The optimal aircraft gas turbine engine control in low gas mode in the conditions of external additive noise

Currently, mathematical and computer modeling are the basis for the design of complex technical systems, which include aircraft structures, of course. Direct tasks for calculating the strength, flight, dynamic and other aircraft structures characteristics are widely described in the literature, methods for their solution are known. In aircraft engineering the inverse problem solution is primarily connected with strength characteristic calculation of aircraft structures and heat transfer problems. The inverse problems also include aircraft engines modes controlling tasks. Due to the fuel combustion disturbance, the engine is exposed to random disturbances in the form of Gaussian white noises in real live operation. At the bench test stage, not all system feedbacks can be accurately known. Thus, direct problems describing the engine operation are represented as stochastic differential equations systems with unknown parameters and additive white noises in the right-hand side. For such mathematical models, the inverse problem solution with respect to control parameters is made difficult by the need to estimate unknown parameters that can be realized in real conditions by measuring the phase characteristics of the system