CN119224748A - Intersatellite high-precision distance measurement method and system based on optical frequency comb - Google Patents
Intersatellite high-precision distance measurement method and system based on optical frequency comb Download PDFInfo
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Abstract
The invention provides an inter-satellite high-precision distance measurement method based on an optical frequency comb, which is applied to distance measurement between a first satellite and a second satellite, and modulates transmitting time information by controlling the generation time and initial phase of an optical frequency comb pulse signal on the first satellite and the second satellite respectively, so that the transmission channel noise is restrained in a bidirectional comparison mode based on time delay information of analysis processing of the optical frequency comb signal received by the first satellite and the second satellite, and the accurate inter-satellite distance is calculated finally. The invention also provides an inter-satellite high-precision distance measurement system based on the optical frequency comb. Therefore, the invention solves the problem of limited space application scene, eliminates the problem of distance ambiguity caused by the repetition period of the optical frequency comb pulse, and simultaneously avoids the problem of high required optical frequency comb transmitting power caused by long inter-satellite distance.
Description
Technical Field
The invention relates to the technical field of inter-satellite distance measurement, in particular to an inter-satellite high-precision distance measurement method and system based on an optical frequency comb.
Background
The method for realizing the inter-satellite high-precision absolute distance measurement has important significance for improving the efficiency of space applications such as satellite navigation, electronic reconnaissance, remote sensing imaging, satellite formation flying, scientific detection and the like.
At present, the mature inter-satellite distance measurement technology is mainly divided into two technical routes based on microwaves and based on lasers. The technology of microwave distance measurement is the earliest and most mature in development, but the distance measurement accuracy is limited by the wavelength of microwaves. With the development perfection of laser technology, the inter-satellite distance measurement technology based on laser gradually becomes a research hot spot, has higher precision but has the problem of distance ambiguity, and is mainly suitable for relative distance measurement.
The optical frequency comb is an important invention in the 21 st century, and the optical frequency comb signal has excellent time-frequency domain characteristics of narrow pulse width, wide spectrum range, distinguishable longitudinal mode, high repetition frequency stability and the like, so that the development of the precision measurement field is greatly promoted. At present, the existing optical frequency comb ranging methods are various, but the most basic ranging methods mainly comprise 4 kinds, including a time-of-flight method, a multi-wavelength interferometry, a double optical comb interferometry and a dispersion interferometry.
However, in practical distance measurement application, especially in inter-satellite large-scale long-distance measurement, the conventional optical frequency comb measurement technology has the problems of limited acting distance, distance ambiguity and the like, so that the application prospect of the optical frequency comb measurement technology in inter-satellite absolute distance measurement is greatly limited.
Therefore, in order to meet the practical demands of the development of future space engineering application fields on the high-precision distance measurement technology, a method and a system for exploring the high-precision absolute distance between optical frequency combs with longer acting distance and no distance ambiguity are needed.
Disclosure of Invention
The invention aims to provide an inter-satellite high-precision distance measurement method based on an optical frequency comb, which is used for solving the problem of limited space application scene, eliminating the problem of distance ambiguity caused by the repetition period of the pulse of the optical frequency comb and simultaneously avoiding the problem of high emission power of the required optical frequency comb caused by long inter-satellite distance.
In order to achieve the above object, in one aspect, the present invention provides an inter-satellite high-precision distance measurement method based on an optical frequency comb, the method being applied to distance measurement between a first satellite and a second satellite, comprising the steps of:
The first satellite receives a first optical frequency comb signal transmitted by the second satellite when the first satellite receives a clock face, obtains a first transmitting clock face of the second satellite by tracking the phase of the received first optical frequency comb signal, and calculates a first time delay of the first satellite based on the first receiving clock face and the first transmitting clock face;
The second satellite receives a second optical frequency comb signal transmitted by the first satellite when receiving the clock face of the second satellite, obtains a second transmitting clock face of the first satellite by tracking the phase of the received second optical frequency comb signal, and calculates a second time delay of the second satellite based on the second receiving clock face and the second transmitting clock face;
The first time delay and the second time delay are calculated to an intermediate epoch, and a first target time delay and a second target time delay at the same moment are obtained;
And calculating path propagation delay between the first satellite and the second satellite according to the first target delay and the second target delay, and calculating the inter-satellite distance between the first satellite and the second satellite based on the path propagation delay.
Further, the path propagation delay is calculated based on the following formula:
ΔTAB＝(ΔTA+ΔTB)/2;
Wherein Δt AB is the path propagation delay, Δt A is the first target delay, and Δt B is the second target delay.
Further, the inter-satellite distance between the first satellite and the second satellite is calculated based on the following formula:
LAB＝(ΔTA+ΔTB)/2*c;
Wherein L AB is the inter-satellite distance, and c is the speed of light.
Further, the first delay is a difference between the first receiving clock face and the first transmitting clock face, and the second delay is a difference between the second receiving clock face and the second transmitting clock face.
The inter-satellite high-precision distance measurement method based on the optical frequency comb can solve the problem that the space application scene is limited, is compatible with the existing microwave system, solves the problem of distance ambiguity caused by the pulse repetition period of the optical frequency comb, and avoids the problem of high required optical frequency comb transmitting power caused by the inter-satellite distance.
On the other hand, based on the same invention structure, the invention also provides an inter-satellite high-precision distance measurement system based on an optical frequency comb, wherein the system is configured in a first satellite and a second satellite which relatively carry out inter-satellite distance measurement, and comprises the following components:
the satellite-borne atomic clock module is used for generating a stable frequency source to provide a frequency reference for locking an optical frequency comb;
the optical frequency comb module is used for generating an optical frequency comb signal with a specified initial phase at a specified time according to a control instruction, wherein the optical frequency comb signal comprises a propagation optical frequency comb used as a measurement signal and a reference optical frequency comb used as a tracking signal;
The optical transmission system module is used for transmitting the signals of the propagation optical frequency comb to a relative satellite, receiving the relative propagation optical frequency comb from the relative satellite and transmitting the signals of the relative propagation optical frequency comb and the reference optical frequency comb to the linear optical sampling system module, wherein the relative satellite is a satellite for performing inter-satellite distance measurement with a current satellite;
The linear optical sampling system module is used for calculating time delay information between the relative propagation optical frequency comb and the reference optical frequency comb;
the microwave terminal module is used for interacting the time delay information measured by the current satellite and the relative satellite respectively;
The information processing module is used for calculating the first time delay information of the current satellite and the second time delay information of the relative star to an intermediate epoch to obtain a first target time delay and a second target time delay at the same moment, calculating the path propagation time delay between the current satellite and the relative star according to the first target time delay and the second target time delay, and calculating the inter-satellite distance between the current satellite and the relative star based on the path propagation time delay.
Further, the optical transmission system module is specifically configured to:
And transmitting the signals generated by the propagation optical frequency comb to the opposite star through a laser receiving and transmitting channel, receiving the opposite propagation optical frequency comb transmitted by the opposite star through the laser receiving and transmitting the signals of the opposite propagation optical frequency comb and the reference optical frequency comb to the linear optical sampling system module.
Further, the linear optical sampling system module is specifically configured to:
Interfering the counter-propagating optical frequency comb and the reference optical frequency comb in a 50% splitting ratio fiber optic splitter;
inputting the interfered signals into a balance detector to filter direct current components in the signals so as to obtain alternating current signals;
And converting the alternating current signal into a voltage signal, amplifying the voltage signal, inputting the voltage signal into a low-pass filter, and performing quantitative acquisition through an analog-to-digital converter to obtain time delay information between the opposite propagation optical frequency comb and the reference optical frequency comb.
Further, the information processing module is further configured to estimate, according to the time delay information received from the linear optical sampling system module, first time delay information of the current satellite by using a kalman filter.
Further, the microwave terminal module is specifically configured to send the first delay information to the opposite star, and receive the second delay information sent by the opposite star.
Further, the path propagation delay is calculated based on the following formula:
ΔTAB＝(ΔTA+ΔTB)/2;
Wherein Δt AB is the path propagation delay, Δt A is the first target delay, and Δt B is the second target delay;
The inter-satellite distance between the current satellite and the relative other satellite is calculated based on the following formula:
LAB＝(ΔTA+ΔTB)/2*c;
Wherein L AB is the inter-satellite distance, and c is the speed of light.
Therefore, the inter-satellite high-precision distance measurement method and system based on the optical frequency comb adopt the optical frequency comb signal with controllable time and initial phase as the measurement signal, avoid the problem of distance ambiguity of the traditional optical frequency comb signal measurement technology, enable the optical frequency comb signal to realize inter-satellite long-distance measurement, and simultaneously obtain the time delay of the optical frequency comb signal propagated by the other satellite and the reference optical frequency comb signal by controlling the time and the phase of the reference optical frequency comb signal and utilizing the linear optical sampling technology, thereby having lower requirements on the transmitting power of the optical frequency comb signal propagated by the other satellite, improving the sensitivity of the satellite to the optical frequency comb signal processing and expanding the range finding action distance of the optical frequency comb.
Drawings
FIG. 1 is a flow chart of steps of the method for measuring inter-satellite high-precision distance based on an optical frequency comb according to an embodiment of the present invention;
FIG. 2 is a system block diagram of the inter-satellite high-precision distance measurement system based on an optical frequency comb according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of the inter-satellite high-precision distance measurement method based on an optical frequency comb according to an embodiment of the present invention;
Fig. 4 is a schematic diagram of a specific structure of the inter-satellite high-precision distance measurement system based on an optical frequency comb according to an embodiment of the present invention.
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention.
It should be noted that references in the specification to "one embodiment," "an example embodiment," etc., indicate that the embodiment described may include a particular feature, structure, or characteristic, but every embodiment may not necessarily include the particular feature, structure, or characteristic. Furthermore, such phrases are not intended to refer to the same embodiment. Further, when a particular feature, structure, or characteristic is described in connection with an embodiment, it is submitted that it is within the knowledge of one skilled in the art to effect such feature, structure, or characteristic in connection with other embodiments whether or not explicitly described.
Furthermore, certain terms are used throughout the specification and the claims that follow to refer to particular components or parts, and it will be understood by those of ordinary skill in the art that manufacturers may refer to a component or part by different terms or terminology. The present specification and the following claims do not take the form of an element or component with the difference in name, but rather take the form of an element or component with the difference in function as a criterion for distinguishing. In the following description and in the claims, the terms "include" and "comprise" are used in an open-ended fashion, and thus should be interpreted to mean "include, but not limited to. The term "coupled," as used herein, includes any direct or indirect electrical connection. Indirect electrical connection means include connection via other devices.
Example 1
Fig. 1 shows an inter-satellite high-precision distance measurement method based on an optical frequency comb according to an embodiment of the present invention, where the method is applied to distance measurement between a first satellite and a second satellite, any two satellites whose inter-satellite distances are to be measured can be used as the first satellite and the second satellite, and the first satellite and the second satellite have no primary and secondary parts, and the method of the present embodiment includes the following steps:
S101, a first satellite receives a first optical frequency comb signal transmitted by the second satellite when receiving the first receiving clock face, obtains the first transmitting clock face of the second satellite by tracking the phase of the received first optical frequency comb signal, and calculates the first time delay of the first satellite based on the first receiving clock face and the first transmitting clock face.
In the embodiment, a first satellite is taken as a satellite a, a second satellite is taken as a satellite B, in step S101, the satellite a receives a first optical frequency comb signal transmitted by the satellite B when receiving a clock face, then tracks the phase of the received optical frequency comb signal to obtain t 1 when receiving the clock face of the satellite B, that is, t 1 when receiving the clock face, t 2,t2 lags t 1 when receiving the clock face, and then calculates to obtain a first time delay of the first satellite according to t 1 and t 2, where the first time delay includes a change of path propagation delay of the satellite B in a link system and a change of a clock difference itself between the satellite a and the satellite B.
The first delay is the difference between the first receiving clock face and the first transmitting clock face, and the first delay ΔT A'＝t2-t1 is combined with the above example.
In the implementation, the first satellite and the second satellite are both provided with an inter-satellite high-precision distance measurement system based on an optical frequency comb, the second satellite generates a first optical frequency comb signal with a designated initial phase at a designated moment according to a control instruction by the system, the first optical frequency comb signal comprises a propagation optical frequency comb used as a measurement signal and a reference optical frequency comb used as a tracking signal, and after the system on the first satellite receives the optical frequency comb signal transmitted to the propagation optical frequency comb by the second satellite, the first time delay of the first satellite is calculated according to the optical frequency comb signal phase of the transmission optical frequency comb of the second satellite and the reference optical frequency comb generated by the system.
Further, the propagation optical frequency comb from the second satellite side and the reference optical frequency comb of the first satellite can be interfered in the optical fiber beam splitter with 50% beam splitting ratio, the interfered signals are input into the balance detector to filter direct current components in the signals, alternating current signals are obtained, the alternating current signals are converted into voltage signals and amplified and then input into the low-pass filter, and finally the first time delay is obtained through quantitative acquisition of the analog-to-digital converter.
S102, the second satellite receives the second optical frequency comb signal transmitted by the first satellite when receiving the clock face, obtains the second transmitting clock face time of the first satellite by tracking the phase of the received second optical frequency comb signal, and calculates the second time delay of the second satellite based on the second receiving clock face time and the second transmitting clock face time. The step S101 and the step S102 in this embodiment are not logically separated from each other, and the step S101 may be performed first, the step S102 may be performed first, or the step S101 and the step S102 may be performed simultaneously.
In combination with the above example, in this embodiment, the satellite B receives the second optical frequency comb signal transmitted by the satellite a at the time t 4 of its receiving clock face, and the phase of the received second optical frequency comb signal is tracked to obtain the time t 3 of the transmitting clock face of the satellite a, that is, the time t 3 of the second transmitting clock face, and the time t 4,t4 of the second receiving clock face lags the time t 3, so as to calculate the second delay of the second satellite according to the time t 3 and the time t 4, where the second delay includes the change of the path propagation delay of the satellite a in the link system and the change of the clock difference itself between the satellite a and the satellite B.
Wherein the second delay is the difference between the second receiving clock face and the second transmitting clock face, and in combination with the above example, the second delay Δt B'B＝t4-t3 is the second delay.
In the implementation, the first satellite generates a second optical frequency comb signal with a specified initial phase at a specified time according to a control instruction by the system, wherein the second optical frequency comb signal comprises a propagation optical frequency comb used as a measurement signal and a reference optical frequency comb used as a tracking signal, and after receiving the optical frequency comb signal transmitted to the propagation optical frequency comb by the first satellite, the system on the second satellite calculates a second time delay of the second satellite according to the optical frequency comb signal phase of the transmission optical frequency comb of the first satellite and the reference optical frequency comb generated by the system.
Further, the propagation optical frequency comb from the first satellite side and the reference optical frequency comb from the second satellite side can be interfered in the optical fiber beam splitter with 50% beam splitting ratio, the interfered signals are input into the balance detector to filter direct current components in the signals, alternating current signals are obtained, the alternating current signals are converted into voltage signals and amplified, then the voltage signals are input into the low-pass filter, and finally the voltage signals are quantitatively collected through the analog-to-digital converter, so that second time delay is obtained.
And S103, the first time delay and the second time delay are calculated to an intermediate epoch to obtain the first target time delay and the second target time delay at the same moment, wherein the step S103 can be executed in a first satellite or a second satellite, and the first satellite or the second satellite can receive time delay information obtained by calculating the other satellite end through a microwave communication link, such as the first satellite receives the second time delay obtained by calculating the second satellite through the microwave communication link or receives the first time delay obtained by calculating the first satellite through the microwave communication link in the second satellite.
Because the first receiving clock face time T 2 and the second receiving clock face time T 4 are different times, the embodiment directly calculates the first time delay delta T 'A and the second time delay delta T' B of the double unidirectional observation values to the middle epoch by using the reference satellite orbit and the clock difference, so as to obtain the first target time delay delta T A and the second target time delay delta T B of the same time, in particular, after the time delay information calculated by the other satellite end is obtained by a satellite (the first satellite or the second satellite) on any side, the first time delay delta T 'A and the second time delay delta T' B are further calculated to the middle epoch, so as to obtain the first target time delay delta T A and the second target time delay delta T B of the same time, wherein the first target time delay delta T2 refers to the time delay information obtained by the first time delay delta T A 'through the middle epoch, and the second target time delay delta T B refers to the time delay information obtained by the second time delay delta T B' through the first time delay to the middle epoch, and the first target time delay delta T26 and the second target time delay delta T B are calculated respectively.
S104, calculating path propagation delay between the first satellite and the second satellite according to the first target delay and the second target delay, and calculating the inter-satellite distance between the first satellite and the second satellite based on the path propagation delay. Step S104 of the present embodiment may be performed on the first satellite side or the second satellite side.
The satellite A clock and the satellite B clock are provided with clock differences, and local oscillator optical frequency combs at two ends are locked on the respective clocks, so that the optical frequency combs at two ends generate a time difference, and the time difference is set as T AB. In combination with the foregoing example, in the processing system of the satellite a, a time difference may be calculated according to the time and the phase of the received optical frequency comb signal, where the time difference is the first target time delay Δt A,ΔTA, and the time difference is Δt A＝ΔTpath+ΔTAB when the first target time delay Δt path includes the change Δt AB of the path transmission delay of the satellite B in the link system and the change Δt AB of the two clock differences.
Since the link is bi-directional, the path propagation delay of the signal from satellite A to satellite B is substantially the same as the path propagation delay from satellite A to satellite B to satellite A, and so the time difference DeltaT B calculated by satellite B is DeltaT B＝ΔTpath-ΔTAB.
The path propagation delays of the satellite A and the satellite B can be obtained by the method, namely DeltaT AB＝(ΔTA+ΔTB)/2, wherein DeltaT AB is the path propagation delay, deltaT A is the first target delay, and DeltaT B is the second target delay.
Further, the inter-satellite absolute distance between the satellite a and the satellite B can be obtained by combining the light velocity c, i.e., the inter-satellite distance between the first satellite and the second satellite is calculated based on the following formula:
LAB＝(ΔTA+ΔTB)/2*c;
Wherein L AB is the inter-satellite distance, and c is the speed of light.
Since the pairing can be performed at almost the same time, the error caused by link jitter can be basically counteracted.
The method of the embodiment modulates the transmitting time information by controlling the generation time and the initial phase of the optical frequency comb pulse signal, suppresses the transmission channel noise in a bidirectional comparison mode, and finally realizes accurate inter-satellite distance measurement.
Example two
Referring to fig. 2, based on the same inventive configuration, the present invention provides an inter-satellite high-precision distance measurement system 100 based on an optical frequency comb in a second embodiment, the system 100 is configured in a first satellite and a second satellite which are opposite to each other for inter-satellite distance measurement, specifically, the system 100 is configured in both the first satellite and the second satellite, the system 100 includes a satellite-borne atomic clock module 10, an optical frequency comb module 20, an optical transmission system module 30, a linear optical sampling system module 40, a microwave terminal module 50 and an information processing module 60, wherein:
The satellite-borne atomic clock module 10 is used for generating a stable frequency source to provide a frequency reference for locking an optical frequency comb, the optical frequency comb module 20 is used for generating an optical frequency comb signal with a specified initial phase at a specified time according to a control instruction, the optical frequency comb signal comprises a propagation optical frequency comb used as a measurement signal and a reference optical frequency comb used as a tracking signal, the optical transmission system module 30 is used for transmitting the signal of the propagation optical frequency comb to a relative satellite and receiving the relative propagation optical frequency comb from the relative satellite and transmitting the signal of the relative propagation optical frequency comb and the reference optical frequency comb to the linear optical sampling system module, the relative satellite is a satellite for performing inter-satellite distance measurement with the current satellite, the linear optical sampling system module 40 is used for calculating time delay information between the relative propagation optical frequency comb and the reference optical frequency comb, the microwave terminal module 50 is used for interacting the time delay information measured by the current satellite and the relative satellite respectively, the information processing module 60 is used for calculating the first time delay information of the current satellite and the second time delay information of the relative satellite to an intermediate epoch, the first target and the second time delay information of the relative satellite are obtained, the first target and the time delay between the current target and the current satellite and the second target and the current time delay is calculated according to the time delay information of the first target and the relative time delay between the current target and the current time delay and the current satellite.
In this embodiment, the system 100 configured on the first satellite is only used as an example, wherein the current satellite is the first satellite, and the opposite satellite is the second satellite opposite to the first satellite, and the system 100 configured on the second satellite can specifically refer to the related description on the first satellite, which is not repeated in this embodiment.
The satellite-borne atomic clock module 10 of the present embodiment may be an optical clock or an ultrastable laser.
The optical frequency comb signal generated by the propagation optical frequency comb is used as a measuring signal to be transmitted to the other end, and the reference optical frequency comb is used as a tracking signal to assist in processing the received opposite propagation optical frequency comb.
Further, the optical transmission system module 30 of the present embodiment is specifically configured to send the signal generated by the propagating optical frequency comb to the opposite satellite (i.e. the second satellite) through the laser transceiving channel, and receive the signal from the opposite propagating optical frequency comb sent by the opposite satellite through the laser transceiving channel, and transmit the signals of the opposite propagating optical frequency comb and the reference optical frequency comb to the linear optical sampling system module 40.
The linear optical sampling system module 40 is configured to process the optical frequency comb signal propagating with respect to the other star and the reference optical frequency comb signal of the other star and obtain time delays of the two signals. In the module, a small difference exists between the repetition frequencies of two optical frequency comb signals, the repetition frequency of the star reference optical comb is set to be f r, the repetition frequency of the star transmission optical comb is set to be f r+Δfr, and the small repetition frequency difference delta f r is the key for realizing the linear optical sampling technology. In this regard, the linear optical sampling system module 40 of this embodiment is specifically configured to interfere the relative propagation optical frequency comb and the reference optical frequency comb in the optical fiber beam splitter with 50% beam splitting ratio, input the interfered signals to the balance detector to filter the direct current component in the signals to obtain the alternating current signal, convert the alternating current signal into the voltage signal, amplify the voltage signal, input the voltage signal to the low-pass filter, and perform quantization acquisition through the analog-to-digital converter to obtain the time delay information between the relative propagation optical frequency comb and the reference optical frequency comb.
The microwave terminal module 50 of the present embodiment is configured to interact with a microwave terminal module of another satellite, taking a first satellite as an example, the optical frequency comb module 20 of the first satellite obtains the time delay information calculated by the first satellite from the linear optical sampling system 40, and then sends the time delay information to the other satellite (i.e. the second satellite), and the microwave terminal module 50 is also configured to receive the time delay information calculated by the second satellite, where the time delay information calculated by the first satellite is recorded as first time delay information, and the time delay information calculated by the second satellite is recorded as second time delay information. The first delay information of the present embodiment corresponds to the first delay Δt A' of the first embodiment, and the second delay information corresponds to the second delay Δt B'B of the first embodiment.
Further, the information processing module 60 is further configured to estimate, according to the time delay information received from the linear optical sampling system module 40, the first time delay information of the current satellite by using a kalman filter. Specifically, the information processing module 60 further estimates, by using a kalman filter, the time deviation of the optical frequency comb pulse propagating relative to the other satellite relative to the reference optical frequency comb pulse of the other satellite according to the optical pulse delay obtained by the linear optical sampling system module 40, and calculates the time delay information of the first satellite and the second satellite to the same time, and then calculates the distance between the two satellites. The microwave terminal module 50 is specifically configured to send the first delay information to the opposite star and receive the second delay information sent by the opposite star.
Further, the path propagation delay is calculated based on the following formula:
ΔTAB＝(ΔTA+ΔTB)/2;
Wherein Δt AB is a path propagation delay, Δt A is a first target delay, Δt B is a second target delay;
the inter-satellite distance between the current satellite and the relative other satellite is calculated based on the following formula:
LAB＝(ΔTA+ΔTB)/2*c;
Wherein L AB is the inter-satellite distance, and c is the speed of light.
An example of a specific application of the optical frequency comb-based inter-satellite high accuracy distance measurement system 100 will be described below.
Referring to fig. 3 to 4, in an application example, a first satellite is a satellite a, a second satellite is a satellite B, and both the satellite a and the satellite B are configured with the inter-satellite high-precision distance measurement system 100 based on optical frequency combs according to the above embodiment, the following distance measurement manner is performed between the satellite a and the satellite B:
1. The satellite-borne atomic clock modules of the satellite A and the satellite B generate stable frequency sources, and provide accurate frequency base references for optical frequency comb locking.
2. The optical frequency comb module of the satellite B is locked to the satellite-borne atomic clock module of the satellite B, and a propagation optical frequency comb signal X B with the phase of pi/6 is generated at the time t 1 according to a control command.
3. The optical transmission system module of satellite B transmits the propagated optical frequency comb signal X B.
4. The optical frequency comb module of the satellite A is locked to the satellite-borne atomic clock module of the satellite A, and a reference optical frequency comb signal X AL is generated according to a control command.
5. After the linear optical sampling system module of the satellite A receives the propagation optical frequency comb signal X B of the satellite B when the clock face of the linear optical sampling system module is t 2, the propagation optical frequency comb signal X B of the satellite B interferes with the reference optical frequency comb signal X AL of the satellite A in a 50:50 optical fiber beam splitter, the interfered signals enter a balance detector, the direct current component of the signals is filtered by the balance detector, the obtained alternating current signals are converted into voltages and amplified and then enter a low-pass filter, finally, the ADC (analog-to-digital converter) quantifies and collects the signals, and the time delay between the broadcasting optical frequency comb signal X B of the satellite B and the reference optical frequency comb signal X AL of the satellite A is calculated
6. The information processing module of the satellite A receives the optical pulse time delay obtained by the linear optical sampling system moduleThe accurate time offset deltat' A is further estimated using a kalman filter.
7. The microwave terminal module of satellite a transmits the time T 2 and the corresponding time offset Δt' A to satellite B.
8. The optical frequency comb module of the satellite A is locked to the satellite-borne atomic clock module of the satellite A, and a propagation optical frequency comb signal X A with the phase of pi/3 is generated at the time t 3 according to a control command.
9. The optical transmission system module of satellite a transmits the propagating optical frequency comb signal X A to satellite B.
10. The optical frequency comb module of the satellite B is locked to the satellite-borne atomic clock module of the satellite B, and a reference optical frequency comb signal X BL is generated according to a control command.
11. After the linear optical sampling system module of the satellite B receives the satellite A propagation optical frequency comb signal X A at the clock face t 4, the satellite A propagation optical frequency comb signal X A interferes with the satellite B reference optical frequency comb signal X BL in a 50:50 optical fiber beam splitter, the interfered signals enter a balance detector, the direct current component of the signals is filtered by the balance detector, the obtained alternating current signals are converted into voltages and amplified and then enter a low-pass filter, finally, the ADC quantifies and collects the signals, and the time delay between the satellite A propagation optical frequency comb signal X A and the satellite B reference optical frequency comb signal X BL is calculated
12. The information processing module of the satellite B receives the optical pulse time delay obtained by the linear optical sampling system moduleThe accurate time offset deltat' B is further estimated using a kalman filter.
13. The microwave terminal module of satellite B transmits time T 4 and the corresponding time offset Δt 'B to satellite a and receives time T 2 and the corresponding time offset Δt' A transmitted by the microwave terminal module of satellite a.
14. The information processing module of the satellite B calculates the delta T 'B of the satellite B clock face time T 4 and the delta T' A of the satellite A clock face time T 2 to the same time to obtain delta T A and delta T B of the same time, and then calculates the inter-satellite absolute distance of the satellite A and the satellite B according to the formula L AB＝(ΔTA+ΔTB)/2*c.
15. The microwave terminal module of satellite a receives the time T 4 of the transmission of the microwave terminal module of satellite B and the corresponding time offset Δt' B.
16. The information processing module of the satellite A calculates delta T 'A of the clock face time T 2 of the satellite A and delta T' B of the clock face time T 4 of the satellite B to the same time to obtain delta T A and delta T B of the same time, and then calculates the inter-satellite absolute distance of the satellite A and the satellite B according to the formula L AB＝(ΔTA+ΔTB)/2*c.
In summary, the inter-satellite high-precision distance measurement method and system based on the optical frequency comb provided by the invention adopt the optical frequency comb signal with controllable time and initial phase as the measurement signal, avoid the problem of distance ambiguity in the traditional optical frequency comb signal measurement technology, so that the inter-satellite long-distance absolute distance measurement can be realized, and simultaneously, the time delay of the optical frequency comb signal transmitted by the other satellite and the reference optical frequency comb signal is obtained by controlling the time and the phase of the reference optical frequency comb signal and utilizing the linear optical sampling technology, so that the requirement on the transmitting power of the optical frequency comb signal transmitted by the other satellite is lower, the sensitivity of the satellite on the optical frequency comb signal processing is improved, and the range finding action distance of the optical frequency comb is expanded.
It should be noted that the present application may be implemented in software and/or a combination of software and hardware, e.g., using Application Specific Integrated Circuits (ASIC), a general purpose computer or any other similar hardware device. In one embodiment, the software program of the present application may be executed by a processor to perform the above steps or functions. Likewise, the software programs of the present application (including associated data structures) may be stored on a computer readable recording medium, such as RAM memory, magnetic or optical drive or diskette and the like. In addition, some steps or functions of the present application may be implemented in hardware, for example, as circuitry that cooperates with the processor to perform various steps or functions.
The method according to the invention may be implemented as a computer implemented method on a computer, or in dedicated hardware, or in a combination of both. Executable code or parts thereof for the method according to the invention may be stored on a computer program product. Examples of computer program products include memory devices, optical storage devices, integrated circuits, servers, online software, and the like. Preferably, the computer program product comprises non-transitory program code means stored on a computer readable medium for performing the method according to the invention when said program product is executed on a computer.
Of course, the present invention is capable of other various embodiments and its several details are capable of modification and variation in light of the present invention, as will be apparent to those skilled in the art, without departing from the spirit and scope of the invention as defined in the appended claims.
Claims (10)
1. The inter-satellite high-precision distance measurement method based on the optical frequency comb is characterized by being applied to distance measurement between a first satellite and a second satellite and comprising the following steps of:
The first satellite receives a first optical frequency comb signal transmitted by the second satellite when the first satellite receives a clock face, obtains a first transmitting clock face of the second satellite by tracking the phase of the received first optical frequency comb signal, and calculates a first time delay of the first satellite based on the first receiving clock face and the first transmitting clock face;
The second satellite receives a second optical frequency comb signal transmitted by the first satellite when receiving the clock face of the second satellite, obtains a second transmitting clock face of the first satellite by tracking the phase of the received second optical frequency comb signal, and calculates a second time delay of the second satellite based on the second receiving clock face and the second transmitting clock face;
The first time delay and the second time delay are calculated to an intermediate epoch, and a first target time delay and a second target time delay at the same moment are obtained;
And calculating path propagation delay between the first satellite and the second satellite according to the first target delay and the second target delay, and calculating the inter-satellite distance between the first satellite and the second satellite based on the path propagation delay.
2. The optical frequency comb-based inter-satellite high-precision distance measurement method according to claim 1, wherein the path propagation delay is calculated based on the following formula:
ΔTAB＝(ΔTA+ΔTB)/2;
Wherein Δt AB is the path propagation delay, Δt A is the first target delay, and Δt B is the second target delay.
3. The optical frequency comb-based inter-satellite high-precision distance measurement method according to claim 2, wherein the inter-satellite distance between the first satellite and the second satellite is calculated based on the following formula:
LAB＝(ΔTA+ΔTB)/2*c;
Wherein L AB is the inter-satellite distance, and c is the speed of light.
4. The optical frequency comb-based inter-satellite high-precision distance measurement method according to claim 1, wherein the first time delay is a difference between the first receiving clock face and the first transmitting clock face, and the second time delay is a difference between the second receiving clock face and the second transmitting clock face.
5. An inter-satellite high-precision distance measurement system based on an optical frequency comb, which is configured in a first satellite and a second satellite which relatively perform inter-satellite distance measurement, and comprises:
the satellite-borne atomic clock module is used for generating a stable frequency source to provide a frequency reference for locking an optical frequency comb;
the optical frequency comb module is used for generating an optical frequency comb signal with a specified initial phase at a specified time according to a control instruction, wherein the optical frequency comb signal comprises a propagation optical frequency comb used as a measurement signal and a reference optical frequency comb used as a tracking signal;
The optical transmission system module is used for transmitting the signals of the propagation optical frequency comb to a relative satellite, receiving the relative propagation optical frequency comb from the relative satellite and transmitting the signals of the relative propagation optical frequency comb and the reference optical frequency comb to the linear optical sampling system module, wherein the relative satellite is a satellite for performing inter-satellite distance measurement with a current satellite;
The linear optical sampling system module is used for calculating time delay information between the relative propagation optical frequency comb and the reference optical frequency comb;
the microwave terminal module is used for interacting the time delay information measured by the current satellite and the relative satellite respectively;
The information processing module is used for calculating the first time delay information of the current satellite and the second time delay information of the relative star to an intermediate epoch to obtain a first target time delay and a second target time delay at the same moment, calculating the path propagation time delay between the current satellite and the relative star according to the first target time delay and the second target time delay, and calculating the inter-satellite distance between the current satellite and the relative star based on the path propagation time delay.
6. The optical frequency comb-based inter-satellite high-precision distance measurement system according to claim 5, wherein the optical transmission system module is specifically configured to:
And transmitting the signals generated by the propagation optical frequency comb to the opposite star through a laser receiving and transmitting channel, receiving the opposite propagation optical frequency comb transmitted by the opposite star through the laser receiving and transmitting the signals of the opposite propagation optical frequency comb and the reference optical frequency comb to the linear optical sampling system module.
7. The optical frequency comb-based inter-satellite high-precision distance measurement system according to claim 5, wherein the linear optical sampling system module is specifically configured to:
Interfering the counter-propagating optical frequency comb and the reference optical frequency comb in a 50% splitting ratio fiber optic splitter;
inputting the interfered signals into a balance detector to filter direct current components in the signals so as to obtain alternating current signals;
And converting the alternating current signal into a voltage signal, amplifying the voltage signal, inputting the voltage signal into a low-pass filter, and performing quantitative acquisition through an analog-to-digital converter to obtain time delay information between the opposite propagation optical frequency comb and the reference optical frequency comb.
8. The optical frequency comb based inter-satellite high accuracy distance measurement system of claim 5, wherein the information processing module is further configured to estimate the first time delay information of the current satellite using a kalman filter based on the time delay information received from the linear optical sampling system module.
9. The optical frequency comb-based inter-satellite high-precision distance measurement system according to claim 5, wherein the microwave terminal module is specifically configured to transmit the first delay information to the opposite satellite and receive the second delay information transmitted by the opposite satellite.
10. The optical frequency comb-based inter-satellite high-precision distance measurement system according to any one of claims 5 to 9, wherein the path propagation delay is calculated based on the following formula:
ΔTAB＝(ΔTA+ΔTB)/2;
Wherein Δt AB is the path propagation delay, Δt A is the first target delay, and Δt B is the second target delay;
The inter-satellite distance between the current satellite and the relative other satellite is calculated based on the following formula:
LAB＝(ΔTA+ΔTB)/2*c;
Wherein L AB is the inter-satellite distance, and c is the speed of light.
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