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Design of Flight Control Laws for Agile and Highly Swept Aircraft Configurations

Kuchar, Richard and Steinhauser, Reinhold and Looye, Gertjan (2015) Design of Flight Control Laws for Agile and Highly Swept Aircraft Configurations. Deutscher Luft- und Raumfahrtkongress 2015, 22.-24.09.2015, Rostock, Deutschland.

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In the course of the FaUSST project scope, a versatile and flexible method for the synthesis of flight control laws (FCL) for agile and highly swept aircraft configurations was required in preparation for upcoming closed-loop assessments of these configurations within the succeeding MEPHISTO project. Therefore methods and tools were required to allow for the integration within the commonly applied, distributed workflow-driven integration environment tool RCE, project specific interfaces and defined aircraft datasets (such as aircraft geometry, aerodynamics, mass and propulsion) together with control synthesis parameters (tuners) as defined within the “Common Parametric Aircraft Configuration Scheme” (CPACS). The resulting control law design philosophy is characterized by the use of model based control strategies – namely the Nonlinear Dynamic Inversion (NDI) method for the inner control loops. This allows the respective outer control loops to be set up as a linear controller structure, as the non-linear control path (the actual aircraft) can be treated as a continuously linearized system – widely independent from the actual aircraft configuration. In addition to this behavior, the described approach allows the partial use of existent methods and tools, currently in use for the generation of open-loop 3-DOF and 6-DOF flight dynamics models – based on the Modelica physical equation language for the actual implementation of the flight dynamics model equations. Thus the respective inner control loops can be automatically derived (auto-coded) by the inversion of the overall model equation system. The outer control loop can then be optimized for a multitude of target functions and tuners as requested by closed-loop flight dynamics assessment capabilities within the project scope. This is achieved by using the DLR-SR optimization tool MOPS (Multi-Objective Parameter Synthesis) being controlled by externally applied control synthesis parameters within CPACS. In the context of the FaUSST project, a “Proof-of-Concept” setup – regarding the described inner/outer control law structure and methods – has been implemented. Ongoing tasks within the MEPHISTO project scope are the further investigation, overall automation and enhancement of the used methods and derived control laws in conjunction with the respective assessment applications.

Item URL in elib:https://elib.dlr.de/100531/
Document Type:Conference or Workshop Item (Speech)
Title:Design of Flight Control Laws for Agile and Highly Swept Aircraft Configurations
AuthorsInstitution or Email of AuthorsAuthor's ORCID iD
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Keywords:Flight Control Law Synthesis, RCE, CPACS, Modelica, NDI
Event Title:Deutscher Luft- und Raumfahrtkongress 2015
Event Location:Rostock, Deutschland
Event Type:national Conference
Event Dates:22.-24.09.2015
Organizer:Deutsche Gesellschaft für Luft- und Raumfahrt e.V.
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:fixed-wing aircraft
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Systems and Cabin (old)
Location: Oberpfaffenhofen
Institutes and Institutions:Institute of System Dynamics and Control > Aircraft System Dynamics
Deposited By: Kuchar, Richard
Deposited On:07 Dec 2015 16:36
Last Modified:15 Jul 2019 10:23

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