Searched for: subject%3A%22Load%255C%2Balleviation%22
(1 - 20 of 22)

Pages

List view
Grid view
document
Lancelot, P.M.G.J. (author)
The exponential growth of the aviation sector combined with environmental and energy supply challenges have led companies to innovate to reduce aircraft fuel consumption. Among the many areas currently under research, this thesis investigates the possibility of making aircraft wings lighter thanks to flight load alleviation systems and more...
doctoral thesis 2023
document
Schildkamp, R.R.M. (author), Chang, J. (author), Sodja, J. (author), De Breuker, R. (author), Wang, Xuerui (author)
This paper proposes an incremental nonlinear control method for an aeroelastic system’s gust load alleviation and active flutter suppression. These two control objectives can be achieved without modifying the control architecture or the control parameters. The proposed method has guaranteed stability in the Lyapunov sense and also has...
journal article 2023
document
Carrillo Córcoles, Xavier (author)
The flared folding wingtip (FFWT) is a concept presented by Airbus to increase the aerodynamic efficiency and provide a means of load alleviation. A gate-to-gate demonstration of this concept has already been presented with the AlbatrossONE, a scaled aircraft featuring the FFWT concept. In this demonstration, the aircraft fold the wingtips...
master thesis 2022
document
Schildkamp, R.R.M. (author), Wang, Xuerui (author), Chang, J. (author), De Breuker, R. (author), Sodja, J. (author)
This paper presents the development and initial characterization of an active, para- metric wing section with aileron and spoiler control surfaces. This wing section is intended to replace the currently used passive wing section setup and facilitate research in active con- trol techniques of aeroelastic phenomena such as flutter, gust load...
conference paper 2022
document
Krüger, Wolf R. (author), Meddaikar, M.Y. (author), Dillinger, J.K.S. (author), Sodja, J. (author), De Breuker, R. (author)
This article presents the application of aeroelastic tailoring in the design of wings for a flying demonstrator, as well as the validation of the design methodology with flight test results. The investigations were performed in the FLEXOP project (Flutter Free Flight Envelope Expansion for Economical Performance Improvement), funded under the...
journal article 2022
document
Schildkamp, R.R.M. (author), Chang, J. (author), Sodja, J. (author), De Breuker, R. (author), Wang, Xuerui (author)
This paper proposes an incremental nonlinear control method for aeroelastic sys- tem gust load alleviation and active flutter suppression. These two control objectives can be achieved without modifying the control architecture or the control parameters. The proposed method has guaranteed stability in the Lyapunov sense and also has robustness...
conference paper 2022
document
van Eemeren, Adri (author)
Both GKN Aerospace Fokker Aerostructures B.V. (Fokker) and Delft University of Technology (DUT) are partaking in a Clean Sky 2 program called MANTA. MANTA stands for: MovAbles in the Next generaTion Aircraft, and is a program created by the European Union in order to meet the ’ACARE Flightpath 2050 objectives’ by achieving...
master thesis 2021
document
Srikanth Vasudevan, Srikanth (author)
High Altitude Long Endurance (HALE) configurations have gained much popularity in the recent past. Although, HALE aircraft enable efficient and environmental-friendly flying, they necessitate a large Aspect-Ratio wing. These slender structures are prone to large, non-linear deformations which further increase the unsteady nature of aerodynamic...
master thesis 2021
document
Binder, S. (author), Wildschek, Andreas (author), De Breuker, R. (author)
This paper presents an analysis of the interaction and trade-off between active aeroelastic control and passive structural tailoring on a free-flying fully flexible aircraft model. Both technologies are included in the preliminary design of a typical transport aircraft configuration with a conventional control surface layout containing...
journal article 2021
document
Bordogna, M.T. (author), Lancelot, P.M.G.J. (author), Bettebghor, Dimitri (author), De Breuker, R. (author)
In aircraft design, proper tailoring of composite anisotropic characteristics allows to achieve weight saving while maintaining good aeroelastic performance. To further improve the design, dynamic loads and manufacturing constraints should be integrated in the design process. The objective of this paper is to evaluate how the introduction of...
journal article 2020
document
Fernandez Barrio, Jorge (author)
A proportionate controller is investigated experimentally for unsteady load alleviation purposes on a 2D wing model with a trailing edge flap. This study is supposed to be a simplified version of a Smart Rotor, a mechanism which deals with the reduction of unsteady loads acting on a wind turbine and aims to understand the behavior of this type...
master thesis 2020
document
Declerck, Laurent (author)
The compound helicopter gains interest as operational needs push future rotorcraft capabilities beyond current standards. The compound helicopter is investigated as part of the Future Vertical Lift Program to replace the entire U.S. Army helicopter fleet. The compound helicopter resembles a mix between a fixed-wing aircraft...
master thesis 2019
document
Isacco, Roberto (author)
Fundamental phase in the preliminary design of an aircraft is the load case choice. Historically, the manoeuvres have been considered as the principal critical loads, while in conceptual design the gusts have been not investigated since, being an intrinsically dynamic phenomenon, they are expensive to analyze. Nevertheless, they are a critical...
master thesis 2019
document
Natella, M. (author), De Breuker, R. (author)
This paper presents a unified framework for aeroelastic tailoring of fully-flexible free-flying composite aircraft. A continuous-time state-space model is used to describe the flow. The 3D composite wing structure is condensed into a Timoshenko beam model utiliz-ing a cross-sectional modeler. The aerodynamic and structural models are tightly...
conference paper 2019
document
Mancini, Andrea (author)
The need to reduce the pollutant impact of aircraft emission drives the research on aircraft design progress through off-design performance improvement. This report proposes to investigate the effect of maneuver load alleviation technology via wing control surfaces. A methodology is presented to model the MLA technology in aircraft conceptual...
master thesis 2018
document
Cancino Queirolo, Mauricio Andrés (author)
Morphing winglets are devices that can improve aircraft aerodynamic efficiency and also be used as load alleviation devices. However, this implementation comes with a weight penalty due to the morphing mechanisms. In the present study two morphing winglet cases are tested, where due to mechanisms compatibilities, only a variable Cant-Span...
master thesis 2018
document
Bussemaker, Jasper (author)
Improving the performance of large transport aircraft requires high aspect ratio and lightweight wings, making aeroelasticity an important factor in wing structural design. Active control of aeroelastic loads can be used to improve the aeroelastic behavior of the wing.<br/><br/>Two active load control techniques are considered: Maneuver Load...
master thesis 2018
document
Frederik, J.A. (author), Kröger, Lars (author), Gülker, Gerd (author), van Wingerden, J.W. (author)
A commonly applied method to reduce the cost of wind energy, is alleviating the periodic loads on turbine blades using Individual Pitch Control (IPC). In this paper, a data-driven IPC methodology called Subspace Predictive Repetitive Control (SPRC) is employed. The effectiveness of SPRC will be demonstrated on a scaled 2-bladed wind turbine....
journal article 2018
document
van Bruchem, Barend-Jan (author)
Helicopters are complex and expensive aircraft with a level of technology that is immature compared to fixed- wing counterparts. Helicopters suffer from vibratory loads stemming from the main rotor and exhibit control and stability problems in the low-speed flight regime. Operating a helicopter near the limits of its flight envelope may result...
master thesis 2017
document
Verhagen, M.R. (author)
master thesis 2015
Searched for: subject%3A%22Load%255C%2Balleviation%22
(1 - 20 of 22)

Pages

List view
Grid view