Уточнение метода инвариантов для расчёта динамических параметров газа в трубопроводах пневмосистемы запуска ракетного двигателя

Abstract

The analysis of heat-exchange processes between gas and walls of pipelines, which supply gas to the turbo pump unit, as well as control tubes of valves in the pneumatic starting system of a multiple ignition rocket engine was made. It was shown that the gas flow in the pipelines can be considered as adiabatic flow, while in the control tubes – as isothermal one. There was made an improvement of the Riemann invariants method, which allowed taking into account nonisentropic flow in the exhaust pipeline and pipeline flow resistance.