HERMES CubeSat Payload Thermal Balance Test and Comparison with Finite Volume Thermal Model

Scientific payloads onboard CubeSats usually have complex geometries and occasionally narrower allowed temperature ranges with respect to the rest of spacecraft. In these cases, capability correctly predict thermal behaviour payload once in orbit is mandatory. To achieve this ability, a balance test required identify model payload. The consists application different external boundary conditions together addition heat dissipation simulate load produced by active electronics during operation. Those experimental data are fundamental validate numerical make its predictions reliable. This paper presents configuration procedures performed on Demonstration Model be embarked each satellite HERMES constellation. compared results finite volume payload, proving method reliable for space analyses. obtained show jumps caused applied components. A weak correlation between interface internal equipment has been observed, thus that almost decoupled from Service Module variations. Based outcomes, some modifications design implemented, aim lower operative critical, temperature-sensitive equipment.