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| Naji, M. |
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| Motta, Antonella |
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| Aletan, Dirar |
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| Mohamed, Tarek |
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| Ertürk, Emre |
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| Taccardi, Nicola |
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| Kononenko, Denys |
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| Petrov, R. H. | Madrid |
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| Alshaaer, Mazen | Brussels |
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| Bih, L. |
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| Casati, R. |
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| Muller, Hermance |
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| Kočí, Jan | Prague |
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| Šuljagić, Marija |
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| Kalteremidou, Kalliopi-Artemi | Brussels |
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| Azam, Siraj |
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| Ospanova, Alyiya |
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| Blanpain, Bart |
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| Ali, M. A. |
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| Popa, V. |
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| Rančić, M. |
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| Ollier, Nadège |
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| Azevedo, Nuno Monteiro |
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| Landes, Michael |
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| Rignanese, Gian-Marco |
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Breuker, Roeland De
Delft University of Technology
in Cooperation with on an Cooperation-Score of 37%
Topics
Publications (22/22 displayed)
- 2024Aeroelastic Tailoring of a Strut-Braced Wing for a Medium Range Aircraftcitations
- 2023Optimization Framework of a Ram Air Inlet Composite Morphing Flapcitations
- 2022Application of Aeroelastic Tailoring for Load Alleviation on a Flying Demonstrator Wing †citations
- 2022Assessment of an Increased-Fidelity Aeroelastic Experiment for Free Flying Wing Response to Gust Excitation
- 2022Aeroelastic Wing Demonstrator with a Distributed and Decentralized Control Architecturecitations
- 2022An aeroelastic optimisation framework for manufacturable variable stiffness composite wings including critical gust loadscitations
- 2021Development and testing of an active trailing edge morphing demonstrator for a rotary wingcitations
- 2021Skin Panel Optimization of the Common Research Model Wing using Sandwich Compositescitations
- 2021Aeroelastic optimisation of manufacturable tow-steered composite wings with cruise shape constraint and gust loadscitations
- 2021Developing the Model Reduction Framework in High Frame Rate Visual Tracking Environment
- 2020Static and dynamic aeroelastic tailoring with composite blending and manoeuvre load alleviationcitations
- 2020Ground Testing of the FLEXOP Demonstrator Aircraftcitations
- 2019Aeroelastic optimization of composite wings including fatigue loading requirementscitations
- 2018FLEXOP – Application of aeroelastic tailoring to a flying demonstrator wing
- 2018Aeroelastic optimization of composite wings subjected to fatigue loadscitations
- 2017Aeroelastic Design of Blended Composite Structures Using Lamination Parameterscitations
- 2017Aeroelastic tailoring for static and dynamic loads with blending constraints
- 2016Aeroelastic Optimization of Variable Stiffness Composite Wing with Blending Constraintscitations
- 2016A Conceptual Development of a Shape Memory Alloy Actuated Variable Camber Morphing Wing
- 2016Derivation and application of blending constraints in lamination parameter space for composite optimisationcitations
- 2015Special Issue
- 2015Development and Testing of an Unconventional Morphing Wing Concept with Variable Chord and Camber
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document
Aeroelastic Wing Demonstrator with a Distributed and Decentralized Control Architecture
Abstract
This study investigated the design and development of an autonomous aeroservoelastic wing concept with distributed flaps. This wing demonstrator was developed in the scope of the SmartX project, aiming to demonstrate in-flight performance optimization and multi-objective control with over-actuated wing designs. Following a successful test campaign with a previous wing design based on active morphing, this study aims to develop an over-actuated aeroelastic wing design suitable for aeroelastic control, including flutter suppression, maneuver and gust load alleviation. A decentralized control architecture is developed for the over-actuated and over-sensed system, allowing efficient sensing data processing and control algorithms. Aerodynamic and structural analyses are performed to determine actuator torque requirements and actuation mechanism design. Furthermore, buckling analysis is performed to size the wing structure. A state-space aeroelastic dynamic model is established to analyze the gust response and control effectiveness of the wing. It is established that a linear quadratic regulator significantly improves the closed-loop performance. Furthermore, the hypotheses are confirmed that fast actuation improves load alleviation performance and high-frequency disturbance rejection effectiveness. The manufacturing and integration of the wing demonstrator are discussed, which lay a foundation for future static and dynamic wind-tunnel experiments.