Under-actuated control method suitable for damping angular velocity of satellite attitude

Abstract

The invention discloses an under-actuated control method suitable for damping the angular velocity of a satellite attitude. The method includes firstly determining a satellite control failure shaft and two normally working shafts, and determining the angular velocity offset value of the two normally working shafts according to the size relation between main inertias of the two normally working shafts and the actual attitude angular velocity of the failure shaft; then determining the angular velocity deviation according to the actual attitude angular velocity of the angular velocity offset value of the two normally working shafts, and obtaining control moments of the two normally working shafts according to the angular velocity deviation; and controlling the angular velocities of the three shafts through the control moments until all angular velocity deviations of the three shafts are smaller than an angular velocity deviation expectation amplitude. The control method is simple in algorithm, good in dynamic behavior and high in project operability.

Description

technical field [0001] The invention relates to a satellite attitude control method, in particular to an underdrive control method suitable for satellite attitude angular velocity damping. Background technique [0002] Satellites in orbit generally have jet control and control based on angular momentum management devices (such as flywheel / momentum wheel, control moment gyro, etc.). The control based on the angular momentum management device is generally only used for attitude control under normal conditions due to the constraint of limited angular momentum. Jet control has a large torque and no angular momentum constraints, and can effectively damp the initial angular velocity of a large star. Therefore, it is often used in the satellite orbit stage, the sun safety emergency mode under system abnormalities, and the safety mode transition. Normal ground and other occasions. [0003] For a spacecraft with angular momentum bias in the Y-axis direction, the dynamic equation un...

AI Technical Summary

Problems solved by technology

The gyroscope used to measure the angular velocity of the satellite has a certain range, that is, when the angular velocity of the star exceeds a certain value, the output of the gyroscope is saturated and cannot be sensitive to the actual angular velocity of the star's attitude.

Without considering the actual engineering constraints, even if the designed underactuated control law can theoretically guarantee system stability and state convergence, it may not be possible to obtain the correct star when the angular velocity of the star exceeds the gyro measurement range during the control dynamic process. The angular velocity causes the system to become unstable

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