A technique for integrating orbit trajectories influenced by attitude dependent forces is presented. The method employs an Encke type correction algorithm to account for the attitude dependence not modeled in the main orbit integration process. The formulation improves computational efficiency over the straightforward integration of the fully coupled system by eliminating the need to compute the acceleration due to the geopotential at the time step required for the attitude dependent forces. Examples are shown for the integration of coupled orbital and attitude motion and for the integration of the orbit trajectory when the attitude profile is known a priori.
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