Scanning control method of antenna azimuth axis in SOTM satellite finding

An antenna orientation and scanning control technology, which is applied in the field of satellite communication, can solve the problems of antenna star-finding accuracy reduction, system stability impact, antenna system azimuth axis mis-scanning, etc., to ensure satellite pointing accuracy, improve retrieval success rate, and retrieve The effect of looser conditions

Active Publication Date: 2016-02-24
BEIJING INST OF AEROSPACE CONTROL DEVICES
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Problems solved by technology

However, if the moment of inertia of the antenna is large, the instantaneous start and stop of the antenna will affect the stability of the system, and the long-term operation will reduce the reliability of the antenna system, resulting in the reduction of the initial star-finding accuracy of the antenna.
[0005] Therefore, how to avoid the instability of the antenna system caused by the sudden start and stop of the antenna in the case of large dynamic carrier, and solve the problem of misscanning of the azimuth axis of the antenna system is a key to realize the accurate alignment of the antenna to the satellite during the satellite search in motion. difficulty

Method used

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  • Scanning control method of antenna azimuth axis in SOTM satellite finding
  • Scanning control method of antenna azimuth axis in SOTM satellite finding
  • Scanning control method of antenna azimuth axis in SOTM satellite finding

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Embodiment

[0067] The preset acceleration and deceleration increment FSLOPE=0.0005°, the low-speed angular rate FVSLOW=6° / s, the maximum angular rate FVMAX=40° / s, and the control period T=0.005s, the drive control diagram realized by the present invention is figure 2 Shown. figure 2 The middle section 1 is the acceleration state section, the second section is the rotation section after accelerating to the maximum angular rate, the 3 section is the deceleration state section after the signal maximum point is found, and the 4 section is the final reverse state section. From figure 2 It can be seen that the scanning process of the azimuth axis of the entire antenna system is very smooth, and there is no big action of sudden start and stop. And when the maximum value of the satellite signal is detected, the antenna system is also smoothly decelerating. When the rotation angular velocity is decelerated to zero speed, since the range of the reversal angular velocity setting is appropriate, th...

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Abstract

The invention provides a scanning control method of an antenna azimuth axis in SOTM (Satcom On The Move) satellite finding. According to the method, on the basis of tracking carrier motion by an antenna, the antenna azimuth axis is driven to carry out whole ring scanning through an accelerating process, and a satellite signal is recorded. Then the secondary method fuzzy retrieval mechanism of the satellite signal is utilized, the effective range of the satellite signal is determined, and an antenna decelerating process is started to carry out deceleration. Finally after the antenna is decelerated to a preset rate, an antenna inverted rotation process is set, the antenna is controlled to reversely rotate to a satellite signal strongest point, and the scanning driving control in antenna azimuth axis satellite finding is completed. According to the method, the system instability problem caused by antenna sudden stop and start moments is solved, and through implementing an effective satellite largest signal determining mechanism, the scanning control in antenna azimuth axis satellite finding is realized.

Description

Technical field [0001] The invention provides a scanning control method for the azimuth axis of the antenna when the satellite is on the move, which is suitable for the occasion that the azimuth axis of the antenna is required to quickly and stably scan to the maximum value of the satellite signal when the satellite is on the move, and belongs to the technical field of satellite communication. Background technique [0002] When the inertial navigation scheme-based moving antenna system seeks stars, the inertial navigation system uses the initial alignment method to calculate the current pitch angle P, roll angle R and heading angle Y of the carrier, and then guides the antenna to point to the target satellite through coordinate conversion. Due to algorithm errors and calculation errors, there are also errors in the initial alignment of the inertial navigation system under large dynamics of the carrier, which will inevitably reduce the accuracy of the inertial navigation system gui...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H01Q3/06
CPCH01Q3/06
Inventor 郭涛王盛邬江
Owner BEIJING INST OF AEROSPACE CONTROL DEVICES
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