Thermal processes modeling in the aircraft hydraulic systems

Аuthors

Volkov A. , Dolgushev V. G.^*, Pugachev Y. N., Chulkov M.

Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia

*e-mail: gidropulsar@yandex.ru

Abstract

Aircraft hydraulic systems are characterized by the change of the working fluid consumption over wide range during the flight. The most long-continued mode is the low consumption mode, at which volumetric and mechanical loses in the hydro-system power unit are great, and there is a possible risk of the pump overheating. Thus, the requirement to the power unit to generate only the power necessary for surmounting actual load affecting the hydraulic drive, originates. The presented article describes a mathematical model of the hydro-system and power unit with the dependence of the pump-in pressure feedback on the load of the worst loaded hydraulic derive. The presented equations allow determining hydrodynamic parameters of the hydraulic drive with power unit, which pump-in pressure is a function of the pressure drop in the hydraulic drive cavities. The article demonstrates that such structure of the power unit allows reducing heat emission in the hydraulic system by 30–40 %, and reduce maximum temperature of the working fluid and increase its durability.

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