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Logo Sustainable and Energy Efficient Aviation of TU Braunschweig
B2.4- Hybrid load alleviation by fluidic/reversed control and nonlinear structures
  • ICA B "Flight Physics and Vehicle Systems"
    • B5.2 - Application of physics-based finite-element tools in stiffness tailored structures for cryogenic hydrogen storage for improved mechanical and thermo-mechanical response
    • B4.2 - Consistent Multilevel Model Coupling and Knowledge Representation in Multidisciplinary Analysis and Design
    • B4.1- Collaborative Multidisciplinary Structural Design and Thermal Management for Electric Aircraft
    • B3.5 - Production technologies for hybrid suction designs - Bonding of micro-perforated sheets for hybrid laminar flow control suction panels
    • B3.2 - Advancing the additive xHLFC suction panel concept towards wind-tunnel readiness
    • B3.1 - Protective, multifunctional suction shells for hybrid laminar flow control: Design, integration, simulation and testing
    • B2.5 - EverScale - Enhancement and verification of load alleviation technologies by subscale flight testing
    • B2.4- Hybrid load alleviation by fluidic/reversed control and nonlinear structures
    • B2.3 - ARGO2 - Integrated design of control methods for stability of elastic aircraft
    • B1.9 - Validation of turbulent boundary layer-induced sound transmission through a fuselage section
    • B1.8 - Wind-tunnel experiments of advanced design of swept-wing with suction surfaces
    • B1.7 - Extension of Correlation-based Transition Transport Models for Laminar Aircraft Design
    • B1.6 - Effective Design Methods and Design Exploration for Laminar Wing and Fuselage
    • B1.5 - Sensitivities of Laminar Suction Boundary Layers for Large Reynolds Numbers
    • B1.3- Physics of broadband noise of sound sources from installed propulsors
    • JRG-B1 - Physics of Laminar Wing and Fuselage
    • JRG-B2 - Flow Physics of Load Reduction
    • B1.1 - Propeller and wing aerodynamics of distributed propulsion
    • B1.2 - Aerodynamic analysis of partly embedded boundary layer ingesting propulsors
    • B1.3 - Fast non empiric prediction of propulsion installation related noise
    • B1.4 - Transition Prediction and Design of Hybrid Laminar Flow Control on Blended Wing Bodies Based on 3D Parabolized Stability Equations
    • B2.1 - Load reduction potential of nonlinear stiffness and damping technologies
    • B2.2 - Structural technologies enabling load alleviation
    • B2.3 - Active load Reduction for enabling a 1-G wing using fOrward-looking and distributed sensors (ARGO)
    • B2.4 - Morphing structures for the 1g-wing
    • B3.1 - Global and Local Design Methodology for Laminar Flow Control
    • B3.2 - Process simulation and multiscale manufacturing of suction panels for laminar flow control
    • B3.3 - Thin Plies in Application for Next Generation Aircraft (TANGA)
    • B3.4 - New methods for failure and fatigue analysis of suction panels for laminar flow control
    • B5.1 - ADEMAO: Aircraft Design Engine based on Multidisciplinary Analysis and Optimization
    • JRG-B5 - Long-Range Aircraft Configurations and Technology Analyses
    • JRP - Permeation assessment for cryogenic applications by means of Fiber Bragg Grating sensors
    • ⯇ back to research

B2.4- Hybrid load alleviation by fluidic/reversed control and nonlinear structures

Project description

Concepts of hybrid load alleviation

Effective load alleviation enables radical mass reduction of aircraft wing primary structures and, directly and through secondary effects, also a reduction of overall aircraft mass, energy consumption and emissions. Previous research has shown that both active and passive concepts face limitations in alleviating dynamic loads over the entire flight envelope and for all relevant load cases. The project HyCoNoS will substantiate feasibility of hybrid load alleviation concepts combining smart structural design exploiting structural and geometric nonlinearities, and unconventional actuation methods such as fluidic actuation and control surfaces operated in efficient reversed mode. These individual active and passive load alleviation concepts will initially be parametrically investigated in preparation of a combined application. The most promising concept combinations will be selected and optimized for mid- and long-range aircraft configurations and operating conditions covering the full flight envelope. Based on these results, a comprehensive comparison of different hybrid concepts for load alleviation will be carried out, evaluating their load reduction potential, integration and compatibility with other systems, and climate-relevant impact for the entire aircraft.

Individual concepts

Fluidic actuators
Flow simulations of fluidic actuators

Active flow control with fluidic actuators has the potential to provide fast, efficient, and highly adaptive lift redistribution to alleviate gust loads. The actuators have a strong impact on the flow field around the wing by creating regions of separated flow or shifting the stagnation point around the trailing edge. This can be used to either influence the airfoil lift or create pitching moments that trigger a non-linear structural behavior.

Non-linear structures
Concept sketch of non-linear structures

This passive approach aims to use buckling elements in the wing structure that create a non-linear stiffness behavior with increasing load factor. The non-linearity is triggered by panel buckling at a critical load factor. The bending-torsion coupling then leads to a progressive reduction of angle of attack in the outer wing region in order to shift the lift distribution inboard and therefore reduce the wing root bending moment.

Reversed control
Concept sketch of control surfaces operated in reversed mode

The objective of this concept is to achieve a highly flexible wing that is able to perform extreme load alleviation by utilizing control surfaces as flaps that will control the wing's deformation rather than directly acting as load control devices. For this purpose, aeroelastic tailoring will be utilized to adjust the stiffness of the structure in order to enhance the post reversal regime and maintain aeroelastic stability. The layout of the control surfaces will be optimized for the purpose of this approach and prescheduled deflections will be designed for alleviating maneuver loads and gust loads.


Doctoral researchers

Jorge Bustamante (IFL)

Evangelos Filippou (TU Delft, Aerospace Structures & Materials)

Florian Siebert (ISM)

Project lead

Dr.-Ing. André Bauknecht (Project lead, ISM)

Dr.-Ing. Matthias Haupt (Project Co-PI, IFL)

Dr.ir. R. Roeland De Breuker (Project Co-PI, TU Delft)

Dr. Juri Sodja (Project Co-PI, TU Delft)

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Cluster of Excellence SE²A –
Sustainable and Energy-Efficient Aviation
Technische Universität Braunschweig
Hermann-Blenk-Str. 42
38108 Braunschweig

se2a(at)tu-braunschweig.de
+49 531 391 66661

 

 

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