A Study Of Micro-satellite High-precision Attitude Control Algorithm And Build Air Bearing Platform

The development of aerospace technology has led to the emergence of miniaturized,large-angle and fast maneuvering small satellite systems.As a result,satellite-related control technology has become more complicated.In addition,the development of aerospace technology has also led to the development of satellite simulation and verification methods.This paper had studied the technology that related to small satellites.Firstly,this paper briefly introduces the research background and significance of this subject.At the same time,the research status of attitude control algorithms for small satellites at home and abroad,the research status of air bearing platform at home and abroad,the research status of automatic balancing in air bearing platform at home and abroad and the research status of air propulsion system at home and abroad is studied.At the end of the chapter gives the structure of this paper research content.Secondly,the description method of the attitude maneuver parameters of small satellites is studied.In addition,this paper has also deduced the kinematics equation and dynamic equation of the attitude maneuver of small satellite.Thirdly,considering the limitations of the flywheel used in attitude maneuver,the model independence,based on Euler axis Rotation and Euler axis rotation based on the hierarchical saturation was considered in the design of PD attitude control law and fuzzy PD attitude control law based on small satellite combined implementing agencies.The simulation results show that the proposed attitude control law based on the combined implementing actuator can quickly achieve attitude maneuvering while guaranteeing control accuracy.In order to ensure that the air bearing platform can meet the experimental conditions,that the automatic balancing of the air bearing platform is studied.In the course of the research,the automatic balancing process of air bearing platform and the mathematical model of automatic balancing method were established.In order to improve the anti-interference performance of the system and reduce the leveling error,that the L1 adaptive automatic balancing method was studied.Moreover,the mathematical simulation results are given.The results show that the balance can complete within a short time and the accuracy control is within the allowable range.Finally,the research on the structure of small satellite cold propulsion system is continuously studied,that including the structure of cold propulsion system,high-pressure gas cylinder,valve assembly and Laval nozzle.Finally,this paper also carries out the research and development of Laval nozzle and valve assembly.Then the thrust test system was also developed.