Static Performance of Hot Bonded and Cold Bonded Inserts in Honeycomb Panels

Bianchi, Gabriel; Aglietti, Guglielmo S.; Richardson, Guy

doi:10.1177/1099636209359840

Cited by 21 publications

(43 citation statements)

References 11 publications

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“…. Test parameters such as the insert diameter, insert depth, core thickness and core density and their effect on the pull-out resistance honeycomb-type sandwich mechanical joints [36][37][38][39][40][41][42][43][44][45][46][47][48][49][50][51]. These parameters are important to be followed in order to optimise the joint and to minimise failure caused by incorrect joint parameters.…”

Section: Pull-out Resistance Test Methods On Sandwich Materialsmentioning

confidence: 99%

See 1 more Smart Citation

Pull-out resistance study of mechanical joints on sandwich materials: a review

Triadi

Wirawan

Prajetelistia

et al. 2022

Plastics, Rubber and Composites

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In applications such light train application, sandwich materials require mechanical joints. One major load produced at the mechanical joining is the pull-out load. The scope of this literature review includes pull-out test results, failure mode during the pull-out test, failure load parameters, and an analytical method to determine the maximum pull-out load. The pullout resistance of the mechanical joint on sandwich material is determined by the failure load and the maximum load. The failure modes on sandwich material include core buckling, shear cracking, tensile rupture and delamination. The failure load of mechanical joints on the sandwich material will increase as insert depth, insert diameter, core thickness and core density increase. Meanwhile, two analytical methods (Aerospace Engineering and Zenkert Methods) are studied, and it is found that the Aerospace Engineering is more accurate. The multiplier for the maximum load value has been found to determine the failure load.

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Section: Pull-out Resistance Test Methods On Sandwich Materialsmentioning

confidence: 99%

“…Failure load equations[36][37][38][40][41][42]50,51].Material EquationsHoneycomb sandwich-through-the-thickness insert FL = 0.29 × ML Honeycomb sandwich-fully potted insert FL = 0.86 × ML Honeycomb sandwich-partially potted insert FL = 0.99 × ML FL, Failure load (N); ML, Maximum load (N).…”

mentioning

confidence: 99%

Pull-out resistance study of mechanical joints on sandwich materials: a review

Triadi

Wirawan

Prajetelistia

et al. 2022

Plastics, Rubber and Composites

View full text Add to dashboard Cite

show abstract

“…In order to determine the reason behind the performance difference observed between the two insert systems a final element study was carried out [21]. The results from this study showed that the unexpectedly lower performance of the hot bonded inserts can be attributed to the stiffness of the filler material.…”

Section: Insert Pull-out Testsmentioning

confidence: 98%

Development of efficient and cost-effective spacecraft structures based on honeycomb panel assemblies

Bianchi

Aglietti

Richardson

2010

2010 IEEE Aerospace Conference

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Due to their high strength to weight ratio and stiffness to weight ratio the use of honeycomb panels is particularly attractive in spacecraft structures. Honeycomb panels are often used in secondary satellite structures such as equipment platforms and solar arrays, but they can also be used as part of the primary structure of a satellite. Indeed honeycomb panel assemblies can be, and are, used to produce efficient and cost-effective primary structures. These types of structures have been used for some time for numerous satellites; however, their development still poses some challenges ranging from the structural performance of the panels themselves to the problem of connecting them to other panels or structural elements. These challenges are faced each time a new satellite is being developed adding cost to the design process. Furthermore, often due to strict timescales in the development process, some of the uncertainties which naturally arise from these challenges cannot always be completely addressed. To compensate for this, conservative design approaches often need to be taken with the ultimate effect of lowering the efficiency of the structure's final design. To meet these challenges and provide a better knowledge base for future satellite development projects a number of research activities have been, and are still, under way at the University of Southampton. The aim of this paper is to describe these research activities and present the key results. ©2010 IEEE

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“…There are a wide variety of different insert elements due to different and changing requirements and the absence of a uniform design approach. To give an example, in the manufacturing process, a distinction is made whether the insert is bonded during the production of the sandwich panel (hot bonded) or is installed after the production of the sandwich panel (cold bonded) (Bianchi et al 2010;Lim & Lee 2011). Other distinguishing criteria are the orientation of the connection, the decisive load case and the installation depth.…”

Section: State Of the Artmentioning

confidence: 99%

Optimization of load introduction points in sandwich structures with additively manufactured cores

Schwenke

Krause

2020

Des. Sci.

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This paper presents how numerical optimization methods, like topology optimization, and new design possibilities through additive manufacturing (AM) can be used for structural improvements of the load introduction points in sandwich structures. A new design approach is presented, which allows a direct load-path optimized integration of the load introduction point into the sandwich core. The corresponding methodical procedure is shown and the application is demonstrated exemplarily for a sandwich structure with a honeycomb core. The advantages for design science are that the new design possibilities of AM can be considered and used when designing the load introduction points. Thus, the additional reinforcements of the sandwich structures to absorb locally introduced forces in the lightweight structure can be minimized. This enables a meaningful technical comparison and it can be decided in the future whether such a design can be used for sandwich structures under economic aspects. In addition, the influence of the initial and boundary conditions on the design is presented and discussed in this paper. The challenges of optimizing multiple load introduction points simultaneously as well as the special aspects to be considered when transferring the design approach to larger sandwich structures are also highlighted.

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Static Performance of Hot Bonded and Cold Bonded Inserts in Honeycomb Panels

Cited by 21 publications

References 11 publications

Pull-out resistance study of mechanical joints on sandwich materials: a review

Pull-out resistance study of mechanical joints on sandwich materials: a review

Development of efficient and cost-effective spacecraft structures based on honeycomb panel assemblies

Optimization of load introduction points in sandwich structures with additively manufactured cores

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