A mathematical model of thermal state for low-thrust liquid rocket engines

Propulsion and Power Plants


Аuthors

Vorobiev A. G.

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

e-mail: formula1_av@mail.ru

Abstract

A mathematical model is suggested to describe a thermal state of low-thrust liquid rocket engines. Main attention is focused on such topics as physical meaning of model components, techniques used for analysis of engine properties, model capabilities to predict operational efficiency of combustion chamber in regard to its thermal mode, model capabilities to analyze engine efficiency for predefined propellant mixing scheme.

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