抄録
An attitude control method by moving solar paddles with distributed mass for a 1kg-class microsatellite is proposed. A lightweight hinge mechanism comprising of an elastic hinge actuated by shape memory alloy is developed in this project that can be utilized for attitude control of microsatellites. Design and fabrication of the hinge is described here. Maneuvers are accomplished by repeating simple sequences of joint motions. The effect of maneuver on power generation is also examined. It has been shown that power generated as a result of reorienting the satellite to the sun exceeds power consumption for any maneuver which makes the design acceptable for implementation in similar applications
