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Journal articles on the topic 'Aircraft crashworthiness'

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Author: Grafiati

Published: 10 December 2022

Last updated: 28 January 2023

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1

Peng, Liang, Xiao Peng Wan, and Mei Ying Zhao. "Improved Fuselage Design for Crashworthiness." Applied Mechanics and Materials 246-247 (December 2012): 777–81. http://dx.doi.org/10.4028/www.scientific.net/amm.246-247.777.

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The principles of fuselage design for crashworthiness are analyzed based on investigating the theory of energy and momentum to the impact of an aircraft’s crash on occupants in order to increase the chance of survival for occupants. It indicates that minimizing the amount of bumped soil leads to the reduction of resistance from soil to the aircraft while crashing along the y-axis direction (horizontal) and increasing the energy absorption improves the crashworthiness of the aircraft along the z-axis direction (vertical). The deformation of the aircraft cabin and the acceleration of the occupants during a crash are the two most important factors to consider for crashworthiness. The improved fuselage design for crashworthiness is proposed for both y-axis and z-axis directions. Suggestions for the crashworthy fuselage design are given in order to obtain high performance of crashworthiness design, which is meaningful to the future design for fuselage’s crashworthiness.

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2

Ren, Y., and J. Xiang. "Energy absorption structures design of civil aircraft to improve crashworthiness." Aeronautical Journal 118, no. 1202 (April 2014): 383–98. http://dx.doi.org/10.1017/s0001924000009180.

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AbstractTo 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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3

Yu, Ze Liang, and Pu Xue. "Crashworthiness Study of Composite Fuselage Section." Key Engineering Materials 725 (December 2016): 94–98. http://dx.doi.org/10.4028/www.scientific.net/kem.725.94.

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Crashworthiness is one of the requirements for design of aircraft to ensure the safety of passengers on aircraft. With increasing applications of advanced composite in aircraft structures, study on the crashworthiness of composite fuselage is desirable and important. For this purpose, this paper investigates the influence of composites on crashworthiness of fuselage section. Firstly, model of fuselage section of aircraft is established. Skin, frame, stringer and stiffener are made of the composite T800/QY8911 or GLARE. Then, the crash responses subjected to vertical impact velocity of 9.14m/s are analyzed. The acceleration history is recorded for assessment of the crashworthiness. In addition, the deformation process and failure mode of composite fuselage section are analyzed. Results indicate that the frame made of brittle composite may fracture in the crash process, which leads to serious damage to the fuselage. While the frame with good toughness can maintain the integrity of fuselage, thereby protecting passengers.

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4

Schwinn, Dominik B. "Integration of Crashworthiness Aspects into Preliminary Aircraft Design." Applied Mechanics and Materials 598 (July 2014): 146–50. http://dx.doi.org/10.4028/www.scientific.net/amm.598.146.

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Crashworthiness proof is a certification requirement by aviation authorities for new aircraft types. The objective of static design is a sufficiently stiff and strong structure to carry bending and torsion during flight and ground maneuvers. High stiffness, however, is critical for good crashworthiness behavior. Therefore, crashworthiness investigations should be included at early design stages of the overall aircraft design process. This paper introduces the crash analysis tool AC-CRASH and shows an approach of integrating it into the preliminary design phase.

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5

Jusuf, Annisa, Afdhal Afdhal, and Minda Mora. "Kajian Desain Kelaiktabrakan Pesawat Terbang." WARTA ARDHIA 42, no. 3 (September 22, 2017): 117. http://dx.doi.org/10.25104/wa.v42i3.241.117-122.

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Lalu lintas penerbangan di Indonesia mengalami tren peningkatan dari tahun ke tahun. Peningkatan frekuensi penggunaan pesawat terbang tentunya akan meningkatkan kemungkinan kejadian kecelakaan. Konsep kelaiktabrakan pesawat terbang menjadi hal penting yang perlu mendapat perhatian untuk mencegah kerusakan struktur dan cedera pada penumpang. Desain kelaiktabrakan struktur pesawat berada pada tahapan desain awal yang terintegrasi kedalam proses desain pesawat secara keseluruhan. Struktur subfloor pada pesawat terbang menjadi bagian yang digunakan untuk menyerap energi kinetik tabrakan dalam kasus pembebanan vertikal pada pesawat terbang. Crash box merupakan komponen pada subfloor yang akan menyerap energi kinetik tabrakan dengan mengubahnya menjadi deformasi plastis. [A Review of Aircraft Crashworthiness Design] Air traffic in Indonesia is experiencing a positive trend in recent years. The increase in the frequency of aircraft operation might particularly increase the possibility of accidents occurrence. Aircraft crashworthiness concept becomes an important matter that need to be considered in order to prevent structural damage and injuries to the passengers. Aircraft structural crashworthiness design is developed in the aircraft preliminary design phase which is, later, integrated into the overall aircraft design process. Aircraft subfloor structure is the part of the aircraft that is used to restrain the kinetic energy of a collision in the case of vertical loading on the aircraft. Subsequently, crash box is a component of the subfloor that will absorb collisions kinetic energy by turning it into plastic deformation.

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6

Wang, Yu Fei, Ban Wang, Jin Yuan Wang, and Dong Qi Meng. "Optimization of Biomechanical Systems For the Fighter Plane Ejection Seats." Advanced Materials Research 815 (October 2013): 880–85. http://dx.doi.org/10.4028/www.scientific.net/amr.815.880.

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Restraint systems and protection devices, referred to as safety devices in this paper, are widely used in automobiles and aircraft for crashworthiness and safety. While such safety devices are designed to isolate, attenuate, and control the impact to the occupants, their performance for crashworthiness and safety may be ineffective or even counterproductive under certain circumstances.

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7

Chen, Pu-Woei, and Yung-Yun Chen. "Optimization Analysis on the Crashworthiness of Light Aircrafts." International Journal of Manufacturing, Materials, and Mechanical Engineering 5, no. 3 (July 2015): 1–23. http://dx.doi.org/10.4018/ijmmme.2015070101.

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To protect passengers, large aircraft are equipped with multiple mechanisms to absorb impact energy during a crash. However, light aircraft rely only on the cabin structure to withstand the compression and energy generated during a crash. This study performed a topology optimization analysis on the model structure by using Abaqus/optimization and used strain energy as the objective function and cabin volume as a constraint to develop the optimal model. Subsequently, this work performed dynamic crash simulations based on the optimal and original models by using Abaqus/explicit. Compared with the original model, the optimal model yielded a 12% increase in the safety zone of the diagonal beams, a 13% increase in the X-direction safety zone, and a 10% increase in the overall safety zone. The results confirm that topology optimization can be used to effectively improve the crashworthiness of light aircraft.

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8

Xue, P., L. Ding, F. Qiao, and X. Yu. "Crashworthiness study of a civil aircraft fuselage section." Latin American Journal of Solids and Structures 11, no. 9 (2014): 1615–27. http://dx.doi.org/10.1590/s1679-78252014000900007.

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9

Ren, Yiru, and Jinwu Xiang. "Improvement of aircraft crashworthy performance using inversion failure strut system." Aircraft Engineering and Aerospace Technology 89, no. 2 (March 6, 2017): 330–37. http://dx.doi.org/10.1108/aeat-09-2015-0205.

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Purpose The purpose of this paper is to improve the crashworthiness of aircraft by using the strut system as an energy absorption device without redesigning other components. Design/methodology/approach The novel strut system consists of metal stepped thin-walled tubes and articulated connecting hinges. The strut is suffering axial load during impact process for rotating of hinges, and the metal stepped tube has an inversion failure behaviour. Findings The metal stepped tube has lower initial impact load and more stable failure behaviour. The geometrical factors have a great influence on the impact load and energy absorption efficiency. The best length ratio between upper and lower sections is about 2:1 and 1:1 for the metal stepped circular and square tubes, respectively. Practical implications The metal stepped tube with inversion mechanism is suitable for aircraft strut system to improve crashworthiness performance. Originality/value A new strut system is provided using metal inversion failure stepped tubes and articulated connecting hinges to improve crash worthiness of aircraft.

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10

Chen, Pu Woei, Shu Han Chang, Yu Yang Hsieh, and Tai Sing Sun. "Crashworthiness Simulation Analysis of Light Sport Aircraft Fuselage Structure." Advanced Materials Research 199-200 (February 2011): 48–53. http://dx.doi.org/10.4028/www.scientific.net/amr.199-200.48.

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In recent years, light sport aircraft, which not only serve the purpose of personal recreation but also act as a means of transportation for medium and short distance travel, have rapidly gained popularity in the general aviation industry worldwide. The FAA established regulations for this new category of airplanes in 2004. However, the crashworthiness requirements for this type of airplane have not been clearly specified. This study used the finite element method to investigate the effect of the impact angle and speed of the LSA fuselage structure on passenger safety during a crash event. We used sink speed defined by NASA AGATE, ASTM and FAR as parameters. The passenger compartment reducing rate defined by MIL-STD-1290A was used for a safety boundary condition. The results show that the maximum cockpit reducing rate of the airplane impact angle is 30o. When the impact angle increases, owing to the engine mount and fire wall’s reinforced structure, this type of airplane can sustain a greater vertical drop speed. When the impact angle is about 80°~90°, the maximum impact speed the fuselage that can be sustained is 33 m/s. This work also completed a simulation of safe and unsafe ranges for light sport aircraft at various impact angles and vertical drop speeds during impact.

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11

Zheng, Jianqiang, Jinwu Xiang, Zhangping Luo, and Yiru Ren. "Crashworthiness design of transport aircraft subfloor using polymer foams." International Journal of Crashworthiness 16, no. 4 (August 2011): 375–83. http://dx.doi.org/10.1080/13588265.2011.593979.

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12

Zhenyu, Feng, Hao Peng, and Zou Tianchun. "Research Development of Crashworthiness Simulation Evaluation on Civil Aircraft." Procedia Engineering 17 (2011): 286–91. http://dx.doi.org/10.1016/j.proeng.2011.10.030.

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13

Laananen, David H. "Crashworthiness analysis of commuter aircraft seats and restraint systems." Journal of Safety Research 22, no. 2 (June 1991): 83–95. http://dx.doi.org/10.1016/0022-4375(91)90016-o.

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14

Hu, Jie. "The Aircraft Airworthiness and Safety Standards Analysis." Applied Mechanics and Materials 533 (February 2014): 371–74. http://dx.doi.org/10.4028/www.scientific.net/amm.533.371.

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The safety of the aircraft is assured by the airworthiness conditions laid down by national and international bodies. This chapter starts with a brief description of the framework in which these regulations are managed. The airworthiness regulations govern the ethos of the design. It is important to understand these aspects prior to the detailed consideration of aircraft component design as they may present constraints to the layout and performance of the aircraft. Although airworthiness is described under the separate headings of structural integrity, system integrity, operation integrity and crashworthiness there is considerable interdependence involved in the overall aircraft configuration.

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15

Zou, Tian Chun, Xiao Min Zhang, Hao Lei Mou, and Zhen Yu Feng. "The Influences of Complex Impact Conditions on Aircraft Fuselage Crashworthiness." Applied Mechanics and Materials 184-185 (June 2012): 546–52. http://dx.doi.org/10.4028/www.scientific.net/amm.184-185.546.

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In this paper, a certain B737 aircraft fuselage section was used to research the influence of different impact conditions on fuselage dynamic characteristics. A finite element model of fuselage was built up from FS380 to FS500. The impact responses of fuselage subjected to 9.133m/s vertical velocity were analyzed under the conditions of 0° roll angle, 10° left roll angle and combination acceleration. The differences of transformation and acceleration history curves under different conditions were compared. The research results show that the performances of 10° left roll angle will change fuselage transformation and acceleration of seats location, the appears of combination acceleration will increase transformation of floor and decrease acceleration at the seats location. The crashworthiness of aircraft structure can be effectively improved by selecting the appropriate landing way.

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16

Ren, Yiru, Jinwu Xiang, Jianqiang Zheng, and Zhangping Luo. "Crashworthiness analysis of aircraft fuselage with sine-wave beam structure." Chinese Journal of Aeronautics 29, no. 2 (April 2016): 403–10. http://dx.doi.org/10.1016/j.cja.2016.02.002.

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17

Mou, Haolei, Yuejuan Du, and Tianchun Zou. "Effects of different roll angles on civil aircraft fuselage crashworthiness." Advances in aircraft and spacecraft science 2, no. 4 (October 25, 2015): 391–401. http://dx.doi.org/10.12989/aas.2015.2.4.391.

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18

Kim, Tae-Uk, Seunggyu Lee, Donggeon Lee, JeongJun Jo, and SeokNam Shin. "Evaluation of the Aircraft Landing Gear Crashworthiness by Crash Drop Test." Transactions of the Korean Society of Mechanical Engineers - A 44, no. 5 (May 31, 2020): 377–82. http://dx.doi.org/10.3795/ksme-a.2020.44.5.377.

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19

Paz, J., J. Díaz, and L. Romera. "Crashworthiness Analysis and Enhancement of Aircraft Structures Under Vertical Impact Scenarios." Journal of Aircraft 57, no. 1 (January 2020): 3–12. http://dx.doi.org/10.2514/1.c035435.

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20

Hashemi, S. M. R., and A. C. Walton. "A systematic approach to aircraft crashworthiness and impact surface material models." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 214, no. 5 (May 1, 2000): 265–80. http://dx.doi.org/10.1243/0954410001532051.

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The underlying objective of this paper is to describe an approach adopted for investigating the crashworthiness of an airliner fuselage. It is based on detailed Finite Element (FE) modelling and supported by a series of static and dynamic tests on a subfloor section. The detailed FE analysis was undertaken to predict the dynamic collapse mechanism of a fuselage section. A parametric analytical study was performed for one of the dynamic tests modelled here to verify the results by taking into consideration the influence of modelling techniques. The structural response of an aircraft during an impact with the ground is highly dependent upon the terrain encountered. Significant structural response difference are likely to be produced when the impact surface is of a soft soil type as against a rigid surface such as concrete. The methodology to develop ground models was based on extending the problem from a simple to a complex structure/ground interaction.

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21

Adams, A., and H. M. Lankarani. "A modern aerospace modeling approach for evaluation of aircraft fuselage crashworthiness." International Journal of Crashworthiness 8, no. 4 (January 2003): 401–13. http://dx.doi.org/10.1533/ijcr.2003.0234.

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22

Beheshti, H. KH, and H. M. Lankarani. "A simplified test methodology for crashworthiness evaluation of aircraft seat cushions." International Journal of Crashworthiness 11, no. 1 (January 2006): 27–35. http://dx.doi.org/10.1533/ijcr.2005.0381.

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23

Meng, F. X., Q. Zhou, and J. L. Yang. "Improvement of crashworthiness behaviour for simplified structural models of aircraft fuselage." International Journal of Crashworthiness 14, no. 1 (February 28, 2009): 83–97. http://dx.doi.org/10.1080/13588260802517360.

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24

Sturm, Ralf, and Martin Hepperle. "Crashworthiness and ditching behaviour of blended-wing-body (BWB) aircraft design." International Journal of Crashworthiness 20, no. 6 (August 4, 2015): 592–601. http://dx.doi.org/10.1080/13588265.2015.1068997.

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25

Chen, Pu-Woei, and Kuan-Jung Chen. "A CRASHWORTHINESS SIMULATION FOR A LIGHT AIRCRAFT CONSTRUCTED OF COMPOSITE MATERIALS." Transactions of the Canadian Society for Mechanical Engineering 39, no. 4 (December 2015): 829–43. http://dx.doi.org/10.1139/tcsme-2015-0066.

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This study analyzes the crashworthiness of a light aircraft that is constructed from composite materials. The finite element method is employed to conduct dynamic impact simulations on carbon fiber composite fuselages. The results show that the safe impact speed for an aluminum alloy cockpit crashed at a 30° impact angle is 9.59 m/s, but a cockpit made of composite material can withstand a speed greater than 18.05 m/s. The safe impact angle for an aluminum alloy cockpit is 16.56°, but that for a composite cockpit is 84.9°. The safety crash zone for a composite material cockpit is 160% greater than that for an aluminum alloy cockpit.

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26

Schwinn, D. B., D. Kohlgrüber, J. Scherer, and M. H. Siemann. "A parametric aircraft fuselage model for preliminary sizing and crashworthiness applications." CEAS Aeronautical Journal 7, no. 3 (May 7, 2016): 357–72. http://dx.doi.org/10.1007/s13272-016-0193-4.

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27

Guida, M., A. Manzoni, A. Zuppardi, F. Caputo, F. Marulo, and A. De Luca. "Development of a multibody system for crashworthiness certification of aircraft seat." Multibody System Dynamics 44, no. 2 (January 26, 2018): 191–221. http://dx.doi.org/10.1007/s11044-018-9612-0.

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28

Rayhan, Saiaf Bin, Xue Pu, and Xi Huilong. "Modeling of fuel in aircraft crashworthiness study with auxiliary fuel tank." International Journal of Impact Engineering 173 (March 2023): 104449. http://dx.doi.org/10.1016/j.ijimpeng.2022.104449.

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29

Chen, Pu Woei, Shu Han Chang, and Chan Ming Chen. "Impact Loading Analysis of Light Sport Aircraft Landing Gear." Applied Mechanics and Materials 518 (February 2014): 252–57. http://dx.doi.org/10.4028/www.scientific.net/amm.518.252.

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This paper examined the critical loading condition of a light sport aircrafts main landing gear during the impact loading condition. The new category airplane was established by the FAA in 2004. The light sport aircraft has great market demand for personnel entertainment purpose and regional transportation. The main object of this research was to establish a static and dynamic loading simulation model for the aluminum alloy landing gear of a light sport aircraft. This work also examined the critical loading parameters of the main landing gear, including the maximum take-off weight and maximum stall speed. The analysis was performed using ANSYS and LS-DYNA to establish the finite element model after simplifying the geometric characteristics and verifying the results by energy conservation, hourglass energy, and sliding energy. The study tested aluminum plates with a thickness from 15~25 mm. The results showed all the samples could sustain the required loading condition, except for the thickness of 15mm that failed under impact loading. The simulation model provides a cost-saving process compared to a real crashworthiness drop test to test the main landing gears compliance with regulations.

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30

RUSU, Bogdan, Simona BLINDU BLINDU, Andra MICU, and Valentin SOARE. "Guidelines for Aircraft Composite Panels." INCAS BULLETIN 12, no. 1 (March 1, 2020): 217–28. http://dx.doi.org/10.13111/2066-8201.2020.12.1.21.

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The objective of this paper is to give a general perspective and present some elementary steps for manufacturing aircraft sandwich panel composites. Composite materials have been widely used in high performance sectors of the aerospace and automotive industry, and there is considerable knowledge and confidence in their static, dynamic and crashworthiness properties. Sandwich composites are becoming more and more used in airframe structural design, mainly for their ability to substantially reduce weight while maintaining their high mechanical properties. The steps for manufacturing a sandwich composite that meets all the requirements for exploitation are very precise and rigorous, involving specific design requirements, specific materials selection and specific manufacturing conditions starting with the lay-up procedure and up to the curing process inside an autoclave. After the curing process, destructive and nondestructive tests and experiments are performed on the composite structures in order to validate the products. At the same time, this paper presents a short briefing about the implication of 3D printing technologies with high temperature resistance resins for sandwich cores used in aerospace applications.

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31

Rayhan, Saiaf Bin, Xue Pu, and Xi Huilong. "Modeling of fuel in crashworthiness study of aircraft with auxiliary fuel tank." International Journal of Impact Engineering 161 (March 2022): 104076. http://dx.doi.org/10.1016/j.ijimpeng.2021.104076.

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32

Paciello, Carmen Simona, Claudio Pezzella, Marika Belardo, Simone Magistro, Francesco Di Caprio, Vincenzo Musella, Giuseppe Lamanna, and Luigi Di Palma. "Crashworthiness of a Composite Bladder Fuel Tank for a Tilt Rotor Aircraft." Journal of Composites Science 5, no. 11 (October 22, 2021): 285. http://dx.doi.org/10.3390/jcs5110285.

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The fulfilment of the crash is a demanding requirement for a Tiltrotor. Indeed, such a kind of aircraft, being a hybrid between an airplane and a helicopter, inherits the requirements mainly from helicopters (EASA CS 29) due to its hovering ability. In particular, the fuel storage system must be designed in such a manner that it is crash resistant, under prescribed airworthiness requirements, in order to avoid the fuel leakage during such an event, preventing fire and, thus, increasing the survival chances of the crew and the passengers. The present work deals with the evaluation of crashworthiness of the fuel storage system of a Tiltrotor (bladder tank), and, in particular, it aims at describing the adopted numerical approach and some specific results. Crash resistance requirements are considered from the earliest design stages, and for this reason they are mainly addressed from a numerical point of view and by simulations that treat both single components and small/medium size assemblies. The developed numerical models include all the main parts needed for simulating the structural behavior of the investigated wing section: the tank, the structural components of the wing, the fuel sub-systems (fuel lines, probes, etc.) and the fuel itself. During the crash event there are several parts inside the tanks that can come into contact with the tank structure; therefore, it is necessary to evaluate which of these parts can be a damage source for the tank itself and could generate fuel loss. The SPH approach has been adopted to discretise fuel and to estimate the interaction forces with respect to the tank structure. Experimental data were used to calibrate the fuel tank and foam material models and to define the acceleration time-history to be applied. Thanks to the optimized foam’s configuration, the amount of dissipated impact energy is remarkable, and the evaluation of tanks/fuel system stress distribution allows estimating any undesired failure due to a survivable crash event.

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33

Paz, J., L. Romera, and Jacobo Díaz. "Crashworthiness Optimization of Aircraft Hybrid Energy Absorbers Enclosing Honeycomb and Foam Structures." AIAA Journal 55, no. 2 (February 2017): 652–61. http://dx.doi.org/10.2514/1.j055245.

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34

Sadiq, S. E., S. H. Bakhy, and M. J. Jweeg. "Crashworthiness behavior of aircraft sandwich structure with honeycomb core under bending load." IOP Conference Series: Materials Science and Engineering 881 (August 11, 2020): 012046. http://dx.doi.org/10.1088/1757-899x/881/1/012046.

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35

Ramalingam, Visnuprean K., and Hamid M. Lankarani. "Analysis of impact on soft soil and its application to aircraft crashworthiness." International Journal of Crashworthiness 7, no. 1 (January 2002): 57–66. http://dx.doi.org/10.1533/cras.2002.0206.

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36

Ren, Yiru, Jinwu Xiang, Shaohua Meng, Yongju Yan, and Nanjian Zhuang. "Crashworthiness of Civil Aircraft Subject to Soft Soil and Concrete Impact surface." Procedia Engineering 80 (2014): 193–201. http://dx.doi.org/10.1016/j.proeng.2014.09.074.

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37

Russo, P., M. Guida, F. Marulo, and B. Vitolo. "Analysis of Integrated Fuselage Composite Seat for Small Aircraft in Crashworthiness Applications." Journal of Materials Engineering and Performance 28, no. 8 (April 12, 2019): 4856–62. http://dx.doi.org/10.1007/s11665-019-04027-w.

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38

Ren, Yiru, and Jinwu Xiang. "Crashworthiness uncertainty analysis of typical civil aircraft based on Box–Behnken method." Chinese Journal of Aeronautics 27, no. 3 (June 2014): 550–57. http://dx.doi.org/10.1016/j.cja.2014.04.020.

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39

Song, Y., B. Horton, and J. Bayandor. "Verified fuselage section water impact modelling." Aeronautical Journal 123, no. 1268 (October 2019): 1740–54. http://dx.doi.org/10.1017/aer.2019.110.

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ABSTRACTAlong many flight corridors, bodies of water serve as preferred emergency landing options. Thus, relevant scenarios must be investigated to improve aircraft crashworthiness in the event of an impact landing on water. Enhancing the damage tolerance of aircraft structures through repetitive experiments can, however, prove highly uneconomical. Such large-scale trials can be influenced by many factors of uncertainty adversely affecting the quality of the results. Therefore, the work presented in this study focuses in particular on evaluating a computational methodology perfected for aircraft water ditching using Coupled Lagrangian-Eulerian (CLE) that allows detailed prediction of structural response of a verified deformable fuselage section during such events. Validation of the fluid-structure interactive (FSI) strategy developed is conducted, thoroughly comparing the method against the analytical and experimental results of multiple wedge drop tests. Finally, the validated FSI strategy is applied to a high-fidelity fuselage section model impacting water to simulate and assess a realistic ditching scenario.

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40

Lankarani, H. M., and S. J. Hooper. "Application of Computer-Aided analysis tools for aircraft occupant and seat crashworthiness problems." International Journal of Crashworthiness 4, no. 4 (January 1999): 433–48. http://dx.doi.org/10.1533/cras.1999.0117.

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41

Adams, A., C. K. Thorbole, and H. M. Lankarani. "Scale modelling of aircraft fuselage: an innovative approach to evaluate and improve crashworthiness." International Journal of Crashworthiness 15, no. 1 (March 23, 2010): 71–82. http://dx.doi.org/10.1080/13588260903047663.

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42

Ren, Yiru, and Jinwu Xiang. "A comparative study of the crashworthiness of civil aircraft with different strut configurations." International Journal of Crashworthiness 15, no. 3 (July 26, 2010): 321–30. http://dx.doi.org/10.1080/13588260903343823.

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43

Ren, Yiru, and Jinwu Xiang. "The crashworthiness of civil aircraft using different quadrangular tubes as cabin-floor struts." International Journal of Crashworthiness 16, no. 3 (June 2011): 253–62. http://dx.doi.org/10.1080/13588265.2011.554204.

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Chen, Jichang, Tianhang Xiao, Mingzhen Wang, Yujin Lu, and Mingbo Tong. "Numerical Study of Wave Effect on Aircraft Water-Landing Performance." Applied Sciences 12, no. 5 (March 1, 2022): 2561. http://dx.doi.org/10.3390/app12052561.

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Aircraft, such as amphibious planes, airliners, helicopters and re-entry capsules, are frequently subject to impacting loads from water-landing/ditching on various free surfaces, especially under wave conditions. Understanding and quantifying the water-landing/ditching performance on wave surfaces are of fundamental important for the design and certification of crashworthiness in the field of aerospace engineering. This study aims to numerically assess the effect of wave surface on water-landing process of an amphibious aircraft. The numerical implementation is realized in Reynolds-averaged Navier–Stokes (RANS) framework by combining finite volume method (FVM), volume of fluid (VOF) approach and velocity-inlet wavemaker. The temporal-spatial characteristic of numerical wave and the accuracy of presented model are, respectively, validated by analytical wave and convergence studies. The aircraft landing simulations with different free surface conditions, i.e., calm water, regular wave with different wave heights are then performed and quantitatively compared through several physical parameters, including acceleration, velocity, pressure, pitch angle and free surface deformation. It was found that the aircraft regular wave-landing process experiences several unique stages comparing with the calm-water-landing case. The results clearly confirm that wave surface can influence the aircraft landing performance to a great extent. The fundamental mechanism is found to be that the wave surface slope and wave particle velocity remarkably change the impacting position and effective impacting velocity of the aircraft.

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Di Caprio, Francesco, Andrea Sellitto, Salvatore Saputo, Michele Guida, and Aniello Riccio. "A Sensitivity Analysis of the Damage Behavior of a Leading-Edge Subject to Bird Strike." Applied Sciences 10, no. 22 (November 19, 2020): 8187. http://dx.doi.org/10.3390/app10228187.

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This paper aims to investigate the crashworthiness capability of a commercial aircraft metallic sandwich leading edge, subjected to bird strike events. A sensitivity analysis is presented, aimed to assess the influence of the skin parameters (inner and outer faces and core thicknesses) on the leading-edge crashworthiness and to determine, among the configurations able to withstand a bird strike event, the best compromise in terms of weight and structural performances. In order to easily manage the design parameters and the output data, the ModeFrontier code was used in conjunction with the FE code Abaqus/Explicit. A dedicated python routine was developed to define a fully parametric simplified leading-edge model. To fulfill the aerodynamic requirements, the external surfaces were considered fixed during the sensitivity analysis, and, thus, only the internal leading edge’s components were modified to study their influence on the structural response. The total mass of the model, the maximum deformation and the energy dissipated due to material failure and the plastic deformations were monitored and used to compare and assess the behavior of each configuration.

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Ren, Yiru, Hanyu Zhang, and Jinwu Xiang. "A novel aircraft energy absorption strut system with corrugated composite plate to improve crashworthiness." International Journal of Crashworthiness 23, no. 1 (March 27, 2017): 1–10. http://dx.doi.org/10.1080/13588265.2017.1301082.

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Paz Mendez, Javier, Jacobo Díaz Garcia, Luis E. Romera Rodriguez, and Filipe Teixeira-Dias. "Crashworthiness study on hybrid energy absorbers as vertical struts in civil aircraft fuselage designs." International Journal of Crashworthiness 25, no. 4 (October 31, 2019): 430–46. http://dx.doi.org/10.1080/13588265.2019.1605723.

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Mou, Haolei, Jiang Xie, and Zhenyu Feng. "Research status and future development of crashworthiness of civil aircraft fuselage structures: An overview." Progress in Aerospace Sciences 119 (November 2020): 100644. http://dx.doi.org/10.1016/j.paerosci.2020.100644.

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Beheshti, Hamid Khademhosseini, and Hamid Lankarani. "An investigation in crashworthiness evaluation of aircraft seat cushions at extreme ranges of temperature." Journal of Mechanical Science and Technology 24, no. 5 (May 2010): 1105–10. http://dx.doi.org/10.1007/s12206-010-0316-5.

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Romano, Maria Grazia, Michele Guida, Francesco Marulo, Michela Giugliano Auricchio, and Salvatore Russo. "Characterization of Adhesives Bonding in Aircraft Structures." Materials 13, no. 21 (October 28, 2020): 4816. http://dx.doi.org/10.3390/ma13214816.

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Structural adhesives play an important role in aerospace manufacturing, since they provide fewer points of stress concentration compared to faster joints. The importance of adhesives in aerospace is increasing significantly because composites are being adopted to reduce weight and manufacturing costs. Furthermore, adhesive joints are also studied to determine the crashworthiness of airframe structure, where the main task for the adhesive is not to dissipate the impact energy, but to keep joint integrity so that the impact energy can be consumed by plastic work. Starting from an extensive campaign of experimental tests, a finite element model and a methodology are implemented to develop an accurate adhesive model in a single lap shear configuration. A single lap joint finite element model is built by MSC Apex, defining two specimens of composite material connected to each other by means of an adhesive; by the Digimat multi-scale modeling solution, the composite material is treated; and finally, by MSC’s Marc, the adhesive material is characterized as a cohesive applying the Cohesive Zone Modeling theory. The objective was to determine an appropriate methodology to predict interlaminar crack growth in composite laminates, defining the mixed mode traction separation law variability in function of the cohesive energy (Gc), the ratio between the shear strength τ and the tensile strength σ (β1), and the critical opening displacement υc.

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