Rhumb line control method is one of the most conventional scheme in the reorientation for spin stabilized spacecraft, since it requires only a spin sun sensor and the reaction control system. However, since rhumb directional control accuracy is governed by so called the time delay from the moment each sun pulse signal is detected, the orientation accuracy is not as precise as other sophisticated maneuver methods that usually incorporate real-time attitude reference systems on board. In practical applications, since arhumb line control is regarded as an open loop scheme and in most cases only inadequate attitude information is available, it has not been attempted so much to extract real-time information and make use of closed loop feature during the maneuver. What this paper presents is the most simplified mathematical description associated with attitude behavior under rhumb line control, which is expressed explicitly in terms only of a series of sun angle signals. For illustration, a directional dispersion analysis is dealt with here and the quasi real-time identification scheme of it is presented with the results of a free drop experiment. Other numerical examples shown here include, as it were, the idea of a realtime rhumb direction finder in generalized ahumb line maneuvers and its extension to an adaptive observer for the advanced use in future.
|出版ステータス||Published - 1994|
|イベント||Guidance, Navigation, and Control Conference, 1994 - Scottsdale, United States|
継続期間: 1994 8 1 → 1994 8 3
|Conference||Guidance, Navigation, and Control Conference, 1994|
|Period||94/8/1 → 94/8/3|
ASJC Scopus subject areas