Simulating the process of filling the fuel lines of the upper stages liquid rocket propulsion systems under flight conditions
Authors: Diesperov N.V., Polyanskiy A.R., Sapozhnikov V.B.
Published in issue: #10(154)/2024
DOI: 10.18698/2308-6033-2024-10-2394
Category: Aviation and Rocket-Space Engineering | Chapter: Thermal, Electric Jet Engines, and Power Plants of Aircrafts
The paper proposes a mathematical model to assess parameters of the fuel lines filling process in the upper stage liquid rocket propulsion systems after partial vacuumization under the flight conditions. This problem arises, in particular, in preparation to igniting the upper stage engine. The upper stage is initially positioned on the launch vehicle at the flight passive stage. The fuel line section before entering the engines is filled with the preservative gas. Before the upper stage separation from the launch vehicle, the preservation gas is removed in preparation for engine start. However, complete vacuum in the fuel line is not achieved, and the low pressure rarefied gas stays in the line. With the shut-off valve open at the line inlet and the spreading fuel component front, this gas is compressing. It results in a radical increase in pressure in the supply line, which theoretically could lead to its destruction. Therefore, assessing pressure pulsations in this process is an important engineering problem that should be solved at the early design stages.
EDN FRLIXS
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