Satellites based on microelectromechanical system (MEMS) technology and tailored to low-cost space missions are investigated to determine their characteristics and feasibility. This work explores an alternative chassis formed from a stack of microfabricated silicon wafers. The outer layers contain optical sensing, micropropulsion and power generation systems whereas internal layers contain computers, RF components and mechanical sensors. This technique has the advantage of saving space and weight while allowing for easy design changes and precise tailoring to mission specifications. This concept is expanded through a design study of the MEMS control moment gyroscope which is used in satellite attitude control. In addition, a feasibility study is performed with special regard to the alternative chassis outlined above. This work (part of a Phase I NASA Institute for Advanced Concepts study) demonstrates that a wide variety of spacecraft components can be fabricated with silicon processing techniques. This approach may lead to batch- fabricated, high-volume, low cost, redundant teams of MEMS spacecraft.
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