| People | Locations | Statistics |
|---|---|---|
| Naji, M. |
| |
| Motta, Antonella |
| |
| Aletan, Dirar |
| |
| Mohamed, Tarek |
| |
| Ertürk, Emre |
| |
| Taccardi, Nicola |
| |
| Kononenko, Denys |
| |
| Petrov, R. H. | Madrid |
|
| Alshaaer, Mazen | Brussels |
|
| Bih, L. |
| |
| Casati, R. |
| |
| Muller, Hermance |
| |
| Kočí, Jan | Prague |
|
| Šuljagić, Marija |
| |
| Kalteremidou, Kalliopi-Artemi | Brussels |
|
| Azam, Siraj |
| |
| Ospanova, Alyiya |
| |
| Blanpain, Bart |
| |
| Ali, M. A. |
| |
| Popa, V. |
| |
| Rančić, M. |
| |
| Ollier, Nadège |
| |
| Azevedo, Nuno Monteiro |
| |
| Landes, Michael |
| |
| Rignanese, Gian-Marco |
|
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
Places of action
| Organizations | Location | People |
|---|
document
Assessment of an Increased-Fidelity Aeroelastic Experiment for Free Flying Wing Response to Gust Excitation
Abstract
The paper proposes a methodology for increased-fidelity aeroelastic testing in a wind tunnel environment to improve the correlation between the aeroelastic response measured in a wind tunnel experiment and the aeroelastic response observed on an aircraft in flight. The focus of the current study is to assess the potential of the proposed methodology to improve load and response predictions by emulating the motion of a free flying aircraft at the root of the wing. For this purpose a numerical aeroelastic model of a free flying aircraft is used to obtain a reference aeroelastic response to gust excitation. The model is reduced to obtain an aeroelastic model comprising only the main wing of the aircraft which is clamped at the root as if it would be mounted in a wind tunnel. The wing is then subjected to five different motion profiles emulating the free flight to a various degree. The considered motion profiles are clamped boundary condition, heave-pitch motion of a free flying aircraft, motion profile following the angle of attack of the aircraft, and two modified heave-pitch motion profiles which match the angle of attack and the aerodynamic loads in the wind tunnel with those in free flight. The study shows that the considered motion profiles can significantly improve the correlation between the wind tunnel experiment and free flight. However, the effectiveness of each motion profile strongly depends on the gust length which indicates that the optimum motion profile depends on the gust length. Finally, the paper presents a conceptual design of a wind tunnel demonstrator to serve as a proof-of-concept for the proposed methodology.