縦長スピン姿勢安定の簡易解析 Simple Analysis of Prolate-Spin Attitude Stability
How can a prolate spacecraft spinning about its axis of minimum moment of inertia be attitude-stabilized by using dual spin? To this question, we find a simple, clear answer. We replace the spacecraft with an equivalent point-mass model and describe its attitude motion as small deviations from its nominal attitude. We show that a friction-like torque applied to the spin axis would reduce wobble motions, and that a similar torque is generated by a wobble damper on a de-spun platform. Thus, we derive a simple attitude-stability theory using minimal mathematical analysis, and this theory is applicable to the spin stabilization of geosynchronous communication spacecraft.
- 日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences
日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences 54(633), 461-466, 2006-10-05