Formalization of criteria for multi-parametric selection of turbofan engine pairs for powerplants of twin-engine aircraft and their automatic control structure to reduce thrust asymmetry

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Resumo

The issues related to the study of the possibilities of automatic thrust control of turbojet twin-circuit engines by the power plant of a twin-engine aircraft in flight are considered. The purpose of the study is to formalize criteria for the multiparametric selection of turbofan pairs for power plants of twin–engine aircraft and to develop the structure of the automatic control system for such installations to reduce the asymmetry of thrust of their engines in flight. During the research, methods of software modeling of algorithms for automatic control of multi-thrust turbojet engines of twin-engine power plants were used. As a result of the study, criteria for the multiparametric selection of pairs of such engines for twin-engine power plants have been formalized for three thrust parameters of turbojet twin-circuit engines of the same series at once and the structure of the automatic control system of the power plant of a twin-engine aircraft to eliminate the asymmetry of thrust of its engines in flight was developed.

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Sobre autores

A. Burova

Moscow Aviation Institute (National Research University)

Autor responsável pela correspondência
Email: frambe@mail.ru
Rússia, Moscow

N. Kochetkov

Moscow Aviation Institute (National Research University)

Email: kolabuy@gmail.com
Rússia, Moscow

V. Nesterov

Moscow Aviation Institute (National Research University)

Email: frambe@mail.ru
Rússia, Moscow

K. Sypalo

Central Aerohydrodynamic Institute

Email: frambe@mail.ru
Rússia, Zhukovsky

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2. Fig. 1. Fuel consumption with decreasing thrust asymmetry of the turbofan power plant of a twin-engine aircraft depending on the level of their initial thrust difference.

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3. Fig. 2. Structure of the ACS of the power plant of a twin-engine aircraft.

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4. Fig. 3. Functional diagram of the algorithm of the ACS of the power plant of a twin-engine aircraft.

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5. Fig. 4. Change in the value of the logical signal I4 from the control unit of the left turbofan engine with the initial thrust difference of their turbofan engines ∆R = RRE – RLE.

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6. Fig. 5. Change in the value of the logical signal I4 from the control unit of the right turbofan engine with the initial thrust difference of their turbofan engines ∆R = RLE – RRE.

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7. Fig. 6. Time graphs of the change in thrust of the turbofan power plant of a twin-engine aircraft with their initial thrust difference ∆R = RLE – RRE

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