Developing a practical, high accuracy attitude determination system for CubeSats.

CubeSats offer a cost-effective platform for space research, but their utility can be limited by inaccurate attitude determination systems. This project focuses on developing advanced noise reduction techniques for microelectromechanical (MEMS) sensors used in CubeSat guidance systems. MEMS sensors are a popular choice for CubeSats because of their low profile and power consumption. Inertial Measurement Units (IMUs) are a component of guidance systems that can work independently of a continuous reference. This research aims to enhance the precision of IMUs to achieve below one degree accuracy, a critical requirement for many space missions that current CubeSat systems struggle to meet. We plan to mitigate various noise sources in MEMS sensors, including thermal, shot, and 1/f noise, as well as IMU-specific issues like cross-axis interference and temperature-dependent scale factor variations. The methodology involves a series of controlled experiments using a custom-built test apparatus that simulates the Low Earth Orbit (LEO) environment, such as orbital motion, vacuum conditions, and thermal cycling. The system will achieve low vibration, 3 axis rotation housed within a vacuum to achieve accurate simulation. By applying thermal control techniques and vibration isolation, we aim to significantly reduce sensor drift. Initial results have shown improvements, reducing gyroscope drift from approximately one degree per second to around one degree every two minutes. We did so by accounting for consistent errors in the output data. If successful, this project will expand the capabilities of CubeSats for various space research applications, including atmospheric studies and planetary exploration, with negligible impact in cost, mass, and power consumption.