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Rotorcraft Fuselage Sizing Methods in the Open-Source Framework PANDORA

Schwinn, Dominik and Petsch, Michael and Kohlgrüber, Dieter and Heubischl, Jörg and Leon Muñoz, Christian Xavier and Weiand, Peter and Buchwald, Michel (2019) Rotorcraft Fuselage Sizing Methods in the Open-Source Framework PANDORA. In: Proceedings of the NAFEMS World Congress 2019. NAFEMS World Congress, 17.-20. Jun. 2019, Quebec City, Kanada.

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Rural depopulation resulting in altered hospital coverage, new challenges for medical evacuation during military operations, and increased off-shore activities of energy suppliers, lead to changed requirements of helicopter emergency medical services (HEMS). Recently, interest has significantly increased to overcome the traditional physical limitation of flight speed by providing helicopters with auxiliary propulsive devices, so-called compound rotorcraft. In order to assess these novel rotorcraft concepts, an integrated, multidisciplinary, and automated design procedure has been established at the German Aerospace Center (DLR) using the data model CPACS (Common Parametric Aircraft Configuration Schema). The design processes of rotary- and fixed-wing aircraft highly resemble each other: In the first stage of a typical aircraft design process, the conceptual stage, basic characteristics are established that typically consist of e.g. outer dimensions (i.e. its aerodynamic shape), flight performance, mass breakdown, etc. At this stage of the design process mostly fast, analytical, and statistical methods are applied featuring many simplifications. In the subsequent preliminary design phase the detail level increases. The continuously growing computational power has enabled design engineers to integrate higher fidelity methods at this design stage. At the DLR Institute of Structures and Design, tools have been developed in the last couple of years that use finite element (FE) methods to size aeronautical fuselage structures according to static load cases to allow a more precise prediction of the structural mass, and thus in turn to a different maximum take-off mass which is considered as a major design parameter. Although based on the same framework approach, these FE based tools developed for preliminary sizing of rotary- and fixed-wing fuselages diverged over the years due to different project requirements, such as specific modeling aspects, different syntax for the involved FE solvers, or different design emphases. These issues resulted in different tools to generate FE meshes and to conduct analyses with some inconsistencies between the individual tools. In order to unify the tools, the development of the software framework PANDORA (Parametric Numerical Design and Optimization Routines for Aircraft) has been started at DLR in 2016 from scratch using the Python programming language. The key idea behind PANDORA is to generate one common software framework to model, analyze, and size both fixed- and rotary-wing fuselage structures. Particular focus in the development of PANDORA lies in the use of dedicated open-source packages and the interchangeability of different commercial and open-source FE solvers. This paper first shows the approach of the PANDORA toolbox for fixed-wing aircraft. Then, the process of adapting respectively integrating specific modeling and analysis methods for rotorcraft fuselages into the new framework is shown. Concluding this article an outlook of new enhancements into PANDORA is given highlighting its benefits in the context of preliminary structural analysis of novel rotorcraft concepts.

Item URL in elib:https://elib.dlr.de/128471/
Document Type:Conference or Workshop Item (Speech)
Title:Rotorcraft Fuselage Sizing Methods in the Open-Source Framework PANDORA
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Schwinn, DominikUNSPECIFIEDhttps://orcid.org/0000-0003-2341-9632UNSPECIFIED
Petsch, MichaelUNSPECIFIEDhttps://orcid.org/0000-0002-2743-375XUNSPECIFIED
Kohlgrüber, DieterUNSPECIFIEDhttps://orcid.org/0000-0002-6626-0927UNSPECIFIED
Leon Muñoz, Christian XavierUNSPECIFIEDhttps://orcid.org/0000-0002-6557-6655UNSPECIFIED
Weiand, PeterUNSPECIFIEDhttps://orcid.org/0000-0002-0964-6225UNSPECIFIED
Date:June 2019
Journal or Publication Title:Proceedings of the NAFEMS World Congress 2019
Refereed publication:Yes
Open Access:Yes
Gold Open Access:No
In ISI Web of Science:No
Keywords:fuselage sizing; structural sizing; aircraft design; rotorcraft design; finite element method; open-source software; software development; PANDORA
Event Title:NAFEMS World Congress
Event Location:Quebec City, Kanada
Event Type:international Conference
Event Dates:17.-20. Jun. 2019
Organizer:NAFEMS Ltd.
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 (old), L - The Innovative Rotorcraft (old)
Location: Braunschweig , Stuttgart
Institutes and Institutions:Institute of Structures and Design > Structural Integrity
Institute of Flight Systems > Rotorcraft
Deposited By: Schwinn, Dominik
Deposited On:25 Jul 2019 09:42
Last Modified:29 Mar 2023 00:42

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