JP2002325059A - Satellite communication earth station system and communication controller for earth station - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a satellite communication earth station system in which the load can be distributed substantially uniform among a plurality of airborne earth stations. SOLUTION: The satellite communication earth station system comprises a primary GES 4A and a secondary GES 4B which are imparted with the same ID. Consequently, it seems as if one virtual GES exists from an AES 3. A log-in request from the AES 3 is accepted at the primary GES 4A. Upon accepting the log-in request, the primary GES 4A determines a GES other than that determined as the log-in destination immediately before as the log-in destination. Consequently, the load can be made uniform substantially among a plurality of GES 4A, 4B.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a satellite communication earth station system for use in an aeronautical satellite communication system for communicating via a communication satellite with an aircraft earth station which is a communication device mounted on an aircraft, and an earth system. The present invention relates to a communication control device used for a station.

[0002]

2. Description of the Related Art Conventionally, an aircraft earth station (hereinafter referred to as "AE
S ". AES: Aircraft Earth Station and the GES, a communication device installed on the ground
That. An aeronautical satellite communication system that communicates with a GES (Ground Earth Station) via a communication satellite is known. This aeronautical satellite communication system usually includes a plurality of communication satellites and a plurality of GES. Each communication satellite covers a predetermined specific communication area on the earth surface, and is provided with, for example, four communication satellites. Each GES is provided in each communication area. That is, each GES uses the corresponding communication satellite as a relay station.

In such an aeronautical satellite communication system, when a log-in request occurs, the AES captures initial capture information broadcast from the GES via a communication satellite. The initial acquisition information includes the ID of the communication satellite and the GES I
D, the frequency to be used for login, the frequency of radio waves broadcasting the initial acquisition information, and the broadcast frequencies of all GESs that cover other communication areas.

[0004] When the AES captures the initial capture information, the AES superimposes the login request data on the radio wave of the login frequency included in the initial capture information, creates a login request signal, and transmits the login request signal to the communication satellite. Via GES. Upon receiving the login request signal, the GES transmits data channel information such as frequency information necessary for subsequent communication to the AES via the communication satellite. As a result, a communication line is established and satellite communication becomes possible.

In the aeronautical satellite communication system described above, since only one GES is provided in one communication area, the load required for GES communication processing increases as the number of AESs increases. For this reason, it has been considered to construct a satellite communication earth station system that includes a plurality of GESs in one communication area and distributes the load required for communication processing.

[0006] A plurality of GESs in one communication area in the satellite communication earth station system individually broadcast unique initial acquisition information. On the other hand, AES has ORT
(Owner Requirement Table), a list containing a plurality of GES IDs and their broadcast frequencies.
In this ORT, a plurality of GESs are assigned priorities.

When the AES captures the initial capture information, the AES
Based on the ID of the ES and the like, it is checked whether or not this initial acquisition information is the initial acquisition information from the GES with the highest priority. If so, the AES logs in to the GES. On the other hand, if not, the AES checks whether it is the next highest priority GES. in this way,
The AES checks the broadcast sources of the captured initial capture information in order from the one with the highest priority, and when they match, the GE
Log in to S.

[0008]

As described above, in the aeronautical satellite communication system described above, the login destination is determined by the AES side. Therefore, there is a problem that login destinations are biased due to various factors, and a large load is applied to any one of the plurality of GESs.

Accordingly, an object of the present invention is to provide a system for communicating between an aircraft earth station and one of a plurality of aeronautical earth stations via a communication satellite, thereby distributing the load among the plurality of aeronautical earth stations and substantially reducing the load. It is to provide a satellite earth station system and a satellite earth station that can be equalized.

[0010]

According to the present invention, there is provided a satellite communication earth station system for communicating via a communication satellite with an aircraft earth station which is a communication device mounted on an aircraft. With a plurality of aeronautical earth stations assigned the same earth station identification information, the login request transmitted from the aircraft earth station via the communication satellite is a predetermined reception earth station among the plurality of aeronautical earth stations. When received, at the receiving earth station, any one of the plurality of aeronautical earth stations is used as a login destination of the aircraft earth station so that the load of communication processing among the plurality of aeronautical earth stations becomes substantially equal. The decision is made.

[0011]

Embodiments of the present invention will be described below in detail with reference to the accompanying drawings.

Embodiment 1 FIG. 1 is a conceptual diagram showing an overall configuration of an aeronautical satellite communication system according to Embodiment 1 of the present invention. FIG. 1 illustrates the earth's surface as a rectangle. This aeronautical satellite communication system includes a plurality of ground-side satellite communication earth station systems 1, a plurality of communication satellites 2, and an AES 3 mounted on one or more aircraft. The satellite communication earth station system 1 includes a plurality of (two in FIG. 1) GES 4, and the GES 4 and the AES 3 communicate via the communication satellite 2.

More specifically, this aeronautical satellite communication system uses the entire surface of the earth as its communication area.
Provide a communication service to ES3. This aeronautical satellite communication system, for example, covers four areas E
1, E2, E3, E4 (hereinafter collectively referred to as “communication area E”), and each area E1 to E4 is
And two communication satellites 2. The communication satellite 2 is a geostationary satellite, and the communication satellite 2 and the communication area to be covered correspond to each other in a fixed manner. Each communication area E1 to E4 has two GEs.
S4A and S4B are provided, and AES3 existing in a certain communication area E can communicate with any one of the two GESs 4A and 4B.

The GES 4 broadcasts initial acquisition information via the communication satellite 2 in the corresponding communication area E. The initial acquisition information includes the ID of the GES 4, the broadcast radio frequency of the initial acquisition information, the frequency to be used for login, the ID of the communication satellite 2, and all other GESs that control the communication area E.
4 broadcast frequencies. When a login request occurs, the AES 3 captures the initial capture information, and transmits a login request signal to the GES 4 via the communication satellite 2 according to the content of the initial capture information. When the login request is approved by the GES 4, the GES 4 returns a communication permission signal to the AES 3 via the communication satellite. Thus, the login is completed, and the satellite communication between AES3 and GES4 is performed.

The two GESs 4 are composed of a primary GES 4A and a secondary GES 4B, and both have the same ID (earth station identification information). That is, when viewed from the AES3, it appears that one GES virtually exists. Thereby, the AES 3 transmits the login request to the primary GES 4A and the secondary GES 4A.
The login request is transmitted without specifying any one of ES4B. Therefore, unlike the case where separate IDs are assigned to a plurality of GESs and the initial acquisition information is separately broadcasted, the login destination can be entrusted to the satellite communication earth station system 1 side.

The primary GES of the two GESs 4A and 4B
4A has a function of broadcasting the above initial capture information, accepting a login request from AES3, determining a login destination, and transmitting a communication permission signal to AES3. That is, the primary GES4 corresponds to the receiving earth station. Secondary GES
4B has no such function and the primary GES4
Only when A designates a login destination, communication processing after login is executed. That is, the primary GES 4A centrally manages the GES determination of the login destination.

FIG. 2 is a block diagram showing a configuration of the satellite communication earth station system 1 provided in one communication area E. The satellite communication earth station system 1 includes the primary GES4A and the secondary GES4B as described above. Primary GES4
A and the secondary GES 4B are both connected to the exchange 10 so that they can communicate with the external communication network 11. With this configuration, a control station (not shown) is installed at a position distant from the installation location of the GES 4, and this control station is connected to the GES 4 via the communication network 11, thereby enabling communication between the AES 3 and the control station. Is possible.

The primary GES 4A includes an antenna 20A, a transmission / reception unit 21A, and a communication control unit 22A. The antenna 20A is necessary for efficiently transmitting and receiving radio waves to and from the communication satellite 2, and its directivity is directed in the direction in which the communication satellite 2 exists. Transceiver 21A
Processes a high-frequency signal transmitted from the communication satellite 2 and received by the antenna 20A and supplies the processed signal to the communication control unit 22A, or converts a transmission signal supplied from the communication control unit 22A into a high-frequency signal and transmits the signal to the communication satellite 2 from the antenna 20A. It is transmitted to.

The communication control section 22A controls the communication processing of the primary GES 4A. More specifically, the primary G
The communication control unit 22A of the ES 4A has a function of broadcasting initial acquisition information and determining a login destination when a login request is issued from the AES 3. Further, the communication control unit 22A of the primary GES 4A also has a function of executing communication processing after login.

More specifically, the communication control unit 22A
The initial acquisition information is broadcast to the communication area E via a Psmc channel which is a predetermined broadcast channel. That is, the communication control unit 22A gives the initial capture information to the transmission / reception unit 21A,
A broadcast signal including the initial capture information is transmitted from the transmission / reception unit 21A to the communication area E via the communication satellite 2. This initial capture information is always broadcast.

In addition, when a login request is received from the AES 3 that has captured the initial capture information, the communication control unit 22A controls the primary GES 4A and the secondary GES 4B so that the load of the communication processing is equal between the primary GES 4A and the secondary GES 4B. One of the secondary GESs 4B is determined as the login destination of the AES3. More specifically, the communication control unit 22A
Determines a GES that is different from the GES determined as the communication destination for the immediately preceding login as the communication destination when there is a login request from the AES3. That is, the communication control unit 2
2A alternately determines the primary GES 4A and the secondary GES 4B as the GES of the communication destination. By doing this,
The communication processing load can be equalized between the primary GES 4A and the secondary GES 4B.

The communication control unit 22A includes a logon management unit 1
2 are connected. The communication control unit 22A performs the above-described GE
The determination processing of S and the like are executed based on the logon information stored in the logon management unit 12. The logon information is, for example, registration information on AES3 for which communication is permitted, AES3 logon information, and frequency plan information. The logon information of AES3 includes, for example, as shown in FIG.
The ID of the login destination GES and the login time are associated with each other. With this logon information, the communication control unit 2
2A can know the GES determined as the communication destination for the previous login.

On the other hand, the secondary GES4B
B, a transmission / reception unit 21B and a communication control unit 22B. The antenna 20B is necessary for efficiently transmitting and receiving radio waves to and from the communication satellite 2 similarly to the primary GES 4A, and its directivity is directed in advance to the direction in which the communication satellite 2 exists. The transmission / reception unit 21B processes a high-frequency signal similarly to the primary GES 4A.

The communication control section 22B has a function of executing communication processing. More specifically, the communication control unit 22B
It does not have a function of accepting a login request or determining a login destination. When the primary GES 4A designates a login destination, the AES 3 is transmitted via the communication satellite 2.
Can communicate with

The communication control unit 22B of the secondary GES4B
The logon management unit 12 is also connected. That is,
The primary GES 4A and the secondary GES 4B can share the logon information managed by the logon management unit 12.

Further, the primary GES4A and the secondary GES
4B shares the channel management unit 13. More specifically, the channel management unit 13 includes a communication control unit 22A of the primary GES4A and a communication control unit 22B of the secondary GES4B.
, And mainly manages the C channel.

The C channel is a bidirectional channel for transmitting audio data between AES3 and GES4, and a plurality of C channels are set. In other words, the C channel is a line mode SC used bidirectionally between AES3 and GES4.
This is a PC (Single Channel Per Carrier) channel. This C channel is time division multiplexed, providing voice and data traffic on the primary channel and providing signaling, monitoring and data messages on sub-channels.

The channel management unit 13 holds information such as the frequency of the plurality of C channels and manages the use status of the C channels. For example, when an increase in the number of C channels is requested from AES3 communicating with the primary GES4A, the channel management unit 13 searches for a free C channel, and if it is free, newly searches that C channel for that AES.
Assign to 3. Thus, effective use of the C channel can be achieved.

The channels used in this aeronautical satellite communication system include a P channel, an R channel, and a T channel in addition to the C channel. The P channel is a packet mode time division (TDM) channel for continuously transmitting signals and user data from GES4 to AES3. The P channel used for the system management function is called Psmc, and the P channel used for other functions is called Pd. The R channel is a random access channel for transmitting a signal from AES3 and user data. The R channel used for the system management function is called Rsmc, and the R channel used for other functions is called Rd. The T channel is a reserved time division multiple access (TDMA) channel used only by AES3. GES4
Reserves a transmission time slot requested by AES3 according to the message length. The AES 3 on the transmitting side transmits a message to the reserved time slot according to the priority.

FIG. 4 is a sequence diagram for explaining communication control in the primary GES 4A. This communication control is based on ICAO (International Civil Aviatio).
n Organization (ICAO SARPs Annex10; SARP)
s: Standards and Recommendation Practices) Complies with the communication control specified in Vol. III, Chapter 4.

The primary GES4A transmits the initial capture information to Psmc
Broadcasting via a channel (S1). That is, the communication control unit 22A of the primary GES 4A includes a broadcasting unit as one function of software. On the other hand, AES3
When a login request is issued, the above-mentioned initial capture information is captured (S2). When AES3 captures the initial capture information,
The ID of the GES 4 included in the initial acquisition information, the broadcast frequency, the frequency to be used for login, the ID of the communication satellite, and the like are confirmed, and a login request signal is transmitted via the communication satellite 2 to the GES.
4 (S3). In this case, the login request signal is a signal superimposed on a radio wave of a frequency to be used for login included in the initial acquisition information.

Upon receiving the login request signal, the primary GES 4A refers to the registration information managed by the logon management unit 12 and determines whether or not login is possible (S).
4). That is, the AE that is the destination of the login request signal
It is determined whether or not S3 is AES for which communication permission has been received in advance. If you cannot log in, the primary GES4A
Rejects the login request (S5). On the other hand, if login is possible, the primary GES 4A determines a login destination based on the logon information managed by the logon management unit 12 (S6). As described above, a GES different from the immediately preceding login destination is determined as the login destination so that the load is equal between the primary GES 4A and the secondary GES 4B, as described above. That is, the primary GES4A
Determines alternately the primary GES4A and the secondary GES4B as login destinations. As described above, the communication control unit 22A of the primary GES 4A includes an earth station determining unit as one function of software.

After determining the login destination, the primary GES 4A transmits an appropriate data channel to AES (S7). More specifically, the primary GES 4A allocates a Pd channel, an Rd channel, and a T channel to AES3. As a result, AES3 sets the primary GES4
It can communicate with GES4 using the channel assigned by A (S8).

When the primary GES 4A is determined as a login destination, since the primary GES 4A has the ID of the AES 3 and the assigned channel information, it communicates with the AES 3 using the information. On the other hand, secondary GE
If S4B is determined as the login destination, the secondary G
Since the ES4B does not hold the ID of the AES3 and the assigned channel information, it is necessary to notify the primary GES4A of these information to the secondary GES4B. Therefore,
If the secondary GES4B is determined as the login destination, the primary GES4A, along with the data channel assignment,
After indicating the ID of the AES3 and the assigned channel information, the secondary GES 4B is instructed to execute communication processing (S9). As a result, AES3 becomes the primary GES4
Secondary GES4B using channel assigned from A
Can be communicated with (S8).

As described above, according to the first embodiment,
Since the same ID is given to the two primary GES4A and the secondary GES4B, the login is accepted by one primary GES4A, and the login destination is determined by the primary GES4A that is in charge of the login acceptance.
Unlike the related art in which the login destination is determined on the S3 side, the load can be equalized between the primary GES 4A and the secondary GES 4B. Therefore, for example, even if AES3 increases in the future, good communication can be realized.

Embodiment 2 FIG. 5 is a block diagram showing a configuration of a satellite communication earth station system according to Embodiment 2 of the present invention. 5, the same reference numerals are used for the same functional parts as those in FIG.

The first embodiment exemplifies a case where one communication area E is covered by one communication satellite 2. On the other hand, the second embodiment exemplifies a case where one communication area E is covered by a plurality of communication satellites 30A and 30B.

More specifically, in the second embodiment,
The same ID is assigned to the two communication satellites 30A and 30B. Therefore, from the viewpoint of AES3, it appears that one communication satellite virtually exists. In other words, this is because only the one ID is included in the initial acquisition information broadcast from the primary GES4A.

The two communication satellites 30A and 30B are connected to the primary G
One-to-one correspondence with ES4A and secondary GES4B. That is, the primary GES 4A directs the directivity to the direction in which one communication satellite (hereinafter, referred to as “primary communication satellite”) 30A is present, and the secondary GES 4B is directed to the other communication satellite (hereinafter, referred to as “secondary communication satellite”). Directivity is directed to the direction in which 30B exists. Thus, two GES4A,
4B transmits and receives signals using the separate communication satellites 30A and 30B as relay stations.

When transmitting a login request signal from the AES 3, the login request signal is received by the primary GES 4A via the primary communication satellite 30A. Also, primary GES4
A, the data channel information transmitted after the login destination is determined in the same manner as in the first embodiment is transmitted to one entire communication area E via the primary communication satellite 30A. Is received, and subsequent communication is performed.

In this case, the primary GES4
When A is assigned, AES3 and primary GE
The signal transmitted from S4A uses primary communication satellite 30A as a relay station, and when secondary GES4B is assigned as a login destination, AES3 and secondary GES4B
Use the secondary communication satellite 30B as a relay station. On the other hand, the login destination is determined so that the load is equal for a plurality of GESs 4 as in the first embodiment, so that the communication satellites used are also distributed.

As described above, according to the second embodiment,
Two communication satellites 30A and 30B assigned one ID
And each communication satellite 30A, 30B is a primary GE
Since the S4A and the secondary GES 4B are associated one-to-one, the load can be distributed between the two communication satellites, unlike the case where one communication satellite covers one communication area.

Embodiment 3 FIG. 6 is a block diagram showing a configuration of a satellite communication earth station system according to Embodiment 3 of the present invention. 6, the same reference numerals are used for the same functional parts as in FIG.

In the second embodiment, an example is described in which one GES is associated with one communication satellite. For example, for the primary communication satellite 30A, the primary GES4
A and so on. On the other hand, the third embodiment exemplifies a case where two GESs are associated with one communication satellite.

More specifically, the primary GES 4A according to the third embodiment includes a working GES 40A and a backup GES 40A.
41A. The working GES 40A of the primary GES 4A (hereinafter referred to as “primary working GES”) 40A is a GES operated preferentially in the primary GES 4A, and the primary communication satellite 30
Communicate with A. The spare GES (hereinafter referred to as “primary spare GES”) 41A of the primary GES 4A is a primary working GES 40.
It is provided for A in advance and communicates with the secondary communication satellite 30B.

Similarly, the secondary GES4B is the current GES4
OB and spare GES41B. This secondary GES4
B working GES (hereinafter referred to as “secondary working GES”) 40
B differs from the primary working GES 40A in that the secondary communication satellite 3
0B, the secondary GEES4B spare GE
S (hereinafter, referred to as “secondary spare GES”) 41B communicates with primary communication satellite 30A.

In the third embodiment, the primary working GES 40A and the secondary working GES 40B are operated from the start of operation. In this case, the primary spare GES4
1A and the secondary spare GES 41B are waiting. On the other hand, these four GESs 40A, 41A, 40B, 41
The same ID is assigned to B. Therefore,
From the viewpoint of AES3, it appears that one GES virtually exists. When the primary operation GES 40A and the secondary operation GES 40B are operated, the login request from the AES 3 is accepted by the primary operation GES 40. In this case, the process of determining the login destination described in the first embodiment is performed by the primary operation GES 40. The operation is performed by the operation GES 40A.

In such a situation, for example, if a failure occurs in the primary communication satellite 30A, the primary working GES 40
A cannot use the primary communication satellite 30A. Therefore, in this case, the operating GES is the primary working GES 40A.
Is switched to the primary backup GES 41A that has been waiting.
In this case, the primary backup GES 41A can accept a login request and determine a login destination.

On the other hand, when a failure occurs in the secondary communication satellite 30B, the operating GES is switched from the secondary working GES 40B to the standby secondary GES 41B which has been waiting. Since the secondary GES 4B does not have a function of accepting a login request and determining a login destination, when switching, the secondary GES 41B allows the secondary GES 41B to continue the communication process that was being executed.

The GES according to the third embodiment will be described in more detail. The primary working GES 40A and the primary spare GES 41A, and the secondary working GES 40B and the secondary spare GES 41B are all given the same ID. From the viewpoint of AES3, it appears that one GES virtually exists. In addition, the primary working GES
40A includes an antenna 50A, a transmission / reception unit 51A, and a communication control unit 52A. The primary spare GES 41A
Antenna 60A, transmitting / receiving section 61A and communication control section 62
A is provided. Further, the secondary working GES 40B includes an antenna 70B, a transmission / reception unit 71B, and a communication control unit 72B.
The secondary spare GES 41B has an antenna 80
B, a transmission / reception unit 81B and a communication control unit 82B. Here, the function of receiving the login request and the function of determining the login destination described in the first embodiment are provided in the communication control unit of the primary working GES.

Each GES 40A, 41A, 40B and 4
1B communication control units 52A, 62A, 72B and 82B
Are usually the transmitting and receiving units 51A, 61A, 7A in the same GES.
1B and 81B. More specifically, the communication control unit 52A of the primary working GES 40A
It is connected to the transmitting / receiving unit 51A of the same primary working GES 40A. Similarly, primary spare GES 41A, secondary working GE
Each communication control unit 6 of S40B and secondary backup GES41B
2A, 72B and 82B each have the same primary spare G
ES41A, secondary working GES40B and secondary spare GE
It is connected to the transmission / reception units 61A, 71B and 81B of S41B.

However, in consideration of the case where a failure occurs in the communication satellite 2, each of the communication control units 52A, 62A, 72B and 82B can be connected to the paired GES transmission / reception units.

More specifically, when a failure occurs in the primary communication satellite 30A, the communication control unit 52A of the primary working GES 40A can connect to the transmission / reception unit 61A of the paired primary backup GES 41A, The communication control unit 62A can be connected to the transmission / reception unit 51A of the paired primary working GES 40A. As a result, the primary working G
Even when the operation is switched from the ES 40A to the primary spare GES 41A, the primary spare GES 41A can execute the reception of the login request and the determination of the login destination. In addition, the communication processing that has been executed by the primary working GES 40A can be continued by the primary backup GES 41A.

When a failure occurs in the secondary communication satellite 30B, the communication control unit 82B of the secondary working GES 40B
The transmitting / receiving unit 71B of the paired secondary spare GES 41B
And the communication control unit 72B of the secondary backup GES 41B.
Is the transmitting / receiving unit 8 of the paired secondary working GES 40B.
1B. As a result, the secondary working GES40B
Can be continued in the secondary spare GES 41B.

As described above, in the third embodiment, communication control units 52A, 62A, 72B and 82B
Have a means for switching the GES as one function of the execution software.

Whether or not a failure has occurred in the communication satellite 2 can be determined by transmitting a failure occurrence signal from the communication satellite 2 to the GES 4. That is, the primary working GES40
A and the communication control units 52A, 52 of the secondary working GES 40B
2B, when receiving the failure occurrence signal from the primary communication satellite 30A and the secondary communication satellite 30B, respectively, switches the connection destination to the transmission / reception units 61A and 71B of the primary backup GES 41A and the secondary backup GES 41B. As a result, the operation can be switched from the working GES to the backup GES. This operation switching is performed by the primary GES4A and the secondary GES4A.
Performed independently in 4B. That is, for example, even if the primary GES4A is switched from working to standby,
That is, the switching is not always performed in the secondary GES4B.

The logon management unit 12 and the channel management unit 13 are provided with four GES4s as in the second embodiment.
Common to 0A, 41A, 40B and 41B. That is, four GES 40A, 41A, 40
B and 41B communication control units 52A, 62A, 72B
And 82B, a log-on management unit 12 and a channel management unit 13 are connected.

In the above description, the case where the operation is switched from the working GES to the backup GES when a failure occurs in the communication satellite 2 has been described. However, in the GES according to the third embodiment, for example, even when a failure occurs in the active GES itself, it is possible to switch to the backup GES. That is, for example, when a failure occurs in the primary working GES 40A itself, the communication control unit 52A of the primary working GES 40A sets the connection destination to the transmitting / receiving unit 61 of the primary backup GES 41A.
Switch to A. When a failure occurs in the secondary working GES 40B itself, the communication control unit 82B of the secondary working GES 40B switches the connection destination to the transmitting / receiving unit 71B of the secondary backup GES 41B.

As described above, according to the third embodiment,
Since the spare GES is provided, satellite communication can be continued even if a failure occurs in the communication satellite and / or the working GES itself.

Other Embodiments Embodiments of the present invention have been described above.
The present invention is not limited to the above embodiment.
For example, in the above embodiment, two GESs, a primary GES 4A and a secondary GE
The case where S4B is provided is taken as an example. But GES
Needless to say, the number may be three or more. In this case, any one of the three or more GESs is set as a reception GES, and the login destination is determined so that communication processing for the three or more GESs is equal in the reception GES. Specifically, three or more GESs are sequentially determined as login destinations. In this way, even when three or more GESs are provided, communication processing of each GES can be equalized.

When three or more GESs are provided, 3
The above communication satellite may be provided. Also in this case, it is sufficient that three or more GESs can separately communicate with three or more communication satellites. Further, as in the third embodiment, the working GES and the backup GES are used.
In this case, the direction of the directivity of the backup GES may be any communication satellite different from the direction of the directivity of the working GES.

Further, in the above embodiment, the logon management section 12 and the channel management section 13 have been described as having a configuration independent of the GES. However, for example, the logon management unit 12 and the channel management unit 13 may be incorporated as one function of the communication control unit 22A (52A) of the primary GES 4 (primary working GES 40A).

[0063]

As described above, according to the present invention, a login request is accepted at a reception earth station among a plurality of aeronautical earth stations to which the same earth station identification information is added,
Since the login destination is determined so that the load of the communication processing is substantially equal among a plurality of aeronautical earth stations, it is possible to prevent the loads related to the communication processing of the aeronautical earth stations from being concentrated and excessive.

[Brief description of the drawings]

FIG. 1 is a conceptual diagram showing an overall configuration of an aeronautical satellite communication system according to Embodiment 1 of the present invention.

FIG. 2 is a block diagram illustrating a configuration of a satellite communication earth station system.

FIG. 3 is a diagram showing login information of AES.

FIG. 4 is a sequence diagram for explaining communication control of a primary GES.

FIG. 5 is a block diagram showing a configuration of a satellite communication earth station system according to Embodiment 2 of the present invention.

FIG. 6 is a block diagram showing a configuration of a satellite communication earth station system according to Embodiment 3 of the present invention.

[Explanation of symbols]

1 satellite communication earth station system, 2 communication satellite, 3 AE
S, 4 GES, 4A primary GES, 4B secondary GES,
22A communication control unit, 30A primary communication satellite, 30B
Secondary communication satellite, 40A Primary working GES, 41A Primary backup GES, 40B Secondary working GES, 41B Secondary backup GES.

Continued on the front page F term (reference) 5K067 AA12 BB06 BB21 DD17 DD19 EE02 EE07 EE10 EE16 EE24 JJ02 JJ04 5K072 AA12 AA15 BB22 DD04 DD13 DD15 EE04 FF03 FF12

Claims (6)

[Claims] 1. A satellite communication earth station system for communicating with an aircraft earth station, which is a communication device mounted on an aircraft, via a communication satellite, a plurality of aeronautical earth stations assigned the same earth station identification information. When a login request transmitted from the aircraft earth station via the communication satellite is received by a predetermined reception earth station of the plurality of aeronautical earth stations, the reception earth station includes: A satellite communication earth station wherein any one of the plurality of aeronautical earth stations is determined as a login destination of the aircraft earth station so that a communication processing load is substantially equal among the aeronautical earth stations. system. 2. A satellite communication earth station system for communicating with an aircraft earth station, which is a communication device mounted on an aircraft, via a communication satellite, comprising at least one reception earth station for receiving a login request. A plurality of aviation earth stations assigned the same earth station identification information to the reception earth station, the reception earth station having at least the earth station identification information, and being required for the aircraft earth station to transmit a login request. Broadcasting means for broadcasting initial acquisition information, such that, when a login request is received from the aircraft earth station via the communication satellite, the load of communication processing between the plurality of aeronautical earth stations is substantially equal. Earth station determining means for determining an aeronautical earth station to which the aircraft earth station logs in. 3. The earth station determining means according to claim 2,
Holding logon information relating to the logon status between the aircraft earth station and the aeronautical earth station, and determining the plurality of aeronautical earth stations as the login destination of the aircraft earth station in order based on the held logon information. Satellite earth station system. 4. A satellite according to claim 2, wherein said plurality of aeronautical earth stations are associated one-to-one with a plurality of communication satellites covering one communication area. Communication earth station system. 5. The plurality of aeronautical earth stations according to claim 4, wherein each of the plurality of aerial earth stations includes a plurality of sets of a working earth station and a spare earth station which are operated preferentially, and a failure occurs in the operation of the working earth station. A satellite communication earth station system comprising means for switching to a spare earth station in such a case. 6. An earth station communication control device provided at a predetermined receiving earth station among a plurality of aeronautical earth stations communicating with an aircraft earth station which is a communication device mounted on an aircraft via a communication satellite. When the log-in request transmitted from the aircraft earth station via the satellite is received by the reception earth station, the plurality of aeronautical earth stations have a plurality of communication processing loads substantially equal to each other. A communication control device for an earth station, wherein one of the aeronautical earth stations is determined as a login destination of the aircraft earth station.