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Konzeptstudie zu Stoßkontrollsystemen

Künnecke, Sven Christian und Riemenschneider, Johannes und Vasista, Srinivas (2020) Konzeptstudie zu Stoßkontrollsystemen. DLRK 2020, 2020-09-01 - 2020-09-03, Online (ursprünglich Aachen).

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

Kurzfassung

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.

elib-URL des Eintrags:https://elib.dlr.de/135938/
Dokumentart:Konferenzbeitrag (Vortrag)
Titel:Konzeptstudie zu Stoßkontrollsystemen
Autoren:
AutorenInstitution oder E-Mail-AdresseAutoren-ORCID-iDORCID Put Code
Künnecke, Sven ChristianSven.Kuennecke (at) dlr.dehttps://orcid.org/0000-0002-7139-3492NICHT SPEZIFIZIERT
Riemenschneider, JohannesJohannes.Riemenschneider (at) dlr.dehttps://orcid.org/0000-0001-5485-8326NICHT SPEZIFIZIERT
Vasista, SrinivasSrinivas.Vasista (at) dlr.dehttps://orcid.org/0000-0002-7917-6740NICHT SPEZIFIZIERT
Datum:2 September 2020
Referierte Publikation:Ja
Open Access:Nein
Gold Open Access:Nein
In SCOPUS:Nein
In ISI Web of Science:Nein
Status:veröffentlicht
Stichwörter:Shock Control, Morphing Wing, Adaptive Bumps, Wave Drag Reduction, Variable Contour Bumps, Morphing Spoiler
Veranstaltungstitel:DLRK 2020
Veranstaltungsort:Online (ursprünglich Aachen)
Veranstaltungsart:nationale Konferenz
Veranstaltungsbeginn:1 September 2020
Veranstaltungsende:3 September 2020
Veranstalter :Deutsche Gesellschaft für Luft- und Raumfahrt (DGLR)
HGF - Forschungsbereich:Luftfahrt, Raumfahrt und Verkehr
HGF - Programm:Luftfahrt
HGF - Programmthema:Flugzeuge
DLR - Schwerpunkt:Luftfahrt
DLR - Forschungsgebiet:L AR - Aircraft Research
DLR - Teilgebiet (Projekt, Vorhaben):L - Konzepte und Integration (alt), L - Strukturen und Werkstoffe (alt)
Standort: Braunschweig
Institute & Einrichtungen:Institut für Faserverbundleichtbau und Adaptronik > Adaptronik
Hinterlegt von: Künnecke, Sven Christian
Hinterlegt am:07 Sep 2020 07:28
Letzte Änderung:24 Apr 2024 20:38

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