The Space Technology (ST)-5 satellites were launched March 22, 2006 on a Pegasus XL launch vehicle into a Sun-synchronous orbit. The three micro-satellites which constituted the ST-5 mission were kept in a formation which allowed three successive measurements taken of the Earth s magnetic field in order to study short term fluctuations of the field. The attitude of each satellite was computed on the ground using data from the science grade magnetometer as well as the miniature spinning Sun sensor (MSSS) which was the primary attitude sensor. Attitude and orbit maneuvers were performed using a single axial cold gas thruster. This paper describes the ground attitude estimation process and performance as well as anomaly resolutions.
Space Technology 5 Post-Launch Ground Attitude Estimation Experience
2007-09-24
Conference paper
No indication
English
NOVEL ATTITUDE CONTROL DESIGN OF SPACE LAUNCH VEHICLE
TIBKAT | 2021
|Launch vehicle attitude control
NTRS | 1975
Space technology - Space Launch Initiative
Online Contents | 2002