Propulsion and Power Plants
Аuthors
Kurgan State University, 63/4, Sovetskaya str., Kurgan, 640020, Russia
e-mail: ip.popow@yandex.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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