Requirements for a redundant strapdown inertial sensor complex applied to V/STOL aircraft as developed by NASA are presented. Flight test data of a redundant, skewed axis strapdown inertial system are given, demonstrating the feasibility of the primary design aspects. This data consisted of parity equation responses through various flight conditions, showing residual noise levels on redundant gyro and accelerometer comparisons as a measure of minimum failure-level detectability, plus failure isolation and navigation performance through several simulated instrument failures.
Design and testing of a redundant skewed inertial sensor complex for integrated navigation and flight control
1979-05-01
Conference paper
No indication
English
Multi-sensor Inertial Navigation Systems Employing Skewed Redundant Inertial Sensors
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