The way in which COBE (launched by the SS in late 1982) performs its attitude control is described, along with the design of its on-orbit system. COBE, to be situated in a 900 km high, sun-synchronous orbit, contains two unique control features: (1) the orientation of the spinning satellite is controlled to a sun-normal attitude in the sun/local vertical plane; and (2) pitch and roll control is maintained by a unique triaxial arrangement of reaction wheels, magnetic torque bars and sensors, located in the body's tranverse plane. Inherent in this triaxial configuration concept is a built-in redundancy that will maintain attitude control in the event of any single-point sensor/actuator component failure. Each of the three control drive electronics operates independently and directly of a system of dedicated sensors. This system functions independently of a computer or an ephemeris communication link, leading to greater reliability.
On-orbit attitude control of the Cosmic Background Explorer (COBE)
1985-01-01
Conference paper
No indication
English
Cosmology and the Cosmic Background Explorer (COBE)
AIAA | 1989
|Early results from the Cosmic Background Explorer (COBE)
NTRS | 1991
|Early results from the Cosmic Background Explorer (COBE)
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