JPH0691486B2 - Azuele antenna tracking method - Google Patents

Description

The present invention relates to a tracking method for an as-ele antenna ( _AZ- El antenna).

It is necessary to track the satellite using a parabolic antenna to catch the flight status of the satellite. In tracking such an artificial satellite, it is desirable to be able to determine whether or not the tracking is possible without being influenced by the antenna installation position and the orbit of the artificial satellite, and to control the tracking of the antenna without any trouble if possible. .

[Conventional technology]

As shown in Fig. 4, the azimuth ( _AZ ) operating range of the As-ele antenna currently used in artificial satellite tracking stations (the antenna used by the Japan Space Agency is also this antenna). In such an operating range, the azimuth angle A _S at the start of the artificial satellite path is the quadrant I and the quadrant I in FIG.
In the case of II quadrant, whether to wait for the artificial satellite in the clockwise direction (CW) region or the counterclockwise direction (CCW) region is determined by using the azimuth angle A _S and the maximum azimuth angle A _M in the path. I am doing it.

[Problems to be solved by the invention]

In the determination technique using such A _S and the maximum azimuth angle A _{M in} the path, when the artificial satellite path normally occurs, for example, from quadrant I to quadrant IV in FIG. Does not hinder the above judgment, but a specific path (path 1 is CCW; path 2 is
When CW) occurs, the judgment cannot be made.

That is, as described above, in both path 1 and path 2 shown in FIG. 5, A _S is in the second quadrant, and when passing through the meridian (0 °), A _M for both paths is Because it becomes 360 °,
It is the conventional determination method of rotating the as-ele antenna that the rotation direction of the antenna is determined to be clockwise (CW).

This judgment is correct for Path 2 but not for Path 1, so if you try to rotate the antenna under that judgment, you will not be able to turn the antenna after the 180 ° meridian, Will be impossible and you will lose sight of the satellite.

In the case where A _S is the III quadrant and the IV quadrant, it may not constitutes a determination of whether or not may track the path.

[Means for solving problems]

The present invention provides a tracking system for an asele antenna that can solve the above-mentioned problems. The means detects azimuth information and meridian passage information at the start of a satellite path, and responds to these information by the asele antenna. The initial position and rotation direction of the antenna within the working range and the propriety of the tracking are determined to cause the tracking of the as-ele antenna.

[Action]

According to the method of the present invention, since the initial position and the rotation direction within the operating range of the Azuele antenna and the possibility of tracking thereof are determined from the azimuth angle and the meridian passage information at the start of the artificial satellite path, the artificial satellite path is No matter what specific path appears, it will not hinder the above determination. Therefore, the reliability of the determination is significantly improved.

〔Example〕

Hereinafter, embodiments of the present invention will be described with reference to the accompanying drawings.

FIG. 1 is a flow chart for explaining one embodiment of the present invention. As shown in this flowchart, it is determined whether or not the azimuth angle at the start of the pass (the azimuth angle at the beginning of the view) A _S is in the first quadrant or the second quadrant of the operating range of the as-ele antenna shown in FIG. (Step S1). This A _S is provided by the flight detection system.

If A _S is in quadrant I or quadrant II, then in step S2 a determination is made whether the path passes the meridian. The judgment information is given from the flight detection system. If it does not pass (N in step S2), CW or
Control of the tracking control device is generated by any of the CCWs (step S3).

If the passage of the meridian line has occurred (Y in step S2), it is determined in step S4 whether or not the first meridian passage pattern (see FIG. 3) is the pattern. If it is a pattern, the tracking initial position of the Azuele antenna is
Tracking control that causes the rotation direction to be the CW direction in the CW region is generated (step S5). Then, if the number of times of passage through the meridian is less than 3 times (the number of times determined by the number of determinations in step S6) in the path (N in step S6), the tracking control is continued, that is, the tracking of the artificial satellite is performed clockwise. Can be tracked. When the number of times of passage through the meridian exceeds three times (Y in step S6), it is determined in step S7 whether the meridian passage pattern is →→ or →→, and the determination is negative. If so (N in step S7), the tracking control is continued. On the other hand, the determination in step S7 is affirmative, that is, it is determined from the meridional passage pattern in this case that the flight trajectory of the artificial satellite is in an untraceable flight trajectory (Y in step S7). , Its tracking control is no longer possible (step S8).

If it is determined in step S4 that the meridian passage pattern is a pattern, the tracking initial position of the Azuele antenna is in the CCW region, and the tracking control in which the rotation direction is the CCW direction is generated (step S9). And
If the number of times of passage through the meridian is less than 3 times (the number of times determined by the number of determinations in step S10) (N in step S10), the tracking control is continued, that is, the tracking of the artificial satellite can be correctly tracked counterclockwise. it can.

However, the number of times of passage through the meridian exceeds 3 (Y in step S10), and the meridian passage pattern is →→ or →→.
It is determined in step S11 which of the above is the case, and if the determination is negative (N in step S11), the above tracking control is continued. On the other hand, the determination in step S11 becomes affirmative, that is, it is determined from the meridian passage pattern in this case that the flight trajectory of the artificial satellite has a flight trajectory that cannot be traced (step S11 Y), its tracking control is no longer possible (step
S12).

The determination in step S1 is negative, that is, A _S is in quadrant III or IV.
If it is a quadrant (N of step S1), the process proceeds to step S12, and if the number of times of meridian passage in one pass is two or more and two consecutive meridian passage patterns are → or → (step N) tracking control of S12 is performed, but on the contrary, the judgment is affirmative, that is, it is judged from the value of A _S and the meridian passage pattern that the satellite's flight trajectory is in a flight trajectory that cannot be tracked. Therefore, tracking control is impossible (step S13).

In addition, in the said Example, although the example which uses the number of meridian passages and a meridian passage pattern as meridian passage information was demonstrated, you may add meridian passage time to these information. Also, the case where the azimuth angle at the start of the pass is in the quadrant I or the second quadrant has been described, but when the azimuth angle at the start of the pass is in the other two quadrants, the reference line corresponding to the azimuth angle is passed. The information should be used. Of course,
In this case, the tracking mode of the tracking station is also changed correspondingly.

〔The invention's effect〕

As described above, according to the present invention, it is possible to make an accurate determination for a path of an artificial satellite, regardless of what specific path the satellite path appears in. Therefore, the reliability of the determination Has the effect of being significantly improved.

[Brief description of drawings]

1 and 2 are flowcharts for explaining an embodiment of the present invention, FIG. 3 is a diagram showing a meridian passage pattern, FIG. 4 is a diagram showing an operating range of a conventional as-ele antenna, and FIG. The figure is a diagram showing an example of a path that cannot be determined by the conventional technique. In the figure, I and II indicate the quadrants I and II of the asele antenna operating range, and the meridian passage patterns.

Claims (1)

[Claims] 1. An azimuth information and a meridian passage information at the start of a satellite path are detected, and in response to the information, an initial position and a rotation direction within an operating range of an Azuele antenna and its propriety are determined. A tracking method for an as-ele antenna, wherein tracking control for the as-ele antenna is produced.