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

Abstract

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.

Impact resistance of composite circular corrugated core sandwich structures

“…[3][4][5] As a result, corrugated sandwich structures are widely used in fighter wings and tail sections of aircraft, wind turbines, ships, automobiles, buildings, and in other applications. [6][7][8][9][10][11][12][13][14][15] Therefore, research on the impact resistance of composite corrugated sandwich structures offers value and practical significance for important engineering applications.…”

Effect of Axial Deformation on Elastic Properties of Irregular Honeycomb Structure

“…Honeycomb structures have many excellent characteristics, such as a higher elastic modulus [1], higher shear modulus [2], and higher energy absorption [3][4][5][6]. Therefore, negative Poisson's ratio materials are widely used in aerospace [7,8], automobiles, ships [9,10], and other fields. Zhang et al [11] studied a hierarchical regular hexagonal honeycomb structure.…”

Design and Integrated Analysis of a Flexible Support Microstructure with a Honeycomb Sandwich for the Optical Window of a Hypersonic Remote Sensor

“…It has been widely used in main load-bearing structural parts such as wings, fuselage, and tail, but it is rarely used in flexible support structures. The semicircular ring-shaped honeycomb sandwich structure is a typical transverse-isotropic material, which has low in-plane rigidity, so that it can obtain greater elastic deformation, and also has good performance of vibration and noise reduction, heat insulation, and sound insulation [ 18 , 19 ].…”