Harnessing Radiation Torques to Drive the Precession of a Spin-Stabilized Spacecraft

Details Harnessing Radiation Torques to Drive the Precession of a Spin-Stabilized Spacecraft Harnessing Radiation Torques to Drive the Precession of a Spin-Stabilized Spacecraft

Sep 1998

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1998dda....30.0902m&link_type=abstract

American Astronomical Society, DDA meeting #30, #09.02; Bulletin of the American Astronomical Society, Vol. 30, p.1145

Astronomy and Astrophysics

Astronomy

Scientific paper

Analytical and numerical calculations are presented which explore the spin dynamics of a cylindrical spacecraft with a rigidly attached conical solar shield immersed in the solar radiation and wind environments. The precession rates desirable for cataloging instruments (such as HIPPARCOS) can be easily driven by canting the solar shield by a few degrees (i.e., "cone" angle a few degrees less than 90). The frequency of attitude adjustments from onboard gas jets can be reduced by an order of magnitude, easing data reduction efforts and improving mission science throughput.

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