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The application of the detection filter to aircraft control surface and actuator failure detection and isolationThe performance of the detection filter in detecting and isolating aircraft control surface and actuator failures is evaluated. The basic detection filter theory assumption of no direct input-output coupling is violated in this application due to the use of acceleration measurements for detecting and isolating failures. With this coupling, residuals produced by control surface failures may only be constrained to a known plane rather than to a single direction. A detection filter design with such planar failure signatures is presented, with the design issues briefly addressed. In addition, a modification to constrain the residual to a single known direction even with direct input-output coupling is also presented. Both the detection filter and the modification are tested using a nonlinear aircraft simulation. While no thresholds were selected, both filters demonstrated an ability to detect control surface and actuator failures. Failure isolation may be a problem if there are several control surfaces which produce similar effects on the aircraft. In addition, the detection filter was sensitive to wind turbulence and modeling errors.
Document ID
Document Type
Conference Paper
Bonnice, W. F.
(Draper (Charles Stark) Lab., Inc. Cambridge, MA, United States)
Wagner, E.
(Draper (Charles Stark) Lab., Inc. Cambridge, MA, United States)
Motyka, P.
(Charles Stark Draper Laboratories, Inc. Cambridge, MA, United States)
Hall, S. R.
(MIT Cambridge, MA, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1985
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 85-1973
Meeting Information
Guidance, Navigation and Control Conference(Snowmass, CO)
Funding Number(s)
Distribution Limits
No Preview Available