近年，宇宙重力波望遠鏡など，相対位置精度μm級，姿勢精度秒角級を必要とする編隊飛行ミッションが増加している．このような精密制御を長期間実現するには，燃料消費を抑えたμN級の微小推力による制御が必要となる．これを実現するために，太陽輻射圧を活用する多面型液晶デバイスを提案する．本デバイスは，微細な立体構造を持つ反射板とピクセル単位のON/OFF制御が可能な液晶により，並進力とトルクを発生する．
一方で，本デバイスは反射板形状や宇宙機への搭載配置などの設計自由度が高く設計指針は確立していない．また，宇宙空間では液晶劣化により反射特性が変化するため，軌道上で反射特性を正確に把握することが難しい．
本研究では，太陽輻射圧を効率的に活用する反射板形状や搭載配置を探索し，設計論を確立する．また，多面型液晶デバイスを試作し，宇宙環境試験により反射特性の劣化を評価することで，劣化モデルを構築する．最後に，宇宙機の運動情報と劣化モデルから反射特性を推定し，推定結果を制御系に反映することで，高精度な軌道姿勢制御手法を確立する．

In recent years, formation flying missions—such as space-based gravitational wave observatories requiring relative position accuracy at the micrometer level and attitude accuracy at the arcsecond level—have been increasing. Sustaining such precise control over long durations requires micro-Newton-level thrust with minimal fuel consumption. To meet this need, a multifaceted LCD device that exploits solar radiation pressure is proposed. This device generates translational forces and torques through reflective panels with fine three-dimensional structures and pixel-level ON/OFF-controllable liquid crystals.
However, the device has high design freedom in terms of reflector shape and mounting configuration on the spacecraft, and no design guidelines have been established. Furthermore, in space, radiation exposure may degrade the reflective properties of the LCD, making it difficult to accurately characterize in-orbit reflective behavior.
In this research, reflector shapes and mounting configurations that efficiently exploit solar radiation pressure are explored and a design theory is established. A prototype multifaceted LCD device is also fabricated, and space environment tests are conducted to evaluate reflective property degradation, yielding a degradation model. Finally, by estimating reflective properties from spacecraft motion data and the degradation model and incorporating the estimates into the control system, a high-precision orbit and attitude control method is established.