Computation study of the low-thrust rocket engine chamber thermal state operating on the oxygen + methane gaseous propellant components with the structural elements regenerative external cooling by an oxidizer
Authors: Novikov A.V., Andreev E.A., Bardakova E.I.
Published in issue: #11(155)/2024
DOI: 10.18698/2308-6033-2024-11-2402
Category: Aviation and Rocket-Space Engineering | Chapter: Thermal, Electric Jet Engines, and Power Plants of Aircrafts