Computational study of the various mixture formation schemes and determination of the main factors influencing the working process parameters of the low-thrust rocket engine combustion chamber
Authors: Novikov A.V., Andreev E.A., Bardakova E.I.
Published in issue: #12(144)/2023
DOI: 10.18698/2308-6033-2023-12-2325
Category: Aviation and Rocket-Space Engineering | Chapter: Thermal, Electric Jet Engines, and Power Plants of Aircrafts
Due to a significant increase in the number of the space systems launches around the world, tightening of requirements to ecological safety in the space objects operation is observed. A promising approach to design and development of a new generation of the rocket and space systems including the low-thrust rocket engines (LTRE) lies in introducing the methane-based propellant paired with oxygen. When developing the low-thrust rocket engines on the oxygen-methane fuel, the adopted mixture formation scheme provides a decisive influence on the future engine thrust and economic characteristics. With a mathematical experiment, this allows, as a result of selecting an optimal scheme, obtaining the к chamber coefficient maximum values, which for the isobaric combustion chamber could be equal to the consumption system coefficient. This approach leads to a significant reduction in the expensive bench tests cost. The article presents calculation results for various mixture formation schemes. They could assist in estimating the influence of various factors on the к complex consumption coefficient within the chosen scheme. Analysis of the results obtained makes it possible to select the most appropriate mixture formation scheme and develop preliminary recommendations in designing a combustion chamber for the low-thrust rocket engine.
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