阅读说明：本技术 一种基于同频模式的高精度星地时间比对方法及系统 (High-precision satellite-ground time comparison method and system based on same frequency mode ) 是由 郭燕铭 张首刚 卢晓春 高帅和 白燕 潘志兵 高玉平 于 2021-05-21 设计创作，主要内容包括：本发明提供了一种基于同频模式的高精度星地时间比对方法及系统,地面站和航天器分别向对方发射同一频点的微波测距信号,获得下行观测伪距和上行观测伪距；将下行伪距和上行伪距配对组成双向单程测量伪距组合,计算获得地面站和空间航天器时频设备之间的星地双向相对钟差；计算并扣除双向相对钟差计算时的各项误差,实现星地时间同步；所述的各项误差包括设备时延误差、运动时延误差、周期性相对论效应误差和引力时延误差。本发明通过空地双向测量微波链路同频模式有效修正和减小电离层和对流层等误差,实现空间航天器与地面站之间的高精度时间比对,最终实现ps量级的星地时间比对精度。(The invention provides a high-precision satellite-ground time comparison method and system based on a same frequency mode.A ground station and a spacecraft respectively transmit microwave ranging signals of the same frequency point to each other to obtain a downlink observation pseudo range and an uplink observation pseudo range; pairing the downlink pseudo range and the uplink pseudo range to form a bidirectional one-way measurement pseudo range combination, and calculating to obtain a satellite-ground bidirectional relative clock error between the ground station and the space spacecraft time-frequency equipment; calculating and deducting various errors in the calculation of the bidirectional relative clock error to realize satellite-ground time synchronization; the errors comprise equipment time delay errors, motion time delay errors, periodic relativistic effect errors and gravitational time delay errors. The invention effectively corrects and reduces errors of an ionized layer, a troposphere and the like through an air-ground bidirectional measurement microwave link common-frequency mode, realizes high-precision time comparison between a space spacecraft and a ground station, and finally realizes ps-magnitude satellite-ground time comparison precision.)

1. A high-precision satellite-ground time comparison method based on a same frequency mode is characterized by comprising the following steps:

step 1, the ground station and the spacecraft respectively transmit the same frequency point f to each other₁Obtaining f from the microwave ranging signal₁Downlink observation pseudo range and uplink observation pseudo range of the frequency point;

step 2, mixing f₁Pairing the frequency point downlink pseudo range and the uplink pseudo range to form a bidirectional one-way measurement pseudo range combination, and calculating to obtain a satellite-ground bidirectional relative clock error between the ground station and the space spacecraft time-frequency equipment;

step 3, calculating and deducting various errors in the calculation of the bidirectional relative clock error to realize satellite-ground time synchronization; the errors comprise equipment time delay errors, motion time delay errors, periodic relativistic effect errors and gravitational time delay errors.

2. The method according to claim 1, wherein the two-way single-pass measurement pseudorange combination is a combination of two one-way measurements received or transmitted by the ground station and the space vehicle at the same time.

3. The same-frequency-mode-based high-precision satellite-ground time comparison method according to claim 1, wherein the measured distances of the pseudo ranges all adopt phase centers, and the precision orbit determination processing results are respectively corrected to the coordinate values of the phase centers of the receiving antenna and the transmitting antenna of the spacecraft by using the phase center result calibrated in advance.

4. The same-frequency-mode-based high-precision satellite-ground time comparison method according to claim 1, wherein the spacecraft adopts different microwave time-frequency antennas A and B for transmitting and receiving signals to ground, and under the same-frequency mode, the two-way one-way measurement pseudo-range combination is expressed as

Wherein G represents a ground station, S represents a spacecraft, c is a vacuum light velocity, t^SndAnd t^RcvRespectively the moment of transmission and the moment of reception,andare respectively f₁Downlink measurement pseudo range and f of frequency point₁Measuring an uplink pseudo range of the frequency point; r_AAnd R_BPhase center position vectors, x, for spacecraft antennas A and B, respectively_SAnd x_GRespectively, the clock error of the spacecraft and the ground station, delta^SndAnd delta^RcvFor hardware transmission delay, delta, of signal transmitting and receiving channels^relIs a periodic phaseEquivalent time delay to theoretical effect, delta^OFFor phase centre shift equivalent delay, delta^gIs the gravitation time delay, and epsilon is the ranging noise.

5. The method according to claim 1, wherein in step 2, if the clock difference between the ground station and the spacecraft is Δ t, then t is t₀Relative clock error between space spacecraft and ground station at timeWhere Δ d is the correction amount of error due to spatial distance inconsistency, dx (t, t)₀) From time t to t₀Correction of non-simultaneous clock error, dx, of time_GAnd dx_SRespectively representing clock error non-simultaneous error correction of the ground station G and the spacecraft S.

6. The method according to claim 1, wherein the motion delay error utilizes a precise ephemeris and a precise clock error file to perform time scale reduction and motion delay error correction on the same-frequency bidirectional one-way observation pseudoranges at different times and at different antenna positions, and distance compensationClock error compensation

7. The same frequency mode-based high-precision satellite-to-ground time comparison method according to claim 1, wherein the periodic relativistic effect error isWherein, W₀Is the gravitational potential on the earth's horizon; GM is an earth gravity constant; a is a semi-major axis for the operation of the space spacecraft; r is groundDisturbance of spherical non-spherical gravitational potential; r is the geocentric distance of the atomic clock; tau is the atomic clock time.

8. The same-frequency-mode-based high-precision satellite-ground time comparison method according to claim 1, wherein the gravitational time delay error isWhere ρ is_GAnd ρ_SThe distances from the ground survey station G and the spacecraft S to the geocentric,the distance of the ground station G to the spacecraft S.

9. A high-precision satellite-ground time comparison system based on the same frequency mode according to the method of claim 1, comprising ground equipment and satellite-borne equipment, and is characterized in that the frequency point f is transmitted from the ground equipment to the satellite-borne equipment of the space spacecraft₁And receiving the frequency point f emitted by the space spacecraft satellite-borne equipment₁The microwave signal of (2); the satellite-borne equipment receives the frequency point f transmitted by the ground equipment₁And transmitting the microwave signal to the ground at a frequency point f₁The microwave signal of (2).

Technical Field

The invention belongs to the technical field of space time-frequency transmission, and particularly relates to a satellite-ground bidirectional time comparison method and system.

Background

The conventional long-distance time transmission method comprises laser time comparison, bidirectional time comparison, common vision method and the like, is limited by the precision of an atomic clock and the level of hardware, and the highest precision can only reach a sub-ns order, so that the wide application of the high-precision time-frequency reference in space science is limited. The method is characterized in that an atomic clock or an atomic clock group with different characteristics is carried and operated on a space spacecraft by utilizing environmental advantages such as earth space microgravity, low interference and the like, a time frequency signal source with higher precision by more than one magnitude than the ground is realized, and a space high-precision time frequency generating and operating system (space precision time frequency reference for short) with better stability and uncertainty than 1E-17 magnitude is established in space. After the space precision time-frequency standard is built, the first task is to accurately evaluate the time-frequency performance of the space precision time-frequency standard, and then the space precision time-frequency standard can be further utilized to realize high-precision time transmission, so that the high-precision time requirements of various space vehicles and ground users are met.

Disclosure of Invention

In order to overcome the defects of the prior art, the invention provides a high-precision satellite-ground time comparison system which is based on a microwave link common-frequency mode, effectively corrects and reduces errors such as an ionized layer, a troposphere and the like through an air-ground bidirectional measurement microwave link common-frequency mode, realizes high-precision time comparison between a space spacecraft and a ground station, and finally realizes the satellite-ground time comparison precision of ps magnitude.

The technical scheme adopted by the invention for solving the technical problems is as follows: a high-precision satellite-ground two-way time comparison method based on a same frequency mode comprises the following steps:

step 1, the ground station and the spacecraft respectively transmit the same frequency point f to each other₁Obtaining f from the microwave ranging signal₁Downlink observation pseudo range and uplink observation pseudo range of the frequency point;

step 2, mixing f₁Pairing the frequency point downlink pseudo range and the uplink pseudo range to form a bidirectional one-way measurement pseudo range combination, and calculating to obtain a satellite-ground bidirectional relative clock error between the ground station and the space spacecraft time-frequency equipment;

step 3, calculating and deducting various errors in the calculation of the bidirectional relative clock error to realize satellite-ground time synchronization; the errors comprise equipment time delay errors, motion time delay errors, periodic relativistic effect errors and gravitational time delay errors.

The bidirectional one-way measurement pseudo range combination is a combination of two one-way measurements which are simultaneously received or transmitted by the ground station and the space spacecraft.

And the measured distances of the pseudo ranges all adopt phase centers, and the precision orbit determination processing results are respectively corrected to the coordinate values of the phase centers of the receiving antenna and the transmitting antenna of the spacecraft by utilizing the phase center result calibrated in advance.

The spacecraft adopts different microwave time-frequency antennas A and B to transmit and receive signals to the ground, and under the same frequency mode, the pseudo-range combination of two-way one-way measurement is expressed as

Wherein G represents a ground station, S represents a spacecraft, c is a vacuum light velocity, t^SndAnd t^RcvRespectively the moment of transmission and the moment of reception,andare respectively f₁Downlink measurement pseudo range and f of frequency point₁Measuring an uplink pseudo range of the frequency point; r_AAnd R_BPhase center position vectors, x, for spacecraft antennas A and B, respectively_SAnd x_GRespectively, the clock error of the spacecraft and the ground station, delta^SndAnd delta^RcvFor hardware transmission delay, delta, of signal transmitting and receiving channels^relEquivalent time delay for periodic relativistic effect，δ^OFFor phase centre shift equivalent delay, delta^gIs the gravitation time delay, and epsilon is the ranging noise.

In the step 2, assuming that the clock difference between the ground station and the spacecraft is Δ t, t is₀Relative clock error between space spacecraft and ground station at time

Where Δ d is the correction amount of error due to spatial distance inconsistency, dx (t, t)₀) From time t to t₀Correction of non-simultaneous clock error, dx, of time_GAnd dx_SRespectively representing clock error non-simultaneous error correction of the ground station G and the spacecraft S.

The motion delay error utilizes a precise ephemeris and a precise clock error file to carry out time scale reduction and motion delay error correction on the same-frequency bidirectional one-way observation pseudo-range at different moments and antenna positions,

distance compensation

Clock error compensation

Said periodic relativistic effect errorWherein, W₀Is the gravitational potential on the earth's horizon; GM is an earth gravity constant; a is a semi-major axis for the operation of the space spacecraft; r is the disturbance of the non-spherical gravitational potential of the earth; r is the geocentric distance of the atomic clock; tau is the atomic clock time.

The gravity time delay errorWhere ρ is_GAnd ρ_SGround survey station G and spacecraft S toThe distance between the earth centers of the two adjacent earth centers,the distance of the ground station G to the spacecraft S.

The invention also provides a high-precision satellite-ground two-way time comparison system based on the same frequency mode for realizing the method, which comprises ground equipment and satellite-borne equipment, wherein the ground equipment transmits a frequency point f to the satellite-borne equipment of the space spacecraft₁And receiving the frequency point f emitted by the space spacecraft satellite-borne equipment₁The microwave signal of (2); the satellite-borne equipment receives the frequency point f transmitted by the ground equipment₁And transmitting the microwave signal to the ground at a frequency point f₁The microwave signal of (2).

The invention has the beneficial effects that: at present, time synchronization is carried out between a Beidou system satellite-borne device carrying a hydrogen clock or a rubidium clock and other devices carrying high-precision atomic clocks, and the traditional microwave time synchronization method is mainly divided into a one-way time synchronization method and a two-way time synchronization method, wherein the time synchronization is carried out by four or more satellites due to signal one-way propagation of the traditional one-way time synchronization method, so that motion time delay errors (including space distance inconsistency errors and clock difference non-simultaneous errors) do not exist, and after errors generated in the signal one-way propagation process are eliminated item by item, ns-level time synchronization accuracy can be finally realized; while a part of errors can be counteracted by bidirectional difference of the traditional bidirectional time synchronization method, but motion delay errors (including inconsistent spatial distance errors and clock difference non-simultaneous errors) cannot be eliminated accurately, the influence of the motion delay errors is eliminated by generally utilizing a broadcast ephemeris (position precision m grade, speed precision cm/s grade) or a precise ephemeris (position precision cm grade, speed precision mm/s grade) in combination with a motion delay error elimination model, the motion delay error correction precision superior to a sub-ns grade can be achieved, and finally, the time synchronization precision of the sub-ns grade is realized. The invention provides a high-precision satellite-ground two-way time comparison system based on a same frequency mode and a specific implementation method, wherein the scheme adopts a double-antenna single-frequency (-20 GHz-40GHz) simultaneous transmitting or simultaneous receiving mode (a satellite-borne equipment transmitting antenna and a ground station transmitting antenna are in the same one and the same one are adopted in a traditional time synchronization scheme, the scheme adopts a single-antenna single-frequency (-23 GHz, Ka frequency band) Time Division Multiple Access (TDMA) mode (a single-antenna transmitting and receiving time of satellite-borne equipment has a certain time slot) to carry out two-way signal receiving and transmitting and receiving, partial errors are eliminated through two-way offset, and the sub-nanosecond-magnitude two-way time synchronization precision can be achieved, along with the improvement of the precision of the satellite-borne atomic clock on-board and the traditional methods can not meet the requirements of space-based on-high precision time evaluation and the time of space-borne equipment and the corresponding equipment hardware level The invention provides a method for transmitting and receiving signals simultaneously in a clock face or simultaneously receiving signals by a receiving antenna of satellite-borne equipment and a receiving antenna of a ground station in the same clock face), the invention provides a method for receiving and transmitting signals of the same frequency by using two different antennas (the distance between the bottoms of the two antennas is more than 5cm) of the satellite-borne equipment, on the basis, a motion delay error model suitable for the two antennas provided by the invention is further utilized to eliminate motion delay errors (including space distance inconsistency errors and clock difference non-concurrency errors) caused by satellite motion by combining a precise ephemeris (the position precision is superior to 10cm grade and the speed precision is superior to 1mm/s grade), and finally, after the distance measurement information and other errors (periodic relativistic errors, gravitational delay errors and equipment delay errors) of the same frequency point are comprehensively processed, the invention provides a bidirectional time synchronization method of the same frequency mode, the requirement of ps-level satellite-ground high-precision time comparison can be met.

Drawings

FIG. 1 is a structural diagram of a high-precision satellite-ground two-way time comparison system based on a same frequency mode according to the present invention;

FIG. 2 is a schematic diagram of the installation position of the same-frequency mode satellite-borne equipment of the invention;

FIG. 3 is a flow chart of the present invention based on the same frequency mode high precision bidirectional time synchronization scheme;

FIG. 4 is a two-way single-pass measurement of the present invention based on a common frequency mode;

FIG. 5 is a schematic diagram of high-precision satellite-ground two-way time comparison based on the same frequency mode according to the present invention;

FIG. 6 is a flow chart of a motion delay error correction scheme in a high-precision satellite-ground bidirectional time alignment based on a same frequency mode.

Detailed Description

The present invention will be further described with reference to the following drawings and examples, which include, but are not limited to, the following examples.

Aiming at the problem of time comparison between a space spacecraft carrying an ultra-high-precision atomic clock group (generally better than [email protected]) and a ground station, in order to obtain higher time comparison precision, a more stable measurement link and a support of a high-precision satellite-ground time comparison system and method are needed. The invention aims to provide a high-precision satellite-ground bidirectional time comparison system and method based on a same frequency mode.

The invention relates to a high-precision satellite-ground two-way time comparison system based on a same frequency mode, which comprises:

and (4) ground equipment. The frequency point of the emission to the space-borne equipment of the space spacecraft is f₁And receiving the frequency point f emitted by the space spacecraft satellite-borne equipment₁A microwave signal.

Satellite-borne equipment. The frequency point of receiving the emission of the ground equipment is f₁And transmitting the microwave signal to the ground at a frequency point f₁The microwave signal of (2).

In the high-precision satellite-ground bidirectional time comparison system based on the same frequency mode, the ground equipment comprises:

generating said f₁Ground microwave time-frequency load of the frequency point microwave signal;

the microwave time-frequency transmission ground antenna is connected with the ground microwave time-frequency load, and is used for transmitting the microwave signals to the space spacecraft on one hand and receiving the microwave signals of different frequency bands transmitted from the space spacecraft on the other hand;

the ground data transmission system receives pseudo-range observation data downloaded by the microwave ranging signal;

and the satellite-ground time-frequency link control center is connected with the ground data transmission system and used for calculating the relative clock error of the space spacecraft clock and the ground station clock.

In the high-precision satellite-ground bidirectional time comparison system based on the same frequency mode, the satellite-borne device includes:

generating said f₁Space time-frequency load of the frequency point microwave signal;

the microwave time-frequency transmission ground antenna A is connected with the space microwave time-frequency load and transmits the microwave signal to a ground station;

the microwave time-frequency transmission ground antenna B is connected with the space microwave time-frequency load and receives the microwave signals of different frequency bands transmitted from the ground station;

and the precise orbit determination receiver is connected with the space microwave time-frequency load, receives signals from a satellite and performs orbit determination on the space spacecraft.

And the space data transmission system transmits the observation data, the orbit data, the clock error data and the like downloaded by the microwave ranging signal to the ground.

The invention relates to a high-precision satellite-ground two-way time comparison method based on a same frequency mode, which is characterized by comprising the following steps:

step 1, implementing pseudo-range measurement between the ground station and the space spacecraft by the ground equipment time-frequency transmission antenna of the time comparison system, the transmitting antenna A of the space spacecraft space-borne equipment and the microwave ranging signals respectively transmitting the same frequency point to each other, and obtaining f₁And the downlink observation pseudo range and the uplink observation pseudo range of the frequency point.

Step 2, f obtained in step 1 is used₁And pairing the downlink pseudo range and the uplink pseudo range of the frequency point to form a bidirectional one-way measurement pseudo range combination, and then calculating to obtain the satellite-to-ground bidirectional relative clock error between the ground station and the time frequency equipment of the space spacecraft.

Step 3, calculating and deducting various errors in the calculation of the bidirectional relative clock error, and realizing satellite-ground high-precision time synchronization; wherein each error includes: device delay errors, motion delay errors (spatial distance asymmetry errors and clock error non-simultaneous errors), periodic relativistic effect errors, and gravitational delay errors.

The invention has the further improvement that the step 1 specifically comprises the following steps:

in the process of one-time measurement in the same frequency mode, distance measurement signals are mutually sent out by a ground station and a space spacecraft for measurement of the other party, then measurement data are exchanged, and resolving and pairing are carried out, so that a bidirectional one-way measurement pseudo-range combination is obtained;

the bidirectional one-way measurement pseudo range combination is a combination of two one-way measurements which are transmitted or received by the ground station and the space spacecraft at the same time;

the invention has the further improvement that because the frequency point and the path of the uplink pseudo-range and the downlink pseudo-range are almost consistent, the bidirectional time synchronization method can eliminate most atmospheric time delay errors, so atmospheric time delay error correction can be omitted.

The invention has the further improvement that as the precise orbit determination process estimates the centroid position of the space spacecraft, the precise orbit of the used space spacecraft is also the centroid orbit, and the pseudo-range phase measurement distances of the space spacecraft are all phase centers, the centroid coordinate of the space station needs to be corrected in phase center during data processing, the precise orbit determination process result is respectively corrected to the phase center coordinate values of the antennas A and B by utilizing the phase center result calibrated in advance, and the expression is as follows:

wherein R is_SIs the centroid coordinate of the space spacecraft, R_AAnd R_BPhase center position vectors, F, for space station to ground antennas A and B, respectively₁And F₂Respectively represent the transformation expression of the spacecraft centroid correction to the earth antenna phase center A and B.

The further improvement of the invention is that in step 1, the two parties performing time comparison are respectively a ground station G and a space spacecraft S, and in order to reduce the same frequency interference of receiving and transmitting signals, the space spacecraft S adopts different microwave time-frequency antennas A and B to receive and transmit signals to the ground, so that under the same frequency mode, the bidirectional one-way measurement pseudo range combination is expressed as:

in the formula (1), c is the vacuum light velocity, t^SndAnd t^RcvRespectively the moment of transmission and the moment of reception,andare respectively f₁Measuring pseudo range and f in downlink of frequency point (AG represents propagation path, satellite-borne equipment antenna A transmits signal, and ground station G receives signal)₁Measuring pseudo range of uplink (GB represents a propagation path, a ground station G transmits signals, and a satellite-borne equipment antenna B receives signals) of a frequency point; r_AAnd R_BPhase center position vectors, x, for space spacecraft ground antennas A and B, respectively_SAnd x_GRespectively, the clock error of the space spacecraft and the ground station, delta^SndAnd delta^RcvFor hardware transmission delay, delta, of signal transmitting and receiving channels^relEquivalent time delay for periodic relativistic effects, delta^OFFor phase centre shift equivalent delay, delta^gIs the gravitation time delay, and epsilon is the ranging noise.

The invention has the further improvement that in the step 2, two parties for realizing the satellite-ground bidirectional time synchronization are a ground station G and a space spacecraft S respectively, because the phase centers of the uplink and downlink signal transceiving antennas of the space spacecraft S are not consistent, the space transmission delay of signals and the high-speed motion of satellites are realized, the satellite-ground bidirectional pseudo-range measured value contains the satellite position and clock difference information at different moments, and therefore, the time-space information contained in the bidirectional pseudo-range needs to be reduced to the same moment t₀. Assuming that the clock difference between the ground station and the space vehicle is Δ t, t₀Relative clock error table of space spacecraft and ground station at momentThe expression is as follows:

in the formula (2), Δ d is a correction amount of error due to spatial distance inconsistency, dx (t, t)₀) From time t to t₀The clock difference at the time is not a simultaneous error correction. The bidirectional space distance correction caused by the asymmetry of the space distance is calculated by a precise orbit of the space spacecraft, the clock error correction caused by the clock error non-simultaneously is calculated by a forecast clock error of the space spacecraft, the hardware transmission delay is calibrated periodically, and the atmospheric delay, the periodic relativistic effect, the gravity delay and the phase center offset can be calculated by relying on a mathematical model.

The invention is further improved in that the time delay error of the equipment is compensated by a precise calibration method.

The invention is further improved in that the uplink and downlink signal propagation paths and clock differences are not consistent due to high-speed relative motion between the space vehicle and the ground station, so that the motion delay error needs to be compensated, and the compensation method comprises the following steps: by using a precise ephemeris (the position precision of the spacecraft is better than 10cm, the speed precision is better than 1mm/s) and a precise clock error file, time scale reduction and motion delay error correction are carried out on the same-frequency bidirectional one-way observation pseudo-range at different moments and antenna positions, and the distance compensation and the clock error compensation are respectively calculated as the following formulas (3) and (4):

a further improvement of the invention is that the relativistic effects on the atomic clocks on board the spacecraft include nominal frequency deviation (NFO) which can be eliminated by advance calibration before the spacecraft is on the sky, and periodic relativistic effects which can be taken advantage ofAnd (4) eliminating by using a model. Because the periodic relativistic effect in the satellite-ground bidirectional time comparison pair does not have path symmetry, ephemeris is required to be relied on for compensation, and the compensation error is finally and directly transmitted to the time comparison result, J is required to be fully considered when ps-level time precision is considered₂The influence of periodic relativistic errors of terms and higher-order terms is that for the periodic relativistic correction model between the space spacecraft and the ground station:

wherein, W₀＝6.969290134×10^-10·c²Is the gravitational potential on the earth's horizon; GM is an earth gravity constant; a is a semi-major axis for the operation of the space spacecraft; r is the disturbance of the non-spherical gravitational potential of the earth; r is the geocentric distance of the atomic clock; tau is the atomic clock time.

A further improvement of the invention consists in the elimination of the geometrical and gravitational delays in the transmission of the signal from the space vehicle to the ground station receiver, due to the effect of the generalized relativistic effect. Since the ground station and space spacecraft coordinate systems are both earth-Centered Inertial Systems (ECIs), the disparity in the two-way geometric transmission delay can be ignored. However, under the picosecond-level time transfer accuracy, the gravity time delay caused by the gravity of the earth center needs to be considered, and the modified model is as follows:

where ρ is_GAnd ρ_SThe distances from the ground survey station G and the spacecraft S to the geocentric,for the distance of the ground stations G to the geocentric of the spacecraft S, the effect of autorotation of the earth can be ignored under ECI, but is taken into account if in the geocentric geostationary system.

The invention is further improved in that after time scale reduction and various error corrections are carried out by the combined formula (2), the relative clock error delta t can be calculated by using the bidirectional one-way observation data at the same reference time.

The invention is further improved in that the satellite-ground time synchronization precision can reach ps level.

The embodiment of the invention provides a high-precision satellite-ground bidirectional time comparison system based on a same frequency mode, and please refer to fig. 1. Please refer to fig. 2 for the installation position of the satellite-borne device in the same frequency mode.

The invention relates to a high-precision satellite-ground bidirectional time comparison method based on a same frequency mode, which mainly comprises bidirectional one-way pseudo range differential resolving clock error and motion delay error correction, and specifically comprises the following steps:

(1) through f₁Referring to fig. 5, in a one-time measurement process of the two-way one-way measurement, distance measurement signals are mutually sent by the space spacecraft and the ground station to be measured by the other party, then measurement data are exchanged, calculation is performed, and pairing is performed, so that a relative measurement value is obtained.

In fig. 5, the two parties that need to realize time synchronization are a space spacecraft S and a ground station G, respectively, and a ground antenna a of the space spacecraft S is located atThe moment transmitting frequency point is f₁The microwave signal of (1) is finally transmitted at the ground station G after the time delay of the space spacecraft S transmitting device, the time delay of space propagation, other additional time delays and the device time delay of the ground station receiving deviceThe time is detected to obtain a signal downlink pseudo-range observed valueSimilarly, the ground station G isThe moment transmitting frequency point is f₁Of the space vehicle S, the ground antenna B of the space vehicle SThe signal is detected at the moment to obtain a signal uplink pseudo-range observed valueThen the one-time two-way one-way pseudorange observation equation is:

wherein c is the vacuum light velocity t^SndAnd t^RcvRespectively the moment of transmission and the moment of reception,andare respectively f₁Downlink measurement pseudo range and f of frequency point₁Measuring an uplink pseudo range of the frequency point; r_AAnd R_BPhase center position vectors, x, of space station to ground antennas A and B, respectively, in the Earth's centroid inertial System_SAnd x_GRespectively, the clock error of the space station and the ground station, delta^SndAnd delta^RcvFor hardware transmission delay, delta, of signal transmitting and receiving channels^relEquivalent time delay for periodic relativistic effects, delta^OFFor phase centre shift equivalent delay, delta^gIs the gravitation time delay, and epsilon is the ranging noise.

(2) Computing relative clock error between space spacecraft and ground station using bidirectional one-way observed pseudoranges

Reducing the spatio-temporal information contained in the bi-directional pseudoranges in equation (1) to the same time t₀Then, the difference of the reduced uplink pseudo-range and the reduced downlink pseudo-range can obtain the t of the space spacecraft and the ground station₀The relative clock difference value Δ t of the time is calculated as follows:

in the formula, Δ d is a correction amount of spatial distance inconsistency, dx (t, t)₀) From time t to t₀The clock difference at the time is not the simultaneous correction amount.

(3) Correcting motion delay error

In order to avoid co-channel signal interference, a fixed distance exists between the positions of an earth transmitting antenna A and an earth receiving antenna B of the satellite-borne equipment, which causes the increase of inconsistent errors of a signal propagation path and clock difference, and the influence of motion delay errors needs to be fully considered in order to meet the requirements of ps-level time synchronization precision.

For the correction of the motion delay error, a precise ephemeris (the precision of the spacecraft position is better than 10cm, the precision of the speed is better than 1mm/s) and a precise clock difference file are used for performing time scale reduction and motion delay error correction on the same-frequency bidirectional one-way observation pseudoranges at different moments and at different antenna positions, and the distance compensation calculation and the clock difference compensation calculation are respectively as the following formulas (3) and (4), and the specific flow refers to fig. 6.

(4) Deduct each item error (remove the motion time delay error), realize the ultra-high precision time synchronism

In order to improve the accuracy of time synchronization, each error term contained in equation (2) needs to be subtracted, and the subtraction methods of each error term are as follows:

1) delay error of equipment

Regardless of the path, the device delay error is only associated with a device zero value. For both known stabilization devices, this value will be a certain quantity, the influence of which can be reduced or eliminated by precise calibration.

2) Relativistic effect error

Due to the high-speed relative motion between the space vehicle and the ground station, the satellite-borne equipment is subjected to generalized relativity theory and narrow relativity theory to cause the deviation of the ranging signals in the propagation process, and therefore relativity error needs to be compensated.

For Nominal Frequency Offset (NFO), the method of calibration in advance can be used to eliminate it. Assuming the fundamental frequency of the satellite-borne atomic clock as f₀Then the frequency is adjusted to f:

wherein, W₀＝6.969290134×10^-10·c²Is the gravitational potential on the earth's horizon; GM is an earth gravity constant; a is a semi-major axis of the orbit of the space spacecraft; r is the disturbance of the non-spherical gravitational potential of the earth; r is the geocentric distance of the atomic clock; tau is the atomic clock time.

The periodic relativistic effect can be eliminated by adopting a model method, and the specific model is as follows:

periodic relativistic effect errors in the bidirectional time synchronization process can be eliminated through (2) and (6).

3) Gravitational delay

Under ps-level time synchronization precision, only gravity time delay caused by gravity of the earth center needs to be considered, and a compensation model for the error is as follows:

where ρ is_GAnd ρ_SThe distances from the ground survey station G and the spacecraft S to the geocentric,for the distance of the ground stations G to the geocentric of the spacecraft S, the effect of autorotation of the earth can be ignored under ECI, but is taken into account if in the geocentric geostationary system.

4) Other errors

Other errors such as hardware noise can be processed by the existing mature hardware scheme or algorithm, and are not introduced as the key content of the invention.

Referring to fig. 3 to 6, in the embodiment of the present invention, assuming that two parties for implementing time synchronization are an LEO satellite and a ground station, respectively, time synchronization between the LEO satellite and the ground station is taken as an example for description, and in a common-frequency mode, assuming that uplink and downlink signals of the LEO satellite and the ground station are measured in a system of simultaneous transmission or simultaneous reception, and a distance between a transmitting antenna a of an LEO satellite-borne device and a jieshou antenna B is d cm, a specific step of implementing ultra-high precision time synchronization between the satellite and the ground is as follows:

step 1, LEO satellite S isThe moment transmitting frequency point is f₁(30 GHz) microwave signal, which is delayed by LEO satellite S transmitter equipment, spatial propagation delay, other additional delays, and after equipment delay by ground station receiver equipment, and finally at ground station GThe time is detected to obtain a pseudo-range observed value of the ground station GSimilarly, the ground station G isThe moment transmitting frequency point is f₁(-30 GHz) microwave signal, LEO satellite S atThe signal is detected at a momentObtaining pseudo range observed value of LEO satellite SThen the pseudorange observations received by each of the LEO satellite and the ground station are expressed as:

wherein c is the vacuum light velocity t^SndAnd t^RcvRespectively the moment of transmission and the moment of reception,andare respectively f₁Downlink measurement pseudo range and f of frequency point₁Measuring an uplink pseudo range of the frequency point; r_AAnd R_BPhase center position vectors, x, of space station to ground antennas A and B, respectively, in the Earth's centroid inertial System_SAnd x_GRespectively, the clock error of the space station and the ground station, delta^SndAnd delta^RcvFor hardware transmission delay, delta, of signal transmitting and receiving channels^relEquivalent time delay for periodic relativistic effects, delta^OFFor phase centre shift equivalent delay, delta^gIs the gravitation time delay, and epsilon is the ranging noise.

Step 2, the uplink and downlink observation pseudo ranges are reduced to the ranging values at the same reference moment, and pairing solving is carried out

And converting pseudo-range observation values at different moments into two-way ranging values at the same reference moment by using post-precise ephemeris data of the LEO satellite. A new set of measurement equations can be reconstructed by using the two-way ranging values at the same time, and the expression is as follows:

step 3, error correction

And correcting and deducting errors such as motion delay errors, equipment delay errors, relativistic effect errors, gravitational delay and the like by using various error deduction methods. The motion delay error elimination needs to establish an error correction model by means of a post-precision ephemeris file and the antenna carrying condition of the satellite-borne equipment.

Step 4, calculating the relative clock difference delta t between the LEO and the ground station

After differential operation and error model correction are carried out through the step (7), the bidirectional clock error between the LEO satellite and the ground station is calculated to be delta t:

although the present invention has been described in detail with reference to the above embodiments, those skilled in the art can make modifications and equivalents to the embodiments of the present invention without departing from the spirit and scope of the present invention, which is set forth in the claims of the present application.