Application of the finite element method to predict the crashworthy response of a metallic helicopter under floor structure onto water

Hughes, Kevin; Campbell, J.; Vignjević, Rade

doi:10.1016/j.ijimpeng.2007.03.009

Cited by 25 publications

(13 citation statements)

References 1 publication

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“…Several authors [2,5,15,23] adopted Lagrangian FE discretisation in order to simulate vertical impacts on water of both rigid and deformable structures. They found that the Lagrangian approach for the representation of the fluid domain allows to accurately predict the deceleration peak at the initial stage of the impact.…”

Section: Numerical Formulations For Fluid-structure Interaction and Dmentioning

confidence: 99%

“…Since the introduction of fluid-structure interaction (FSI) techniques in commercial finite element (FE) codes, several authors [15,23,30,31] proposed numerical models aiming to investigate the problem of vertical impacts on water of aeronautical structures. While vertical impacts have been extensively analysed both numerically and experimentally [1,2,14,24], there are still difficulties related to the numerical simulation of ditching events [6,11,13,27,29].…”

Section: Introductionmentioning

confidence: 99%

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Modelling strategies for numerical simulation of aircraft ditching

Bisagni

Pigazzini

2017

International Journal of Crashworthiness

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Ditching, which is a controlled landing of an airplane on water, is an emergency condition to be investigated in order to improve the aircraft global crashworthiness. The complex hydrodynamic phenomena involved in ditching events are difficult to simulate and the accuracy of the results depends on the capability to reproduce the forces related to the interaction of the fuselage with the water surface. In the first part of the paper, the vertical impact on water of a rigid sphere is analysed using the explicit solver LS-DYNA in order to compare different modelling strategies. Four models of the fluid domain are presented: Lagrangian, arbitrary Lagrangian-Eulerian, smoothed particle hydrodynamics and hybrid Lagrangian-smoothed particle hydrodynamics. In the second part, the ditching of a scaled simplified airplane is simulated considering two different models for the water region. Experimental data from the literature are used to validate the simulations. The analysis, where the water and the air are modelled with the arbitrary Lagrangian-Eulerian method, shows a better correlation with the experimental data because this formulation can reproduce the suction force which acts on the fuselage and affects significantly the ditching dynamics.

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Section: Numerical Formulations For Fluid-structure Interaction and Dmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Modelling strategies for numerical simulation of aircraft ditching

Bisagni

Pigazzini

2017

International Journal of Crashworthiness

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“…The survivable impact velocity is between 6ms -1 and 12ms -1 , thus impact velocity of B737, ATR42-300, A320 and YS-11aircraft during crash test are 9·14ms -1 , 9·14ms -1 , 7ms -1 and 6·1ms -1 , respectively. Vertical drop test under flat rigid floor ground condition is the most common situation, but the water and soft soil are also the common accidents (11)(12)(13) . For example, an Airbus A320-214 ditched in the Hudson River for the lost of power on 15 January 2009, and everybody is survival.…”

Section: Different Aircraft Design Concept and Its Energy Absorption mentioning

confidence: 99%

Energy absorption structures design of civil aircraft to improve crashworthiness

Ren¹,

Xiang²

2014

Aeronaut. j. (1968)

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To improve the crashworthiness of civil aircraft, the design concept of energy absorption structure for civil aircraft is investigated. Two typical different design principles could be identified. The first category includes Helicopter and Light fixed-wing Aircraft (HLA), and Transport, Mid-size and Commuter type Aircraft (TMCA) are classified into the second group. Frame, strut and bottom structure are the three kinds of energy absorption structure for TMCA. The strut layout of conventional civil aircraft is studied and some energy absorption devices are adopted. High efficiency energy absorption structures such as the foam and sine-wave beam are employed as the bottom structure for both of HLA and LMCA. The finite element method is used to analyse and design energy absorption structure in aircraft crashworthiness problem. Results show that the crashworthiness of civil aircraft could be largely improved by using proper strut layout and excellent energy absorption device. The stiffness combination of frame and strut should be considered to get better global aircraft deformation. Supporting platform and failure model are the two core problems of bottom energy absorption structure design. Foam and sine-wave beam under the lifted frame could improve the crashworthiness of civil aircraft.

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“…Owing to the nature of these operations, and the complex manoeuvres that helicopters are required to undertake, occupants require protection for scenarios that do not exist in fixed wing aircraft [1,10]. Modern helicopters are designed with advanced materials and crashworthy structures using computer-aided engineering tools such as MSC Dytran and LS-DYNA [4,8] coupled with test procedures that parallel those used for crash analysis in the automotive industry, albeit for different scenarios. For a helicopter, post-crash risks, such as fire, ditching in open water or crashing in remote locations, were all identified in the HeliSafe TA project as drivers for occupant protection systems to mitigate injuries in survivable crashes [16].…”

Section: Introductionmentioning

confidence: 99%

A multi-body systems approach to simulate helicopter occupant protection systems

Vadlamudi

Blundell

Zhang

2011

International Journal of Crashworthiness

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This paper reports on the work of computer simulations carried out at Coventry University as part of the European 6th Framework HeliSafe TA project, which considered the potential improvements in occupant safety for civil helicopters. A multi-body systems approach with additional use of finite elements for critical components such as a pilot airbag and the harnesses was adopted in the computer models to simulate helicopter crash/rollover scenarios and to investigate the effectiveness of occupant protection systems deployed during helicopter crash scenarios. ADAMS and Madymo simulations of helicopter impact/rollover events were demonstrated. A cabin/cockpit model of a Bell UH-1D helicopter was developed to replicate the physical crash test setup and a parametric study for the pilot airbag and a range of harness concepts was performed. The use of validated multi-body systems-based cabin/cockpit models has proved to be effective in the development of new restraint system concepts for occupant protection.

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Application of the finite element method to predict the crashworthy response of a metallic helicopter under floor structure onto water

Cited by 25 publications

References 1 publication

Modelling strategies for numerical simulation of aircraft ditching

Modelling strategies for numerical simulation of aircraft ditching

Energy absorption structures design of civil aircraft to improve crashworthiness

A multi-body systems approach to simulate helicopter occupant protection systems

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