Mathematical model of an estimation of mass characteristics oxygen-hydrogen expander cycle liquid rocket engine on its basic design parameters
Aerospace propulsion engineering
Аuthors
*,Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia
*e-mail: borovik.igor@mai.ru
Abstract
In the article the mathematical model of an estimation of mass characteristics oxygen-hydrogen expander cycle liquid rocket engine on its basic design parameters is considered. Results of the research a degree of influence of each of the basic design parameters (mass flow rate, oxidizer to fuel ratio, nozzle expansion ratio and chamber pressure) on weight characteristics of oxygen-hydrogen expander cycle liquid rocket engine made by means of developed model is shown. Operational effectiveness extendible nozzle cone for increase in specific impulse expander cycle liquid rocket engine is shown. The analysis of data received on model (on an example of engine RD-0146) has allowed to formulate recommendations on further perfection expander cycle liquid rocket engine.Keywords:
liquid rocket engine, expander cycle, upper stage, orbital transfer vehicle, specific impulse, combustor chamber, turbopump ,extendible nozzle, basic design parametersDownload