SINGLE SENSOR 3-AXIS ATTITUDE DETERMINATION SYSTEM FOR CUBESATS

摘要

The classical methods used for satellites 3-axis attitude determination require at least two onboard independent sensors. The paper presents a 3-axis attitude determination method that can be implemented on board small satellites using measurements from a single sensor. The simulations results are presented for the cubesat satellite type orbit with the apogee at 1450 km, the perigee at 300 km and an inclination of 69.5 degrees, achieved with the Vega rocket maiden flight on 13 February 2012.