Membrane and vapor compression technologies use in the two-stage dehumidifying scheme of the rocket launch complex thermal regulation system

Abstract

Objective of this study is to perform analysis aimed at assessing the degree of reduction in energy consumption of the launch complex temperature regime air support system by introducing a two-stage dehumidifying unit that includes a vapor-compression refrigeration machine (VCRM) and membrane dryers in the scheme. As part of the study, a thermal regulation system with the required outlet dew point of –25 °C under normal conditions was considered, which was designed to ensure operation with a promising heavy-class launch vehicle. The paper describes the existing methods of membrane dehumidifying along with corresponding designs of the membrane modules, as well as the most promising models for use at the launch complexes. Scientific novelty of this work lies in developing schematic diagrams of the thermal regulation systems using both the principles of VCRM and hollow fiber membranes.