Crashworthiness study of a civil aircraft fuselage section

Xue, Pu; Ding, Menglong; Qiao, C F; Yu, Tongxi

doi:10.1590/s1679-78252014000900007

Cited by 21 publications

(13 citation statements)

References 12 publications

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“…Many investigations use composite materials to improve the energy absorption capability for various structures as well as civil aircraft fuselage under impact loading. [26][27][28][29][30][31][32][33][34] Many studies have proposed experimental methods for determining the absorbed energy of composite materials using different specimens with different shapes as well as various impact speeds. 16,35 Feindler et al 18 used a compressive rate of 0.25 mm/s to test CFRP specimens in omega-shaped and plate-shaped specimens with three different laminate layups (45°and 0°).…”

Section: Relevant Studiesmentioning

confidence: 99%

Evaluation on crashworthiness and energy absorption of composite light airplane

Chen

Lin

2018

Advances in Mechanical Engineering

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The main aim of this study was to explore the safety differences when using aluminum alloy and three different fiber reinforced composites as material for the cockpit and fuselage of light aircraft under crash landing. In accordance with the cockpit reduction amount stipulated by MIL-STD-1290A in which the reducing rates in all directions cannot exceed 15%, this study established the safety zones of impact speeds and impact angles. The overall safety zones of the carbon fiber reinforced composites and glass fiber reinforced composites cockpits were higher than that of the aluminum alloy cockpit by 38.56% and 32.12%, respectively. Among the four different fuselage materials, when carbon fiber reinforced composites was used as the cockpit material, except that the reducing rate for the crashing in the Y direction was slightly higher than the aluminum alloy cockpit, the reducing rate in the X direction and the inclined beam A direction during crashes were less than other materials, and the safety of its overall cockpit was also the most superior to other materials. The energy absorption capability of the aluminum alloy fuselage was better than the fuselages of all composite materials.The energy absorption capacity during a crash will directly influence the damage level for passengers. On the other hand, due to the different structural design in the airframes of rotorcrafts, small airplanes, and large airplanes, the mechanisms of crashworthiness and energy absorption are different. Because of the space constraints, rotorcrafts and small airplanes can only rely on the fuselage, floor, seats, and landing gear to

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Section: Relevant Studiesmentioning

confidence: 99%

Evaluation on crashworthiness and energy absorption of composite light airplane

Chen

Lin

2018

Advances in Mechanical Engineering

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“…The presence of energy absorbing structures and their ability in the absorbing the impact energy during the course of an impact have been discussed by Xue et al [15] and Heimbs [16].…”

Section: Code Of Federal Regulations Have Been Published By the Us Gmentioning

confidence: 99%

Vertical Impact Simulations of a Full-Size and Simplified Scaled Models of an Aircraft Fuselage Section

Prasad

Tay

Lankarani

2015

Volume 1: Advances in Aerospace Technology

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Computer modeling and simulations on the crashworthiness of aircraft using validated models have provided insight into the energy-absorption characteristics of structures and have allowed parametric studies in the evaluation of different crash energy management designs. In this study, the dynamic responses of a detailed and simplified full-size, and scaled fuselage models in vertical impact are investigated. The detailed full-size model, constructed from a Boeing 737 mid-fuselage section, consists of a stiff auxiliary fuel tank and a cargo door. The detailed full-size model is dropped from a height of 4.26 m (14 ft) onto a rigid surface, which corresponds to a vertical impact speed of 9.14 m/s (30 ft/s). The drop simulations are performed using the non-linear explicit code, LS-DYNA. Correlation of the detailed full-size model with the physical test conducted by the Federal Aviation Administration is demonstrated. Scale modeling technique applied to the aircraft fuselage section is utilized and for scaling purposes, a simplified full-size model is constructed without the auxiliary fuel tank and cargo door. The crash responses of the simplified full-size models in relation to the detailed full-size model are shown and discussed. The scaling approach involves geometrical scaling of the simplified full-size model with scale factors of 1/5th, 1/10th and 1/20th. The vertical impact simulations of the scaled models are carried with identical impact speed as that of the detailed full-size model. General scaling laws for geometry, mass, velocity, acceleration and forces are utilized to predict the results for the scaled models. The approach and results presented in this study have demonstrated an efficient and innovative method on the design and crashworthiness of a fuselage section.

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“…Authors have considered several scenarios, including explosions, foreign object impacts or hard landing crashes [5]. During the latter, the vertical deceleration is critically influenced by the sub-floor structures [6]. In the commercial aircraft range, the highest contribution for kinetic energy dissipation stems from deformation of the main fuselage [7].…”

Section: Introductionmentioning

confidence: 99%

Optimisation of thin-walled hybrid vertical struts for crashworthy aircraft designs

Paz

Díaz

Romera

et al. 2019

Struct Multidisc Optim

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This research concerns the crashworthiness enhancement of a model of a Boeing 737-200 fuselage section. Using a validated numerical specimen, four thin-walled crushable hybrid energy absorbers are added to the aircraft to work as vertical struts. The absorbers are composed of a hollow aluminium tube, a star-shaped glass-fibre reinforced polymer inner matrix and foam extrusions. The absorbers-with variable tube edge and thickness, composite thickness and core height-are single-and multi-objectively optimised. Surrogate models and genetic algorithms are used for the minimisation of acceleration loads, injury levels and the strut's weight. Results yield a more efficient frames' collapse evolution with plastic dissipation increased by over 50%. Consequently, acceleration peaks are up to 50% lower at the two measured locations while maintaining low mass values. Injury levels were also reduced from severe to moderate according to an Eiband diagram.

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Crashworthiness study of a civil aircraft fuselage section

Cited by 21 publications

References 12 publications

Evaluation on crashworthiness and energy absorption of composite light airplane

Evaluation on crashworthiness and energy absorption of composite light airplane

Vertical Impact Simulations of a Full-Size and Simplified Scaled Models of an Aircraft Fuselage Section

Optimisation of thin-walled hybrid vertical struts for crashworthy aircraft designs

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