The purpose of the research is to perform a comparative analysis of compressed air preparation systems on the basis of moisture content. The article discusses conventional and perspective methods for drying compressed air using condensation, adsorption and membrane technologies. The article considers a temperature control system with the required dew point of minus 25°С at the exit under standard conditions, which corresponds to the dew point temperature plus 3 °С at a pressure of 1.0 MPa, or class 4 according to GOST R ISO 8573-1–2016. The main advantages of using advanced technological drying system designs are described, including the design of a modern drier with a rotary adsorber that can reduce the dew point temperature of compressed air to minus 25…30 °С at 1.0 MPa pressure without any losses on the adsorbent regeneration. This research is the first to analyze the applicability of modern adsorption and membrane modules to the launch complex functions. All the air drying designs were considered in this paper in relation to air temperature control systems based on air refrigerators using the I-d hygrometric chart for variable pressures.

The purpose of the study was to conduct a comparative analysis of domestic selective property polymer membranes used in gas separation problems and to estimate the prospects of using appropriate membrane technologies for air drying in launch complex thermostatic control systems. The study analyzes models of membrane dryers through the example of a temperature control system with the required outlet dew point minus 25 °C under normal conditions. The existing methods of membrane drying with the corresponding designs of membrane modules and the most promising models for use at launch complexes are described. The scientific novelty of the work lies in the development of schematic diagrams of thermostatic control systems using cartridges with hollow fiber membranes, structurally adapted to solve the tasks at the launch rocket complex.

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.