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

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