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Konzeptstudie zu Stoßkontrollsystemen

Künnecke, Sven Christian and Riemenschneider, Johannes and Vasista, Srinivas (2020) Konzeptstudie zu Stoßkontrollsystemen. DLRK 2020, 01. - 03. Sep. 2020, Online (ursprünglich Aachen).

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Official URL: https://dlrk2020.dglr.de/nc/paper_download/index.html

Abstract

To save fuel and to improve the associated reduction of greenhouse gas emissions in aviation the laminar wing technology offers a promising potential. This includes technologies such as NLF (Natural Laminar Flow) and HLFC (Hybrid Laminar Flow Control). At transonic flights a supersonic region can occur in the flow field on the wing which leads to the development of a transonic shock. This shock increases the wave drag and consequently the total drag of the wing and thus of the whole aircraft. This leads to higher fuel consumption and accordingly to higher emissions. Shock Control Bumps (SCBs) are bumps or contour changes on the wing surface which offer a promising solution to reduce the strength of the transonic shock and thus wave drag. This phenomenon has been investigated intensively from an aerodynamic perspective which allows conclusions to be drawn regarding the shape and position on the wing of these bumps. Furthermore, these aerodynamic investigations show that the largest potential lies in adaptive SCBs which can be adjusted and modified according to changing flight and flow conditions. In this regard, the two most important control parameters are the height and position of the bump. Apart from aerodynamic effects of shock control systems, concepts for the technical feasibility of adaptive SCBs have been published. In this work, several concepts for enabling SCBs or reducing the shock strength are summarized and compared against each other. Aspects such as technical feasibility, structural and systems designs are considered in light of their benefits that they afford. Among them are on the one hand concepts which use primarily the spoiler actuator to from a bump and on the other hand concepts with several smaller actuators like the Tube Spring or the Fish-Mouth actuator as well as pressurized chambers. However, in this work special attention is paid to concepts of morphing contour bumps on the spoiler, e.g. reshaping of the original geometry, in contrast to other concepts like porous materials or plasma heating elements. Furthermore, a new concept of an adaptive SCB will potentially also be presented, pending on the availability of results.

Item URL in elib:https://elib.dlr.de/135938/
Document Type:Conference or Workshop Item (Speech)
Title:Konzeptstudie zu Stoßkontrollsystemen
Authors:
AuthorsInstitution or Email of AuthorsAuthor's ORCID iD
Künnecke, Sven ChristianSven.Kuennecke (at) dlr.dehttps://orcid.org/0000-0002-7139-3492
Riemenschneider, JohannesJohannes.Riemenschneider (at) dlr.dehttps://orcid.org/0000-0001-5485-8326
Vasista, SrinivasSrinivas.Vasista (at) dlr.dehttps://orcid.org/0000-0002-7917-6740
Date:2 September 2020
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Status:Published
Keywords:Shock Control, Morphing Wing, Adaptive Bumps, Wave Drag Reduction, Variable Contour Bumps, Morphing Spoiler
Event Title:DLRK 2020
Event Location:Online (ursprünglich Aachen)
Event Type:national Conference
Event Dates:01. - 03. Sep. 2020
Organizer:Deutsche Gesellschaft für Luft- und Raumfahrt (DGLR)
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:fixed-wing aircraft
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Concepts and Integration (old), L - Structures and Materials (old)
Location: Braunschweig
Institutes and Institutions:Institute of Composite Structures and Adaptive Systems > Adaptronics
Deposited By: Künnecke, Sven Christian
Deposited On:07 Sep 2020 07:28
Last Modified:05 Jul 2021 07:16

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