elib
DLR-Header
DLR-Logo -> http://www.dlr.de
DLR Portal Home | Imprint | Privacy Policy | Contact | Deutsch
Fontsize: [-] Text [+]

Numerical simulation of flexible aircraft structures under ditching loads

Siemann, Martin and Kohlgrüber, Dieter and Voggenreiter, Heinz (2017) Numerical simulation of flexible aircraft structures under ditching loads. CEAS Aeronautical Journal, 8 (3), pp. 505-521. Springer. DOI: 10.1007/s13272-017-0257-0 ISBN 1869-5582 ISSN 1869-5582

Full text not available from this repository.

Official URL: https://link.springer.com/article/10.1007/s13272-017-0257-0

Abstract

Aircraft certification requires demonstrating an aircraft’s structural capacity to withstand hydrodynamic loads as experienced during an emergency landing on water known as ditching. Currently employed means to analyze ditching comprise comparison with previously certified aircraft, sub-scale experimental testing, and semi-analytical as well as uncoupled computational methods; all of these are subject to simplifications that limit their predictability and accuracy. Therefore, there is the motivation to employ advanced, coupled numerical simulations to enhance the analysis capabilities. This paper presents a numerical simulation approach combining Smoothed Particle Hydrodynamics and Finite Element method, which permits investigating the structural behavior under ditching loads within one simulation. Comprehensive validation studies based on comparison with experimental results from novel guided ditching experiments of generic panels in aeronautical design have been undertaken and high accuracy has been achieved regarding acting force and strain time histories. Additionally, the profound analysis of the structural behavior of flexible panels allows assessing the main mechanisms that cause the acting hydrodynamic loads to increase significantly when the structure is being deformed. Presented results extend the fundamental knowledge in this field. The validated simulation approach is finally applied to analyze the structural behavior of a detailed stringer-frame-reinforced panel representing a generic aircraft bottom fuselage structure. Comparison between the structural behavior of the generic panels and the aft fuselage structure is established. Furthermore, conclusions with regard to ditching simulations involving larger or even full aircraft structures are drawn.

Item URL in elib:https://elib.dlr.de/113240/
Document Type:Article
Title:Numerical simulation of flexible aircraft structures under ditching loads
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Siemann, MartinMartin.Siemann (at) dlr.dehttps://orcid.org/0000-0002-7213-0715
Kohlgrüber, DieterDieter.Kohlgrueber (at) dlr.dehttps://orcid.org/0000-0002-6626-0927
Voggenreiter, HeinzUNSPECIFIEDUNSPECIFIED
Date:September 2017
Journal or Publication Title:CEAS Aeronautical Journal
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:No
Volume:8
DOI :10.1007/s13272-017-0257-0
Page Range:pp. 505-521
Publisher:Springer
ISSN:1869-5582
ISBN:1869-5582
Status:Published
Keywords:Crashworthiness; Aircraft ditching; Fluid-structure interaction; SPH-FE Approach; Validation
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 - Structures and Materials
Location: Stuttgart
Institutes and Institutions:Institute of Structures and Design > Structural Integrity
Deposited By: Siemann, Dr. Martin
Deposited On:21 Sep 2017 10:53
Last Modified:06 Sep 2019 15:24

Repository Staff Only: item control page

Browse
Search
Help & Contact
Information
electronic library is running on EPrints 3.3.12
Copyright © 2008-2017 German Aerospace Center (DLR). All rights reserved.