i=C ,-D2 ,-D1, D1, D2, phase difference ,-D2 between the difference station of carrier signal are corresponded to respectively
Phase difference between the difference station of sound signal ,-D1 sound signals difference station between phase difference, D1 sound signals difference station between phase difference and D2
Phase difference between the difference station of sound signal；
For fi, as i=C ,-D2 ,-D1, D1, D2, carrier signal ,-D2 sound signals ,-D1 sound signals, D1 are corresponded to respectively
The signal frequency of sound signal, D2 sound signals, unit Hz；
Represent the 1st signal source S1, the 2nd signal source S2The difference of corresponding passive space vehicle time delay actual value,
Unit is s；
Represent the difference of the time delay error of ionosphere introducing, unit s；
Represent the difference of the time delay error of troposphere introducing, unit s；
Represent the difference of the time delay error of instrument and equipment introducing, unit s；
Represent the difference of the time delay error of the clock correction introducing of two survey stations, unit s；
Represent the difference of system random error, unit s.
Since two, ground survey station is very close, the difference of time delay error that ionosphere introduces, troposphere introduce when
The difference of delay difference is eliminated, and the difference of the time delay error of the clock correction introducing of the difference for the time delay error that instrument and equipment introduces and two survey stations is logical
It crosses difference to be also eliminated, i.e.,：Δτino=0, Δ τtro=0, Δ τins=0, Δ τcl=0, therefore, Δ φi=2 π fi(Δτg+
Δτσ)；
Then, the 1st signal source S1With the 2nd signal source S2Differential delay to earth station is expressed as：Δτg=Δ φi/(2π
fi)-Δτσ。
Step 6, the 1st signal source S is established1With the 2nd signal source S2The relationship of the baseline and differential delay value of composition；
This step is specially：
The principle for measuring the extraction of differential delay value according to same beam interference has：
Wherein：τ1It is signal from the 1st signal source S1To the 1st ground survey station GS1Light time；
τ2It is signal from the 1st signal source S1To the 2nd ground survey station GS2Light time；
τ3It is signal from the 2nd signal source S2To the 1st ground survey station GS1Light time；
τ4It is signal from the 2nd signal source S2To the 2nd ground survey station GS2Light time, unit s；
According to I-VLBI principles, depending on the 1st signal source S of the moon1With the 2nd signal source S2For two, two lunar surface observation stations, ground
Survey station is the signal source of close proximity, the 1st signal source S1With the 2nd signal source S2The baseline of composition is B；For moon baseline B, the 1st
Ground survey station GS1Geometric delaysWith the 2nd ground survey station GS2Geometric delaysIt is expressed as：
Therefore, with wave beam differential delay valueIt is expressed as
In conjunction with formula 4 and formula 6 it is found that
If being reference with ground survey station, Double deference latency measurement amount can be obtained.If being constituted with two signal sources of lunar surface
Baseline is reference, and two ground survey stations can be considered as signal source, and Double deference latency measurement amount is that two, ground survey station is believed to two
The difference of the light time in number source.The position of ground survey station can accurately measure, and the relative position of two ground survey stations
Also what one is particularly good at is first accurately measured, therefore the letter of the baseline B of two signal sources composition is contained in Double deference time delay observed quantity
Breath.
Carrying out simple derive below proves.
And due to
Wherein：B is the 1st signal source S1With the 2nd signal source S2The baseline of composition；s1For the 1st ground survey station GS1Direction to
Amount；S2For the 2nd ground survey station GS2Direction vector；C is the light velocity；
Therefore, baseline and the relationship of differential delay value are：
Δτg=Bs1/c-B·s2/ c (formula 8).
Wherein, equation left side Δ τgFor the known observed quantity that can be measured, equation the right is the table for including moon baseline B
Up to formula.
Step 7, it according to the relationship of baseline and differential delay value, resolves and arrives moon rotation information.
This step is specially：
According to above-mentioned derivation result it is found that containing the information of moon baseline B in Double deference time delay observed quantity.Pass through length
The observation of time can obtain multigroup Double deference latency measurement amount.Assuming that the relationship between Double deference latency measurement amount and baseline B
It is denoted as
Δτg=F (B)+σ (formula 9)
The information of lunar surface baseline can be obtained according to this formula, what multigroup latency measurement amount resolved believes to multigroup baseline
Breath.Since two signal sources are located at moonscape, the two moves together with the rotation of the moon.Therefore, the variation of baseline is with regard to table
The rotation information of the moon is levied.So by observing for a long time, multigroup differential delay measurement amount Δ τ is obtainedg、s1And S2's
Value；Therefore, every group of differential delay measurement amount Δ τg、s1And S2Value, resolved according to formula 8 and obtain a baseline information；It is multigroup
The variation of baseline information characterizes the rotation information of the moon.
In conclusion it is provided by the invention based on the inverse method for realizing moon wheel measuring with beam interference measuring technique,
It has the following advantages：
1, using two ground survey stations of 50km or so measure with beam interference, eliminate the influence of all kinds of errors,
Measurement accuracy can improve 2 magnitudes.
2, it is transmitted using ground elapsed time and Time synchronization technique is realized compared to using time synchronization and Transfer Technology on star
Difficulty substantially reduces, and the precision of time synchronization also significantly improves.
3, two signal sources are operated in similar frequency point, it is not required that the complete phase of working frequency points of two signal sources
Together.
4, the downlink signal for directly receiving two signal sources is handled, and it is inconsistent can to eliminate signal source transponder delay
Property the error brought influence.
Therefore, the advantages of present invention has high certainty of measurement, measurement pattern very simple, and realization is relatively easy to, can be extensive
It promotes the use of.
The above is only a preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, various improvements and modifications may be made without departing from the principle of the present invention, these improvements and modifications are also answered
Depending on protection scope of the present invention.
Claims (4)
1. a kind of based on the inverse method for realizing moon wheel measuring with beam interference measuring technique, which is characterized in that including following
Step：
Step 1, two ground survey stations in ground configuration within 50km, respectively the 1st ground survey station GS1It is surveyed with the 2nd ground
Stand GS2；Two signal sources, respectively the 1st signal source S are arranged in moonscape1With the 2nd signal source S2；
Step 2, it is assumed that the 1st ground survey station GS1For main website, the 2nd ground survey station GS2It, will using optical fiber time-frequency Transfer Technology for secondary station
The time frequency signal of main website is transferred to secondary station, realizes the 1st ground survey station GS1With the 2nd ground survey station GS2Time and frequency sharing；
Step 3, the 1st signal source S is set1With the 2nd signal source S2It is operated under coherency states；1st ground survey station GS1Respectively to the 1st
Signal source S1With the 2nd signal source S2Send uplink signal, the 1st signal source S1With the 2nd signal source S2It is carried out after receiving uplink signal
Coherent forwarding；Meanwhile the 2nd ground survey station GS2Respectively to the 1st signal source S1With the 2nd signal source S2Send uplink signal, the 1st signal
Source S1With the 2nd signal source S2Coherent forwarding is carried out after receiving uplink signal；
Step 4, the 1st ground survey station GS1With the 2nd ground survey station GS2The 1st signal source S is received simultaneously1The downlink signal of forwarding, goes forward side by side
Row signal phase is estimated, phase difference between the 1st station is obtained；
1st ground survey station GS1With the 2nd ground survey station GS2The 2nd signal source S is received simultaneously2The downlink signal of forwarding, and carry out signal
Phase estimation obtains phase difference between the 2nd station；
Step 5, it is based between the 1st station phase difference between phase difference and the 2nd station, obtains the 1st signal source S1With the 2nd signal source S2Between
Phase difference between difference station is resolved with beam interference measuring principle to the 1st signal source S further according to multifrequency point1With the 2nd signal source S2It arrives
The differential delay value of earth station；
Step 6, the 1st signal source S is established1With the 2nd signal source S2The relationship of the baseline and differential delay value of composition；
Step 7, it according to the relationship of baseline and differential delay value, resolves and arrives moon rotation information；
Wherein, in step 4, the 1st ground survey station GS1With the 2nd ground survey station GS2The 1st signal source S is received simultaneously1The downlink of forwarding is believed
Number, and signal phase estimation is carried out, phase difference between the 1st station is obtained, specially：
For the 1st signal source S1, downlink signal includes a carrier signal and two pairs of DOR sound signals；Wherein, carrier signal is remembered
For C, two pairs of DOR sound signals are denoted as-D2 ,-D1, D1, D2 respectively；Carrier signal ,-D2 sound signals ,-D1 sound signals, D1 sound signals,
Phase difference is denoted as respectively between 1st station of D2 sound signalsWherein, i=C ,-D2 ,-D1, D1, D2；
Due to containing the corresponding phase of signal source time delay actual value in phase difference result between the 1st station, ionosphere, troposphere and
The phase error that instrument and equipment introduces, is represented by：
Wherein：ForAs i=C ,-D2 ,-D1, D1, D2, the 1st signal source S is respectively represented1Corresponding carrier signal ,-D2
The signal frequency of sound signal ,-D1 sound signals, D1 sound signals, D2 sound signals, unit Hz；
It is the 1st signal source S1Corresponding passive space vehicle time delay actual value, unit s；
It is the 1st signal source S1The time delay error that corresponding ionosphere introduces, unit s；
It is the 1st signal source S1The time delay error that corresponding troposphere introduces, unit s；
It is the 1st signal source S1The time delay error that corresponding instrument and equipment introduces, unit s；
It is the 1st signal source S1The time delay error that the clock correction of corresponding two survey stations introduces, unit s；
It is the 1st signal source S1Corresponding system random error, unit s；
For the 2nd signal source S2, downlink signal equally includes a carrier signal and two pairs of DOR sound signals；Wherein, carrier wave is believed
Number it is denoted as C, two pairs of DOR sound signals are denoted as-D2 ,-D1, D1, D2 respectively；Carrier signal ,-D2 sound signals ,-D1 sound signals, D1 sounds
Signal, D2 sound signals the 2nd station between phase difference be denoted as respectivelyWherein, i=C ,-D2 ,-D1, D1, D2；
Due to containing the corresponding phase of signal source time delay actual value in phase difference result between the 2nd station, ionosphere, troposphere and
The phase error that instrument and equipment introduces, is represented by：
Wherein：ForAs i=C ,-D2 ,-D1, D1, D2, correspond to respectively carrier signal ,-D2 sound signals ,-D1 sound signals,
The signal frequency of D1 sound signals, D2 sound signals, unit Hz；
It is the 2nd signal source S2Corresponding passive space vehicle time delay actual value, unit s；
It is the 2nd signal source S2The time delay error that corresponding ionosphere introduces, unit s；
It is the 2nd signal source S2The time delay error that corresponding troposphere introduces, unit s；
It is the 2nd signal source S2The time delay error that corresponding instrument and equipment introduces, unit s；
It is the 2nd signal source S2The time delay error that the clock correction of corresponding two survey stations introduces, unit s；
It is the 2nd signal source S2Corresponding system random error, unit s.
2. it is according to claim 1 based on the inverse method for realizing moon wheel measuring with beam interference measuring technique, it is special
Sign is that step 5 is specially：
1st signal source S1With the 2nd signal source S2Between difference station between phase meter be shown as
Wherein：I=C ,-D2 ,-D1, D1, D2；
For △ φi, as i=C ,-D2 ,-D1, D1, D2, phase difference ,-D2 messages between the difference station of carrier signal are corresponded to respectively
Number difference station between phase difference ,-D1 sound signals difference station between phase difference, D1 sound signals difference station between phase difference and D2 messages
Number difference station between phase difference；
For fi, as i=C ,-D2 ,-D1, D1, D2, carrier signal ,-D2 sound signals ,-D1 sound signals, D1 messages are corresponded to respectively
Number, the signal frequencies of D2 sound signals, unit Hz；
The difference of the 1st signal source S1, the corresponding passive space vehicle time delay actual values of the 2nd signal source S2 are represented, it is single
Position is s；
Represent the difference of the time delay error of ionosphere introducing, unit s；
Represent the difference of the time delay error of troposphere introducing, unit s；
Represent the difference of the time delay error of instrument and equipment introducing, unit s；
Represent the difference of the time delay error of the clock correction introducing of two survey stations, unit s；
Represent the difference of system random error, unit s；
Since two, ground survey station is very close, the difference of time delay error that ionosphere introduces, troposphere introduce when be delayed
The difference of difference is eliminated, and the difference of the time delay error of the clock correction introducing of the difference for the time delay error that instrument and equipment introduces and two survey stations passes through difference
Divide and be also eliminated, i.e.,：△τino=0, △ τtro=0, △ τins=0, △ τcl=0, therefore, △ φi=2 π fi(△τg+△
τσ)；
Then, the 1st signal source S1With the 2nd signal source S2Differential delay to earth station is expressed as：△τg=△ φi/(2πfi)-△
τσ。
3. it is according to claim 2 based on the inverse method for realizing moon wheel measuring with beam interference measuring technique, it is special
Sign is that step 6 is specially：
The principle for measuring the extraction of differential delay value according to same beam interference has：
Wherein：τ1It is signal from the 1st signal source S1To the 1st ground survey station GS1Light time；
τ2It is signal from the 1st signal source S1To the 2nd ground survey station GS2Light time；
τ3It is signal from the 2nd signal source S2To the 1st ground survey station GS1Light time；
τ4It is signal from the 2nd signal source S2To the 2nd ground survey station GS2Light time, unit s；
According to I-VLBI principles, the 1st signal source S1With the 2nd signal source S2The baseline of composition is B；For moon baseline B, the 1st ground
Survey station GS1Geometric delaysWith the 2nd ground survey station GS2Geometric delaysIt is expressed as：
Therefore, with wave beam differential delay valueIt is expressed as
In conjunction with formula 4 and formula 6 it is found that
And due to
Wherein：B is the 1st signal source S1With the 2nd signal source S2The baseline of composition；S1For the 1st ground survey station GS1Direction vector；S2
For the 2nd ground survey station GS2Direction vector；C is the light velocity；
Therefore, baseline and the relationship of differential delay value are：
△τg=Bs1/c-B·s2/ c (formula 8).
4. it is according to claim 3 based on the inverse method for realizing moon wheel measuring with beam interference measuring technique, it is special
Sign is that step 7 is specially：
By observing for a long time, multigroup differential delay measurement amount Δ τ is obtainedg、s1And S2Value；
Therefore, every group of differential delay measurement amount Δ τg、s1And S2Value, resolved according to formula 8 and obtain a baseline information；It is more
The variation of group baseline information characterizes the rotation information of the moon.
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