An Inertial Navigation Navigation Correction Method Based on Cosine Scanning of Pass-in-Motion Antennas

Abstract

The invention discloses a communication-in-motion antenna cosine scanning inertial navigation course correction method. A cosine scanning method is adopted to search a satellite signal; only rotation of an azimuth axis exists in the method and pitching motion can be omitted, so that control complexity can be lowered; in addition, when a becoming machine is not high in precision, a signal deviation curve is obtained by a circular cone scanning mode, and randomness occurs, so that the method is more suitable for communication-in-motion equipment with not high becoming machine precision, thereby further saving cost; through an AGC signal difference value, the antenna azimuth deviation can be compensated through a proportion control method; a mode adopting the AGC signal maximum value inverse solution navigation course for azimuth compensation is performed; and by adoption of the method, the linear relation between AGC signal cosine scanning left and right difference value and azimuth deviation angles and the optimal linear coefficient can be found, so that a complex calculation process can be omitted; and in addition, through proportional control, compensation can be more stable, and click disturbance can be lower.

Description

technical field [0001] The invention belongs to the technical field of satellite communication, and in particular relates to an inertial navigation direction correction method for antenna cosine scanning in motion, which is suitable for occasions where low-cost inertial navigation requires the system to maintain the accuracy of antenna tracking satellites for a long time. Background technique [0002] Communication in motion is a broadband mobile satellite communication system that uses fixed service satellite resources and antenna systems installed on carriers to establish and maintain satellite links between carriers and target satellites in static and moving states. Its essence is to keep the antenna azimuth, pitch, and polarization three-dimensionally aligned with the satellite at all times while in motion. Under the existing technical conditions, most mobile communication products need expensive attitude and heading reference system AHRS (Attitude and heading reference ...

AI Technical Summary

Problems solved by technology

However, the heading angle of the inertial navigation system does not meet the Shura oscillation period, and its error increases with time. During the long-term use of the inertial navigation system, there will be a large error accumulation in the heading angle, which will lead to the continuous deterioration of the satellite pointing accuracy of the antenna system.

Simply relying on the high-precision navigation technology of the inertial navigation system to realize the long-term high-precision satellite signal tracking function of the mobile communication antenna system, the cost is relatively high. How to overcome the disadvantages of the low-cost inertial navigation system that the heading angle error accumulates over time and achieve long-term uninterrupted The high-precision and stable satellite tracking function of the antenna system under running conditions is a difficulty in the current communication system based on the inertial navigation scheme

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