Attitude Control Hardware for Operationally Responsive Space Platforms in LEO

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Small Satellites (or Smallsats, in short) are increasingly recognized for their versatility and efficienty. In**particular, their applications are now found for data collection that could directly benefit both the Operationally**Responsive Space (ORS) intelligence goals as well as commercial sector's high revenue ambitions. Currently,**all small satellites rely on reaction wheels to achieve 3-axis control and increasing the agility of small satellites**while using reaction wheels is significantly hampered by the high mass and power trade-off when using**reaction wheels. Control Moment Gyroscope is the unique alternative actuation mechanism that provides the**hosting satellite the increased agility while requiring less power and mass compared to reaction wheels which**is invaluable in a smallsat application. Despite this crucial advantage and its wide usage in larger commercial**and intelligence satellites, there is no proper Control Moment Gyroscope available in the market for this class**of small satellites.**The proposed research is to develop a Control Moment Gyroscope hardware suitable for the microsatellite**class of satellites (<150 kg). We propose to design, develop and engineer a prototype control moment**gyroscope (CMG) capable of providing > 100 mNm torque, >200 mNms angular momentum, while consuming**<7 W power and mass < 700 grams. This will allow spacecraft agile maneuvering and result in ground high**value target frequent revisits as well as space object tracking, within considerably lower launch cost.**The project aims to provide innovative space product to broaden applications of small satellites in both civilian**and military applications by developing a highly accurate, agile control actuator. In long run, the project is to**build on MSCI and York University's Attitude Control System (ACS) research to further develop advanced**attitude hardware for advanced satellite design.