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Redundant integrated flight control/navigation inertial sensor complexA redundant strapdown inertial navigation system for integrated flight control/navigation use is described. Design of the system, which consists of four tuned-gimbal gyros, eight accelerometers, and four processors, is discussed, with emphasis on its compact configuration (13 by 13 by 14 in.), based on symmetry properties of an octahedron. A matrix operator for least-squares combination of data from an arbitrary number of two-degree-of-freedom gyros is derived, and general parity equations for error analysis are given. Self-contained detection and isolation of a two-axis gyro failure is considered; system failure probability, which depends on component failure rates and self-correction capacities, is analyzed. Test data, including typical parity equation responses during motion and simulated gyro and accelerometer failures, are also presented.
Document ID
19770059956
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Ebner, R. E.
(Litton Systems, Inc. Woodland Hills, CA, United States)
Mark, J. G.
(Litton Systems, Inc. Woodland Hills, Calif., United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1977
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 77-1109
Meeting Information
Meeting: Guidance and Control Conference
Location: Hollywood, FL
Start Date: August 8, 1977
End Date: August 10, 1977
Accession Number
77A42808
Funding Number(s)
CONTRACT_GRANT: NAS1-13847
Distribution Limits
Public
Copyright
Other

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