Impact response and crashworthy design of composite fuselage structures: An overview

Liu, Xiaochuan; Bai, Chunyu; Xi, Xulong; Zhou, Sicong; Zhang, Xinyue; Li, Xiaocheng; Ren, Yiru; Yang, Jialing; Yang, Xianfeng

doi:10.1016/j.paerosci.2024.101002

Cited by 5 publications

(1 citation statement)

References 151 publications

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“…The aircraft safety has always been the most basic and important requirement for civil aviation transportation, but the emergency landing events or the crash events are still frequently occurred due to the mechanical failure, human error and other factors [1]. After the investigation of aviation crash accidents, most crash accidents occurred during the aircraft take-off and land phases, which were the survivable crash accidents, and the aircraft with better crashworthiness can effectively ensure the safety of occupants [2][3]. Crashworthiness is the ability of civil aircraft fuselage structure and internal systems to maximum protect the occupants' safety in a crash or emergency landing event, which mainly involving human tolerance limit, fuselage structure, seat system, etc.…”

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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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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Advanced Sensors and Sensing Systems for Structural Health Monitoring in Aerospace Composites

Ogunleye,

Rusnáková,

Javořík

et al. 2024

Adv Eng Mater

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This review examines the state‐of‐the‐art sensors and sensing technologies employed for structural health monitoring (SHM) in aerospace composites, highlighting the shift from conventional nondestructive evaluation techniques to real‐time monitoring systems. The review discusses the challenges associated with composite materials, such as their anisotropic nature and susceptibility to invisible damage, and how these challenges have driven the improvement of SHM techniques. Fiber‐optic sensors, including interferometric, distributed, and grating‐based sensors, are analyzed for their high sensitivity and multiplexing capabilities, making them suitable for distributed sensing applications. Piezoelectric sensors are evaluated for their effectiveness in both active and passive damage detection methods. At the same time, piezoresistive self‐sensing systems are explored for their potential to integrate sensing directly into composite materials. The review also addresses the challenges encountered in implementing SHM systems. It suggests solutions like protective coatings, advanced data processing algorithms, and modular system design to overcome these challenges. In conclusion, this review provides a comprehensive overview of the current SHM technologies for aerospace composites, underscoring the need for sustained research and development to improve sensor technology, expand data processing capabilities, and ensure seamless integration with aircraft systems, thus contributing to the safety and efficiency of aerospace operations.

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On static and dynamic stability of bio-inspired composite plates under variable axial load

Mohamed,

Eltaher,

Mohamed

et al. 2024

Acta Mech

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Impact response and crashworthy design of composite fuselage structures: An overview

Cited by 5 publications

References 151 publications

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

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

Advanced Sensors and Sensing Systems for Structural Health Monitoring in Aerospace Composites

On static and dynamic stability of bio-inspired composite plates under variable axial load

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