Small satellite missions are characterized by tight constraints on cost, mass, power, and volume that make them unable to fly high performance inertial measurement units (IMUs) required for orbital missions demanding precise orientation and positioning. Instead, small satellite missions typically fly low-cost MEMS (micro-electro-mechanical system) IMUs. Unfortunately, the performance characteristics of these MEMS IMUs make them ineffectual in many spaceflight applications when employed in a single IMU system configuration. This study will create an “effective” tactical-grade IMU, thus allowing future small satellites to tackle
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