Attitude control device for satellite

Abstract

Abstract PURPOSE:To suppress attitude fluctuation of an artificial satellite main unit by otaining angular momentum provided in mass of the artificial satellite total unit, simulation differentiating this momentum to obtain disturbance torque influencing the artificial satellite win unit by a movable part, and giving control torque by a thruster so as to negate this disturbance torque. CONSTITUTION:Attitude control torque, acting in an artificial satellite main unit by a thruster 8, acts so as to negate disturbance torque generated about the center of mass of the artificial satellite main unit by a movable part of a robot arm 2 or the like. As a result of negating this disturbance torque, an attitude angular speed of the artificial satellite main unit 1 is prevented from fluctuating by a motion of this movable part. That is, when assumed ha for angular momentum calculated by an angular moment arithmetic part 3, hs for angular momentum generated by the attitude angular speed of the artificial satellite main unit 1 and gamma for attitude control torque applied to the artificial satellite by the thruster 8, a relation where *ha+*hs=gamma is materialized. (* represents one time differentiating operation.)

Inventors

• 👤 Katsuhiko Yamada
• 👤 克彦 山田

Bibliographic Details