Adhesive Joining of Zerodur–CFRP–Zerodur Sandwich Structures for Aerospace Applications

Ammbrois, Stefano De la Pierre des; Corazzari, Ingrid; Damiano, Olivier; Cornillon, Laurence; Terenzi, Andrea; Casalegno, Valentina; Ferraris, Monica

doi:10.1002/mame.202000464

Cited by 13 publications

(2 citation statements)

References 10 publications

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“…The CTE of CFRP laminates is deter-mined by the properties and proportions of the carbon fiber and adhesive resin [13]. Cy-anate esters are widely used in CFRP design due to their low coefficient of thermal expan-sion [26]. In this paper, M40/cyanate ester unidirectional prepreg is used as the basic ma-terial of the support structure, and the basic properties of the material are shown in Table 1.…”

Section: Design Of Zero-expansion Laminated Platesmentioning

confidence: 99%

Thermal Stability Design of Asymmetric Support Structure for an Off-Axis Space Camera

et al. 2021

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With the development of space optical remote sensing technology, especially off-axis space cameras, the thermal dimensional stability of the support structure has become increasingly demanding. However, the asymmetry of the camera structure has not been fully considered in the past design of the thermal stability of off-axis cameras. In order to solve this problem, a support structure with very low thermal deformation in the asymmetric direction is presented in this paper for an off-axis TMA camera. By means of the negative axial thermal expansion coefficient of carbon-fiber-reinforced plastics (CFRP), a composite laminate with near zero-expansion was obtained by adjusting the direction of fiber laying, and the asymmetric feature of the off-axis remote sensing camera structure was fully considered, thus enabling the support structure to have good thermal dimensional stability. We carried out a thermal load analysis and an optical analysis of the whole camera in the case of a temperature rise of 5 °C. The results show that the zero-expansion support structure has good thermal stability, and the thermal deformation in the asymmetric direction of the camera is obviously smaller than that of the isotropic laminate support structure. Compared with the isotropic support structure, the influence of thermal deformation on MTF is reduced from 10.43% to 2.61%. This study innovatively incorporates the asymmetry of the structure into the thermal sta-bility design of an off-axis TMA camera and provides a reference for the thermal stability design of other off-axis space cameras.

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Section: Design Of Zero-expansion Laminated Platesmentioning

confidence: 99%

Thermal Stability Design of Asymmetric Support Structure for an Off-Axis Space Camera

et al. 2021

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“…The demand for low-weight and high-rigidity materials in high-performance sectors has given way to the development of composite materials [ 1 ]. Among others, sandwich structures deserve special attention due to their use in a wide variety of sectors, which include conventional packaging with corrugated craft cores [ 2 ], and high-performance applications in aerospace [ 3 , 4 ], automotive [ 5 ], aeronautics [ 6 ], lightweight civil infrastructure [ 7 ], and so on. Sandwich panels are composed of a lightweight core and two (top and bottom) skins [ 8 ].…”

Section: Introductionmentioning

confidence: 99%

Manufacturing and Characterization of Highly Environmentally Friendly Sandwich Composites from Polylactide Cores and Flax-Polylactide Faces

et al. 2021

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This work focuses on the manufacturing and characterization of highly environmentally friendly lightweight sandwich structures based on polylactide (PLA) honeycomb cores and PLA-flax fabric laminate skins or facings. PLA honeycombs were manufactured using PLA sheets with different thicknesses ranging from 50 to 500 μm. The PLA sheets were shaped into semi-hexagonal profiles by hot-compression molding. After this stage, the different semi-hexagonal sheets were bonded together to give hexagonal panels. The skins were manufactured by hot-compression molding by stacking two Biotex flax/PLA fabrics with 40 wt% PLA fibers. The combined use of temperature (200 °C), pressure, and time (2 min) allowed PLA fibers to melt, flow, and fully embed the flax fabrics, thus leading to thin composite laminates to be used as skins. Sandwich structures were finally obtained by bonding the PLA honeycomb core with the PLA-flax skins using an epoxy adhesive. A thin PLA nonwoven was previously attached to the external hexagonal PLA core, to promote mechanical interlock between the core and the skins. The influence of the honeycomb core thickness on the final flexural and compression properties was analyzed. The obtained results indicate that the core thickness has a great influence on the flexural properties, which increases with core thickness; nevertheless, as expected, the bonding between the PLA honeycomb core and the skins is critical. Excellent results have been obtained with 10 and 20 mm thickness honeycombs with a core shear of about 0.60 and facing bending stresses of 31–33 MPa, which can be considered as candidates for technical applications. The ultimate load to the sample weight ratio reached values of 141.5 N·g−1 for composites with 20 mm thick PLA honeycombs, which is comparable to other technical composite sandwich structures. The bonding between the core and the skins is critical as poor adhesion does not allow load transfer and, while the procedure showed in this research gives interesting results, new developments are necessary to obtain standard properties on sandwich structures.

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The Influence of Moisture Absorption‐Drying of Composite Materials on the Bonding Performance of the Joints

Chen

Zhang

et al. 2022

Macro Materials & Eng

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Composite materials are susceptible to environmental threats correlated to moisture absorption, which affects the bonding performance of the joints. Therefore, drying should be taken into account during actual manufacturing operations. In this work, the influence of moisture absorption‐drying of composite materials on the bonding performance of the joints is investigated to provide a theoretical direction for the co‐bonding process. Firstly, the surfaces of composite materials are treated with three methods: sanding, dry peel ply, and wet peel ply. Secondly, the composite materials are subjected to moisture absorption‐drying treatment at 26 °C/65% relative humidity (RH) and 70 °C/85% RH. Finally, the above materials are bonded to evaluate the bonding performance. These results show that the bonding performance of the joints treated with two peel plies decreases significantly after moisture absorption. After moisture absorption‐drying at 26 °C/65% RH, the bonding performance of the joints treated with dry peel ply cannot fully recover, while wet peel ply can be fully recoverable. However, the bonding performance of all joints cannot fully recover after absorbing moisture‐drying at 70 °C/85% RH, whose recovery has relations with surface treatment.

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Adhesive Joining of Zerodur–CFRP–Zerodur Sandwich Structures for Aerospace Applications

Cited by 13 publications

References 10 publications

Thermal Stability Design of Asymmetric Support Structure for an Off-Axis Space Camera

Thermal Stability Design of Asymmetric Support Structure for an Off-Axis Space Camera

Manufacturing and Characterization of Highly Environmentally Friendly Sandwich Composites from Polylactide Cores and Flax-Polylactide Faces

The Influence of Moisture Absorption‐Drying of Composite Materials on the Bonding Performance of the Joints

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