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Airborne Antenna High-precision Pointing Tracking Method Based on Stable Strapdown and Attitude Tracking

A technology of stable tracking and pointing tracking, which is applied to antennas, antennas, electrical components and other directions suitable for movable objects, and can solve the problems of low availability, poor accuracy and strong dependence of single-pulse self-tracking

Active Publication Date: 2016-09-28
CHINA ELECTRONICS TECH GRP NO 39 RES INST
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Problems solved by technology

[0009] In order to overcome the problems of poor accuracy and strong dependence of program tracking and solve the problem of low availability of monopulse self-tracking, this invention proposes a high-precision pointing tracking method for airborne antennas based on strapdown attitude stable tracking

Method used

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  • Airborne Antenna High-precision Pointing Tracking Method Based on Stable Strapdown and Attitude Tracking

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Embodiment Construction

[0022] Describe the present invention below in conjunction with specific embodiment:

[0023] Refer to attached figure 1 , the airborne antenna high-precision pointing and tracking method based on strapdown attitude stabilization tracking in this embodiment adopts the following steps:

[0024] Step 1: Start the strapdown attitude system. Before the aircraft takes off, the main inertial navigation system of the aircraft will transmit the longitude, latitude and satellite azimuth of the starting point of the aircraft to the strapdown attitude system, and the strapdown attitude system will complete the initial alignment ; The strapdown attitude system includes a three-axis fiber optic gyroscope, a three-axis accelerometer and a computing platform;

[0025] Step 2: After the aircraft takes off, the strapdown attitude system enters the state of inertial navigation. The strapdown attitude system follows and detects the attitude changes and position changes brought about by the move...

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Abstract

The present invention proposes an airborne antenna high-precision pointing and tracking method based on strapdown attitude stable tracking. First, the strapdown attitude system completes the initial alignment, and secondly, the strapdown attitude system enters the state of inertial navigation. When it can accept satellite tracking signal, the strapdown attitude system enters the integrated navigation state. When the satellite tracking signal is interrupted, the strapdown attitude system takes the state of the aircraft body at the moment before the satellite tracking signal is interrupted as the initial state to re-enter the inertial navigation state; according to the azimuth angle of the aircraft , satellite positioning longitude, etc. to obtain the azimuth, height, and polarization angle code disk values ​​required by the aircraft's airborne antenna to correctly track the satellite, and then drive the airborne antenna to rotate to the corresponding code disk value, so as to isolate the movement of the body and align the airborne antenna to the satellite . The invention overcomes the problems of poor precision and strong dependence of program tracking, and also solves the problem of low usability of monopulse self-tracking, and proposes a new research direction for high-precision pointing and tracking of airborne antennas.

Description

technical field [0001] The invention relates to the technical field of airborne antenna servo control, in particular to an airborne antenna high-precision pointing and tracking method based on strapdown attitude stable tracking. Background technique [0002] Airborne satellite communication systems are developing rapidly, and more and more aircraft are installed on them. Airborne antennas need to track geosynchronous satellites accurately and quickly. [0003] Usually the method used is a program algorithm (we call it program tracking here). It uses the aircraft inertial navigation system (hereinafter referred to as inertial navigation) / GPS to measure the geographic longitude, latitude, and altitude of the aircraft, and the inertial navigation system gives the aircraft attitude parameters (the aircraft's heading angle relative to the true north direction, the aircraft's roll relative to the horizontal plane) angle, the pitch angle of the aircraft relative to the horizontal ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): H01Q1/28H01Q3/08
Inventor 艾文光王双平雒俊鹏张静
Owner CHINA ELECTRONICS TECH GRP NO 39 RES INST
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