Stability and Control for Buck-Boost Converter for Aeronautic Power Management

The need for greener and cleaner aviation has accelerated the transition towards more electric systems on the More Electric Aircraft. One of the key challenges related to the increasing number of electrical devices onboard is the control of bidirectional power converters. In this work, stability analysis and control of a buck-boost converter for aeronautic applications are presented. Firstly, stability of the buck-boost converter in the Lyapunov sense is proven by resorting to input-to-state stability notions. Then, a novel control design based on second order sliding mode control and uniting control, aimed at overcoming the difficulties generated by the nonlinear input gain function of the system not being sign definite, is presented. Extensive and detailed simulations, designed to emulate one of the possible energy management policies onboard a More Electric Aircraft, confirm the correctness of the theoretical analysis both in buck and in boost mode.

Automated summary

The need for greener and cleaner aviation has led to the adoption of more electric systems on aircraft. Controlling bidirectional power converters is a major challenge in these systems. This study presents stability analysis and control for a buck-boost converter used in aeronautic applications. The stability of the converter is proven using Lyapunov's stability theorem, and a novel control design based on second order sliding mode control and uniting control is proposed to overcome the difficulties caused by the nonlinear input gain function.