Enrico Vialardi

EMC Modeling of an Industrial Variable Speed Drive With an Adapted PEEC Method

This paper presents an adapted partial element equivalent circuit (PEEC)-based methodology applied to the modeling of interconnections of power electronics devices. Although this method is already well known, the originality of this work is its use to model a device presenting an industrial complexity. To make possible this modeling, two adapted integral methods, based on two different meshings, are presented. They are dedicated respectively to the computation of parasitic inductances and capacitances and lead to an equivalent circuit of the system. From a time-domain simulation of this circuit, current and voltage sources can be extracted and used to compute the radiated near magnetic field. This approach has been applied to model a real industrial static converter via system couplings, a variable speed drive. Good agreements have been obtained between simulated and measured results on conducted and emitted electromagnetic analysis.

MoM and PEEC Method to Reach a Complete Equivalent Circuit of a Static Converter

This paper presents an application of the Method of Moments (MoM), to compute parasitic capacitances of a power electronics layout. By coupling these capacitances to a resistive and inductive equivalent circuit obtained thanks to Partial Element Equivalent Circuit (PEEC) method, a complete electrical equivalent circuit made of lumped elements is obtained. Its simulation by means of a SPICE-like tool enables the evaluation of the EMC efficiency of a power electronics structure. This method is applied to a boost converter and the results obtained by numerical simulation (MoM and finite element method - FEM) are compared to measurements. Finally, radiated EMC investigations are presented thanks to circuit simulation and measurements.

Study of Lightning Effects on Aircraft With Predominately Composite Structures

Nowadays, with the trends of having more electrical aircrafts with predominately composite structures, designers must be sure that electrical equipment inside is well-protected in case of lightning. It is for that purpose that a modeling approach is detailed in order to predict the impact of lightning on electrical equipment inside aircraft. An aircraft-like structure is defined with several electrical configurations. And direct or induced current inside different cables is evaluated. The use of the partial element equivalent circuit method is explained. Measurements on the experimental setup have successfully confirmed the evaluated current.

Modeling and simulating the lightning phenomenon: Aeronautic materials comparison in conducted and radiated modes

The composite materials are becoming more and more used in aircrafts design. Their light weight and their excellent robustness make them attractive compared to metallic materials which have been widely employed till now (aluminum for instance). However, an important drawback is their electric conductivity which is quite weak compared to the metallic one. Thus, in case of lightning phenomenon, the outside circulating current is not evacuated in the same way as in aluminum structures with possible damages to the on-board devices. The objective of this article is to compare the performances of two cylindrical samples made of composite and aluminum respectively. The PEEC (Partial Element Equivalent Circuit) method is applied to model their electrical behavior in terms of an equivalent circuit, which is then supplied with the standardized lightning current in order to evaluate its impact upon the structure. The conducted and radiated EMC modes are both investigated by means of two different test-cases. Conclusions concerning the level of currents, frequency range involved and EMC performance are then drawn.

2D modeling of bulk current injection probe and validation with measurements

Electronic Equipment designed to be loaded onto an aircraft must be certified in accordance with established EMC standards. This paper is focused on section 20 of RTCA-DO160 which refers to conducted susceptibility in aeronautics. Since equipment can succeed or not in qualification test, aim is to be able to predict these levels of disturbance for limiting costs and time design. Moreover, aircraft manufacturers are mostly looking for precise answers about the sensitivity and reproducibility of these tests. In this sense, a 2D model of probe coupling to wires is developed in this work.