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The all-composite sandwich structure with the honeycomb core is a lightweight and high-strength structure with broad application scenarios. The face sheet and honeycomb core of the proposed all-composite sandwich structure in this work are composed of carbon-fiber-reinforced polymer (CFRP) composites. The mechanical response and damage mechanism of...
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Context 1
... shown in Figure 5, the impact model of the all-composite sandwich structure with the honeycomb core is built on the ABAQUS/Explicit finite element platform. The configuration of the all-composite sandwich structure is consistent with the compression model. ...
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... shown in Figure 5, the impact model of the all-composite sandwich structure with the honeycomb core is built on the ABAQUS/Explicit finite element platform. The configuration of the all-composite sandwich structure is consistent with the compression model. ...
Context 3
... this section, the dynamic mechanical response and damage evolution process of the all-composite sandwich structure with the honeycomb core under quasi-static out-ofplane compression and out-of-plane impact loading are studied by constructing the numerical calculation framework and the fine finite element models, and some results are compared with the literature conclusions. Figure 5. Finite element model of all-composite sandwich structure with honeycomb core subjected to impact. ...
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In this study, a high-strength carbon fiber reinforced composite laminate for rail vehicles was machined as a perforated sample and repaired with a patch of the same material. The response of the repaired laminate to a low-velocity impact with an energy of 30 J was investigated through experiments and simulations. The finite element simulation mode...
Citations
... Previous studies show that many experiments and simulations have investigated the low-velocity-impact response of single-layer honeycomb sandwich panels. Unfilled honeycombs [51][52][53][54] and polyurethane foam-filled single-layer aluminum honeycombs are the most common [55][56][57]. Increasing the number of core layers and forming the gradient structure enhance the impact resistance of sandwich panels, and filled foam is also commonly used to reinforce the performance of sandwich panels. ...
Sandwich panels are often subjected to unpredictable impacts and crashes in applications. The core type and impactor shape affect their impact response. This paper investigates the responses of five tandem Nomex honeycomb sandwich panels with different core-types under low-velocity-impact conditions with flat and hemispherical impactors. From the force response and impact displacement, gradient-tandem and foam-filled structures can improve the impact resistance of sandwich panels. Compared with the single-layer sandwich panel, the first peak of contact force of the foam-gradient-filled tandem honeycomb sandwich panels increased by 34.84%, and maximum impact displacement reduced by 50.98%. The resistance of gradient-tandem Nomex honeycomb sandwich panels under low-velocity impact outperformed uniform-tandem structures. Foam-filled structures change the impact responses of the tandem sandwich panels. Impact damage with a flat impactor was more severe than the hemispherical impactor. The experimental results are helpful in the design of tandem Nomex honeycomb sandwich panels.
... Frequently employed shapes include hexagonal cells, triangular cells, square cells and other similar variations. Studies which present certain similarities refer to tensile and compressive properties determination of different 3D printed honeycomb structures [23][24][25], the additive manufacturing of aircraft spare components [26] and the also mechanical evaluation of different sandwich structures with honeycomb cores, realized by additive manufacturing [27,28]. Also, due to the widespread use of the 5052-aluminum alloy as an aviation structural material, there are many references regarding its properties [29,30]. ...
Manufacturing aircraft components through 3D printing has become a widespread concept with proven applicability for serial production of certain structural parts. The main objective of the research study is to determine whether a chlorinated polyethylene material reinforced with milled carbon fibers has the potential of replacing the current 5052 NIDA aluminum alloy core of the IAR330 helicopter tail rotor blade, under the form of a honeycomb structure with hexagonal cells. Achieving this purpose implied determining the tensile and compression mechanical properties of the material realized by fused deposition modeling. The tensile tests have been conducted on specimens manufactured on three printing directions, so that the orthotropic nature of the material may be taken into account. The bare compression tests were realized on specimens manufactured from both materials, with similar honeycomb characteristics. All the mechanical tests have been performed on the Instron 8872 servo hydraulic testing system and the results have been evaluated with the Dantec Q400 Digital Image Correlation system. The experimental tests have been reproduced as finite element analyses which have been validated by results comparison, in order to determine if the compression model is viable for more complex numerical analysis.
The high-resolution spacecraft poses an urgent need for opto-mechanical structure with ultra-high stability and light-weight. Owing to the advantages of both carbon fiber-reinforced carbon-based composites (C/C composites) and honeycomb sandwich structure, a novel C/C honeycomb sandwich structure strategy is proposed in this study. It was fabricated by using weaving fabrics and Chemical Vapor Infiltration (CVI) process, then was tested under out-of-plane compression. Taking the weave structure of honeycomb wall, anisotropy characteristics and damage mechanism of C/C composites, as well as the parameters of core size, a multi-scale damage model is established and validated to investigate mechanical behavior of the novel structure. The effects of influence factors (side length, thickness and height of core) on mechanical properties and damage mode of the novel sandwich structure are investigated. The results demonstrate that the optimal honeycomb core sizes for improving the light-weight and high load-bearing integration performance are l = 5 mm–7.5 mm and t = 0.3 mm–0.4 mm. The matrix damage occurs in the middle region of core, while fiber damage occurs at the end of core when its height reaches 15 mm. This study is helpful for design and optimization for opto-mechanical structure of high-resolution spacecraft.
Auxetic structures (AXSs) are a novel class of materials with unique mechanical deformation behavior associated with negative Poisson ratio. The combination of AXS configurations with various types of materials has unveiled a wide field of applications, including military high velocity protection against explosions and ballistic projectiles. However, the characteristic geometric re-entrant model
of AXSs imposes limitations and difficulties when using conventional manufacturing methods to assemble the structure lattice. Additive manufacturing (AM) has recently been explored as a more efficient and cost-effective method to fabricate AXSs, regardless of the type of material. This review paper focuses on the development and applications of AM processed AXSs. The review highlights
the significance and great potential for this class of materials that can be produced relatively fast and at a low cost. The advantages of AXS/AM are expected to extend to important industrial sectors,
particularly for military ballistic armor, where the feasibility for products with improved properties is critical. The use of AM offers a viable solution to overcome the difficulties associated with the conventional manufacturing methods, and thus offers greater design flexibility, cost efficiency, and reduced material waste. This review paper aims to contribute to the understanding of the current state-of-the-art and future research prospects for the production and applications of AXS/AM.
