Thermo-mechanical design of honeycomb panel with fully-potted inserts used for spacecraft design

Boudjemai, A.; Bouanane, M.H.; Mankour, Abdeljelil; Salem, H.; Hocine, R.; Amri, R.

doi:10.1109/rast.2013.6581238

Cited by 6 publications

(3 citation statements)

References 26 publications

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“…More in detail and by considering the mechanical loads, the radiator is supposed to carry the entire weight of Space Nuclear Power System, which it is cooling. 28 Usually, the devices which are to be cooled are connected by pots and inserts inside the panels. However, in order to avoid many assumptions and computational complications, the load is uniformly distributed over the surface.…”

Section: Thermomechanical Topology Optimization: Validation On a Realmentioning

confidence: 99%

A new methodology for thermostructural topology optimization: Analytical definition and validation

Caivano

Tridello

Codegone

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part L:

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In the last few years, the rapid diffusion of components produced through additive manufacturing processes has boosted the research on design methodologies based on topology optimization algorithms. Structural topology optimization is largely employed since it permits to minimize the component weight and maximize its stiffness and, accordingly, optimize its resistance under structural loads. On the other hand, thermal topology optimization has been less investigated, even if in many applications, such as turbine blades, engines, heat exchangers, thermal loads have a crucial impact. Currently, structural and thermal optimizations are mainly considered separately, despite the fact that they are both present and coupled in components in service condition. In the present paper, a novel methodology capable of defining the optimized structure under simultaneous thermomechanical constraints is proposed. The mathematical formulation behind the optimization algorithm is reported. The proposed methodology is finally validated on literature benchmarks and on a real component, confirming that it permits to define the topology, which presents the maximized thermal and mechanical performance.

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Section: Thermomechanical Topology Optimization: Validation On a Realmentioning

confidence: 99%

A new methodology for thermostructural topology optimization: Analytical definition and validation

Caivano

Tridello

Codegone

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part L:

View full text Add to dashboard Cite

show abstract

“…In [14] a thermal effect of the inserts in the honeycomb core was demonstrated. It was concluded that any electronic equipment (including batteries) that might be attached to the honeycomb would cause dissipation of possibly excessive heat through the inserts causing additional thermal loading within the panel.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation of the thermoelastic performance of an aerospace aluminium honeycomb composite panel

Ganilova

Cartmell

Kiley

2021

Composite Structures

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Aluminium composite sandwich panels are widely used to enhance the design of structures subjected to dynamic mechanical loading in thermally harsh environments. Spacecraft structures fall into this category because typical environmental conditions include combined and variable mechanical and thermal loading. Usually mechanical loadings arise as a consequence of localised structural dynamics and the thermal loadings are attributable principally to the effects of solar irradiation and eclipse during the vehicle's orbit. Together these have the potential to influence satellite de-point in particular. Therefore, building a combined physics model which is representative of the thermal and mechanical loadings has emerged as an interesting and useful aim, which can be thought of as defining an important thermoelastic deformation problem in this application. The performance of such a structure loaded in this way could obviously be considered in the context of separate thermodynamic and mechanical interpretations. However, multiphysics modelling is currently in hand based on the premise that the pseudo-static thermal loadings and the mechanical loadings encountered in various operating environments are not necessarily decoupled processes, and this will be the subject of a separate publication. The analytical modelling fully represents both static and dynamic mechanical and thermal loading conditions.It has become clear that predictive accuracy may be compromised by separation of the phenomena, at least without the introduction of a judicious correction factor. Therefore, in this paper an attempt has been made to identify experimentally the presence, and then to understand the attendant effects, of the coupling between the thermal and mechanical effects in an aluminium composite sandwich panel under test. The authors have performed a series of experiments on an aluminium honeycomb composite panel under three-point mechanical bending and controlled environmental temperature. The panel was subjected to a controllable, centrally located, very slowly increasing mechanical load in conjunction with thermal loading in the form of precisely controlled lowered and elevated environmental temperature. The tests were performed on a computer controlled Instron 8801 100 kN test machine for which the rate of change of applied mechanical load was automatically linked through feedback control to the rate of change of displacement. This ensured that the exact load-deflection profile can be obtained, even for materials with highly nonlinear characteristics.Both forms of loading have been shown to influence the displacement of the panel in significant ways, thereby confirming the importance of a combined physics approach.

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“…Honeycomb sandwich structures have been fabricated to fulfill the needs of low weight high specific strength materials for space applications. Honeycomb sandwich structures have been used in space for past several years due to their unique and exceptional characteristics like high strength to weight ratio, high stiffness to weight ratio and energy-absorbing capabilities [2][3][4][5][6]. For instance, Surrey satellite technology (SSTL) has used the sandwich structure in modern spacecrafts like NigeriaSat-2 and geostationary minisatellite platform-transfer (GMP-T) [1].…”

Section: Introductionmentioning

confidence: 99%

Mechanical and electrical properties of hybrid honeycomb sandwich structure for spacecraft structural applications

Shifa

Tariq

Chandio

2019

Jnl of Sandwich Structures & Materials

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Multiphase composite sheets containing carbon fiber and functionalized multiwall carbon nanotubes in epoxy matrix were manufactured through compression molding technique. The loading of f-MWCNTs was varied (0.0, 0.1, 0.25 and 0.5 wt.% of epoxy matrix), while the quantity of carbon fiber was kept constant, i.e. ∼60 wt.% of the final composite in all samples. Prepared multiphase composite sheets were subjected to flexural test and the sheet offering maximum flexural strength was selected for subsequent hybrid sandwich structure manufacturing. Hybrid sandwich structure was manufactured via vacuum bagging process by bonding composite face sheet to the aluminum honeycomb core through an adhesive. Mechanical performance of hybrid sandwich structure was evaluated by performing flexural and quasi-static indentation tests, while electrical performance of hybrid sandwich structure was investigated by performing electromagnetic interference shielding effective and electrostatic dissipation tests. Optical and scanning electron microscopy was carried out for microstructural investigations. Fractography was also performed on composite face sheet after flexural test to study the underlying high flexural strength mechanism. Neat sandwich structure without functionalized multiwall carbon nanotubes addition was also manufactured and tested for comparison. Results show that hybrid sandwich structure outperformed the neat sandwich structure in all tests.

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Thermo-mechanical design of honeycomb panel with fully-potted inserts used for spacecraft design

Cited by 6 publications

References 26 publications

A new methodology for thermostructural topology optimization: Analytical definition and validation

A new methodology for thermostructural topology optimization: Analytical definition and validation

Experimental investigation of the thermoelastic performance of an aerospace aluminium honeycomb composite panel

Mechanical and electrical properties of hybrid honeycomb sandwich structure for spacecraft structural applications

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