Sun-Tracking Attitude Control of Spacecraft with Inclined Principal Axes of Inertia by Using Solar Radiation Pressure

抄録

In an interplanetary mission, the influence of solar radiation pressure (SRP) is a dominant disturbance in terms of the attitude control of a spacecraft, and a continuous disturbance due to the SRP shortens their mission life time. On the other hand, practical uses of the SRP are rapidly developed such as in Hayabusa and IKAROS, and their effectiveness is increasingly acknowledged. The objective of this study is to establish attitude control methods of a spacecraft by actively using the SRP. Moreover, we derive general and precise control methods by taking into account that the principal axes of inertia of a spacecraft are usually inclined from its symmetrical axes slightly, and verify the control methods by applying it to a model of Akatsuki.