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Vertical Drop Test of Composite Fuselage Section of a Regional Aircraft.

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Title: Vertical Drop Test of Composite Fuselage Section of a Regional Aircraft.
Authors: Di Palma, L.1, Di Caprio, F.2, Chiariello, A.2, Ignarra, M.3, Russo, S.4, Riccio, A.5, De Luca, A.6, Caputo, F.7
Source: AIAA Journal. Jan2020, Vol. 58 Issue 1, p474-487. 14p.
Abstract: In this paper, a vertical drop test of a full composite fuselage section of a regional aircraft has been presented. This test was performed to investigate the structural response of a prototype of a composite fuselage section as well as the biomechanical response of the anthropomorphic dummies under a vertical crash loading condition. The research activity, carried out within the framework of Metodi di CERtificazione e Verifica Innovativi ed Avanzati (CERVIA)‡‡ project, allowed collecting suitable amount of data for the assessment of the reliability of numerical models. The test article consists of a composite fuselage section with a diameter of 3445 mm and a total length of 4750 mm. It includes all main structural components, the passengers, and the cargo floor structure. Fuselage section has been also equipped with an aeronautical three-seat row. The accelerations, recorded in different locations, demonstrate that the structure is able to absorb a considerable impact energy amount, thus to mitigate the acceleration levels induced to the passengers. [ABSTRACT FROM AUTHOR]
Copyright of AIAA Journal is the property of American Institute of Aeronautics & Astronautics and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)
Database: Engineering Source
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DbLabel: Engineering Source
An: 141186911
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PubType: Academic Journal
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  Data: Vertical Drop Test of Composite Fuselage Section of a Regional Aircraft.
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  Data: <searchLink fieldCode="AR" term="%22Di+Palma%2C+L%2E%22">Di Palma, L.</searchLink><relatesTo>1</relatesTo><br /><searchLink fieldCode="AR" term="%22Di+Caprio%2C+F%2E%22">Di Caprio, F.</searchLink><relatesTo>2</relatesTo><br /><searchLink fieldCode="AR" term="%22Chiariello%2C+A%2E%22">Chiariello, A.</searchLink><relatesTo>2</relatesTo><br /><searchLink fieldCode="AR" term="%22Ignarra%2C+M%2E%22">Ignarra, M.</searchLink><relatesTo>3</relatesTo><br /><searchLink fieldCode="AR" term="%22Russo%2C+S%2E%22">Russo, S.</searchLink><relatesTo>4</relatesTo><br /><searchLink fieldCode="AR" term="%22Riccio%2C+A%2E%22">Riccio, A.</searchLink><relatesTo>5</relatesTo><br /><searchLink fieldCode="AR" term="%22De+Luca%2C+A%2E%22">De Luca, A.</searchLink><relatesTo>6</relatesTo><br /><searchLink fieldCode="AR" term="%22Caputo%2C+F%2E%22">Caputo, F.</searchLink><relatesTo>7</relatesTo>
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  Data: <searchLink fieldCode="JN" term="%22AIAA+Journal%22">AIAA Journal</searchLink>. Jan2020, Vol. 58 Issue 1, p474-487. 14p.
– Name: Abstract
  Label: Abstract
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  Data: In this paper, a vertical drop test of a full composite fuselage section of a regional aircraft has been presented. This test was performed to investigate the structural response of a prototype of a composite fuselage section as well as the biomechanical response of the anthropomorphic dummies under a vertical crash loading condition. The research activity, carried out within the framework of Metodi di CERtificazione e Verifica Innovativi ed Avanzati (CERVIA)‡‡ project, allowed collecting suitable amount of data for the assessment of the reliability of numerical models. The test article consists of a composite fuselage section with a diameter of 3445 mm and a total length of 4750 mm. It includes all main structural components, the passengers, and the cargo floor structure. Fuselage section has been also equipped with an aeronautical three-seat row. The accelerations, recorded in different locations, demonstrate that the structure is able to absorb a considerable impact energy amount, thus to mitigate the acceleration levels induced to the passengers. [ABSTRACT FROM AUTHOR]
– Name: AbstractSuppliedCopyright
  Label:
  Group: Ab
  Data: <i>Copyright of AIAA Journal is the property of American Institute of Aeronautics & Astronautics and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract.</i> (Copyright applies to all Abstracts.)
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              Text: Jan2020
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