CN105738922A - Service reliability analysis method and system of navigation satellite constellation system - Google Patents

Abstract

The invention relates to a service reliability analysis method and system of a navigation satellite constellation system. The objective of the invention is to solve problems in analysis on the service reliability of the navigation satellite constellation system. The method includes the following steps that: S1, the service availability of the navigation satellite constellation system is calculated; S2, the average service continuity of all satellites in the constellation system is calculated; and S3, the service reliability of the constellation system is calculated according the service availability and the average service continuity. According to the method of the invention, the service availability and the average service continuity of the constellation system are calculated, so that the service reliability of the constellation system is obtained, a calculation process is simple and is easy to implement; the obtained service reliability can be utilized to measure whether services provided by the navigation satellite constellation system are reliable, and therefore, the service quality of the navigation satellite constellation system can be better mastered.

Description

The service reliability of aeronautical satellite constellation systems analyzes method and system

Technical field

The present invention relates to aeronautical satellite constellation systems technical field, the service reliability being specifically related to a kind of aeronautical satellite constellation systems analyzes the service reliability analysis system of method and a kind of aeronautical satellite constellation systems.

Background technology

Aeronautical satellite constellation systems for by possible most economical in the way of provide reliable location, navigation, time service service and PNT to service to the public.The service reliability of aeronautical satellite constellation systems refers to for healthy aeronautical satellite constellation systems, any point in coverage, in predetermined time interval, the instantaneous subscriber pseudorange error of aerial signal standard positioning services maintain the percentage of time within the reliability thresholds of regulation, whether reliable be used for weighing the service that aeronautical satellite constellation systems provides.

But, there is no the research of related fields at present, for understanding the service quality of aeronautical satellite constellation systems, it is necessary to provide the service reliability of a kind of aeronautical satellite constellation systems to analyze method.

Summary of the invention

The technical problem to be solved is how to analyze the service reliability of aeronautical satellite constellation systems.

For solving above-mentioned technical problem, the present invention proposes the service reliability of a kind of aeronautical satellite constellation systems and analyzes method and system.

First aspect, the method includes:

S1, calculate the service availability of described constellation systems；

S2, calculate the average service seriality of all satellites in described constellation systems；

S3, according to described service availability and described average service seriality, calculate the service reliability of described constellation systems.

Further, described step S1 calculates described service availability by following formula:

$A_I=1-\left(\frac{N_{USS}\×t}{\mathrm{\τ}}\right)$

Wherein, A_IFor described service availability, τ is Preset Time, N_USSThe maximum times of unplanned interruption occurs for described constellation systems in described Preset Time, and t is the mean repair time of each unplanned interruption.

Further, described step S2 includes:

S21, calculate the average integrity of all satellites in described constellation systems；

S22, according to described average integrity, calculate described average service seriality.

Further, described step S21 calculates described average integrity by following formula:

$I=\frac{N_{USS}}{\mathrm{\τ}\×N_{sat}}$

Wherein, I is described average integrity, N_satFor the number of described constellation systems Satellite, τ is Preset Time, N_USSThe maximum times of unplanned interruption is there is for described constellation systems in described Preset Time.

Further, described step S22 calculates described average service seriality by following formula:

C_I=1-I

Wherein, C_IFor described average service seriality.

Further, described step S3 calculates the service reliability of described constellation systems by following formula:

R_I=A_I×C_I

Wherein, R_IFor described service reliability, A_IFor described service availability, C_IFor described average service seriality.

Second aspect, this system includes:

First computing module, for calculating the service availability of described constellation systems；

Second computing module, for calculating the average service seriality of all satellites in described constellation systems；

3rd computing module, for according to described service availability and described average service seriality, calculating the service reliability of described constellation systems.

Further, described first computing module calculates described service availability by following formula:

$A_I=1-\left(\frac{N_{USS}\×t}{\mathrm{\τ}}\right)$

Wherein, A_IFor described service availability, τ is Preset Time, N_USSThe maximum times of unplanned interruption occurs for described constellation systems in described Preset Time, and t is the mean repair time of each unplanned interruption.

Further, described second computing module includes:

First computing unit, for calculating the average integrity of all satellites in described constellation systems；

Second computing unit, for according to described average integrity, calculating described average service seriality.

Further, described first computing unit calculates described average integrity by following formula:

$I=\frac{N_{USS}}{\mathrm{\τ}\×N_{sat}}$

Wherein, I is described average integrity, N_satFor the number of described constellation systems Satellite, τ is Preset Time, N_USSThe maximum times of unplanned interruption is there is for described constellation systems in described Preset Time.

The present invention is by calculating the service availability of constellation systems and average service continuity, and then obtains the service reliability of described constellation systems, and this calculating process is simply, easily realize.Whether the service reliability obtained can be used for weighing the service that aeronautical satellite constellation systems provides reliable, makes people be better understood by the service quality of aeronautical satellite constellation systems.

Accompanying drawing explanation

Can be more clearly understood from inventive feature information and advantage by reference accompanying drawing, accompanying drawing is schematic and should not be construed as and the present invention is carried out any restriction, in the accompanying drawings:

Fig. 1 illustrates that the service reliability according to aeronautical satellite constellation systems of the present invention analyzes the schematic flow sheet of method one embodiment；

Fig. 2 illustrates that the service reliability according to aeronautical satellite constellation systems of the present invention analyzes the structured flowchart of system one embodiment.

Detailed description of the invention

In order to be more clearly understood that the above-mentioned purpose of the present invention, feature and advantage, below in conjunction with the drawings and specific embodiments, the present invention is further described in detail.It should be noted that when not conflicting, embodiments herein and the feature in embodiment can be mutually combined.

Elaborate a lot of detail in the following description so that fully understanding the present invention; but; the present invention can also adopt other to be different from other modes described here to implement, and therefore, protection scope of the present invention is by the restriction of following public specific embodiment.

Before introducing technical scheme, first the technical term related to made an explanation or illustrate:

(1) service availability, 95% site error refer in aeronautical satellite constellation systems any point in coverage, any 24 hours intervals, estimating is less than the percentage of time of error threshold.

(2) service continuity, refers within the time of regulation, and healthy standard positioning services aerial signal is by available for lasting health and do not produce the probability of unplanned interruption, it is assumed that the standard positioning services aerial signal at initial time is available.

(3) integrity, refers to the size of confidence level to the information correctness that aeronautical satellite constellation systems provides.Integrity includes working as standard positioning services aerial signal when utilized, should not provide the ability alerting (early warning and alarm) in time to receiver.

Three above technical term is noun well known to those skilled in the art, the quantitative criteria according to the known each technical term of above-mentioned definition, and therefore above-mentioned technical term is not only the description of character property, self also represents a concrete quantized value.

The present invention provides the service reliability of a kind of aeronautical satellite constellation systems to analyze method, as it is shown in figure 1, the method includes:

S1, calculate the service availability of described constellation systems；

S2, calculate the average service seriality of all satellites in described constellation systems；

S3, according to described service availability and described average service seriality, calculate the service reliability of described constellation systems.

Wherein, there is no sequencing between step S1, S2.

When service availability is meansigma methods, calculated service reliability is average service reliability；When service availability is the most bad value, calculated service reliability is the most bad service reliability.

The present invention is by calculating the service availability of constellation systems and average service continuity, and then obtains the service reliability of described constellation systems, and this calculating process is simply, easily realize.And, whether the service that the available service reliability measurement aeronautical satellite constellation systems obtained provides is reliable, is better understood by the service quality of aeronautical satellite constellation systems.

Further, described step S3 can calculate the service reliability of described constellation systems by following formula:

R_I=A_I×C_I

Wherein, R_IFor service reliability, A_IFor described service availability, C_IFor described average service seriality.

Here, the present invention, by setting up the quantitative relationship between service availability, average service seriality and service reliability three, obtains the value of service reliability.

Further, described step S1 can calculate described service availability by following formula:

$A_I=1-\left(\frac{N_{USS}\×t}{\mathrm{\τ}}\right)$

Wherein, A_IFor described service availability, τ is Preset Time, N_USSThe maximum times of unplanned interruption occurs for described constellation systems in described Preset Time, and t is the mean repair time of each unplanned interruption.

Preset Time and observation period, it is generally 1 year namely 8760 hours.

Generally, there is at most 3 unplanned interruptions in 1 year in constellation systems.

Further, described step S2 comprises the steps that

S21, calculate the average integrity of all satellites in described constellation systems；

S22, according to described average integrity, calculate described average service seriality.

Further, described step S21 can calculate described average integrity by following formula:

$I=\frac{N_{USS}}{\mathrm{\τ}\×N_{sat}}$

Wherein, I is described average integrity, N_satFor the number of described constellation systems Satellite, τ is Preset Time, N_USSThe maximum times of unplanned interruption is there is for described constellation systems in described Preset Time.

Further, described step S22 can calculate described average service seriality by following formula:

C_I=1-I

Wherein, C_IFor described average service seriality.

The present invention also provides for the service reliability of a kind of aeronautical satellite constellation systems and analyzes system, as in figure 2 it is shown, this system 100 includes:

First computing module 101, for calculating the service availability of described constellation systems；

Second computing module 102, for calculating the average service seriality of all satellites in described constellation systems；

3rd computing module 103, for according to described service availability and described average service seriality, calculating the service reliability of described constellation systems.

Further, described first computing module calculates described service availability by following formula:

$A_I=1-\left(\frac{N_{USS}\×t}{\mathrm{\τ}}\right)$

Wherein, A_IFor described service availability, τ is Preset Time, N_USSThe maximum times of unplanned interruption occurs for described constellation systems in described Preset Time, and t is the mean repair time of each unplanned interruption.

Further, described second computing module 102 includes:

First computing unit 1021, for calculating the average integrity of all satellites in described constellation systems；

Second computing unit 1022, for according to described average integrity, calculating described average service seriality.

Further, described first computing unit calculates described average integrity by following formula:

$I=\frac{N_{USS}}{\mathrm{\τ}\×N_{sat}}$

Wherein, I is described average integrity, N_satFor the number of described constellation systems Satellite, τ is Preset Time, N_USSThe maximum times of unplanned interruption is there is for described constellation systems in described Preset Time.

The service reliability of aeronautical satellite constellation systems of the present invention is analyzed the service reliability that system is aeronautical satellite constellation systems of the present invention and is analyzed the function structure module of method, its appropriate section that refer to about the explanation of content, explanation or beneficial effect in the service reliability analysis method of aeronautical satellite constellation systems of the present invention, does not repeat them here.

In the present invention, term " first ", " second " only for descriptive purposes, and it is not intended that instruction or hint relative importance.Term " multiple " refers to two or more, unless otherwise clear and definite restriction.

Although being described in conjunction with the accompanying embodiments of the present invention, but those skilled in the art can make various modifications and variations without departing from the spirit and scope of the present invention, and such amendment and modification each fall within the scope being defined by the appended claims.

Claims (10)

1. the service reliability of an aeronautical satellite constellation systems analyzes method, it is characterised in that including:

S1, calculate the service availability of described constellation systems；

S2, calculate the average service seriality of all satellites in described constellation systems；

S3, according to described service availability and described average service seriality, calculate the service reliability of described constellation systems.

2. method according to claim 1, it is characterised in that described step S1 calculates described service availability by following formula:

$A_I=1-\left(\frac{N_{USS}\×t}{\mathrm{\τ}}\right)$

Wherein, A_IFor described service availability, τ is Preset Time, N_USSThe maximum times of unplanned interruption occurs for described constellation systems in described Preset Time, and t is the mean repair time of each unplanned interruption.

3. method according to claim 1, it is characterised in that described step S2 includes:

S21, calculate the average integrity of all satellites in described constellation systems；

S22, according to described average integrity, calculate described average service seriality.

4. method according to claim 3, it is characterised in that described step S21 calculates described average integrity by following formula:

$I=\frac{N_{USS}}{\mathrm{\τ}\×N_{sat}}$

Wherein, I is described average integrity, N_satFor the number of described constellation systems Satellite, τ is Preset Time, N_USSThe maximum times of unplanned interruption is there is for described constellation systems in described Preset Time.

5. method according to claim 4, it is characterised in that described step S22 calculates described average service seriality by following formula:

C_I=1-I

Wherein, C_IFor described average service seriality.

6. according to the arbitrary described method of claim 1-5, it is characterised in that described step S3 calculates the service reliability of described constellation systems by following formula:

R_I=A_I×C_I

Wherein, R_IFor described service reliability, A_IFor described service availability, C_IFor described average service seriality.

7. the service reliability of an aeronautical satellite constellation systems analyzes system, it is characterised in that including:

First computing module, for calculating the service availability of described constellation systems；

Second computing module, for calculating the average service seriality of all satellites in described constellation systems；

3rd computing module, for according to described service availability and described average service seriality, calculating the service reliability of described constellation systems.

8. system according to claim 7, it is characterised in that described first computing module calculates described service availability by following formula:

$A_I=1-\left(\frac{N_{USS}\×t}{\mathrm{\τ}}\right)$

Wherein, A_IFor described service availability, τ is Preset Time, N_USSThe maximum times of unplanned interruption occurs for described constellation systems in described Preset Time, and t is the mean repair time of each unplanned interruption.

9. system according to claim 7, it is characterised in that described second computing module includes:

First computing unit, for calculating the average integrity of all satellites in described constellation systems；

Second computing unit, for according to described average integrity, calculating described average service seriality.

10. system according to claim 9, it is characterised in that described first computing unit calculates described average integrity by following formula:

$I=\frac{N_{USS}}{\mathrm{\τ}\×N_{sat}}$

Wherein, I is described average integrity, N_satFor the number of described constellation systems Satellite, τ is Preset Time, N_USSThe maximum times of unplanned interruption is there is for described constellation systems in described Preset Time.