JPS6022803A - Controller of satellite tracking antenna - Google Patents

Abstract

PURPOSE:To attain the miniaturization and simplicity of the structure of an axis driving section by providing a zenith tracking means forecasting orbit to a satellite tracking antenna controller of three-axis mount structure. CONSTITUTION:A tracking receiver 2 receives a radio wave output of an antenna 1 and gives an automatic tracking error signal to an elevating angle control circuit 3, an azimuth angle control circuit 5 and an orthogonal elevating angle control circuit. Each control circuit controls the attitude of the antenna 1 by using respectively mechanical systems 15-17. In the automatic tracking mode, the elevating angle and the azimuth angle of the antenna are controlled via the mechanical systems 15, 17, the elevating angle and azimuth angle data at that time are detected by detectors 12, 14 and fed to a zenith tracking device 18. The zenith tracking device 18 forecasts an orbit of a satellite based on the data and when it is discriminated that the satellite approaches the vicinity of the zenith and the driving speed of the vertical axis exceeds a prescribed value, the mode is changed over into the zenith mode and the preceding drive by using the three axes where the vertical axis is driven in a constant speed is conducted.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of the Invention] The present invention relates to a control device for an antenna device having a five-axis mount structure. In particular, the present invention relates to an antenna control device for continuously and automatically tracking satellites passing near the zenith.

[Description of prior art]

In the conventional 6-axis mounted aerial device, which has image configurations on the vertical axis, horizontal axis, and orthogonal horizontal axes, the control angle range of the orthogonal horizontal axes needed to be wide when tracking a satellite passing the zenith. . This means that the larger the antenna diameter, the more complex the structure of the three-axis mount, and the smaller the shape.
Therefore, the mount itself becomes large, and the device becomes expensive and large in size due to the increase in the capacity of the drive motor and the capacity of the motor drive amplification section.

[Purpose of the invention]

The present invention eliminates the above-mentioned drawbacks and provides a control device for simplifying and downsizing the structure of the drive section of the mounted antenna device 6. The objective is to provide the following.

[Key points of the invention]

The present invention consists of a vertical axis whose azimuth angle can be changed, a horizontal axis whose elevation angle can be changed, and an orthogonal horizontal axis which is on this horizontal axis and is mounted perpendicularly and whose angle can be changed.
Satellite tracking aerial 1st pier control system fe that controls each of the above six axes so that the aerial beam supported by the axis is received by the antenna 16 and the radio wave intensity from space flying objects including satellites and rockets is maximized. ? A zenith tracking device is provided with a zenith tracking GfL configured to calculate a trajectory prediction by extrapolation.

[Explanation based on examples]

FIG. 1 shows the configuration of an apparatus according to an embodiment of the present invention. In Fig. 1, the radio wave output of the antenna 1, which has an axis configuration of a vertical axis for tracking, a horizontal axis, and an orthogonal horizontal axis, is received by the tracking receiver (g machine 2), and the automatic tracking error is the output of the tracking receiver Sakura 2. The signal has an elevation angle of 1j1
] control circuit 3, azimuth control circuit 5, and orthogonal elevation control circuit 4. The output of the elevation control circuit 3 drives a motor 9 via an amplifier 6, and its rotational output is sent to a mechanical system 15.
The elevation angle of the antenna 1 is controlled via. Similarly, the azimuth angle is also controlled by the control circuit 5, amplifier 6, motor 11, and mechanical system 17. With such a configuration, the elevation angle and azimuth angle are controlled and automatic tracking is performed.

Here, the feature of the present invention is that the azimuth angle and elevation angle during automatic tracking are detected by the detector 12 and the detector 14, and are provided to the zenith tracking device 18, and the zenith tracking device 18 uses the azimuth angle and the elevation angle to Prediction calculation ``! The goal is to heal.

Next, the operation will be explained based on FIG. Initial acquisition of the satellite has already been completed, and the antenna is now at a reception level that allows automatic tracking. If the rotation of the horizontal axis is not within the lower limit, tracking is performed in an automatic tracking mode in which tracking is performed along the vertical and horizontal axes. During this period, the above-mentioned orbit prediction calculation is performed, and as the satellite approaches the zenith, the required driving speed of the vertical axis will increase, but if it is determined that this speed exceeds the maximum driving speed of the vertical axis, the automatic tracking mode will be set to the zenith. Switching to the tracking mode, tracking on the horizontal axis and orthogonal horizontal axes and advance driving at a constant speed on the vertical axis are performed. Furthermore, when the satellite passes the zenith and the two elevation angles become less than a predetermined angle, the vertical axis constant speed drive ends and the automatic tracking mode returns again. The tracking operation ends when the rotation of the horizontal axis reaches the lower limit.

FIG. 3 shows a tracking trajectory when driving without correcting the trajectory prediction results. The predicted satellite orbit shows passage directly above the antenna device, ie at an elevation angle of 90'. Let the radial velocity be 15 degrees per second,
The vertical and horizontal axes trajectories when the vertical axis maximum speed is 100 per second are shown by solid lines, and the trajectories when automatic tracking by the horizontal and orthogonal horizontal axes is performed from the state of the solid lines are shown by broken lines. The vector amount indicates the amount of correction on the horizontal axis and the orthogonal horizontal axis.

Figure 4 shows the case where the vertical axis is driven in advance from an elevation angle of around 765° under the same conditions as Figure 2, and the vector amounts to be corrected for the horizontal axis and orthogonal horizontal axis are smaller than in Figure 2. . This clearly shows that the driving angle range of the orthogonal horizontal axes is limited.

FIG. 5 shows the correction amount of the horizontal axis and the orthogonal horizontal axis at the maximum elevation angle during vertical axis advance driving. It can be seen that under the conditions shown in FIG. 4, the control range of the orthogonal horizontal axes may be 5 degrees in the orbit in which the satellite passes through the zenith. In addition,
In Figures 3, 4, and 5, EL is the elevation angle, AZi is the azimuth angle, EL axis is the horizontal axis, and Or OS 8
-EL The L axis indicates the orthogonal horizontal axis.

〔Effect of the invention〕

Since the drive angle range of the orthogonal horizontal axes can be narrowed compared to the advance drive of the vertical axis, limited drive is possible, which has the effect of simplifying the orthogonal horizontal axis structure in the antenna device. Furthermore, the capacity of the motor required for driving can be reduced by limiting the driving range.

[Brief explanation of drawings]

FIG. 1 is a block diagram of an apparatus according to an embodiment of the present invention. FIG. 2 is a flowchart showing the tracking operation. Figure 3 shows the tracking trajectory when the vertical axis data is not corrected. Figure 4 shows the tracking trajectory when the vertical axis data is corrected. Figure 5 shows the amount of correction for the horizontal axis and orthogonal horizontal axis using the maximum elevation angle tube parameter. 1... Antenna, 2... Tracking receiver, 3.4.5...
・Control circuit, 6.7.8...Amplifier, 9.10.11
... Drive motor, 12.13.14... Angle detector, 15.16.17... Mechanical system, 18... Zenith tracking device. 4? Applicant: Nissui Denki Co., Ltd. Agent: Naotaka Ide, patent attorney Figure 1 Figure 3

Claims (1)

[Claims] (1) 5 having a vertical axis that can change the azimuth angle, a horizontal axis that can change the elevation angle, and an orthogonal horizontal axis that is located on the horizontal axis and is installed perpendicular to the horizontal axis and whose angle can be changed. In a satellite tracking antenna control system that fully controls each of the above three axes so that the antenna supported by @11 and the radio wave intensity received by this antenna from spacecraft including satellites and rockets are maximized, 1. A satellite tracking antenna control device comprising: a zenith tracking device configured to calculate an orbit prediction based on the method, the zenith tracking device being configured to command advance driving of the vertical axis.