Design and testing of a redundant skewed inertial sensor complex for integrated navigation and flight controlRequirements 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.
Document ID
19790022031
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Ebner, R. E. (Litton Systems, Inc., Woodland Hills Calif., United States)
Howell, W. E. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 9, 2013
Publication Date
May 1, 1979
Publication Information
Publication: AGARD The Guidance and Control of Helicopters and V(STOL Aircraft at Night and in Poor Visibility