Integrated redundant reference system for the flight control and for generating heading and attitude informations
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United States of America Patent
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Apr 3, 1990
Grant Date -
N/A
app pub date -
Oct 6, 1987
filing date -
Oct 7, 1986
priority date (Note) -
Expired
status (Latency Note)
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Abstract
A plurality of two-axis rate gyros are arranged in relation to an aircraft-fixed coordinate system such that they redundantly supply angular rate information. A plurality of accelerometers supply correspondingly redundant acceleration information. First signal processing means comprise means for failure detection and elimination, such that angular rate and acceleration information subjected to error are eliminated. The angular rate and acceleration information thus cleared from errors supply stabilization signals for the autopilot. Second signal processing means obtain the angular rate and acceleration information cleared from errors and integrated if required, and therefrom supply heading and attitude reference signals.
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