Method and system for obtaining attitude of three-axis stabilized satellite without gyroscope

A technology of satellite attitude and acquisition method, applied in directions such as integrated navigators, can solve the problems of large satellite attitude drift, affecting the normal operation of satellites, and limiting the accuracy of satellite attitude dynamics model, so as to improve the estimation accuracy and improve the continuous efficiency. The effect of reduced performance and accuracy requirements

Active Publication Date: 2017-05-31
SHANGHAI AEROSPACE CONTROL TECH INST
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Problems solved by technology

[0004] At present, the three-axis satellite attitude determination and control system without gyroscope generally only uses star sensors to estimate the satellite attitude and attitude angular velocity, and is limited by the accuracy of the satellite attitude dynamic model when the data of the star sensor is invalid for more than ten minutes , the satellite attitude will gradually drift, which may affect the normal operation of the satellite

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  • Method and system for obtaining attitude of three-axis stabilized satellite without gyroscope
  • Method and system for obtaining attitude of three-axis stabilized satellite without gyroscope
  • Method and system for obtaining attitude of three-axis stabilized satellite without gyroscope

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[0036] Specific embodiments of the present invention will be further described below in conjunction with the accompanying drawings.

[0037] Such as figure 1 As shown, the present invention discloses a method for obtaining the attitude of a three-axis stabilized satellite without using a gyroscope. The method includes:

[0038] S1. Use the satellite attitude dynamic equation as the state equation about the satellite inertial angular velocity, use the satellite attitude angle acquisition value and the satellite attitude kinematics equation to obtain the observation equation of the inertial angular velocity, and obtain the angular velocity acquisition gain coefficient matrix and inertia by the Kalman acquisition method Error variance matrix for angular velocity acquisition.

[0039] The coupling interference moment of a satellite with a large flexible appendage to the satellite can be ignored when the attitude is stable, so the attitude dynamic equation of the satellite is desc...

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Abstract

The invention discloses an attitude estimation method of a three-axis stabilized satellite without a gyroscope. The method comprises the steps of estimating an inertial angle velocity of the satellite by using a satellite attitude dynamics equation, thereby replacing inertial reference units of measuring the angle velocity of the satellite; carrying out filtering estimation on an attitude determining value by using a satellite kinematics equation, a star sensor, an infrared earth sensor and a digital sun sensor; and carrying out satellite attitude angle estimation by using attitude determining angles of the star sensor, the infrared earth sensor and the digital sun sensor and taking an attitude measurement value of the star sensor as a benchmark. The beneficial effect that different inertial reference units carry out satellite attitude angle and attitude angle velocity estimation by adopting the star sensor, the infrared earth sensor and the digital sun sensor to improve the reliability of a satellite attitude and orbit control system is obtained.

Description

technical field [0001] The invention relates to the technical field of satellite attitude determination, in particular to a method for acquiring the attitude of a three-axis stable satellite without using a gyroscope. Background technique [0002] High-precision and high-stability three-axis stable satellite attitude determination system is generally equipped with a high-precision inertial reference unit to measure the inertial angular velocity of the satellite, and is also equipped with a high-precision optical sensor such as a star sensor. For an inertial reference unit with a rotational speed component (gyroscope), it is difficult to meet the requirement of long life, or a higher cost is required. The optical sensor is easier to achieve long life. Judging from the in-orbit operation of domestic high-precision and high-stability three-axis stable satellites, the probability of failure of the gyroscope of the inertial reference unit is higher than that of optical sensors s...

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Application Information

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IPC IPC(8): G01C21/24
Inventor 王新钟超李小斌陈为伟石晓涵
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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