Attitude control system design using a flywheel suspended by two gimbals

17th Brazilian Colloquium on Orbital Dynamics

Peres, R.W.^1 ; Ricci, M.C.^1,2

Faculdade de Tecnologia São Francisco (FATESF), Brazil^1

Divisão de Mecânica Espacial e Controle (DMC), Instituto Nacional de Pesquisas Espaciais (INPE), Brazil^2

关键词: Control laws;    Cyclic response;    Disturbance torque;    Geo-stationary orbits;    Solar pressure;    Three axes;    Three-axis;    Wheel speed control;   

Others  :  https://iopscience.iop.org/article/10.1088/1742-6596/641/1/012019/pdf
DOI  :  10.1088/1742-6596/641/1/012019

来源: IOP

【 摘 要 】

This work presents the attitude control system design procedures for a three axis stabilized satellite in geostationary orbit, which contains a flywheel suspended by two gimbals. The use of a flywheel with two DOFs is an interesting option because with only one device it's possible to control the torques about vehicle's three axes; through the wheel speed control and gyrotorquing phenomenon with two DOFs. If the wheel size and speed are determined properly it's possible to cancel cyclic torques using gas jets only periodically to cancel secular disturbance torques. The system, based on a flywheel, takes only one pitch/roll (earth) sensor to maintain precise attitude, unlike mass expulsion based control systems, which uses propellants continuously, beyond roll, pitch and yaw sensors. It is considered the satellite is in nominal orbit and, therefore, that the attitude's acquisition phase has already elapsed. Control laws and system parameters are determined in order to cancel the solar pressure radiation disturbance torque and the torque due to misalignment of the thrusters. Stability is analyzed and step and cyclic responses are obtained.