Solar capture method based on angular velocity estimation information and solar sensor

Abstract

The invention discloses a solar capture method based on angular velocity estimation information and a solar sensor. The method comprises the following steps of: estimating an inertial angular velocityof a satellite body in real time by utilizing dynamic and kinematic equations of the satellite body; measuring a specific azimuth of the sun appearing on a satellite and an estimation value of an inertial angular velocity of the satellite by using a 0-1 type solar sensor, and searching the sun so that the simulated solar sensor faces the sun; calculating a two-dimensional attitude angle accordingto the measurement information of the simulated solar sensor; controlling the satellite attitude capture by utilizing the two-dimensional attitude angle of the simulated solar sensor and the satellite inertial angular velocity estimation information, and reducing an included angle between a sun vector and a certain axis of the satellite body, so that the sun is captured by the sun-facing orientation surface of the satellite. According to the method, the sun is searched by utilizing the inertia angular velocity estimation information and the 0-1 type solar sensor, the sun is captured by utilizing the inertia angular velocity estimation information and the simulated solar sensor, and the energy supply and attitude stability of the satellite under a full-attitude mode are ensured.

Description

technical field [0001] The invention relates to the technical field of satellite attitude control, in particular to a method for capturing the sun based on angular velocity estimation information and a sun sensor. Background technique [0002] When the satellite's orbital attitude is unstable, the control system will switch to the full-attitude sun capture mode. The function of this mode is to make the normal direction of the solar panels of the satellite basically consistent with the sun vector direction, so as to ensure the energy supply of the entire satellite. [0003] At present, satellites generally use an attitude determination system composed of sun sensors and inertial sensors to capture the sun, so that the sun's light can illuminate the solar panels vertically. However, since this method relies on the inertial sensor to always provide effective satellite inertial angular velocity information during the process of the satellite capturing the sun, once the satellit...

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Problems solved by technology

However, since this method relies on the inertial sensor to always provide effective satellite inertial angular velocity information during the process of the satellite capturing the sun, once the satellite inertial sensor fails when it is in orbit, it cannot provide real continuous and effective satellite inertial angular velocity information. Sun capture would not be possible, a situation that would have adverse consequences for the energy security of the entire star

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