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Management of analytical redundancy in digital flight control systems for aircraftThis paper presents a design method for optimal redundancy management for nonlinear systems with application to highly maneuvering aircraft. The approach taken is based on selecting the failure states to be covered by the system design and constructing a cost function that represents the cost of making an incorrect decision. The decision logic which minimizes the cost requires a bank of extended Kalman filters running in parallel. This produces a severe computational requirement. To reduce this requirement, a suboptimal logic is developed based on using a nonlinear single-stage prediction algorithm in the filters with filter gains and decision logic selected using steady-state results obtained from a linearization of the vehicle and sensor dynamics. The design process is then applied to designing a redundancy management system for the F8-C aircraft. Results indicate that the system is superior in failure detection to a system using the same structure but using a linear single-stage prediction algorithm in the filters.
Document ID
19740055499
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Montgomery, R. C.
Price, D. B.
(NASA Langley Research Center Flight Dynamics and Control Div., Hampton, Va., United States)
Date Acquired
August 7, 2013
Publication Date
August 1, 1974
Subject Category
Aircraft
Report/Patent Number
AIAA PAPER 74-887
Meeting Information
Meeting: Mechanics and Control of Flight Conference
Location: Anaheim, CA
Start Date: August 5, 1974
End Date: August 9, 1974
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
74A38249
Distribution Limits
Public
Copyright
Other

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