Study is made of attitude errors of satellite in equatorial orbit at altitudes for which solar radiation pressure is dominant disturbance; there are two methods to minimize solar induced attitude errors and their limitations are examined; attitude errors of split-damper are compared with those of slotted one-piece damper whose hinge is at top or bottom of stabilized package; latter scheme also avoids slot, but violates symmetry; it is shown that chief disadvantage of split-damper scheme stems from design constraints needed to minimize excitation of additional mode of motion introduced by split.
Split-damper inertially coupled passive gravity-gradient attitude control system
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 4 , n 11
1967
6 pages
Article (Journal)
English
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