Title: A new approach in three-axis satellite stabilisation using redundant thruster in elliptical orbit
Authors: M. Fakoor; A. Sattarzadeh; M. Bakhtiari
Addresses: Faculty of New Sciences and Technologies, University of Tehran, Amir Abad, North Kargar Street, 14395-1561, Tehran, Iran ' Faculty of New Sciences and Technologies, University of Tehran, Amir Abad, North Kargar Street, 14395-1561, Tehran, Iran ' Department of Mechanical Engineering, Iran University of Science and Technology, Narmak, 16844, Tehran, Iran
Abstract: Three-axis attitude stabilisation of a satellite in a LEO elliptical orbit, with respect to the effects of applied disturbances such as eccentricity, gravity gradient, solar radiation pressure and aerodynamic loads is presented by applying three reaction wheel actuators. A new attitude stabilisation method is investigated by considering failure in one or more reaction wheels. If any failure happens in reaction wheels, redundant thruster will be added to the system by gimbal mechanism as an input controlling actuator. Control algorithm based on dynamic and kinematic equations of the satellite's motion is developed. Considering the variable satellite model in different situations, neuro-fuzzy controller is employed. For training the intelligent neuro-fuzzy controller, PID controller is utilised. Numerical simulations show that the recommend control method has acceptable results and supplementing of a thruster actuator as redundancy, could increase the space mission reliability.
Keywords: satellite; attitude control subsystem; ACS; neuro-fuzzy; PID controller; reaction wheel; elliptical orbit.
International Journal of Automation and Control, 2018 Vol.12 No.4, pp.495 - 525
Available online: 29 Jun 2018 *Full-text access for editors Access for subscribers Purchase this article Comment on this article