阅读说明：本技术 一种卫星导航授时方法、系统及相关组件 (Satellite navigation time service method, system and related components ) 是由 杨梦雪 李瑞寒 潘振杰 于 2021-07-13 设计创作，主要内容包括：本申请公开了一种卫星导航授时方法、系统及相关组件,该方法包括：获取不同时刻、不同区域对应的电离层特征点的天顶方向电离层延时,根据所有天顶方向电离层延时建立延时关系；根据授时终端的当前位置和当前时刻,通过所述延时关系,确定所述授时终端对应电离层特征点的当前天顶方向电离层延时；根据所述授时终端和对应的授时卫星的相对位置,确定当前天顶方向电离层延时对应的当前电离层延时并进行授时。本申请建立了具体时刻和具体区域对应的电离层特征点的天顶方向电离层延时,针对具体的授时终端查询相应的天顶方向电离层延时,能够更为准确地进行误差计算和卫星授时,修正效率和结果准确度明显高于现有技术。(The application discloses a satellite navigation time service method, a system and related components, wherein the method comprises the following steps: acquiring zenith direction ionospheric delays of ionospheric feature points corresponding to different time and different regions, and establishing a delay relation according to all zenith direction ionospheric delays; determining the current zenith direction ionospheric delay of the corresponding ionospheric feature point of the time service terminal according to the current position and the current time of the time service terminal and through the delay relationship; and determining the current ionospheric delay corresponding to the current zenith direction ionospheric delay according to the relative positions of the time service terminal and the corresponding time service satellite, and performing time service. According to the method and the device, the zenith direction ionosphere delay of the ionosphere characteristic points corresponding to specific time and specific regions is established, the corresponding zenith direction ionosphere delay is inquired aiming at a specific time service terminal, error calculation and satellite time service can be carried out more accurately, and the correction efficiency and the result accuracy are obviously higher than those of the prior art.)

1. A satellite navigation time service method is characterized by comprising the following steps:

acquiring zenith direction ionospheric delays of ionospheric feature points corresponding to different time and different regions, and establishing a delay relation according to all the zenith direction ionospheric delays;

determining the ionospheric delay of the time service terminal corresponding to the current zenith direction of the ionospheric characteristic point according to the current position and the current time of the time service terminal and through the delay relation;

determining the current ionospheric delay corresponding to the current zenith direction ionospheric delay and carrying out time service according to the relative positions of the time service terminal and the corresponding time service satellite;

the process of obtaining the ionospheric delay in the zenith direction of the ionospheric feature points corresponding to any one time and any one area specifically includes:

determining the test terminal of the moment and the area, and selecting a target test satellite;

determining ionospheric delay of the test terminal according to total communication delay, equipment delay and tropospheric delay of the target test satellite to the test terminal;

and determining the ionospheric delay of the ionospheric characteristic point corresponding to the test terminal in the zenith direction by using the ionospheric delay according to the relative positions of the test terminal and the target test satellite.

2. The satellite navigation timing method according to claim 1, wherein the process of selecting the target test satellite includes:

determining a target test satellite meeting test conditions from the time service satellite range of the test terminal;

the test conditions include: the carrier-to-noise ratio exceeds a first preset value, and/or the elevation angle exceeds a preset elevation angle, and/or the carrier tracking stability exceeds a second preset value, and/or the pseudorange measurement error is smaller than a preset error.

3. The satellite navigation time service method according to claim 1, wherein the process of obtaining the zenith direction ionospheric delays of the ionospheric feature points corresponding to different time and different regions and establishing a delay relationship according to all the zenith direction ionospheric delays comprises:

acquiring the zenith direction ionospheric delays of ionospheric characteristic points corresponding to different time and different regions, performing project weighting on all the zenith direction ionospheric delays, and establishing a delay relation.

4. The satellite navigation time service method according to claim 3, wherein the process of performing item weighting on all the zenith direction ionosphere delays and establishing a delay relationship includes:

and according to the corresponding target test satellite, carrying out carrier-to-noise ratio weighting, carrier Doppler weighting and/or elevation weighting on all the ionosphere delays in the zenith direction, and establishing a delay relation.

5. The satellite navigation time service method according to claim 1, wherein the process of obtaining the zenith direction ionospheric delays of the ionospheric feature points corresponding to different time and different regions and establishing a delay relationship according to all the zenith direction ionospheric delays comprises:

acquiring the zenith direction ionospheric delays of ionospheric characteristic points corresponding to different time and different regions, and establishing a delay relation table according to all the zenith direction ionospheric delays.

6. The satellite navigation time service method according to claim 1, wherein the process of obtaining the zenith direction ionospheric delays of the ionospheric feature points corresponding to different time and different regions and establishing a delay relationship according to all the zenith direction ionospheric delays comprises:

acquiring the zenith direction ionospheric delays of ionospheric characteristic points corresponding to different time and different regions, and performing data fitting according to all the zenith direction ionospheric delays to establish a delay relation function.

7. The satellite navigation timing method according to any one of claims 1 to 6, wherein the different regions are specifically regions of different geomagnetic latitudes.

8. A satellite navigation time service system, comprising:

the relation module is used for acquiring the zenith direction ionospheric delays of the ionospheric characteristic points corresponding to different time and different regions and establishing a delay relation according to all the zenith direction ionospheric delays;

the delay determining module is used for determining the ionospheric delay of the time service terminal corresponding to the current zenith direction of the ionospheric characteristic point according to the current position and the current time of the time service terminal and through the delay relation;

the time service module is used for determining the current ionospheric delay corresponding to the current zenith direction ionospheric delay and carrying out time service according to the relative positions of the time service terminal and the corresponding time service satellite;

the relationship module includes:

the hardware setting unit is used for determining a test terminal of an ionosphere characteristic point corresponding to any time and any area and selecting a target test satellite;

the first calculation unit is used for determining the ionospheric delay of the test terminal according to the total communication delay, the equipment delay and the tropospheric delay of the target test satellite to the test terminal;

and the second calculation unit is used for determining the ionospheric delay of the ionospheric characteristic point corresponding to the test terminal in the zenith direction by using the ionospheric delay according to the relative positions of the test terminal and the target test satellite.

9. A satellite navigation time service device is characterized by comprising:

a memory for storing a computer program;

a processor for implementing the steps of the satellite navigation timing method according to any one of claims 1 to 7 when executing the computer program.

10. A readable storage medium, having stored thereon a computer program for implementing the steps of the satellite navigation timing method according to any one of claims 1 to 7 when being executed by a processor.

Technical Field

The invention relates to the field of satellite navigation, in particular to a satellite navigation time service method, a satellite navigation time service system and related components.

Background

Time service (Time Server), i.e., grant Time, is an operation of broadcasting a standard Time signal by some means (radio wave, satellite signal, telephone, internet, optical fiber). In a conventional satellite navigation time service method, a system time obtained by satellite positioning calculation is used as a reference to generate a 1PPS (pulse Per second) time service signal. Under the condition that the position of a user is known, time synchronization can be realized by only 1 satellite generally, and if 4 or more satellites can be observed, the position, the speed and the time information of the antenna of the receiver can be accurately positioned, so that the functions of positioning, speed measurement and precise time service are realized.

In single-point positioning, the time service errors mainly come from satellite clocks, satellite ephemeris, ionosphere delay, troposphere delay, path equipment delay and the like. The most significant of the errors is ionospheric delay errors, and currently, single-frequency users often perform error correction on the ionospheric delay by using a universal model issued by the authorities. The general model observes the ion concentration of an ionized layer in real time by a plurality of reference stations arranged on the ground, calculates and counts the ionized layer delay of a certain area, then fits and constructs the model, and broadcasts corresponding eight model parameters to a single-frequency user. However, the fitting degree of the general model is limited, the correction precision is only about 60% in practical application, and the correction effect is not ideal.

Therefore, how to provide a solution to the above technical problems is a problem to be solved by those skilled in the art.

Disclosure of Invention

In view of the above, the present invention provides a satellite navigation time service method, a system and related components. The specific scheme is as follows: a satellite navigation time service method comprises the following steps:

acquiring zenith direction ionospheric delays of ionospheric feature points corresponding to different time and different regions, and establishing a delay relation according to all the zenith direction ionospheric delays;

determining the ionospheric delay of the time service terminal corresponding to the current zenith direction of the ionospheric characteristic point according to the current position and the current time of the time service terminal and through the delay relation;

determining the current ionospheric delay corresponding to the current zenith direction ionospheric delay and carrying out time service according to the relative positions of the time service terminal and the corresponding time service satellite;

the process of obtaining the ionospheric delay in the zenith direction of the ionospheric feature points corresponding to any one time and any one area specifically includes:

determining the test terminal of the moment and the area, and selecting a target test satellite;

determining ionospheric delay of the test terminal according to total communication delay, equipment delay and tropospheric delay of the target test satellite to the test terminal;

and determining the ionospheric delay of the ionospheric characteristic point corresponding to the test terminal in the zenith direction by using the ionospheric delay according to the relative positions of the test terminal and the target test satellite.

Preferably, the selecting a target test satellite includes:

determining a target test satellite meeting test conditions from the time service satellite range of the test terminal;

the test conditions include: the carrier-to-noise ratio exceeds a first preset value, and/or the elevation angle exceeds a preset elevation angle, and/or the carrier tracking stability exceeds a second preset value, and/or the pseudorange measurement error is smaller than a preset error.

Preferably, the process of obtaining the zenith direction ionospheric delays of the ionospheric feature points corresponding to different times and different regions and establishing the delay relationship according to all the zenith direction ionospheric delays includes:

acquiring the zenith direction ionospheric delays of ionospheric characteristic points corresponding to different time and different regions, performing project weighting on all the zenith direction ionospheric delays, and establishing a delay relation.

Preferably, the process of performing item weighting on all the zenith direction ionospheric delays and establishing a delay relationship includes:

and according to the corresponding target test satellite, carrying out carrier-to-noise ratio weighting, carrier Doppler weighting and/or elevation weighting on all the ionosphere delays in the zenith direction, and establishing a delay relation.

Preferably, the process of obtaining the zenith direction ionospheric delays of the ionospheric feature points corresponding to different times and different regions and establishing the delay relationship according to all the zenith direction ionospheric delays includes:

acquiring the zenith direction ionospheric delays of ionospheric characteristic points corresponding to different time and different regions, and establishing a delay relation table according to all the zenith direction ionospheric delays.

Preferably, the process of obtaining the zenith direction ionospheric delays of the ionospheric feature points corresponding to different times and different regions and establishing the delay relationship according to all the zenith direction ionospheric delays includes:

acquiring the zenith direction ionospheric delays of ionospheric characteristic points corresponding to different time and different regions, and performing data fitting according to all the zenith direction ionospheric delays to establish a delay relation function.

Preferably, the different areas are specifically areas with different geomagnetic latitudes.

Correspondingly, this application still discloses a satellite navigation time service system, includes:

the relation module is used for acquiring the zenith direction ionospheric delays of the ionospheric characteristic points corresponding to different time and different regions and establishing a delay relation according to all the zenith direction ionospheric delays;

the delay determining module is used for determining the ionospheric delay of the time service terminal corresponding to the current zenith direction of the ionospheric characteristic point according to the current position and the current time of the time service terminal and through the delay relation;

the time service module is used for determining the current ionospheric delay corresponding to the current zenith direction ionospheric delay and carrying out time service according to the relative positions of the time service terminal and the corresponding time service satellite;

the relationship module includes:

the hardware setting unit is used for determining a test terminal of an ionosphere characteristic point corresponding to any time and any area and selecting a target test satellite;

the first calculation unit is used for determining the ionospheric delay of the test terminal according to the total communication delay, the equipment delay and the tropospheric delay of the target test satellite to the test terminal;

and the second calculation unit is used for determining the ionospheric delay of the ionospheric characteristic point corresponding to the test terminal in the zenith direction by using the ionospheric delay according to the relative positions of the test terminal and the target test satellite.

Correspondingly, this application still discloses a satellite navigation time service device, includes:

a memory for storing a computer program;

a processor for implementing the steps of the satellite navigation timing method according to any one of the above when the computer program is executed.

Correspondingly, the application also discloses a readable storage medium, wherein a computer program is stored on the readable storage medium, and when being executed by a processor, the computer program realizes the steps of the satellite navigation time service method according to any one of the above.

The application discloses a satellite navigation time service method, which comprises the following steps: acquiring zenith direction ionospheric delays of ionospheric feature points corresponding to different time and different regions, and establishing a delay relation according to all the zenith direction ionospheric delays; determining the ionospheric delay of the time service terminal corresponding to the current zenith direction of the ionospheric characteristic point according to the current position and the current time of the time service terminal and through the delay relation; and determining the current ionospheric delay corresponding to the current zenith direction ionospheric delay according to the relative positions of the time service terminal and the corresponding time service satellite, and performing time service. According to the method and the device, the zenith direction ionosphere delay of a specific time and a specific region is established, the corresponding zenith direction ionosphere delay is inquired aiming at a specific time service terminal, error calculation and satellite time service can be carried out more accurately, and the correction efficiency and the result accuracy are obviously higher than those of the prior art.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.

FIG. 1 is a flowchart illustrating steps of a satellite navigation time service method according to an embodiment of the present invention;

FIG. 2 is a flowchart illustrating sub-steps of a satellite navigation timing method according to an embodiment of the present invention;

FIG. 3 is a schematic diagram illustrating calculation of geomagnetic latitude in an embodiment of the present invention;

fig. 4 is a structural distribution diagram of a satellite navigation time service system according to an embodiment of the present invention.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

Currently, a single-frequency user often performs error correction on ionospheric delay by using a universal model issued by an official party. The general model observes the ion concentration of an ionized layer in real time by a plurality of reference stations arranged on the ground, calculates and counts the ionized layer delay of a certain area, then fits and constructs the model, and broadcasts corresponding eight model parameters to a single-frequency user. However, the fitting degree of the general model is limited, the correction precision is only about 60% in practical application, and the correction effect is not ideal. According to the method and the device, the zenith direction ionosphere delay of a specific time and a specific region is established, the corresponding zenith direction ionosphere delay is inquired aiming at a specific time service terminal, error calculation and satellite time service can be carried out more accurately, and the correction efficiency and the result accuracy are obviously higher than those of the prior art.

The embodiment of the invention discloses a satellite navigation time service method, which is shown in a figure 1 and a figure 2 and comprises the following steps:

s1: acquiring zenith direction ionospheric delays of ionospheric feature points corresponding to different time and different regions, and establishing a delay relation according to all the zenith direction ionospheric delays;

s2: determining the ionospheric delay of the time service terminal corresponding to the ionospheric characteristic point in the current zenith direction through a delay relation according to the current position and the current time of the time service terminal;

s3: determining the current ionospheric delay corresponding to the current zenith direction ionospheric delay and carrying out time service according to the relative positions of the time service terminal and the corresponding time service satellite;

it can be understood that the ionospheric delay and the ionospheric ion concentration have a close correlation, and since the ionospheric ion concentration has a significant difference with the difference between the region and the time, in consideration of the requirement of the present embodiment for the delay accuracy, the ionospheric delay and the time and region delay relationship of different ionospheric feature points in the zenith direction are established in step S1. Specifically, the ionosphere characteristic point is a puncture point of a communication path between any time service terminal and a corresponding time service satellite when the communication path passes through the ionosphere.

Specifically, the process of obtaining the zenith direction ionospheric delay of the ionospheric feature point corresponding to any one time and any one region in S1 specifically includes:

s11: determining the test terminal of the moment and the area, and selecting a target test satellite;

it will be appreciated that this area should be located in the area covered by the visible satellites.

S12: determining ionospheric delay of the test terminal according to total communication delay, equipment delay and tropospheric delay of the target test satellite to the test terminal;

s13: and determining the ionospheric delay of the ionospheric characteristic points corresponding to the test terminal in the zenith direction by using the ionospheric delay according to the relative positions of the test terminal and the target test satellite.

In the conventional technology, a single-frequency user establishes an ionosphere model by using the relative position of a user and a navigation satellite and corrects an ionosphere delay error, and specifically, the ionosphere delay is determined according to the following formula:

F＝1.0+16.0×(0.53-θ)³；

wherein, Δ τ_ionIs ionospheric delay in seconds, F is a tilt factor relative to the navigation satellite, θ is the elevation angle relative to the navigation satellite, x is an intermediate transition variable, Φⁱ _mGeomagnetic latitude, alpha, being a characteristic point of the ionosphere_iAnd beta_iAll are corresponding parameters in an ionized layer model released by an official party.

It can be seen that the conventional ionosphere model does not consider the situation that the ionosphere ion concentrations are inconsistent at specific positions or moments, so that the actual accuracy is poor, and the correction effect is not ideal enough.

In this embodiment, through the actions of steps S11-S13, a plurality of tests are performed to obtain a large amount of test data, and finally a determined delay relationship is obtained, where the delay relationship is specifically a relationship between the ionospheric delay of the ionospheric feature point in the zenith direction and the time and the area. It can be understood that, during each test, the test terminal has a specific time and a specific region, the target test satellite determines that the total communication delay, the equipment delay and the troposphere delay corresponding to the target test satellite can be accurately obtained, so as to calculate the ionosphere delay of the test terminal at the time, and then reversely derive the zenith direction ionosphere delay of the corresponding ionosphere feature point.

Further, the time delay relationship obtained in the steps S11-S13 is applied to satellite navigation time service of an actual time service terminal, at this time, a model similar to a conventional algorithm is used, the current position and the current time of the current time service terminal are utilized to obtain zenith direction ionosphere time delay of ionosphere characteristic points corresponding to the time service terminal, a tilt factor is determined according to the relative position of the time service terminal and a corresponding time service satellite, then the actual ionosphere time delay is determined according to the tilt factor and the zenith direction ionosphere time delay, time service is performed according to the ionosphere time delay, and at this time, the accuracy of a correction result of an ionosphere time delay error is obviously higher than that of the conventional technology.

According to the method and the device, the zenith direction ionosphere delay of a specific time and a specific region is established, the corresponding zenith direction ionosphere delay is inquired aiming at a specific time service terminal, error calculation and satellite time service can be carried out more accurately, and the correction efficiency and the result accuracy are obviously higher than those of the prior art.

The embodiment of the invention discloses a specific satellite navigation time service method, and compared with the previous embodiment, the embodiment further explains and optimizes the technical scheme.

Specifically, the process of selecting the target test satellite in step S11 includes:

determining a target test satellite meeting the test condition from the time service satellite range of the test terminal;

the test conditions included: the carrier-to-noise ratio CN0 exceeds a first preset value, and/or the elevation angle exceeds a preset elevation angle, and/or the carrier tracking stability exceeds a second preset value, and/or the pseudorange measurement error is smaller than a preset error.

It can be understood that, the target test satellite corresponding to the test terminal is selected in order to expect that other delays except the ionospheric delay are accurately measurable as much as possible, and the test satellite is generally a satellite with higher carrier-to-noise ratio CN0, high elevation angle, stable carrier tracking and small pseudorange measurement error, so the test conditions are set, and the target test satellite is determined from the range of the time service satellite for subsequent testing. The ionospheric delay at this time can be obtained only by subtracting the device delay and the tropospheric delay from the total communication delay, and then the ionospheric delay in the zenith direction is obtained. It can be understood that the delay relationship here actually contains the corresponding relationship between the local time of the test terminal and the ionospheric delay.

Further, a process of obtaining zenith direction ionospheric delays of ionospheric feature points corresponding to different time and different regions and establishing a delay relationship according to all the zenith direction ionospheric delays includes:

acquiring the zenith direction ionospheric delays of the ionospheric characteristic points corresponding to different time and different regions, performing project weighting on all the zenith direction ionospheric delays, and establishing a delay relation.

Specifically, according to the corresponding target test satellite, carrier-to-noise ratio weighting, carrier Doppler weighting and/or elevation weighting are carried out on all the ionospheric delays in the zenith direction, and a delay relation is established.

It can be understood that, considering that the influence of each parameter on the delay in the calculation process is different, different terms can be weighted to establish a more specific delay relationship.

Further, after a large amount of test data is obtained, a specific delay relation table can be directly established as a delay relation for subsequent use, or data fitting can be performed according to all the zenith direction ionosphere delays, and a delay relation function is established as a delay relation for subsequent use, that is: the process of obtaining the zenith direction ionospheric delays of ionospheric feature points corresponding to different time and different regions and establishing a delay relation according to all the zenith direction ionospheric delays comprises the following steps: acquiring zenith direction ionospheric delays of ionospheric feature points corresponding to different time and different regions, and establishing a delay relation table according to all the zenith direction ionospheric delays; or acquiring the zenith direction ionospheric delays of the ionospheric feature points corresponding to different time and different regions, and establishing a delay relation according to all the zenith direction ionospheric delays, wherein the process comprises the following steps: acquiring the zenith direction ionospheric delays of ionospheric characteristic points corresponding to different time and different regions, and performing data fitting according to all the zenith direction ionospheric delays to establish a delay relation function. It can be understood that the delay relation function obtained by data fitting has the effect of supplementing and correcting, and a more accurate and reliable result is obtained on the basis of smaller calculated data amount relative to the delay relation table.

It can be understood that the ideal delay relationship should include all delay relationships in each region and within 24 hours around the world, but even if the number of satellites is large enough, the test data is difficult to cover the world, so the obtained test data conventionally corresponds to a region with frequent time service requirements, and in a region with low requirements, the obtained test data is used as a test terminal to determine the delay relationship when the time service requirement occurs for the first time. Furthermore, the test terminals with similar geographic positions can classify the test terminals into the same region, the region is not an administrative region but a geographic region where relative delay errors can be ignored between two points geographically, different regions are specifically regions with different geomagnetic latitudes, and the geomagnetic latitudes can be obtained by calculating the longitude and the low latitude.

Specifically, as shown in fig. 3, the communication path between the target test satellite B and the test terminal P has a puncture point in the ionosphere, which is an ionosphere feature point C, and the ionosphere height is usually 350km, that is, the height of the ionosphere feature point C relative to the earth surface is set to be h ═ 350km, in this embodiment, the unit angle is 180 ° in half cycle angle, and the time unit is second.

Calculating the geocentric angle between the ionosphere characteristic point C and the test terminal P asWhere θ is the elevation angle of the test terminal P relative to the target test satellite B.

Calculating the latitude to the ground of the ionosphere characteristic point C to be phi_I＝Φ_u+ Ψ cosA if Φ_I> +0.416, let Φ_IIf phi is +0.416_IIf less than-0.416, let phi_I-0.416, where a is the azimuth angle of the test terminal P with respect to the target test satellite B, Φ_uTo test the latitude of the terminal P.

Taking the west longitude as negative, calculating the longitude to the earth of the ionosphere characteristic point CWherein λ_uIs the longitude of the test terminal P.

Then calculating to obtain the geomagnetic latitude phi of the ionized layer characteristic point C_m＝Φ_I+0.064cos(λ_I-1.617)。

Further, the local time of the ionosphere feature point C may be determined to be t ═ 4.32 × 10⁴λ_I+t_GPSIn seconds.

It can be understood that the zenith direction ionospheric delays of the ionospheric feature points corresponding to different regions and different times are determined through steps S11-S13, and a delay relationship is obtained, where the delay relationship includes delay features of specific times and regions, and can provide a more accurate correction basis for the delay error correction of a subsequent time service terminal.

Correspondingly, an embodiment of the present application discloses a satellite navigation time service system, as shown in fig. 4, including:

the system comprises a relation module 1, a time delay module and a time delay module, wherein the relation module 1 is used for acquiring the zenith direction ionosphere time delays of different moments and different regions and establishing a time delay relation according to all the zenith direction ionosphere time delays;

the delay determining module 2 is used for determining the ionospheric delay of the current zenith direction of the time service terminal according to the current position and the current time of the time service terminal and through a delay relation;

the time service module 3 is used for determining the current ionospheric delay corresponding to the current zenith direction ionospheric delay and carrying out time service according to the relative positions of the time service terminal and the corresponding time service satellite;

the relation module 1 includes:

a hardware setting unit 11, configured to determine a test terminal at any time and in any area, and select a target test satellite;

the first calculating unit 12 is configured to determine an ionospheric delay of the test terminal according to a total communication delay, an equipment delay, and a tropospheric delay of the target test satellite to the test terminal;

and the second calculating unit 13 is configured to determine, according to the relative positions of the test terminal and the target test satellite, a zenith direction ionospheric delay corresponding to the test terminal by using the ionospheric delay.

According to the method and the device, the zenith direction ionosphere delay of a specific time and a specific region is established, the corresponding zenith direction ionosphere delay is inquired aiming at a specific time service terminal, error calculation and satellite time service can be carried out more accurately, and the correction efficiency and the result accuracy are obviously higher than those of the prior art.

In some specific embodiments, the hardware setting unit 11 is specifically configured to:

determining a target test satellite meeting test conditions from the time service satellite range of the test terminal;

the test conditions include: the carrier-to-noise ratio exceeds a first preset value, and/or the elevation angle exceeds a preset elevation angle, and/or the carrier tracking stability exceeds a second preset value, and/or the pseudorange measurement error is smaller than a preset error.

In some specific embodiments, the relationship module 1 is specifically configured to:

acquiring the zenith direction ionospheric delays of ionospheric characteristic points corresponding to different time and different regions, performing project weighting on all the zenith direction ionospheric delays, and establishing a delay relation.

In some specific embodiments, the relationship module 1 is specifically configured to:

and according to the corresponding target test satellite, carrying out carrier-to-noise ratio weighting, carrier Doppler weighting and/or elevation weighting on all the ionosphere delays in the zenith direction, and establishing a delay relation.

In some specific embodiments, the relationship module 1 is specifically configured to:

acquiring the zenith direction ionospheric delays of ionospheric characteristic points corresponding to different time and different regions, and establishing a delay relation table according to all the zenith direction ionospheric delays.

In some specific embodiments, the relationship module 1 is specifically configured to:

acquiring the zenith direction ionospheric delays of ionospheric characteristic points corresponding to different time and different regions, and performing data fitting according to all the zenith direction ionospheric delays to establish a delay relation function.

In some specific embodiments, the different regions are specifically regions of different magnetic latitudes.

Correspondingly, the embodiment of the application also discloses a satellite navigation time service device, which comprises:

a memory for storing a computer program;

a processor for implementing the steps of the satellite navigation timing method according to any one of the above when the computer program is executed.

Correspondingly, the embodiment of the application also discloses a readable storage medium, wherein a computer program is stored on the readable storage medium, and when being executed by a processor, the computer program realizes the steps of the satellite navigation time service method according to any one of the above.

For details of the satellite navigation time service method, reference may be made to the detailed description in the above embodiments, which is not described herein again.

The satellite navigation time service device and the readable storage medium in the embodiment of the present application have the same technical effects as those in the above embodiments, and are not described herein again.

Finally, it should also be noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.

The satellite navigation time service method, the satellite navigation time service system and related components provided by the invention are described in detail, specific examples are applied in the description to explain the principle and the implementation mode of the invention, and the description of the embodiments is only used for helping to understand the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present invention.