Simultaneous Multi-step Excitations for Aircraft System Identification

Piotr Lichota , Per Ohme , Krzysztof Sibilski

Abstract

In this study a numerical procedure for designing an aircraft system identification maneuver with simultaneous flight control deflections is described. The elevator, aileron and rudder multi-step excitations that maximize the D-optimality criterion were found by a genetic algorithm. To limit the search-space dimensions the switching points of the inputs were selected on the basis of the discrete wavelet transform. In the investigation, the design was compared with the maneuvers that used harmonically related multisines and typical multi-step inputs (3-2-1-1 on elevator, 1-2-1 on aileron, rudder doublet) for simultaneous flight control deflections. The case of typical excitations applied one at a time was examined as well. Through simulations it was found that the maneuvers with simultaneous flight control deflections that were based on the D-optimality criterion or harmonically related multisine signals are better in the terms of accuracy, aircraft response and resulting g-force than the designs based on the typical excitations.
Author Piotr Lichota ITLMS
Piotr Lichota,,
- The Institute of Aeronautics and Applied Mechanics
, Per Ohme
Per Ohme,,
-
, Krzysztof Sibilski ITLMS
Krzysztof Sibilski,,
- The Institute of Aeronautics and Applied Mechanics
Pages1-20
Publication size in sheets0.95
Book AIAA Atmospheric Flight Mechanics Conference, 2016, The American Institute of Aeronautics and Astronautics, ISBN 978-1-62410-430-5, 1018 p.
Keywords in EnglishSystem Identification; Parameter Estimation; Flight Dynamics; Optimal Input Design; Simultaneous Excitations
Abstract in Polishavailable on-line
DOIDOI:10.2514/6.2016-3704
URL http://arc.aiaa.org/doi/abs/10.2514/6.2016-3704
Languageen angielski
Score (nominal)0
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