磁気トルカを用いた小型衛星の姿勢制御の可制御性について

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  • About Controllability for Attitude Control of a Small Artificial Satellite in the Magnetic Torquers
  • ジキ トルカ オ モチイタ コガタ エイセイ ノ シセイ セイギョ ノ カセイギョセイ ニツイテ

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抄録

Small artificial satellites are often utilized because they do not need large attitude control energy. There are various types of actuators that generate control torque; in particular, magnetic torquers are suitable for attitude control systems of small satellites in advantages of their simple mechanism and small size. Indeed, magnetic torquers have been put to practical use as actuators for relatively small satellites. However, it is more difficult to properly control magnetic torquers than other actuators. This is because control torque generated by magnetic torquers is affected by the geomagnetic magnitude and direction, and herefore, position of satellites in their orbit. This difficulty is a particular problem on magnetic torquers, which is not the case for other actuators. Under these circumstances, conventional control laws for magnetic torquers are designed by each satellite, and control laws for general small satellites have not been discussed. Thus, the purpose of this paper is to show general conditions of controllability of attitude control systems of small satellites with magnetic torquers and to study a tendency of moments of inertia of satellites that enables us to control attitude with small energy. As a result, we prove that plant is controllable for almost all combinations of inertial moments and find out a tendency that we can reduce energy to control attitude when moments of inertia are small and three moments of inertia are similar values.

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