Vibro-Acoustical Sensitivities of Stiffened Aircraft Structures Due to Attached Mass-Spring-Dampers with Uncertain Parameters
The slightest manufacturing tolerances and variances of material properties can indeed have a significant impact on structural modes. An unintentional shift of eigenfrequencies towards dominant excitation frequencies may lead to increased vibration amplitudes of the structure resulting in radiated n...
| Main Authors: | , , |
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| Format: | Article |
| Language: | English |
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MDPI AG
2021-06-01
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| Series: | Aerospace |
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| Online Access: | https://www.mdpi.com/2226-4310/8/7/174 |
| _version_ | 1797528510052433920 |
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| author | Johannes Seidel Stephan Lippert Otto von Estorff |
| author_facet | Johannes Seidel Stephan Lippert Otto von Estorff |
| author_sort | Johannes Seidel |
| collection | DOAJ |
| description | The slightest manufacturing tolerances and variances of material properties can indeed have a significant impact on structural modes. An unintentional shift of eigenfrequencies towards dominant excitation frequencies may lead to increased vibration amplitudes of the structure resulting in radiated noise, e.g., reducing passenger comfort inside an aircraft’s cabin. This paper focuses on so-called non-structural masses of an aircraft, also known as the secondary structure that are attached to the primary structure via clips, brackets, and shock mounts and constitute a significant part of the overall mass of an aircraft’s structure. Using the example of a simplified fuselage panel, the vibro-acoustical consequences of parameter uncertainties in linking elements are studied. Here, the fuzzy arithmetic provides a suitable framework to describe uncertainties, create combination matrices, and evaluate the simulation results regarding target quantities and the impact of each parameter on the overall system response. To assess the vibrations of the fuzzy structure and by taking into account the excitation spectra of engine noise, modal and frequency response analyses are conducted. |
| first_indexed | 2024-03-10T09:59:23Z |
| format | Article |
| id | doaj.art-1c3a7e5b303043f8af486e2d6e82ab33 |
| institution | Directory Open Access Journal |
| issn | 2226-4310 |
| language | English |
| last_indexed | 2024-03-10T09:59:23Z |
| publishDate | 2021-06-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Aerospace |
| spelling | doaj.art-1c3a7e5b303043f8af486e2d6e82ab332023-11-22T02:01:31ZengMDPI AGAerospace2226-43102021-06-018717410.3390/aerospace8070174Vibro-Acoustical Sensitivities of Stiffened Aircraft Structures Due to Attached Mass-Spring-Dampers with Uncertain ParametersJohannes Seidel0Stephan Lippert1Otto von Estorff2Engineering System International GmbH, 63263 Neu-Isenburg, GermanyInstitute of Modelling and Computation, Hamburg University of Technology, 21073 Hamburg, GermanyInstitute of Modelling and Computation, Hamburg University of Technology, 21073 Hamburg, GermanyThe slightest manufacturing tolerances and variances of material properties can indeed have a significant impact on structural modes. An unintentional shift of eigenfrequencies towards dominant excitation frequencies may lead to increased vibration amplitudes of the structure resulting in radiated noise, e.g., reducing passenger comfort inside an aircraft’s cabin. This paper focuses on so-called non-structural masses of an aircraft, also known as the secondary structure that are attached to the primary structure via clips, brackets, and shock mounts and constitute a significant part of the overall mass of an aircraft’s structure. Using the example of a simplified fuselage panel, the vibro-acoustical consequences of parameter uncertainties in linking elements are studied. Here, the fuzzy arithmetic provides a suitable framework to describe uncertainties, create combination matrices, and evaluate the simulation results regarding target quantities and the impact of each parameter on the overall system response. To assess the vibrations of the fuzzy structure and by taking into account the excitation spectra of engine noise, modal and frequency response analyses are conducted.https://www.mdpi.com/2226-4310/8/7/174parameter uncertaintiesfuzzy arithmeticsensitivitiesnon-structural massessecondary structure |
| spellingShingle | Johannes Seidel Stephan Lippert Otto von Estorff Vibro-Acoustical Sensitivities of Stiffened Aircraft Structures Due to Attached Mass-Spring-Dampers with Uncertain Parameters Aerospace parameter uncertainties fuzzy arithmetic sensitivities non-structural masses secondary structure |
| title | Vibro-Acoustical Sensitivities of Stiffened Aircraft Structures Due to Attached Mass-Spring-Dampers with Uncertain Parameters |
| title_full | Vibro-Acoustical Sensitivities of Stiffened Aircraft Structures Due to Attached Mass-Spring-Dampers with Uncertain Parameters |
| title_fullStr | Vibro-Acoustical Sensitivities of Stiffened Aircraft Structures Due to Attached Mass-Spring-Dampers with Uncertain Parameters |
| title_full_unstemmed | Vibro-Acoustical Sensitivities of Stiffened Aircraft Structures Due to Attached Mass-Spring-Dampers with Uncertain Parameters |
| title_short | Vibro-Acoustical Sensitivities of Stiffened Aircraft Structures Due to Attached Mass-Spring-Dampers with Uncertain Parameters |
| title_sort | vibro acoustical sensitivities of stiffened aircraft structures due to attached mass spring dampers with uncertain parameters |
| topic | parameter uncertainties fuzzy arithmetic sensitivities non-structural masses secondary structure |
| url | https://www.mdpi.com/2226-4310/8/7/174 |
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