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Magnetometer and sun sensor-based sun pointing method

A sun sensor and magnetometer technology, applied in attitude control and other directions, can solve the problem of long time to recapture the earth and achieve the effect of small deviation

Active Publication Date: 2017-05-10
SHANGHAI AEROSPACE CONTROL TECH INST
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Problems solved by technology

In this way, there will be the following disadvantages: that is, the randomness of the attitude of the sun axis will cause the angle of the current satellite attitude relative to the orbit to be arbitrary. Relatively long, even need to reach thousands of seconds

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  • Magnetometer and sun sensor-based sun pointing method
  • Magnetometer and sun sensor-based sun pointing method
  • Magnetometer and sun sensor-based sun pointing method

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Embodiment Construction

[0042] The following combination figure 1 with figure 2 , a preferred embodiment of the present invention is described in detail.

[0043] Such as figure 1 As shown, the sun orientation method based on the magnetometer and the sun sensor provided by the present invention is applicable to the sun orientation control of low and medium orbit satellites; wherein, assuming that the sun axis is the -Yb axis of the satellite system, then The sun sensor is installed on the -Yb surface of the satellite facing the sun.

[0044] The described sun orientation method based on magnetometer and solar sensor comprises the following steps:

[0045] S1. Calculate the sun vector azimuth information, including the coordinate components under the satellite orbit system and the satellite system; and calculate the two-dimensional attitude angle measured by the sun sensor;

[0046] S2. Calculate the orientation information of the geomagnetic field vector, including the coordinate components unde...

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Abstract

The invention relates to a magnetometer and sun sensor-based sun pointing method and is suitable for sun pointing control over a middle-low altitude satellite. The method comprises the following steps: in step S1, azimuth information of a sun vector is calculated, the azimuth information comprises coordinate components in a satellite orbit system and a satellite system, and a two dimensional attitude angle measured by a sun sensor; in step S2, azimuth information of a geomagnetic field vector is calculated, the azimuth information comprises coordinate components in the satellite orbit system and the satellite system; in step S3, a sun pointing axis is subjected to attitude calculation operation, and a pitch attitude of the satellite system relative to the satellite orbit system in a sun pointing state can be obtained according to a determined double vector attitude of the sun and the geomagnetic field; in step S4, the pitch attitude which is obtained via the two dimensional attitude angle measured via the sun sensor and the determined double vector attitude is used as an attitude control standard, and stable stabilization control of three sun pointing axes can be realized. Via the method, sun pointing stability in an all attitude mode can be ensured, and minimum deviation of stable attitudes of the three sun pointing axes can be guaranteed.

Description

technical field [0001] The present invention relates to a sun-orientation method, in particular to a sun-orientation method based on a magnetometer and a sun sensor, which is suitable for the sun-orientation of low- and middle-orbit zero-momentum satellites. Background technique [0002] When the satellite's attitude is unstable, it will enter the safety control mode. At this time, the information of the sun sensor is used as the control reference, so that the sunlight can directly illuminate the solar panels of the satellite, thereby ensuring the energy supply of the entire satellite. [0003] Because the sun sensor can only measure two-dimensional angles, when only the sun sensor information is used as the control reference, it can only ensure that the sun axis is parallel to the sun, but the stable control of the sun axis is missing. In view of this situation, the method currently adopted is to make the sun axis in an uncontrolled state, or in a slow rotation state. In t...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08
CPCG05D1/08
Inventor 张艳召吴敬玉陈秀梅李小斌
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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