Such vehicles, typified by Orbiting Solar Observatory satellites, have applicability to missions for which simplicity, reliability, and longevity of spin stabilization combine with requirement for unidirectional pointing of component, such as antenna or solar panel; analysis reveals possibility of obtaining passive stable spin-axis attitude by spinning vehicle about its axis of greatest or least inertia, providing only that effective energy dissipation device is attached to counter-rotating platform which has greatly reduced "spin".
Attitude stability criteria for dual spin spacecraft
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 4 , n 12
1967
6 pages
Article (Journal)
English
© Metadata Copyright Elsevier B. V. All rights reserved.
Attitude Stability Criteria for Dual Spin Spacecraft
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