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Design of Robust Autopilot Control Laws with Nonlinear Dynamic Inversion

Looye, G. (2001) Design of Robust Autopilot Control Laws with Nonlinear Dynamic Inversion. at Automatisierungstechnik, 49 (12), pp. 523-531.

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The application on Nonlinear Dynamic Inversion for the design of a robust attitude controller for a civil aircraft is discussed. The main function of the controller is to improve the flying qualities, including stability, of the aircraft dynamics. For parameter synthesis multi-objective optimisation is used. The required robustness is achieved via a multi-model approach and local robustness criteria. In addition to the feedback gains, physical parameters in the inverse model that are considered uncertain in the design model, are used as synthesis parameters. The control laws are automatically genereted from a symbolic aircraft model in the modeling language Modelica. The design was used as a stability and command augmentation function in an automatic Fly-by-Wire landing system and was successfully flight tested.

Item URL in elib:https://elib.dlr.de/11753/
Document Type:Article
Additional Information: LIDO-Berichtsjahr=2001,
Title:Design of Robust Autopilot Control Laws with Nonlinear Dynamic Inversion
AuthorsInstitution or Email of AuthorsAuthor's ORCID iD
Journal or Publication Title:at Automatisierungstechnik
Refereed publication:No
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Page Range:pp. 523-531
Keywords:Nonlinear Control Robust Flight Control, Nonlinear Dynamic Inversion, multi-objective optimisation, multi-model approach, automatic landing
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Aeronautics
HGF - Program Themes:other
DLR - Research area:Aeronautics
DLR - Program:L ST - Starrflüglertechnologien
DLR - Research theme (Project):UNSPECIFIED
Location: Oberpfaffenhofen
Institutes and Institutions:Institute of Robotics and Mechatronics (until 2012)
Deposited By: DLR-Beauftragter, elib
Deposited On:16 Sep 2005
Last Modified:14 Jan 2010 17:58

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