Abstract
For a rigid satellite only a rotation around the axis with maximum or minimum moment of inertia is stable. For satellites with flexible parts this well known rule is modified. Here the moment of inertia around the spin axis must exceed the lateral moments of inertia by some margin that depends on the properties of the flexible parts. The practical determination of this margin is the main subject of the paper. It is shown that stability limits can be derived from purely static considerations. The methods are illustrated by an extremely simple example that can be analyzed in closed form: a pair of thin radial booms with tip masses and root elasticity. For more realistic configurations results of numerical calculations are given that show the usefulness of the methods for engineering purposes. In addition these results are used to discuss the effects of parameters such as boom geometry, mass distribution, elasticity, and spin rate on the stability of the rotational motion. The paper is based on a method developed by McIntyre and Miyagi (1976). It implements this method by stressing the aspects of its practical application.
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