A point-to-point attitude maneuver intelligent trajectory planning and adjustment method

Abstract

The invention relates to a point-to-point attitude maneuver intelligent track planning and adjusting method. When a maneuver task is judged to be in a satellite maneuver capacity range according to the maximum attitude maneuver angular velocity, the shortest attitude maneuver acceleration time and the required stabilization time after the attitude maneuver is in place of a satellite and the maneuver in-place time expected by the point-to-point attitude maneuver task, a point-to-point attitude maneuver track is intelligently adjusted, the adjusting parameters are the maximum maneuver angular velocity and the angular acceleration in a attitude maneuver process, and then the track planning in a point-to-point maneuver process is carried out according to the adjusted attitude maneuver parameters. The adjustment amount of the parameter changes along with the change of the task execution reservation time. On the premise of ensuring that the satellite maneuvers to a target attitude within thespecified time, the maximum attitude maneuver angular velocity and the maximum attitude maneuver angular acceleration in the attitude maneuver process are reduced. In the maneuver process, the momentoutput by an actuating mechanism is reduced, the gyro moment borne in the maneuver process is reduced, and the service life of the actuating mechanism is prolonged.

Description

technical field [0001] The invention belongs to the field of spacecraft attitude control, and relates to a point-to-point attitude maneuver intelligent trajectory planning and adjustment method. Background technique [0002] Satellite attitude maneuvering ability is getting stronger and stronger, which is reflected in the fast maneuvering speed and the large number of maneuvers, which put forward higher requirements for the actuator (mainly CMG), including the ability to output large torque during maneuvering and the total output of large torque. frequency. At the same time, the on-orbit life of satellites is constantly improving, which puts forward higher requirements for the reliability and life of actuators. [0003] In the process of frequent rapid attitude maneuvers, the bearings of the CMG are frequently subject to large radial forces, which affects the fatigue life of the high-speed bearings and induces the failure of the CMG frame control. Existing satellites in-or...

AI Technical Summary

Problems solved by technology

[0003] During frequent rapid attitude maneuvers, the bearings of the CMG are frequently subjected to large radial forces, which affects the fatigue life of the high-speed bearings and induces CMG frame control failures

Existing satellites in-orbit attitude maneuvers are performed according to the maximum maneuverability of the satellite. No matter whether the attitude maneuver task is urgent or not, the CMG is required to output a large control torque during the maneuver process, which is not good for the service life of the CMG in orbit.

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