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Impact Studies with Reduced Size Aircraft Stabiliser Demonstrators Including Hybrid Laminar Flow Control Technology

Ritt, Stefan Andreas and Vinot, Mathieu (2021) Impact Studies with Reduced Size Aircraft Stabiliser Demonstrators Including Hybrid Laminar Flow Control Technology. Clean Sky 2 Technology Progress, 24.-25. March 2021, Madrid, Spain / virtual.

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Official URL: https://zenodo.org/record/4655873

Abstract

Impact with large-scale projectiles like birds needs analyses at full-scale. The reason is that the impact behaviour can yet not be scaled from small-size demonstrators. The impact studies presented here aim to analyse hybrid laminar flow control (HLFC) structures for stabilizer or wing leading edges. To mature HLFC technology, impact requirements need to be incorporated during the design phase and have to be fulfilled during the certification process. Therefore, simulation methodologies play an important role to integrate impact designs in an early design stage. Within a project where HLFC is applied on the horizontal stabiliser, several design and manufacturing tests are conducted. A reduced-size demonstrator with a short span width but a full cross-section was selected for manufacturing and design purposes. The reduced-size demonstrator has been selected as a mean for impact studies based on earlier simulation and experimental studies. A symmetric vertical stabiliser design of similar size was used to build up a simulation model of an asymmetric horizontal stabiliser design. In several steps, this demonstrator was already verified experimentally by a soft body impact. It was proven that both the design and the design methodology including the demonstrator size was applicable. During the design process of the current horizontal stabiliser HLFC design, structural and manufacturing details were analysed with respect to consequences on the impact behaviour. The structural analyses with respect to impact were performed with explicit finite element and particle flow simulation tools. It is envisaged to subject this demonstrator also to impact testing in order to gather important validation data for the used impact simulation tools. The boundary conditions of the two approaches are similar. However, the HLFC principle is designed different. The current design of the asymmetric demonstrator for a horizontal stabiliser leading edge incorporating a chambered HLFC approach was simulated under soft body impact. It proves sufficient resistance against impact loading. At a later stage, it will be impact tested for validation purposes, too.

Item URL in elib:https://elib.dlr.de/141667/
Document Type:Conference or Workshop Item (Speech)
Title:Impact Studies with Reduced Size Aircraft Stabiliser Demonstrators Including Hybrid Laminar Flow Control Technology
Authors:
AuthorsInstitution or Email of AuthorsAuthor's ORCID iD
Ritt, Stefan Andreasstefan-andreas.ritt (at) dlr.dehttps://orcid.org/0000-0002-5330-509X
Vinot, MathieuMathieu.Vinot (at) dlr.dehttps://orcid.org/0000-0003-3394-5142
Date:24 March 2021
Refereed publication:No
Open Access:Yes
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Status:Published
Keywords:hybrid laminar flow control, HLFC, bird strike, composite, safety, certification, artificial bird, #DLRRAB
Event Title:Clean Sky 2 Technology Progress
Event Location:Madrid, Spain / virtual
Event Type:international Conference
Event Dates:24.-25. March 2021
Organizer:Universidad Carlos III de Madrid
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:Components and Systems
DLR - Research area:Aeronautics
DLR - Program:L CS - Components and Systems
DLR - Research theme (Project):L - Structural Materials and Design
Location: Stuttgart
Institutes and Institutions:Institute of Structures and Design > Structural Integrity
Deposited By: Ritt, Stefan Andreas
Deposited On:06 Apr 2021 10:10
Last Modified:06 Apr 2021 10:10

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