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Rotorcraft Mass Assessment in an Integrated Design Framework

Schwinn, Dominik and Weiand, Peter (2020) Rotorcraft Mass Assessment in an Integrated Design Framework. In: Proceedings of the 2020 SAWE Virtual Tech Fair for Mass Properties Engineers. SAWE Tech Fair for Mass Properties Engineers 2020, 22.06.-10.07.2020, Virtual Conference.

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Mass estimation is an essential discipline in the design process of aeronautical vehicles. The maximum takeoff mass determines most other design parameters and should therefore be estimated sufficiently precise from the beginning. In the conceptual design phase fast analyses are required in order to allow trade-off studies. In general, this phase is dominated by the use of analytical and statistical methods. At the end of this design stage, a basic external layout has been elaborated and basic design parameters have been determined. During the subsequent preliminary design stage, physics based higher fidelity methods are applied to further elaborate the design and to establish an internal configuration. The constantly increasing computational power allows comparably fast analyses in this design stage that may alter the configuration established in the conceptual design stage. Particular challenges in this design approach arise with unconventional configurations, such as compound rotorcraft, or with different propulsion systems to be integrated, for instance electric or hybrid systems, because of a lack of sufficient statistical data. The German Aerospace Center (DLR) has established the integrated design environment IRIS (Integrated Rotorcraft Initial Sizing) to allow an assessment of virtual rotorcraft configurations. It covers the conceptual and parts of the preliminary design stage and uses the data model CPACS (Common Parametric Aircraft Configuration Schema) for the parametric rotorcraft description. Component masses in IRIS are estimated using various statistical methods during the conceptual design stage. Finite Element (FE) methods are applied in the preliminary design phase to allow a more precise estimation of the structural mass which may influence the maximum take-off mass and therefore the performance characteristics calculated in the conceptual design stage. This paper introduces the design environment IRIS, and in particular the PANDORA framework (Parametric Numerical Design and Optimization Routines for Aircraft) which is used for the statistical estimation of the rotorcraft component masses and the structural sizing process to determine the fuselage mass.

Item URL in elib:https://elib.dlr.de/135420/
Document Type:Conference or Workshop Item (Speech)
Title:Rotorcraft Mass Assessment in an Integrated Design Framework
AuthorsInstitution or Email of AuthorsAuthor's ORCID iD
Schwinn, DominikUNSPECIFIEDhttps://orcid.org/0000-0003-2341-9632
Date:25 June 2020
Journal or Publication Title:Proceedings of the 2020 SAWE Virtual Tech Fair for Mass Properties Engineers
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Keywords:rotorcraft; rotorcraft design; mass assessment; structural airframe design; IRIS; PANDORA
Event Title:SAWE Tech Fair for Mass Properties Engineers 2020
Event Location:Virtual Conference
Event Type:international Conference
Event Dates:22.06.-10.07.2020
Organizer:SAWE (Society of Allied Weight Engineers)
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:17 Sep 2020 18:31
Last Modified:17 Sep 2020 18:31

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