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A New Formulation of the Filter-Error Method for Aerodynamic Parameter Estimation in TurbulenceA new formulation of the filter-error method for estimating aerodynamic parameters in nonlinear aircraft dynamic models during turbulence was developed and demonstrated. The approach uses an estimate of the measurement noise covariance to identify the model parameters, their uncertainties, and the process noise covariance, in a relaxation method analogous to the output-error method. Prior information on the model parameters and uncertainties can be supplied, and a post-estimation correction to the uncertainty was included to account for colored residuals not considered in the theory. No tuning parameters, needing adjustment by the analyst, are used in the estimation. The method was demonstrated in simulation using the NASA Generic Transport Model, then applied to the subscale T-2 jet-engine transport aircraft flight. Modeling results in different levels of turbulence were compared with results from time-domain output error and frequency- domain equation error methods to demonstrate the effectiveness of the approach.
Document ID
20160006007
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Grauer, Jared A. (NASA Langley Research Center Hampton, VA, United States)
Morelli, Eugene A. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
May 11, 2016
Publication Date
June 22, 2015
Subject Category
Aircraft Stability And Control
Report/Patent Number
NF1676L-20186
Meeting Information
Meeting: AIAA Atmospheric Flight Mechanics Conference
Location: Dallas,TX
Country: United States
Start Date: June 22, 2015
End Date: June 26, 2015
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 473452.02.07.03.02.01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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