Satellite yaw controlling and guiding method

Abstract

The invention provides a guide rule designing method in yaw gesture control over a satellite. The method comprises the following steps that firstly, the track solar angle (an angle beta for short) and a sun vector under a track system are calculated; secondly, when the angle beta is larger than or equal to a given threshold value, a target yaw angle is calculated according to a current track system sun vector, and when the angle beta is smaller than the given threshold value, the target yaw angle is calculated according to a hypothesis sun vector with the angle beta being an assigned angle; thirdly, when the angle beta crosses zero and when it is met the condition that the target yaw angle is a small angle at the same time, a calculation method of the target yaw angle is switched.

Description

technical field [0001] The invention belongs to the technical field of spacecraft attitude control, and relates to a guidance law design method when a satellite performs yaw attitude control. Background technique [0002] Due to the large variation range of β angle of satellites in inclined orbit, in order to meet the energy demand, one-dimensional rotating solar panels are usually installed on the satellites. . [0003] During the long-term steady-state operation of the satellite, the reaction wheel is usually used for attitude control. By controlling the yaw attitude, the sun vector is controlled in the XOZ plane of the star and the +X axis of the satellite points to the sun. But when the β angle is small (that is, the sun, the earth and the satellite are close to one line), the maximum angular velocity of the target attitude change reaches more than 10° / s. like figure 1 Shown is a schematic diagram of the change of the satellite target yaw attitude angle in one orbit u...

AI Technical Summary

Problems solved by technology

In the process of attitude stabilization, the accuracy of the sailboard to the sun cannot meet the requirements

[0004] The traditional method to solve the above problems is to perform yaw control when the β angle is greater than 5°, according to figure 1 The target attitude angle adjusts the satellite attitude; when the β angle is less than or equal to 5°, the yaw adjustment is not performed, the satellite is stabilized on the ground in three axes, and the sun is tracked by turning the sailboard from 0 to 360°, but at this time the sun is in the XOZ plane of the satellite The ±X plane and ±Z plane of the satellite are illuminated in turn, which is not conducive to the thermal control of the whole satellite, affects the accuracy of the ground orbit determination, and the satellite needs to switch the attitude control mode

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