Modelling of Launch Vehicle Radiated Emission at Payload Interface During Fairing Separation

This paper describes the development of a simulation model to estimate the ElectroMagnetic Compatibility between a launch vehicle and its payload. This was needed to estimate the E-field radiated towards a payload surface by the launcher antennas during the fairing separation transient. The model was developed in the ANSYS HFSS SBR+ simulation environment, and it included CADs of the structure, dynamics of fairing separation and measurements of the LV antenna radiation patterns. The resulting model allowed to simulate various instants of the separation sequence, showing an E-field increase with a peak at around 0.1 seconds after separation. Then, the E-field quickly decreased until, after about one second, the contribution of the fairing reflection became negligible.