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An extensive helicopter Ground Vibration Test: from pretest analysis to the study of non-linearities

Ciavarella, Christopher and Priems, Martijn and Govers, Yves and Böswald, Marc (2018) An extensive helicopter Ground Vibration Test: from pretest analysis to the study of non-linearities. ERF 2018 - 44th European Rotorcraft Forum, 18.-21. Sep. 2018, Delft, Niederlande.

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Abstract

The Ground Vibration Test (GVT) is one of the key milestones in the characterization of an aerospace structure, allowing to describe its structural dynamic behavior. Moreover, a helicopter GVT is associated to additional challenges deriving from the rotorcraft architecture, such as a high modal density and non-linear phenomena. In this paper, these challenges are treated by presenting the extensive H145 GVT campaign carried out in June 2017 by AHD and DLR, from its conception to the first analysis of results. Starting from a H145 FE model, the pre-test analysis began with the selection of target modes from the initial numerical modes set based on modal participation and energy considerations. An optimal sensor distribution was also achieved as results of the implementation of sensor placement metrics like the Normal Displacement Method and sensor elimination methods based on MAC analysis. An extensive description of the testing methods and procedure is as well documented, from the use of a dedicated test rig to the excitation of the structure by means of several exciter constellations using different force levels in order to assess non-linear behavior and therefore identify the structural variability. After data acquisition, the efficient post-processing performed using DLR correlation tool allowed the identification of modes family and the creation of a modal model. In the first analysis of results, modal identification has shown the validity of the pre-test analysis by identifying more than 40 modes for the first helicopter configuration and exhibiting an excellent data quality. Comparison between two H/C configurations has given also a first sample of how structural variability can influence the modal layout. Furthermore, focus has been put on the identification and analysis of non-linear phenomena, proving how non-linear behavior can affect significantly the H/C dynamic response and the modal identification. Finally, a comparison between FE and test results for one H/C configuration has been performed, allowing an objective evaluation of the predictive capability of current FE models. On this basis, the path for future works in the field of FE modal updating and structural optimization is clearly defined.

Item URL in elib:https://elib.dlr.de/122998/
Document Type:Conference or Workshop Item (Speech)
Title:An extensive helicopter Ground Vibration Test: from pretest analysis to the study of non-linearities
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Ciavarella, ChristopherDepartment of Dynamics and Vibrations, Airbus HelicoptersUNSPECIFIED
Priems, MartijnDepartment of Dynamics and Vibrations, Airbus HelicoptersUNSPECIFIED
Govers, YvesYves.Govers (at) dlr.dehttps://orcid.org/0000-0003-2236-596X
Böswald, Marcmarc.boeswald (at) dlr.dehttps://orcid.org/0000-0001-8260-8623
Date:2018
Refereed publication:Yes
Open Access:Yes
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Status:Published
Keywords:ground vibration test, helicopter
Event Title:ERF 2018 - 44th European Rotorcraft Forum
Event Location:Delft, Niederlande
Event Type:international Conference
Event Dates:18.-21. Sep. 2018
Organizer:NWL - The Netherlands Association of Aeronautical Engineers
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:rotorcraft
DLR - Research area:Aeronautics
DLR - Program:L RR - Rotorcraft Research
DLR - Research theme (Project):L - The Quiet und Comfortable Rotorcraft
Location: Göttingen
Institutes and Institutions:Institute of Aeroelasticity > Structural Dynamics and System Identification
Deposited By: Govers, Dr.-Ing. Yves
Deposited On:22 Nov 2018 09:11
Last Modified:31 Jul 2019 20:20

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