Quick retrieval method for satellite attitude

Abstract

The invention relates to a satellite attitude quick rescue method. The method comprises the following steps: firstly, judgment is made whether the current attitude is out of control or not, and normal attitude control is performed if the current attitude is not out of control, otherwise the current actuator stops controlling satellite attitude; secondly, a filter is determined according to existence of gyroscopic observation information, and the current satellite attitude and the angular rate are observed and updated and time update is forecasted; and thirdly, judgment is made whether the target attitude is reached according to the current satellite attitude, judgment is made that the current moment needs controlling the actuator or not if the target attitude is not reached, and attitude maneuver control is performed by utilization of the current attitude determination information and the target attitude command if the current moment needs controlling the actuator, or the procedures are repeated if the current moment does not need controlling the actuator. The satellite attitude quick rescue method can quickly rescue the attitude of an out-of-control near earth satellite, eliminates the dependency of the satellite on earth stations and the work load of the earth stations on one hand and is the backup of each other with the prior spaceborne self-rescue method on the other hand, improves the quick spaceborne self-rescue ability, and guarantees the normal operating life of the satellite.

Description

technical field [0001] The invention relates to a method for rescuing the attitude of an out-of-control satellite, in particular to a method for quickly and autonomously rescuing the attitude of a near-earth out-of-control satellite. This type of satellite at least has a three-axis magnetometer, an attitude control computer and a maneuvering control actuator in normal operation. Background technique [0002] Attitude loss is a relatively common situation in satellite failures. Typical cases include: the design of the attitude control system of Fengyun-1 A star is flawed, and it is permanently out of control after 35 days in orbit; after 165 days of normal operation of Fengyun-1 B star, due to the radiation of high-energy particles in space, the computer on the star failed. Frequent jumps are generated, causing the satellite to lose control; in 1999, 4 of the 6 control gyroscopes of the Hubble Space Telescope failed, causing it to lose control. According to the health status...

AI Technical Summary

Problems solved by technology

[0010] The technical problem of the present invention is to solve the shortcomings of the attitude rescue method based on the ground station control in terms of rapidity, overcome the shortcomings of the existing on-board autonomous attitude rescue method, which have relatively harsh application conditions and high energy consumption for ineffective control, and provide a satellite attitude The rapid rescue method can quickly save the attitude of the out-of-control near-Earth satellite. On the one hand, it eliminates the dependence on the ground station and its workload. , to ensure the normal working life of the satellite

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