The Solar Helispherical Observatory (SOHO) spacecraft is to be placed in a halo orbit around the first Lagrangian point L1 of the Sun-Earth system. The orbit is inherently unstable and consequently requires tight control of delta-V magnitude and direction (25 arcseconds). Attitude control will allow points on the Sun to be observed with a stability of better than 0.8 arcseconds, while tracking the Sun spin axis with a (1 minute) stability of 18.9 arcseconds, in the presence of payload disturbances of 0.02 nms. The soho mission is outlined and the spacecraft and attitude system are described. The control law design adopted to meet the stringent pointing required is examined.
Design Aspects of the Attitude Control System for the SOHO Spacecraft
1991
6 pages
Report
Keine Angabe
Englisch
SOHO spacecraft thermal control aspects
British Library Online Contents | 1997
|SOHO spacecraft thermal control aspects
British Library Conference Proceedings | 1997
|Power System Performance of the SOHO Spacecraft During the 1998 Attitude Recovery
SAE Technical Papers | 1999
|SOHO Mate Spacecraft to Payloads
NTRS | 1995
Spacecraft attitude control power system and spacecraft
Europäisches Patentamt | 2024
|