A Gyro-less Sun Orientation Control Method Based on CMG

Abstract

The invention discloses a gyroscope-free sun orientation control method based on a CMG. The whole process is completed only through the CMG and a sun sensor. First, the CMG is controlled to rotate back to the nominal position, it is ensured that a synthesis angular momentum of a CMG cluster is close to zero, and at the moment, the angular velocity of a satellite body is accordingly reduced. Then,the sun direction is sensed by the 01 type sun sensor, and the satellite body is controlled by the CMG to rotate for sun searching. After sun searching succeeds, the included angle between the sun alignment axis and the sun vector is calculated in real time, the satellite body is controlled by the CMG to rotate, and a satellite is stably aligned with the sun. The whole sun searching and orientation process does not depend on gyroscope measurement information and is not controlled by jet, it is avoided that the sun orientation does not succeed due to the gyroscope failures and the fuel consumption is caused by the jet control, and the energy safety of the satellite is ensured.

Description

technical field [0001] The invention belongs to the field of spacecraft attitude control, and relates to a CMG-based gyro-free sun orientation control method. Background technique [0002] For medium and low-orbit satellites, most of the operating time of the satellite is outside the country, and there are very few arcs supported by the ground. Therefore, the satellite is required to have certain on-orbit autonomous operation and maintenance capabilities. When the system fails, it should be able to detect the failure in time, carry out the reconstruction of the attitude control system, and restore the normal operation state of the system. When the satellite fails due to various reasons such as attitude loss control, loss of reference, etc., in order to ensure the energy security of the satellite, it is necessary to control the satellite to realize the orientation to the sun and ensure the energy acquisition efficiency of the solar panels. [0003] Satellites traditionally c...

AI Technical Summary

Problems solved by technology

[0003] Satellites traditionally controlled by momentum wheels are limited by the small torque output of the momentum wheels. Generally, jet control is used for sun orientation, but jet control will consume satellite fuel, which is not good for the service life of satellites in orbit.

In addition, the existing sun orientation control algorithms all rely on the three-axis angular velocity measured by the gyroscope, but the gyroscope is prone to failure in orbit, and the gyroscope failure is the main reason for the instability of satellite attitude control. Therefore, when the health of the gyroscope is uncertain, The method is not available, limiting the scope of use

Images