Thermal Modelling and Simulation of a Pico-Satellite Using Finite Element Method

‘Swayam’ is a 1U, LEO, Pico-satellite. The temperature of the satellite depends upon various factors and varies accordingly in its orbi. It experiences extreme temperatures as well as rapid temperature variations. These conditions may lead to thermal-stresses or may damage electronic components. Hence, these space conditions should be modelled and simulated, to be able to design insulation techniques. Thermal expansion of the structure during launch needs to be calculated to ensure a smooth ejection. This is done by mapping the steady-state thermal results to a structural model. SIEMENS NX 8.0 is used for steady-state analysis of the satellite during the launch and transient analysis for orbital conditions.

The CAD model created in Pro Engineer wildfire was first simplified and idealized (midsurfacing). FEM model was generated considering parameters: Geometry of parts, importance in thermal analysis and thermal behavior. Boundary conditions: Orbital heat load, internal generated heat, Radiation, Thermal couplings, Fixed constraints were applied to the FEM model and solved using the solver: NX SPACE SYSTEMS THERMAL. The transient analysis was performed for cases of different orbits and different insulation combinations to achieve the required results.

Keywords: modelling, FEM, mapping, transient analysis, simulation, SPACE SYSTEMS THERMAL