Study On The Attitude Control System Of Satellite With Reaction Wheels And Magnetotors

the attitude control system which based on reaction flywheel and magnetictorque has infinite life in theory because of no consumption of cold gas or fuel. Ithas been one of the key research directions for domestic and foreign scholars. Inthis paper, design and simulation study for attitude control system which basedon flywheel was presented in different attitude control modes of a certain satellite.The major technical parameters about reaction flywheel and magnetic torquewere studied through the simulation.First, dynamic model and kinematics model of the micro-satellite wereestablished, and then a certain amount of research on the space interference wasmade.Second, flywheel simulation model which reflected main performanceparameters of the flywheel was established after the analysis about the reactionflywheel model of the control system. It prepared the grind for our further studyabout the influence of the flywheel performance on the attitude control system.Magnetic unloading model of the attitude control system was also presented inthe paper.Then, the design for attitude control system were classified mainly in fourways according to the different control mode when satellite run in space. Itmainly included directional three-axis stability control system, attitude maneuverattitude control system, directional attitude control system and omni-directionalto capture the day the attitude control system. The feasibility of the design forthese control systems was verified by simulation implementation from one to theother. In addition, the simulation about the attitude maneuver control system andall-round to capture the day control system was further investigated in this paper. Through the simulation, we can conclude the reference range of mainperformance parameters about the reaction flywheel and the magnetic torque.Finally, the fault conditions that the micro-satellite may arise were analyzedin the paper. To counter the case that uniaxial reaction flywheel out of order, faulthanding solutions were presented. Three-axis attitude of the micro-satellite wascontrolled by using the remaining two axis reaction flywheels and redundancywheel together. Allocation plan about control moment in fault conditions also wasgiven. In the directional control mode and the attitude maneuver mode, thefeasibility and the effectiveness of fault handing solutions were verified throughsimulation. Then the paper analyzed the influence of the fault on the attitudecontrol system under these two modes.In this paper, the attitude control system of micro-satellite which based onthe reaction flywheel and magnetic torque was studied. The fault conditions thatthe micro-satellite may arise also were analyzed in the paper.From the engineering’s implementation point of view, the performanceparameters about reaction flywheel and magnetic torque of attitude controlsystem of a certain satellite were given in the paper. We hope that the researchmethods and the results of the study in this paper have some help to satellitedevelopment.