Attitude maintenance control method for orbit change based on angular velocity tracking

Abstract

The invention discloses an orbit changing attitude keeping control method based on angular velocity tracking, which comprises the following steps: according to ground simulation of an orbit changing policy, an orbit changing process is simulated, and the changing attitude angular velocity during the whole orbit changing process is calculated; a quadratic curve is used for fitting theoretical three-axis inertial angular velocities during the orbit changing period, and coefficients of the quadratic curve are noted; during an execution process, according to a star sensor and gyro information, an initial orbit changing pointing attitude is built; and during the orbit changing process, the gyro information is used for continuously tracking the quadratic curve. Thus, the gyro information is used for continuously tracking the orbit changing attitude, no restrictions exist on solar illumination and the field of view of the sensor, and the method has the advantages of high precision and strong adaptability.

Description

technical field [0001] The invention relates to an attitude tracking control method for orbit change based on angular velocity tracking, in particular to an attitude tracking control method using gyroscope information during a high-thrust orbit change. Background technique [0002] Due to the limited carrying capacity, it is impossible to directly send the satellite into the predetermined orbit. In particular, high-orbit satellites generally need to rely on their own orbit changes to enter the target orbit. Orbit change control in the transfer section is a process for general high-orbit satellites, and attitude control during orbit change is the basis for successful orbit change. [0003] At present, the commonly used method in China is to use the earth sensor and the sun sensor to determine the orientation of the earth and the sun respectively, and jointly determine the attitude orientation of the satellite during the orbit change. The prominent contradiction of this meth...

AI Technical Summary

Problems solved by technology

The prominent contradiction of this method is that the relationship between the sun, the earth, and the satellite is strongly constrained, which greatly restricts the launch window of the satellite; secondly, the earth sensor used in the orbit change attitude of some satellites has a high speed after entering the target orbit. The earth is invisible in normal posture, which causes a great waste of resources

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