![]() ![]() Significant design work has been conducted to realize the proposed architecture. Fine control is achieved through the use of three reaction wheels or three magnetorquers and one reaction wheel along the pitch axis. In this proposed embedded attitude control system design for a 1U CubeSat, pointing is obtained through a two-stage approach involving coarse and fine control modes. ![]() The accuracy and precision requirements are even more challenging for small satellites where limited volume, mass, and power are available for the attitude control system hardware. The attitude control system architecture is a crucial subsystem for any satellite mission since precise pointing is often required to meet mission objectives. We present a satellite attitude control system design using low-cost hardware and software for a 1U CubeSat. ![]()
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