A multi-stage attitude control method for remote sensing micro-nano satellites

Abstract

The invention relates to a multi-stage attitude control method for a remote sensing micro-nano satellite, and belongs to the technical field of spacecraft attitude control. A three-axis magnetic moment device and a momentum wheel set are adopted as an attitude control execution component, and the attitude control method for the four main stages of recemization after satellite-rocket separation, counterglow capture, counterglow orientation and counter-earth remote sensing is designed, and an attitude mobile control method for the two stages of counterglow orientation and counter-earth remote sensing is designed. According to the recemization stage, the large angular rate of the satellite obtained after satellite-rocket separation is eliminated, and the basic controlled attitude is built; inthe counterglow capture and counterglow orientation stages, it is ensured that a sun sailboard is in the charging state for a long time; in the counter-earth remote sensing stage, it is ensured thatthe remote sensing photographing task is completed. According to the method, traditional PD control is adopted as the foundation, on the basis of feedforward control, quaternion is used for representing attitude errors, the method has the advantages of being rapid in satellite maneuvering response, high in steady state robustness and high in control precision, and the task requirement for a remotesensing micro-nano satellite is met.

Description

technical field [0001] The invention relates to a multi-stage attitude control method for remote sensing micro-nano satellites, belonging to the technical field of spacecraft attitude control. Background technique [0002] For satellites used as remote sensing payload platforms, during non-remote sensing imaging missions, it is necessary to keep the solar panels facing the sun stably to ensure energy supply on the planet; during remote sensing imaging missions, in order to obtain high-resolution remote sensing images, it is necessary to maintain High-precision and stable satellite attitude; at the same time, due to the relatively short time of the remote sensing imaging task, the satellite needs to have the ability to quickly maneuver the attitude to perform attitude conversion during different mission periods. Therefore, it is very necessary to accurately control the attitude of the satellite. [0003] In 2005, Yu Yong and other researchers proposed a micro-satellite attit...

AI Technical Summary

Problems solved by technology

[0004] In the above-mentioned existing attitude control methods of micro-satellites, the different control methods of the satellite in different stages and the control methods of the maneuvering process between stages are not considered, and only one control strategy of the attitude control execution unit is adopted, and the multiple control methods are not considered. Collaborative work between individual attitude control executive components

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