On the effectiveness of double-double design on crashworthiness of fuselage barrel

Garofano, Antonio; Sellitto, Andrea; Acanfora, Valerio; Caprio, Francesco Di; Riccio, Aniello

doi:10.1016/j.ast.2023.108479

Cited by 10 publications

(4 citation statements)

References 41 publications

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“…The FE model of a representative portion of a short‐range regional aircraft composite fuselage barrel has been implemented in the Abaqus environment. [ 13 ] An aircraft seat with rigid body features has been added on the window‐side to properly locate a 50th percentile male WorldSID‐based FE dummy model to simulate the side impact with the fuselage wall. Details on the structure's geometry and material employment are given in Figure .…”

Section: Description Of Finite Element Model Of the Fuselage Barrelmentioning

confidence: 99%

Hybrid Composite‐Polypropylene Sandwich‐Based Design for the Fuselage Panel in Commercial Aircraft to Increase the Passive Safety of Passengers

Garofano,

Acanfora,

Russo

et al. 2024

Macromolecular Symposia

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The passive safety in aircraft concerns all measures able to protect the passengers and crew in the event of an accident or emergency. In this context, an important role is played by the design adopted for components inside the passengers’ cabin, such as the seats and the interior lining. An effective approach in design of passive safety system is provided by anthropomorphic test devices. In this work, a new design of the interior lining of the fuselage wall has been introduced and its crashworthiness features have been studied through a side impact of an unbelted window‐side passenger. The new proposed interior lining is made with a hybrid sandwich‐based design with a polypropylene honeycomb core able to ensure passive safety for passengers and thermal and acoustic insulation.

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Section: Description Of Finite Element Model Of the Fuselage Barrelmentioning

confidence: 99%

Hybrid Composite‐Polypropylene Sandwich‐Based Design for the Fuselage Panel in Commercial Aircraft to Increase the Passive Safety of Passengers

Garofano,

Acanfora,

Russo

et al. 2024

Macromolecular Symposia

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“…Main structural sub-components have been modelled as solid extruded parts while frames as 3D shell parts allowing to run sequential analyses with variable thickness during the optimization process. The optimized [±37.5, ±45] Double-Double lay-up has been employed for the skin [4]. A uniform [90,45,0,45,-45,90,45,-45,0,-45,45,-45]s stacking sequence characterized the frames in the starting configuration.…”

Section: Fe Model Descriptionmentioning

confidence: 99%

“…A uniform [90,45,0,45,-45,90,45,-45,0,-45,45,-45]s stacking sequence characterized the frames in the starting configuration. The IMS/977-2 CFRP [4], a Woven Fabric [4] and the T700 CPLY64 [4] have been adopted for the composite components while Aluminum 2024-T42 for the metal parts. The FE model has been discretized by means of 8node continuum shell elements (SC8R) and 8-node linear brick elements (C3D8R) for composite and aluminum components, respectively, while 4-node general-purpose shell elements (S4R) have been used for frames.…”

Section: Fe Model Descriptionmentioning

confidence: 99%

On the use of double-double design philosophy in the redesign of composite fuselage barrel components

Garofano

2023

Materials Research Proceedings

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Abstract. Mass minimization and mechanical performance maximization constitute the basic aspects of the structural optimization processes. In particular, the laminate redesign in terms of thickness and lay-up grants the main approach for the optimization of composite components. The innovative Double-Double laminate concept provides an effective approach to design composite components for weight and strength requirements, overcoming the use of the conventional 0°, 90° and ±45° ply orientations. In Double-Double designed components, 4-plies building blocks are stacked one upon the other to constitute a laminate. Each building block is made up of four [±Φ, ±Ψ] oriented plies. In the present work, the Double-Double approach has been adopted in the redesign of the composite lay-up and thickness profile of frames in a composite fuselage barrel. The DD optimized frames achieved a total mass reduction by up to 35% while ensuring mechanical performances comparable to the starting configuration.

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“…The aircraft structural response is mainly dominated by the crash response characteristics of typical fuselage section with straight cross section [5][6][7], and conducting the drop test of full-scale fuselage section (including occupant/seat restraint system) is the most direct and effective way to research and verify the aircraft crashworthiness, which can effectively evaluate the fuselage structure deformation, the load transmitted to the seats and occupants and occupant injury risk, etc. Many drop tests of typical fuselage section had been carried out, as listed in Table 1, and the fuselage section presented two different failure modes according to the drop test results: the unrolling failure mode (three plastic hinges failure mode) and the flattening failure mode (multiple plastic hinges failure mode).…”

Section: Introductionmentioning

confidence: 99%

Crash response and occupant injury analysis in vertical drop test of a typical large transport aircraft fuselage section

Feng,

Mou

2024

Preprint

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To analyze the crash characteristics of a typical large aircraft fuselage section and occupant injury, a three-frame typical fuselage section was designed and fabricated, which including two sets of triple seats and four 50th-percentile FAA Hybrid III Anthropomorphic Test Devices (ATDs). The vertical drop test of fuselage section was conducted at 6.02m/s, the crash response and occupant injury were analyzed, and the crashworthiness evaluation and analysis of fuselage section were further conducted. The results show that the sub-cabin floor structures suffer the serious deformation and damage, which is the unrolling failure mode (three plastic hinges failure mode), and one opening plastic hinge is generated in the sub-cargo middle support columns area, and two opening plastic hinges are generated in the connection areas between the both sides cabin floor support columns and fuselage frames. The cabin area is remained basically intact, and the survivable volume is maintained. The connections between the seats and cabin floor guide rails are maintained in good condition, and the occupant seat belts are kept in place. The maximum value of head injury criterion and lumbar spine compression load are 31.47 and 3997.2 N, respectively, which are much lower than the threshold of Airworthiness Standard. The ATDs lean towards the aisle, and the occupant egress paths are maintained. The aircraft crashworthiness is evaluated by considering the survivable volume, retention strength, occupant injury and emergency evacuation, and the Integrated Crashworthiness Index (ICI) is used to evaluate the aircraft crashworthiness by the scoring method, which indicating a low occupant injury risk. The flattening failure mode (multiple plastic hinges failure mode) of fuselage section can be realized by controlling the failure load, failure position and failure sequence of fuselage section, and more crash energy can be absorbed by producing multiple plastic hinges of fuselage section, which can effectively improve the crashworthiness of fuselage section.

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On the effectiveness of double-double design on crashworthiness of fuselage barrel

Cited by 10 publications

References 41 publications

Hybrid Composite‐Polypropylene Sandwich‐Based Design for the Fuselage Panel in Commercial Aircraft to Increase the Passive Safety of Passengers

Hybrid Composite‐Polypropylene Sandwich‐Based Design for the Fuselage Panel in Commercial Aircraft to Increase the Passive Safety of Passengers

On the use of double-double design philosophy in the redesign of composite fuselage barrel components

Crash response and occupant injury analysis in vertical drop test of a typical large transport aircraft fuselage section

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