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Nutation and precession control of the High Energy Solar Physics (HESP) satelliteThe High Energy Solar Physics (HESP) spacecraft is an intermediate class satellite proposed by NASA to study solar high-energy phenomena during the next cycle of high solar activity in the 1998 to 2005 time frame. The HESP spacecraft is a spinning satellite which points to the sun with stringent pointing requirements. The natural dynamics of a spinning satellite includes an undesirable effect: nutation, which is due to the presence of disturbances and offsets of the spin axis from the angular momentum vector. The proposed Attitude Control System (ACS) attenuates nutation with reaction wheels. Precessing the spacecraft to track the sun in the north-south and east-west directions is accomplished with the use of torques from magnetic torquer bars. In this paper, the basic dynamics of a spinning spacecraft are derived, control algorithms to meet HESP science requirements are discussed and simulation results to demonstrate feasibility of the ACS concept are presented.
Document ID
19930067420
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Jayaraman, C. P.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Robertson, B. P.
(McDonnell Douglas Aerospace Seabrook, MD, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Publication Information
Publication: In: AIAA Guidance, Navigation and Control Conference, Monterey, CA, Aug. 9-11, 1993, Technical Papers. Pt. 2 (A93-51301 22-63)
Publisher: American Institute of Aeronautics and Astronautics
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 93-3828
Accession Number
93A51417
Funding Number(s)
CONTRACT_GRANT: NAS5-30363
Distribution Limits
Public
Copyright
Other

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