Near-earth satellite redundant flywheel angular momentum autonomous management method

Abstract

The invention discloses a near-earth satellite redundant flywheel angular momentum autonomous management method, including the steps of S1. dividing given angular momentum increments of a flywheel group into an angular momentum increment of attitude control output by each flywheel in the flywheel group and an angular momentum increment of zero motion; S2. obtaining the central angular momentum of the flywheels; S3. converting a problem of solving flywheel group zero movement into a constrained quadratic form optimization problem, adopting QR decomposition to convert the constrained quadratic form optimization problem into an unconstrained optimization problem, and obtaining a zero movement angular momentum increment of each flywheel, so that the angular momentum of each flywheel approaches the central angular momentum; and S4. according to a relation between flywheel group null space after part of flywheels fail and flywheel group null space when no flywheel fails, completing angular momentum reconstruction of the flywheel group. The advantages of the method are that while the flywheel group generates given moment of force, the rotating speed of each flywheel can approach preset desired rotating speed, thereby preventing frequent zero passage or saturation of the rotating speed of flywheels and realizing on-line reconstruction of a whole system when part of the flywheels fail.

Description

technical field [0001] The invention relates to the technical field of angular momentum management of a satellite flywheel system, in particular to a method for autonomously managing the angular momentum of a near-earth satellite redundant flywheel. Background technique [0002] For the three-axis attitude stabilization satellites of modern long-life satellites, in order to improve the reliability of the system, more than three redundant flywheels are usually installed as the actuators of the attitude control system. If the satellite operates in low-Earth orbit, the angular momentum accumulated by the space disturbance torque on the flywheel system can be unloaded through a magnetic torque device, etc., but it cannot prevent the flywheel speed from being too low or zero-crossing phenomenon, and at the same time, it can only be passively avoided. Saturation occurs. Since the motor works at low speed for a long time and frequently crosses zero, it will have a very adverse eff...

AI Technical Summary

Problems solved by technology

The domestic patent "A Method for Autonomous Management of Angular Momentum of Redundant Flywheel Sets" provides a zero-motion-based angular momentum management method for geosynchronous orbit satellites, but the zero-space projection matrix it uses has more redundant information. , and when some flywheels fail in the flywheel combination, the matrix needs to be recalculated, and the amount of calculation is large

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