Pulse pressure loading of aircraft structural panels

Simmons, M.C.; Schleyer, Graham

doi:10.1016/j.tws.2006.05.002

Cited by 28 publications

(18 citation statements)

References 25 publications

(25 reference statements)

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“…The first and oldest one is riveting. The advantage of this method is not only the simplicity of technology, but also the greater energy absorption in relation to the welded structure [49]. The disadvantage is the possibility of crack initiation at the edges of the holes due to stress concentration.…”

Section: The Methods For Stiffeners Mounting Their Cross Sections Anmentioning

confidence: 99%

“…Connection parameters of hybrid adhesive -riveted joints may also be modified by the prestress [52] or use of appropriate holes tolerances [53]. More and more often, laser welding method is used to connect stiffener with skin [47,43,49]. Although laser beam welding minimizes heat impact on joint, there is a loss of alloying elements from weld zone which reduces the hardness and strength properties.…”

Section: The Methods For Stiffeners Mounting Their Cross Sections Anmentioning

confidence: 99%

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Skew Bending of Aircraft Fuselage Panels with “L” and “C” Stringers Mounted by Hybrid Joint / Ukośne Zginanie Poszycia Samolotu Z U Sztywnieniami Typu “L” I “C”, Mocowanymi Za Pomocą Złącza Hybrydowego

Sadowski¹,

Golewski²

2015

Archives of Metallurgy and Materials

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Skew bendIng of aIrcraft fuSelage panelS wIth "l" and "c" StrIngerS mounted by hybrId joInt Ukośne zginanie poszycia samolotU z Usztywnieniami typU "l" i "c", mocowanymi za pomocą złącza hybrydowegoA section of fuselage skin with dimension 30 x 200 mm was subjected to numerical study and loaded by skew bending (Fig. 3). The thickness of the skin was 0,6 mm, the length of a leg of an angle "L" profile stringer was 12 mm with 1mm thickness. The angle of inclination α of the load plane to the skin plane varies in the range from 10° to 90° with 10° increment. The elastic -plastic material model of D16T aluminum alloy was used in simulations of the fuselage skin as well as for "L" and "C" profile stringers. In the material model description damage of aluminum alloy was taken into account. An adhesive layer with thickness of 0,1mm was modeled using cohesive elements with the failure mode depending on the shear strength and the tensile strength.The paper presents a comparative analysis of the considered structural elements with application of the unsymmetrical "L" profile or the symmetrical "C" profile with the same cross section area.All numerical studies were performed in Abaqus program. Finally, one can conclude that the stiffness of the structural element with application of the symmetrical "C" profile stringer is stronger, whereas the mechanical response of both versions of the hybrid joint significantly depends on the angle of load inclination α.

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Section: The Methods For Stiffeners Mounting Their Cross Sections Anmentioning

confidence: 99%

Section: The Methods For Stiffeners Mounting Their Cross Sections Anmentioning

confidence: 99%

Skew Bending of Aircraft Fuselage Panels with “L” and “C” Stringers Mounted by Hybrid Joint / Ukośne Zginanie Poszycia Samolotu Z U Sztywnieniami Typu “L” I “C”, Mocowanymi Za Pomocą Złącza Hybrydowego

Sadowski¹,

Golewski²

2015

Archives of Metallurgy and Materials

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“…Simmons and Schleyer [10] did experimental and …nite element analysis of the response and failure modes of sti¤ened, aluminum alloy panels with conventional riveting and laser welding. They used a pressure chamber that theoretically gives a triangular pressure pulse on the test structure.…”

Section: Literature Review On Blast Loadingmentioning

confidence: 99%

Sensitivity analysis of blast loading parameters and their trends as uncertainty increases

Borenstein

Benaroya

2009

Journal of Sound and Vibration

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A sensitivity analysis of blast loading parameters is performed to determine which of the parameters'uncertainty has the greatest e¤ect on the maximum de ‡ection of an aluminum plate subjected to a blast load. A numerical simulation using the Monte Carlo method is used to obtain the ensemble averages of the probabilistic runs. The random variables were given a uniform distribution. Two simpli…ed loading models are used. The …rst has an instantaneous rise with an exponential decay, represented by the modi…ed Friedlander equation. The second loading model has a linear rise with an exponential decay. Both of these models are simulated with three di¤erent blast scaled values, giving a total of six di¤erent cases. In addition, the de ‡ection trends due to the loading parameters as uncertainty increases is quanti…ed. Probability density functions of the maximum de ‡ection are also presented. The probabilistic results and trends are also explained using deterministic methods. It appears that the duration time of the loading models is generally the most sensitive parameter to uncertainty.ii Acknowledgements First and foremost, I would like to acknowledge my advisor Professor Haym Benaroya. I feel very lucky and honored to have him as my advisor. He is a great advisor and is always willing to give up his time to help. In addition, he is constantly looking out for his students.For instance, he would make sure that other professors, whom I was a teaching assistant for, do not give me a workload greater than the amount I was supposed to have. He has also provided me with a great deal of support, both academically as well as …nancially.A very big acknowledgement goes to Dr. Jason Florek who has become a great colleague and friend of mine. From the start he has helped me to understand the subject of blast loads and supplied me with many journal articles and books on the subject. He was always willing to help answer any questions I had on the subject, or for that matter, on any subject.I also used his response model in my work. On a personal note, he is always fun to hangout with and made it enjoyable to come to the o¢ ce or go to conferences. He even learned how to play goalie for our MAE United soccer team. Jason, thank you very much for everything.

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“…As the use of lightweight ductile materials in protective structures increases, knowledge of the combined effect of pressure loading and fragment impact on these materials is needed. In addition to the relevance for ongoing research on the effect of combined blast and fragment loading, transient pressure loading of plates with holes is relevant for several other applications, such as deck plating on offshore platforms and bulkheads in ships [16], aircraft design [19] and the use of perforated plates for blast wave mitigation [15].…”

Section: Introductionmentioning

confidence: 99%

Transient pressure loading of clamped metallic plates with pre-formed holes

Rakvåg

Underwood

Schleyer

et al. 2013

International Journal of Impact Engineering

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The combined effect of blast and impact loading against protective structures is still not fully understood. In this paper, the motivation is to investigate the combined effect of pressure and fragment loading on steel plates. To simplify the approach, it is assumed that the fragments strike and perforate the flexible target before the pressure load arrives. These perforations are idealized as pre-formed holes of generalized shapes in thin, ductile Docol 600DL steel plates, which are then subjected to controlled pressure pulses in the laboratory. The tests were carried out in a Pulse Pressure Loading Rig, and two different pressure levels were applied for each plate design. After the tests, the deflections caused by the pressure pulses were measured. Even though the plates were much deformed in some of the tests, no sign of failure was observed. Based on a number of material tests, the parameters in the modified Johnson-Cook constitutive relation were identified. Several sets of non-linear finite element simulations of the pressure loading process were then conducted. The agreement between standard Lagrangian simulations and the experimental results was in general good, but the simulations failed to give an accurate description of the deflection around the pre-formed holes. Fully coupled FSI simulations of the experimental tests were then carried out and these simulations demonstrate significant spatial variation of the pressure load. The FSI simulations also showed that this spatial variation of the pressure load influence the deflection profile, especially in the vicinity of the holes.

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Pulse pressure loading of aircraft structural panels

Cited by 28 publications

References 25 publications

Skew Bending of Aircraft Fuselage Panels with “L” and “C” Stringers Mounted by Hybrid Joint / Ukośne Zginanie Poszycia Samolotu Z U Sztywnieniami Typu “L” I “C”, Mocowanymi Za Pomocą Złącza Hybrydowego

Skew Bending of Aircraft Fuselage Panels with “L” and “C” Stringers Mounted by Hybrid Joint / Ukośne Zginanie Poszycia Samolotu Z U Sztywnieniami Typu “L” I “C”, Mocowanymi Za Pomocą Złącza Hybrydowego

Sensitivity analysis of blast loading parameters and their trends as uncertainty increases

Transient pressure loading of clamped metallic plates with pre-formed holes

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