An attitude and orbit determination and control system for a small geostationary satellite

Thopil, G. A. (2006-12)

Thesis (MScEng (Electrical and Electronic Engineering))--University of Stellenbosch, 2006.


An analysis of the attitude determination and control system required for a small geostationary satellite is performed in this thesis. A three axis quaternion feedback reaction wheel control system is the primary control system used to meet the stringent accuracy requirements. A momentum bias controller is also evaluated to provide redundancy and to extend actuator life. Momentum dumping is preformed by magnetic torque rods using a crossproduct controller. Performance of three axis thruster control is also evaluated. A full state Extended Kalman filter is used to determine attitude and body angular rates during normal operation whereas a Multiplicative Extended Kalman Filter is used during attitude manoeuvres. An analytical orbit control study is also performed to calculate the propellant required to perform station-keeping, for a specific sub-satellite location over a ten year period. Finally an investigation on the effects caused by thruster misalignment, on satellite attitude is also performed.

Please refer to this item in SUNScholar by using the following persistent URL:
This item appears in the following collections: