Modeling the working process in the chamber and calculating the characteristics of a low-thrust rocket engine working on the oxygen-methane gaseous propellant components with the 50 N thrust
Published: 23.06.2025
Authors: Vorozheeva O.A., Koptev I.I., Yagodnikov D.A.
Published in issue: #6(162)/2025
Category: Aviation and Rocket-Space Engineering | Chapter: Thermal, Electric Jet Engines, and Power Plants of Aircrafts
The paper considers selection of an optimal scheme for mixing the components and determines the internal ballistic characteristics of a low-thrust rocket engine (LTRE) operating on gaseous oxygen-methane fuel. The mixing and combustion processes of gaseous oxygen-methane propellant was simulated in a stationary setting in the LTRE chamber for various mixing schemes making it possible to determine an optimal scheme for mixing the fuel components. Selection of the optimal mixing scheme was based on the obtained temperature distribution diagrams and the LTRE specific impulse values, taking into account the high-temperature flow effect on the chamber wall. To simulate combustion, the FLAMELET thin flame front model was applied together with the GRI Mech 3.0.50 kinetic combustion mechanism, which included 50 components participating in 309 elementary reactions.
EDN HOFFCE
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