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High performance high bandwidth control of power electronic converters, inverters, and motor drives has become feasible over the past decade. These devices behave as constant power loads over large bandwidths when they are tightly regulated. However, constant power loads have a severe side affect known as negative impedance instability. In order to mitigate the problem of negative impedance instability a new nonlinear system stabilizing controller has been developed. The details of how this controller works along with its implementation is discussed and demonstrated in hardware.

The purpose of this paper is to review the modeling techniques, stability analysis, and design criteria relevant to the design of power electronics based systems (PEBS) such as dc power systems in aircraft. Throughout this discussion these techniques, analysis, and criteria are applied to a laboratory test system in order to illustrate the use and validity of the techniques discussed.

The steady-state and dynamic performance of a candidate aircraft power distribution system is considered. The system features distribution of both single phase 20-kHz and three-phase 400-Hz power. It is shown that unlike some other recent 20-kHz systems, the power quality of the 20-kHz bus is not a concern due to the use of a synchronous bi-directional rectifier (SBR) as the primary interface to the 20-kHz bus. In addition to showing that the system behaves adequately in the steady-state, the dynamic performance of the system is considered during step changes in load, bolted faults, and sudden variations in jet engine speed.