On Aluminum Honeycomb Impact Attenuator Designs for Formula Student Competitions

Ma, Quoc-Phu; Krzikalla, David; Měsíček, Jakub; Petrů, Jana; Smiraus, Jakub; Slíva, Aleš; Poruba, Zdeněk

doi:10.3390/sym12101647

Cited by 11 publications

(8 citation statements)

References 38 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The behaviour of spring was built based on art. [17]: The mean value has been found to be in accordance with experimental data. The simulation is able to predict the values of absorber crushing (honeycomb), mean collapsing force, and mean acceleration registered on rigid plate (see figure 8) with wing lumped mass hypothesis.…”

Section: Absorber Numerical Characterizationsupporting

confidence: 83%

High Fidelity Crash Analysis of Ngctr-TD Composite Wing

Di Palma,

Albo,

Nardone

et al. 2024

J. Phys.: Conf. Ser.

View full text Add to dashboard Cite

The T-WING project is a research project aimed at designing, manufacturing, qualifying and testing the new wing of Leonardo Next Generation Civil Tilt-Rotor technical demonstrator (NGCTR-TD), as part of Clean Aviation Fast Rotorcraft activities. The methodology proposed in this paper encompasses the development of high-fidelity modelling and simulation procedures in support to virtual certification methods for crashworthiness requirements of tiltrotors. Finite Element Analysis (FEA) of an aircraft drop test is a complex and detailed process that aims to simulate the structural behaviour during an impact or drop event. This type of analysis is critical for assessing the safety of an aircraft in emergency landing situations. Wing crashworthiness requirement is specific for tilt rotors: during a survivable crash event, the wing design must ensure a pre-defined rupture with the purpose of alleviating the inertial load acting on the fuselage to preserve the occupants from injuries and fire, guaranteeing the escape paths. Thus, the highly integrated T-WING wing box concept has been designed with the specific feature of frangible sections near the wing-fuselage intersection. The activation of fracture of the external semi-wings in correspondence of frangible section is triggered by the achievement of a well-defined crash vertical load factor. The objective of the methodology is to simulate the crash effects on the whole wing, using explicit non-linear and time-dependent FE analysis, to verify the wing spanwise placement of the frangible sections, the failure mode, the loads acting at the fuselage links, and the acceleration transmitted to the structure. This work is focused on a standalone analysis of the wing plus a lumped scheme of the fuselage, and it is part of a wider activity which will comprise, in the crash simulation, the most relevant vehicle systems (e.g. fuselage model). Moreover, this numerical activity has been compared with experimental results obtained on a different but similar structure, in terms of global acceleration at wing centre of gravity. Good agreement in terms of acceleration has been found between numerical model and experimental relevant test.

show abstract

Section: Absorber Numerical Characterizationsupporting

confidence: 83%

High Fidelity Crash Analysis of Ngctr-TD Composite Wing

Di Palma,

Albo,

Nardone

et al. 2024

J. Phys.: Conf. Ser.

View full text Add to dashboard Cite

show abstract

“…The energy absorption characteristics and dynamic evolution process have concluded that the combined structure honeycomb has a stronger energy absorption effect under the same conditions. Quoc [17] studied the crushing behavior of the honeycomb structure from a theoretical perspective and then verified it by numerical simulation. Mertani [18] conducted an experimental study on the compression response of a hexagonal honeycomb core from an initial elastic state to a fully crushed state.…”

Section: Introductionmentioning

confidence: 97%

Research on Aluminum Honeycomb Buffer Device for Soft Landing on the Lunar Surface

Wei

Zhang

Zhao

et al. 2021

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

To obtain the resources of the moon, humans have launched a series of exploration activities on the moon, and the landing buffer device is an indispensable device on the lander required to perform lunar surface exploration missions. It can effectively protect the lander during landing scientific payloads such as instruments on the lander. Based on the mechanical properties and deformation mechanism of the aluminum honeycomb as buffer material, this paper compares and analyzes different simulation schemes and finally establishes the bonding model of the honeycomb by using the discrete element method; the parameters of the honeycomb material are matched through compression experiments to verify the discrete element honeycomb simulation and the feasibility of the scheme and its parameters. To meet the buffering requirements of large landers, a spider web honeycomb structure is proposed, its modeling method is studied by using the discrete element secondary development program, and the model is compressed as a whole to verify the energy consumption characteristics of the spider web honeycomb structure. Aiming at the honeycomb buffer device during the landing process, the cobweb honeycomb buffer structure and its corresponding landing coupling model were established using the discrete element method, the landing process was simulated and analyzed, and the landing results were predicted to verify the feasibility of the device, providing a reference for the design of the lander and its buffer device.

show abstract

“…NASA and others [ 2 , 3 , 4 ] concluded that the honeycomb structure has the best energy-absorbing properties in relation to its specific mass. Due to this feature, honeycomb structures are used across a wide range of industries, including the automotive industry [ 5 , 6 ] and the military [ 7 , 8 ].…”

Section: Introductionmentioning

confidence: 99%

A Study of Aluminum Honeycomb Structures under Dynamic Loading, with Consideration Given to the Effects of Air Leakage

Ciepielewski

Miedzińska

2023

Materials

View full text Add to dashboard Cite

Aluminum honeycomb structures are used in the construction of protective materials due to the positive relationship between their mass and their energy-absorbing properties. Applying such materials in the construction of large machinery, such as military vehicles, requires the development of a new method of finite element modeling, one that considers conditions with high strain rates, because a material model is currently lacking in the available simulation software, including LS-DYNA. In the present study, we proposed and verified a method of numerically modeling honeycomb materials using a simplified Y element. Results with a good level of agreement between the full core model and the Y element were achieved. The obtained description of the material properties was used in the subsequent creation of a homogeneous model. In addition, we considered the influence of increases in pressure and the leakage of the air entrapped in the honeycomb cells. As a result, we were able to attain a high level of accuracy regarding the stress values across the entire range of progressive failure, from the loss of stability to full core densification, and across a wide range of strain rates.

show abstract

On Aluminum Honeycomb Impact Attenuator Designs for Formula Student Competitions

Cited by 11 publications

References 38 publications

High Fidelity Crash Analysis of Ngctr-TD Composite Wing

High Fidelity Crash Analysis of Ngctr-TD Composite Wing

Research on Aluminum Honeycomb Buffer Device for Soft Landing on the Lunar Surface

A Study of Aluminum Honeycomb Structures under Dynamic Loading, with Consideration Given to the Effects of Air Leakage

Contact Info

Product

Resources

About