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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

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.

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

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

"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.

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

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

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.

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

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Publications

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
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
DOI: 10.1007/s10846-020-01204-1

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
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
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
DOI: 10.3390/fluids5020047

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

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
DOI: 10.1109/aero50100.2021.9438354