The purpose of the structural subsystem is to provide a simple study structure that will survive launch loads and provide a suitable environment for the operation of all subsystems throughout all phases of the mission life. The structure shall also provide easy access for integration and satellite check-out. Moreover the structural subsystem will carry, support, and mechanically align the satellite equipment.

Structural design shall aim for simple load paths, a maximization in the use of conventional materials, simplified interfaces and easy integration. Due to the size of the satellite and small expense budget, this was done with the philosophy of maximizing usable interior space, while minimizing the complexity and cost of the design.

To validate the selected structure and configuration baseline static and dynamic analyses were performed. Furthermore, the physical and inertial properties of the satellite were determined through the CAD model.

Sinusoidal, random vibration and shock tests at qualification level have been performed in August 2007. The Structural Model passed these various mechanical tests without problems.

SwissCube has a passive thermal management system, i.e. no active thermal components, such as heaters are implemented. Extenal panel temperature are expected to vary between -50°C and +60°C. Internal components are expected to see temperatures between -30°C and +40°C.

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