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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]
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Database: Engineering Source
Description
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]
ISSN:00011452
DOI:10.2514/1.J058517