抄録
Attitude control methods of a solar sail which maximize the effectiveness of ΔVEGA (ΔV Earth Gravity Assist) are proposed. An orbit of a solar sail is controlled by changing its attitude, and there are two types of method to control an orbit of a spinning solar sail. One is to control its attitude directly, and the other is to control its attitude indirectly using an attitude drift motion due to the solar radiation pressure by controlling its spin rate. These methods are applied to an orbit of ΔVEGA, and their efficiency is quantitatively evaluated by solving optimal control problems to maximize the relative velocity with respect to the Earth.
