This paper aims to analyse the behaviour of a selected aluminium CubeSat frame subjected under static and vibrational loads using finite element analysis. Failures of CubeSats due to instability caused by vibration during launch can result in damage of the CubeSats and Launch Vehicle. Hence there is the need to analyse the max von-mises stress and strain of the CubeSat before production and launch to avoid these failures and losses. The CubeSat is modelled and analyzed using Solidworks 2014. Finally, the results obtained are an indication of whether or not the frame structure is able to safely withstand the worst-case scenario static loading and imposed failure modes. In a nutshell the CubeSat Frame structure is able to withstand the launch static and dynamic vibrations without failing. This preliminary finite element analysis has revealed a significant margin of safety and adequate survivability in terms of worst-case static loading and imposed failure modes.