Behavior of the Aviation Engine Control System During the Transition to the Lorenz Attractor

Authors S.S. Tovkach

National Aviation University, 1, Lubomyr Husar Ave., 03058 Kyiv, Ukraine

Issue Volume 13, Year 2021, Number 1
Dates Received 10 January 2021; revised manuscript received 15 February 2021; published online 25 February 2021
Citation S.S. Tovkach, J. Nano- Electron. Phys. 13 No 1, 01010 (2021)
PACS Number(s) 07.05.Tp
Keywords Lorenz attractor, Aviation engine, Electronic control system, Transition process, Distributed system, Differential equations, Mathematical modeling (7) .

The article considers the Lorentz attractor in aviation engine control systems (AECS) to obtain the necessary characteristics of the starting system and the laws of fuel supply, and to determine the emission characteristics. The defined behavior of the control system allows to optimize the control program of adjustable elements of the flowing part of the gas generator in transition modes of operation; to get a full picture of the starting characteristics of the developed engine, including reserves of gas-dynamic stability (GDS) in the starting modes; to establish the necessary programs for regulating the guide devices (GD), air bypass from the compressor; to select the required starter power, start-up cycle and fuel supply program in ground, alpine and flight conditions at the expected temperatures of air, fuel and oil in operation. Euler'sand Runge-Kutta methods, Lorentz attractor are considered as the main approaches to mathematical modeling of AECS. The script of the interface of the modeling program includes the possibility of two-level modeling of the flowing part with the properties of end-to-end automated calculation: input of initial data and calculation of thermodynamic parameters of the engine; design of the flowing part of the engine based on the node approach; strength design and mass analysis; export data to files for CAD systems for further processing and interpretation.

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