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This paper describes a case study of an aircraft auxiliary power unit (APU) considered as controlled object. Considering the specific case of a TG-16M power unit (which is an embedded system: a gas turbine turboshaft and an electrical 28 V DC generator), one has established the mathematical model of this system, based on its non-linear motion equations; operating with the finite difference method, one has obtained the linear and adimensional form of the mathematical model. Equations’ co-efficient were experimentally established and/or calculated, during the ground lab tests of a TG-16M at the Aerospace Engineering Laboratory, University of Craiova. Based on the system’s mathematical model, one has also performed some studies concerning its stability and quality, using Matlab Simulink simulations.

TURBOSHAFT-TYPE APU FOR AIRCRAFT AS CONTROLLED OBJECT