CORDIS - EU research results
CORDIS

FLIGHT PHASE ADAPTIVE AERO-SERVO-ELASTIC AIRCRAFT DESIGN METHODS

Deliverables

12 month Progress Report

The project coordinator submits an annual progress report to the European Commission, when it does not coincide with the EC mandatory periodic reporting, indicating the status of the project. The structure of this progress report will be the same as that of the periodic report. Task 5.1

Manufacturing design for advanced wing

Based on the detailed design of the advanced wing from T26 all manufacturing related tooling design activities are performed This includes design of molds support structures attachment structures as well as data model generation for machining and printing processes

Validation of the integrated design toolchain for collaborative design

Validation of the integrated design toolchain for collaborative design based on reengineering of FLEXOP 1 wing characteristics and design

Manufacturing advanced wing and fuselage finalized

The results of the manufacturing of the advanced wing are finalized Special focus will be given to deviations through the production process versus the initial detail design of the advanced wing The report will include all major characteristic data of the manufactured wing eg mass CoGDue to the accident of the demonstrator several improvements are made to the overall avionics and structural layout of the aircraft The corresponding rebuild steps are described in this deliverable as well

Advanced wing integration and ground test completed

Before closure of the wing structure all relevant systems test equipment wiring sensors and actuators need to integrated and tested A detail description of the final wing buildup and internal layout will be documented as well as results from the initial testing of the integrated equipment Due to the fuselage rebuilt several additional tests are necessary to prove the flight worthiness of the aircraft what are also described in this deliverableThe DD actuator acceptance taxi tests and the GVT for the improved demonstrator under construction are described in this deliverable

"Flight Test Programme - Flight Test Phase #3"

A detailed flight test programme is established defining the test objectives means of compliance requirements on specific test procedures to be followed The Flight test programme also specifies abnormal behaviour measures and quality gatesThe deliverable will describe the planned activities for Cochstedt Y23 program

Sensor concept advanced wing finalized

Based on the flight test programme and the formulated means of compliance a detailed sensor concept for the wings as well as for the overall demonstrator are established This includes also the requirements and interface definitions on borad of the demonstrator as well as in the ground control station and the data link equipment

Reference Model Definition

Based on the expertise of partners a set of models with increasing fidelity will be set up, which provides a foundation for tools, interfaces and parameterization of models. The Flexible Aircraft Benchmark defined within D1.5 will also serve as a basis of the Scale-up (Task 4.1) where different candidate baseline configurations will be defined, and the Design Toolchain from Task 2.6 will be applied to these candidate configurations via the standardized interfaces.

Report on quantified design benefits, as compared with reference

The report assesses the benefit gained with the developed design process on the scaleup aircraft model

Exploitation and Dissemination Plan

Exploitation goals of the consortium and the planning of the individual partners will be compiled in the Exploitation and Dissemination Plan. A preliminary version of the Exploitation and Dissemination Plan will be generated mid-project. The general objectives of the dissemination activities are: • to ensure maximum awareness and visibility of the achievements and results of the project particularly in influential aerospace bodies, • to make known new methodologies and standards that could be obtained as a part of the project results and to encourage their use to carry on this line of investigation, • to promote the use of the new technology developed and tested in the project, across companies and institutions who have an interest in flexible aircraft design. Task 5.3

Validation of data science based methods for modelling and control

This report addresses the aspects of linear parametrized model approximation of dynamical systems in view of control design The modelfree or databased approaches and their application to the flight data specific objectives will be described within the deliverable In this work we are adopting bigdata techniques to analyze the vast data provided by the complex sensing and control system These methodologies are useful in mapping and revealing the underlying structure of the problem Data science technologies for optimal usage of these data are developed in FliPASED and recommendations for methods and useful sensor arrangements for future aerospace applications are described

Report on flight control system layout

Report describing the flight control architecture and structure. This control structure will address the complete integrated avionic process including aircraft shape, sensors and actuator locations and detailed control design. The aim of the report is more to detail the structure and tuning variables rather than the methodology employed to adjust them. This latter will serve as baseline for developments of WP2 activities

Scale-up design objectives

Captures and describes the design objectives for the scaleup study

Scale-up aircraft re-design and control system lay-out

Control system layout to be used in the scaleup aircraft model The parameters will be optimized within the MDO process

"Flight Test Programme – Flight Test Phase #1"

A detailed flight test programme is established defining the test objectives, means of compliance, requirements on specific test procedures to be followed. The Flight test programme also specifies abnormal behaviour measures and quality gates.

Wing and demonstrator actuation and sensing conceptual design requirements

The deliverable will capture the requirements related to the attainement of proposed project goals. To be able to demonstrate wing shape control the shape of the wing has to be estimated and proper actuators with the adequate flight control surfaces have to be placed on the aircraft. The rationale behind the conceptual design requirements will be documented in D1.1.

Standardization recommendations for data and model databases and tools

Based on the lessons learnt during the adaptation of tools in WP2 and their successful application to the demonstrator platform WP3 and to the scaleup task WP4 the recommendations for an iterative modelling framework will be established and formally defined in D17 Data from aircraft design scaleup simulation and flight test data will be assembled into a logical format with recommendations how to standardize the corresponding output analysis and design pairs respecting their interdependency

Data management plan

The DMP will provide guidelines for the project partners with regard to all the datasets that will be generated within the project. The DMP will address the naming conventions, description of datasets, standards and metadata, and data sharing properties on a dataset by dataset basis. The DMP will be updated reflecting the current status of view on the data that will be produced, evolving during the lifespan of the project. Task 5.1

24 month Progress Report

The project coordinator submits an annual progress report to the European Commission when it does not coincide with the EC mandatory periodic reporting indicating the status of the project The structure of this progress report will be the same as that of the periodic reportTask 51

Analytical redundancy methods

In order to achieve the project goals with a reliable avionics architecture the already installed sensor and actuator settings will be used in a novel to define input and output blending, as well as novel sensor and actuator fusion to provide fault tolerance. In addition, the challenging and open problem of optimal sensor/actuator selections is investigated in relation to the novel movables design. The document will describe the proposed FDIR and sensor-actuator selection methods and their application to the demonstrator aircraft configuration

Final Report

The project coordinator submits a final report to the European Commission covering the whole lifspan of the project while the 2nd periodic report which will be submitted at the same time will only cover the period M19M36 The structure of this progress report will be the same as that of the periodic report The report will be submitted after the closure of the project aligned with H2020 regulation

Demonstrator ground and flight test requirements definition

To be able to demonstrate the proposed innovative ac design cycle the flight test will have to provide sufficiently rich information for both iterative refinement of tools and methods and proof about their performance According to the project objectives the ground and flight test requirements will be documented in D13 to be aligned with the remaining workpackages

"Flight Test Programme - Flight Test Phase #2"

A detailed flight test programme is established defining the test objectives means of compliance requirements on specific test procedures to be followed The Flight test programme also specifies abnormal behaviour measures and quality gates

Requirements capture for a/c MDO design

The requirements for Integrated, Collaborative Design Tool Chain are developed first within D1.2, since that lays the foundation of the experimental and analytical research within the project. The aircraft sizing cycle has to fulfil various constraints, while optimizing fuel consumption and passenger comfort, to name a few. So their tradeoff and the required fidelity in the preliminary design stage are described in the deliverable, including the proposed way to incorporate novel steps within the MDO cycle - including control system parameters.

"Flight Test Report - Flight Test Phase #3"

Based on the Flight Test programme for the specific flight test campaign the test conditions eg wheather aircraft configuration CoG weight will be documented as well as occurances or abnomalies during the conducted test flight Flight test data will decribed with respect to formats correction factors etcThe document will describe the two consecutive flight test campaigns of Y23 at DLR Cochstedt

Data Analytics for Model Validation

The data from flight tests will serve as a baseline to validate structural dynamics aerodynamics controls and avionics instrumentation models Analysis tools with standard validation routines will be provided in Nastran and Matlab environment for structural dynamics and controls respectively These tools along with Python based data science software will be used within the project and the underlying theory along with interfaces of these tools will be documented in D16

"Flight Test Report - Flight Test Phase #2"

Based on the Flight Test programme for the specific flight test campaign the test conditions eg wheather aircraft configuration CoG weight will be documented as well as occurances or abnomalies during the conducted test flight Flight test data will decribed with respect to formats correction factors etcThe deliverable will describe the flights conducted in the test campaigns during Y22

Information and interfaces definition for Collaborative Work Process

The interdisciplinary teams within the project will share models data and tools among them D14 formalizes these steps within the iteration loops and establishes a document to define their interdependency and their standard interfaces CAD NASTRAN Dymola MatlabSimulink embedded C code

"Flight Test Report - Flight Test Phase #1"

Based on the Flight Test programme for the specific flight test campaign the test conditions eg wheather aircraft configuration CoG weight will be documented as well as occurances or abnomalies during the conducted test flight Flight test data will decribed with respect to formats correction factors etc

Aero-servo-structural design of the new advanced FliPASED wing

This report addresses the way to construct an Aeroservostructural design of the new advanced FliPASED wing

Report on tool adaptation for collaborative design

The report will consider at first the construction of parametrized structural model using CAD and FEM methods. Then, as a second step, the generation of reduced and parametric dynamical models, tailored to the analysis and the control design will be done. The purpose is to define an approach to bridge the gap between accurate and complex to accurate and simple models.

Project webpage and social media

The project website will provide information on basic project information, partners, publications, links and contact information. Mathematical models of the demonstrator developed for aircraft design will be posted on the project website, together with ground and flight test data of various aircraft configurations, to provide a benchmark for the entire community. Project news will be posted on Linkedin. Task 5.1 and 5.2

Workshop / Final Exploitation and Dissemination Report

Organization of an International Workshop on Interdisciplinary Design Principles for Flexible Wing Aircraft Technology to be held and open to worldwide experts in the area and EU graduate students Final Exploitation and Dissemination Report Exploitation goals of the consortium and the planning of the individual partners will be compiled in the Exploitation and Dissemination Plan A preliminary version of the Exploitation and Dissemination Plan will be generated midproject The general objectives of the dissemination activities are to ensure maximum awareness and visibility of the achievements and results of the project particularly in influential aerospace bodiesto make known new methodologies and standards that could be obtained as a part of the project results and to encourage their use to carry on this line of investigationto promote the use of the new technology developed and tested in the project across companies and institutions who have an interest in flexible aircraft designTask 53

Flight Test Data published in Open Research Data format

The flight test data generated within the project will be published according to the standards of the Open Research Data Pilot The deliverable is tightly coupled with the flight test reports and feeds into the public dissemination workshop at the end of the project The initial release will be done at M39 but the data repository will be populated as we proceed with the ground and flight test campaigns and with the scaleup

Publications

Development of Flight Test Data Analysis Tools

Author(s): Fernando Puelles
Published in: 2022
Publisher: TUM

Retrofit Design of an UAV wing for active drag control

Author(s): Lawan Nuri Sharif
Published in: 2022
Publisher: TUM

Improvement and Further Design of a Thrust Measurement System for In-Flight Applications on an Unmanned aerial Vehicle

Author(s): Pedro Alexandre Tonet Fleig
Published in: 2021
Publisher: TUM

Nonlinear Static Aeroelastic Analysis of T-FLEX UAV

Author(s): Elias Simon Peter
Published in: 2023
Publisher: TUM

Analysis and Structural redesign of the FLEXOP demonstrator main landinggear

Author(s): Sebastian Lang
Published in: 2021
Publisher: TUM

Independent power consumption measurement device developement for the FLEXOP demonstartor

Author(s): Guthörl Matthias Frank
Published in: 2021
Publisher: TUM

Drag Reduction with Active Wing Shape Control

Author(s): Chang Xu
Published in: 2023
Publisher: TUM

Development of Flight Test Data Analysis and Planning Tools

Author(s): Mehdi Hammami
Published in: 2021
Publisher: TUM

Observer-based capture of dynamic behaviour change on a UAV flight control surface

Author(s): Olivia Aschermann
Published in: 2024
Publisher: TUM

Effects of reference signal shaping in UAV servos

Author(s): Joschua Gosda
Published in: 2022
Publisher: TUM

Implementation of Structural Sizing in the MultiDisciplinary Design Toolchain

Author(s): SAI KIRAN EDIGA
Published in: 2023
Publisher: TUM

Software Development and Laboratory Testing of an Electro-Mechanical Actuator Control and Monitoring Unit

Author(s): Kenneth Yhen Hong Leow
Published in: 2022
Publisher: TUM

Arturo Gutierrez Munoz

Author(s): Arturo Gutierrez Munoz
Published in: 2023
Publisher: TUM

Implementation of a conceptual design toolchain for D150 configuration

Author(s): Yi Zhan
Published in: 2023
Publisher: TUM

Embedded Software development for the Actuator Control and Monitoring Unit

Author(s): Yuchen Chou
Published in: 2024
Publisher: TUM

Flexible airplane’s induced drag modelling with panel methods and its reduction with active wing shape deformation

Author(s): Balázs Vidor Huszár
Published in: 2023
Publisher: Budapest Univesity Of Technology And Echonomics

Retrofitting actuators on the T-FLEX demonstartor with enxhanced actuator monitoring system

Author(s): Chen Xiaohui
Published in: 2024
Publisher: TUM

Uncertain systems: analysis and synthesis with application to flutter suppression control

Author(s): Bálint Patartics
Published in: 2022
Publisher: Budapest University of Technology and Economics

Optimal Decoupling of Dynamic Systems: a Convex Approach with Aerospace Applications

Author(s): Tamás Baár
Published in: 2023
Publisher: Budapest University of Technology and Economics

Drag Modelling of FLEXOP Demonstrator with CFD

Author(s): German Nogues Armengol
Published in: 2022
Publisher: TUM

Aerodynamic and Structural Configuration Potential for FLEXOP UAV

Author(s): Johanna Kärner
Published in: 2022
Publisher: TUM

DEVELOPMENT, FLIGHT-TESTING AND EVALUATION OF A SUBSCALE DYNAMIC DEMONSTRATOR TO REPRODUCE THE STALL BEHAVIOR OF A SWEPT WING RESEARCH UAV

Author(s): Bastian Scheufele
Published in: 2022
Publisher: TUM

Fault detection algorithm development for UAV actuators

Author(s): Mohamed El Hedi Letaief
Published in: 2024
Publisher: TUM

Analysis and Structural redesign of the FLEXOP demonstrator main landinggear

Author(s): Sebastian Lang
Published in: 2024
Publisher: TUM

Multidisciplinary Design Optimization of Flexible Aircraft with Flutter Suppression Control

Author(s): Zsombor Wermeser
Published in: 2022
Publisher: Budapest Univesity Of Technology And Echonomics

Application of Grid-based and TP-based Control for Active Flutter Suppression of Flexible Aircraft

Author(s): Gribkov Aleksandr
Published in: 2023
Publisher: Budapest Univesity Of Technology And Echonomics

Feasibility Study of an Aeroelastic Pseudo-Satellite

Author(s): Ákos László Radványi
Published in: 2022
Publisher: Budapest Univesity Of Technology And Echonomics

Drag optimization by means of control surface deflections for T-FLEX demonstrator

Author(s): Martin Löwenhauser
Published in: 2022
Publisher: TUM

Development and Implementation of a Framework for Telemetry Data Visualization and UAV Guidance

Author(s): Marius Weber
Published in: 2022
Publisher: TUM

Design, Implementation and Flight Testing of a Subscale Dynamic Demonstrator.

Author(s): Bastian Scheufele
Published in: 2022
Publisher: TUM

Drag influence on TFLEX UAV from airbrakes and landing gear

Author(s): Olga Balaska
Published in: 2023
Publisher: TUM

Calibration and Testing of an In-Flight Thrust Measurement System for UAV Applications

Author(s): Annina Metzner
Published in: 2022
Publisher: TUM

Investigation and Implementation of Airspeed Calibration Methods based on UAV Flight Test Data

Author(s): Simon Schelle
Published in: 2022
Publisher: TUM

Design, manufacturing and testing of an Instrumented Wing Glove for in-flight UAV applications

Author(s): Daniel Harlander
Published in: 2021
Publisher: TUM

Software development for the ACMU system

Author(s): Victor Magalhaes
Published in: 2023
Publisher: TUM

Surrogate Drag Modeling for a Flexible Wing Passenger Aircraft using Panel Methods

Author(s): Milán Barczi
Published in: 2022
Publisher: Budapest Univesity Of Technology And Echonomics

Application of Orthogonal Multi-Sine Inputs for Flight Testing of UAVs.

Author(s): Marius Weber
Published in: 2022
Publisher: TUM

Loads Analysis of T-FLEX UAV

Author(s): Huang Ching-Ting
Published in: 2023
Publisher: TUM

Comparison of low and high order aerodynamic modelling of an UAV

Author(s): Marius Haag
Published in: 2021
Publisher: TUM

Aerodynamic study of wing manufacturing defects for a UAV

Author(s): Sergio Augustin Gallego
Published in: 2022
Publisher: TUM

Wing shape estimation with Extended Kalman filtering and KalmanNet neural network of a flexible wing aircraft

Author(s): Bence Zsombor Hadlaczky, Noémi Friedman, Béla Takarics, Balint Vanek
Published in: Proceedings of The 5th Annual Learning for Dynamics and Control Conference, Issue 211, 2023, Page(s) 1429-1440
Publisher: PMLR

Comparing Different Potential Flow Methods for Unsteady Aerodynamic Modelling of a Flutter Demonstrator Aircraft

Author(s): Thiemo M. Kier
Published in: AIAA SCITECH 2023 Forum, 2023
Publisher: American Institute of Aeronautics and Astronautics, Inc.
DOI: 10.2514/6.2023-0177

A Novel Updating Algorithm for Linearized State-Space Models of an Unmanned Flexible Aircraft Using Flight Test Data

Author(s): Özge Süelözgen
Published in: AIAA SCITECH 2022 Forum, 2021
Publisher: American Institute of Aeronautics and Astronautics, Inc.
DOI: 10.2514/6.2022-0725

Flight Testing of 65kg FLEXOP Subscale Demonstrator

Author(s): Julius Bartasevicius, Sebastian J. Koeberle, Daniel Teubl, Christian Roessler, Mirko Hornung
Published in: Proceedings of the 32nd Congress of the International Council of the Aeronautical Sciences (ICAS2021), Issue Biannual conference, 2021
Publisher: ICAS

Decoupled parameter identification for a flexible aircraft

Author(s): S. Olasz-Szabó, T. Baár, T.Luspay
Published in: EURO GNC 2022, 2022
Publisher: CEAS

Validation and Update of an Aeroservoelastic Model based on Flight Test Data

Author(s): Matthias Wustenhagen, Ozge Suelozgen, Lukas Ackermann, Julius Bartasevicius
Published in: 2021 IEEE Aerospace Conference (50100), 2021, Page(s) 1-18, ISBN 978-1-7281-7436-5
Publisher: IEEE
DOI: 10.1109/aero50100.2021.9438354

Hardware-in-the-loop testing of a miniaturized real time flutter monitoring system for UAVs

Author(s): Soal, Keith Ian and Nagy, Mihaly and Teubl, Daniel and Volkmar, Robin and Thiem, Carsten and Meddaikar, Muhammad Yasser and Vanek, B. and Govers, Yves and Böswald, Marc
Published in: 30th International Conference on Noise and Vibration Engineering, ISMA 2022, 2022
Publisher: ISMA

COMPARING POTENTIAL FLOW SOLVERS FOR AERODYNAMIC CHARACTERISTICS ESTIMATION OF THE T-FLEX UAV

Author(s): Fanglin Yu; Julius Bartasevicius; Mirko Hornung
Published in: ICAS PROCEEDINGS 33th Congress of the International Council of the Aeronautical Sciences, Issue Biannual conference, 2022
Publisher: International Council of the Aeronautical Sciences
DOI: 10.6084/m9.figshare.21656960

Aeroservoelasticity Investigation with Panel Method

Author(s): Ábel OLGYAY, Béla TAKARICS, Bence KÖRÖSPARTI, János LELKES, Csaba HORVÁTH, Bálint VANEK
Published in: The 18th International Conference on Fluid Flow Technologies, 2022
Publisher: CMFF

Flight Vibration Testing of the T-FLEX UAV using Online Modal Analysis

Author(s): Keith Soal, Robin Volkmar, Carsten Thiem, Julian Sinske, Yasser M. Meddaikar, Yves Govers, Marc Böswald, Daniel Teubl, Julius Bartasevicius, Mihaly Nagy and Balint Vanek
Published in: AIAA SCITECH 2023 Forum, 2023
Publisher: American Institute of Aeronautics and Astronautics, Inc.
DOI: 10.2514/6.2023-0373

Parameter Uncertainty Analysis in Precise Pointing Control of Flexible Spacecraft

Author(s): Janos Bezsilla, Bela Takarics, Balint Vanek, Jian Guo
Published in: IFAC MATHMOD 2022, 2022
Publisher: Vienna, Austria
DOI: 10.1016/j.ifacol.2022.09.102

Application and Validation of a Model Updating Approach for Linearized State-Space Models of Flexible Aircrafts Using Multiple Flight Test Data

Author(s): Özge Süelözgen
Published in: AIAA SCITECH 2023 Forum, 2023
Publisher: American Institute of Aeronautics and Astronautics, Inc.
DOI: 10.2514/6.2023-0374

Model Selection for a Multiple-Model Adaptive Gust Load Alleviation Controller

Author(s): Matthias Wustenhagen
Published in: International Forum on Aeroelasticity and Structural Dynamics IFASD 2022, 2022
Publisher: Organization Committee of IFASD 2021

Flight Testing for Flutter – Operational Design and Lessons Learned

Author(s): Julius Bartasevicius, Mirko Hornung
Published in: SFTE International Symposium 2023, 2023
Publisher: SFTE

Application and Validation of a New Updating Algorithm for Linearized State-Space Models of Flexible Aircrafts Using Flight Test Data

Author(s): Özge Süelözgen, Gertjan Looye
Published in: 19th International Forum on Aeroelasticity and Structural Dynamics (IFASD 2022), 2022
Publisher: Organization Committee of IFASD 2021

In-flight drag measurement and validation for a medium-sized UAV

Author(s): Julius Bartasevicius, Mirko Hornung
Published in: AIAA SCITECH 2023 Forum, 2023
Publisher: American Institute of Aeronautics and Astronautics, Inc.
DOI: 10.2514/6.2023-0372

Design and testing of an in-flight thrust measurement system for a pylon-mounted miniature jet engine

Author(s): Julius Bartasevicius, Pedro A. Fleig, Annina Metzner and Mirko Hornung
Published in: AIAA SCITECH 2022 Forum, 2021
Publisher: American Institute of Aeronautics and Astronautics, Inc.
DOI: 10.2514/6.2022-1827

Robust Minimum Gain Lemma

Author(s): Tamás Baár, Tamás Luspay
Published in: 2021 60th IEEE Conference on Decision and Control (CDC), 2022, ISBN 978-1-6654-3659-5
Publisher: IEEE
DOI: 10.1109/cdc45484.2021.9683413

Synthesis of a Multiple-Model Adaptive Gust Load Alleviation Controller for a Flexible Flutter Demonstrator

Author(s): Matthias Wuestenhagen
Published in: AIAA SCITECH 2022 Forum, 2021
Publisher: American Institute of Aeronautics and Astronautics, Inc.
DOI: 10.2514/6.2022-0440

Comparison of EKF and Neural Network based wing shape estimation of a flexible wing demonstrator

Author(s): B Hadlaczky, N Friedman, B Takarics, B Vanek
Published in: 19th International Forum on Aeroelasticity and Structural Dynamics (IFASD 2022), 2022
Publisher: Organization Committee of IFASD 2021

Gust Load Alleviation Control of Aircraft with Varying Mass Distribution

Author(s): Matthias Wüstenhagen
Published in: AIAA SCITECH 2023 Forum, 2023
Publisher: American Institute of Aeronautics and Astronautics, Inc.
DOI: 10.2514/6.2023-0371

An Integral Flexible Aircraft Model for Optimal Control Surface Scheduling of Manoeuvre Load Alleviation and Wing Shape Control Functions

Author(s): Thiemo Kier
Published in: 19th International Forum on Aeroelasticity and Structural Dynamics (IFASD 2022), 2022
Publisher: Organization Committee of IFASD 2021

Model Based Automatic Control Design for the T-FLEX Demonstrator Using RCE Environment

Author(s): Béla Takarics, Bálint Patartics, Tamás Luspay, Balint Vanek, Charles Poussot-Vassal, Pierre Vuillemin and Matthias Wuestenhagen
Published in: AIAA SCITECH 2023 Forum, 2023
Publisher: American Institute of Aeronautics and Astronautics, Inc.
DOI: 10.2514/6.2023-0175

Aeroservoelastic induced drag modelling and minimization for the T-FLEX demonstrator

Author(s): Yasser M. Meddaikar, Thiemo M. Kier, Julius Bartasevicius, Fanglin Yu, Balint Vanek, Abel Olgyay and Béla Takarics
Published in: AIAA SCITECH 2023 Forum, 2023
Publisher: American Institute of Aeronautics and Astronautics, Inc.
DOI: 10.2514/6.2023-0176

On the necessity of flexible modelling in fault detection for a flexible aircraft

Author(s): Balint Patartics, Yagiz Kumtepe, Bela Takarics, Balint Vanek
Published in: IFAC-PapersOnLine, Issue 54/20, 2021, Page(s) 663-668, ISSN 2405-8963
Publisher: Elsevier
DOI: 10.1016/j.ifacol.2021.11.247

Grid and Polytopic LPV Modeling of Aeroelastic Aircraft for Co-design

Author(s): Réka Dóra Mocsányi, Béla Takarics, Bálint Vanek
Published in: IFAC-PapersOnLine, Issue 53/2, 2020, Page(s) 5725-5730, ISSN 2405-8963
Publisher: Elsievier
DOI: 10.1016/j.ifacol.2020.12.1600

Identification and Modeling of the Airbrake of an Experimental Unmanned Aircraft

Author(s): Peter Bauer, Lysandros Anastasopoulos, Franz-Michael Sendner, Mirko Hornung, Balint Vanek
Published in: Journal of Intelligent & Robotic Systems, Issue 100/1, 2020, Page(s) 259-287, ISSN 0921-0296
Publisher: Kluwer Academic Publishers
DOI: 10.1007/s10846-020-01204-1

Control-oriented Aircraft Modelling and Analysis Framework for Educational Purposes

Author(s): Réka Dóra Mocsányi, Béla Takarics, Bálint Vanek
Published in: IFAC-PapersOnLine, Issue 54/12, 2021, Page(s) 26-31, ISSN 2405-8963
Publisher: Elsevier
DOI: 10.1016/j.ifacol.2021.11.005

Advantages of flexible aircraft model based FDI

Author(s): Bálint Patartics, Bálint Vanek
Published in: IFAC-PapersOnLine, Issue 55/6, 2022, Page(s) 603-610, ISSN 2405-8963
Publisher: Elsevier
DOI: 10.1016/j.ifacol.2022.07.194

Application of Structured Robust Synthesis for Flexible Aircraft Flutter Suppression

Author(s): Balint Patartics, Gyorgy Liptak, Tamas Luspay, Peter Seiler, Bela Takarics, Balint Vanek
Published in: IEEE Transactions on Control Systems Technology, 2021, Page(s) 1-15, ISSN 1063-6536
Publisher: Institute of Electrical and Electronics Engineers
DOI: 10.1109/tcst.2021.3066096

Robust Control Design for the FLEXOP Demonstrator Aircraft via Tensor Product Models

Author(s): Béla Takarics and Balint Vanek
Published in: Asian Journal of Control, Issue Published six times a year, 2021, Page(s) 1-11, ISSN 1934-6093
Publisher: Wiley
DOI: 10.1002/asjc.2547

Grid-Based and Polytopic Linear Parameter-Varying Modeling of Aeroelastic Aircraft with Parametric Control Surface Design

Author(s): Réka Dóra Mocsányi, Béla Takarics, Aditya Kotikalpudi, Bálint Vanek
Published in: Fluids, Issue 5/2, 2020, Page(s) 47, ISSN 2311-5521
Publisher: MDPI
DOI: 10.3390/fluids5020047

Worst Case Uncertainty Construction via Multifrequency Gain Maximization With Application to Flutter Control

Author(s): B Patartics, P Seiler, B Takarics, B Vanek
Published in: IEEE Transactions on Control Systems Technology, Issue 31/1, 2022, Page(s) 155 - 165, ISSN 1063-6536
Publisher: Institute of Electrical and Electronics Engineers
DOI: 10.1109/tcst.2022.3173044

Construction of a Destabilizing Nonlinearity for Discrete-Time Uncertain Lurye Systems

Author(s): B Patartics, P Seiler, J Carrasco, B Vanek
Published in: IEEE Control Systems Letters, Issue 6, 2022, Page(s) 2605 - 2610, ISSN 2475-1456
Publisher: IEEE
DOI: 10.1109/lcsys.2022.3171707

Robust decoupling of uncertain subsystems

Author(s): Tamás Baár, Tamás Luspay
Published in: International Journal of Robust and Nonlinear Control, Issue 32/11, 2023, Page(s) 6086-6109, ISSN 1099-1239
Publisher: John Wiley & Sons Ltd
DOI: 10.1002/rnc.6141

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