FIELD: measurement equipment.
SUBSTANCE: group of inventions relates to control of orientation of space vehicle (SV). As per the proposed method, a signal of gyro measurements of angular speed vector (ASV) is used for shaping of a control signal. After failure of one gyroscope a signal of the average value of ASV astromeasurements is shaped. At failure of two or more gyroscopes an ASV identification signal is shaped, and for formation of control there used is a signal of the average value of ASV astromeasurements. At failure of an astrosensor an ASV identification signal is used for shaping of a control signal. The proposed device structure includes SV and its dummy, an astrosensor, a gyroscopic ASV metre, signal shapes of gyro- and astroquaternions and a quaternion of an ASV identification signal. The device includes two non-linear units and two switching signal shapers. The above elements are connected to each other through circuits with adders, normally closed and normally opened switches.
EFFECT: technical result of the group of inventions consists in improvement of measurement reliability and accuracy of SV angular speed vector.
2 cl, 3 dwg
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Authors
Dates
2014-06-20—Published
2012-06-28—Filed