Fault Judgment Method for Sailboard Rotation of High Orbit Zero Momentum Satellite Based on Angular Momentum Estimation

Abstract

The invention discloses a high-orbit zero-momentum satellite sailboard rotation fault judgment method based on angular momentum estimation. The method comprises the following steps: 1) obtaining a sunlight pressure fitting curve on a satellite solar panel; 2) determining a sunlight pressure moment correction value at the current moment according to the fitted curve and the estimated values of thesunlight pressure moments before the n orbit periods; 3) determining the extrapolated attitude angular velocity of the satellite body according to the corrected value of the sunlight pressure moment at the current moment; 4) according to the extrapolated attitude angular velocity of the satellite body, determining extrapolated triaxial synthetic angular momentum of the satellite body; 5) taking Ras a sampling period, and sampling to obtain an average value and a variance of the extrapolated triaxial synthetic angular momentum of the satellite body in the orbit period before the current moment; and 6) judging whether the satellite sailboard has a rotation fault or not at the current moment according to the average value and the variance. According to the method, whether the satellite sailboard has the rotation fault or not can be autonomously diagnosed on a faulty satellite without additionally adding a sun sensor.

Description

technical field [0001] The invention relates to a high-orbit zero-momentum satellite sailboard rotation fault judgment method based on angular momentum estimation, and belongs to the technical field of high-orbit satellite attitude control. Background technique [0002] High-orbit satellites generally have large-scale solar wings, and the solar light pressure moment is the most important disturbance moment for high-orbit satellites. Due to space electromagnetic interference, when the direction latch position of the sailboard drive mechanism is overturned or the drive line fails, abnormal phenomena such as the reversal or stall (reset) of the south and north sailboard drive mechanisms occasionally occur on orbiting satellites. The reversal or stall of the sailboard driving mechanism not only makes the solar wing unable to track the sun normally, threatening the energy security of the whole star, but also the structural asymmetry caused by the sailboard reversal and stalling m...

AI Technical Summary

Problems solved by technology

Due to space electromagnetic interference, when the direction latch position of the sailboard drive mechanism is overturned or the drive line fails, abnormal phenomena such as the reversal or stall (reset) of the south and north sailboard drive mechanisms occasionally occur on orbiting satellites

The reversal or stall of the sailboard driving mechanism not only makes the solar wing unable to track the sun normally, threatening the energy security of the whole star, but also the structural asymmetry caused by the sailboard reversal and stalling makes the accumulation of angular momentum generated by the solar light pressure disturbance torque more serious. Serious, it has a great impact on the attitude control of the satellite

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