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On-orbit attitude control of the Cosmic Background Explorer (COBE)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.
Document ID
19860047053
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Bramberg, B.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Croft, J.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1985
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AAS PAPER 85-040
Accession Number
86A31791
Distribution Limits
Public
Copyright
Other

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