The interest for an integrated autonomous Guidance and Navigation Control package, satisfying to different mission requirements with a common architecture, is becoming very attractive in the perspective to reduce cost mission and to provide significant benefits when measurements noise conditions may change during the mission and safety entice! spacecraft operations are involved.nIn this paper Laben and Honeywell presents an interesting approach to integrate an Attitude GPS Space receiver and a Miniaturized Inertia! Measurement Unit (MIMU). to enhance the performances of both sensor systems.nIn traditional G&NC systems, based on Inertial Navigation Sensor (INS) measurements, long term drift, affecting zero point stability of gyroscope and accelerometer, are integrated over time during the measurement process, resulting in an increasing attitude and navigation error. These errors can be reduced by periodic reset, shifting the problem to the need of on hoard accurate and precise absolute position and attitude references.
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