Annotation: These days when creating any rocket space complex, it is important to ensure its advancement and competitive ability. To create such complex, the technical systems it consists of must be implemented with minimal economic and energy costs. Rocket and space complexes feature the thermostatting system, which ensures the required humidity and temperature conditions in the integrated launch vehicles throughout all the phases of their pre-launch processing. Development of the competitive rocket and space complex also requires the new approach in the development of the thermostatting system. One of the main tasks is to create a system that can be mass-produced and used as part of any rocket and space complex. Solving this problem will significantly reduce the cost of creating and operating the thermostatting systems and the whole rocket and space complex. One of the ways to solve this task is to create a general-purpose thermostatting system. The modular principle for such thermostatting system would be optimal, which means making up a system from separate modules. It simplifies the all-round installation of various system options and simplifies its setup and operation. The paper demonstrates the possibility and prospects of creating modular thermostatting systems, which enable air supply with the required parameters to different consumers. Characteristics and design of the general-purpose thermostatting module are specified, which can be used as the main component without changing anything in the composition of stationary and mobile thermostatting systems.

Annotation: The paper describes development of the devices for the nuclear quadrupole resonance thermometry at Yuzhnoye SDO and other Ukraine’s enterprises and considers capabilities of the enterprises to manufacture such devices. Also given is refined analytical dependence for temperature calculation using the frequency of the nuclear quadrupole resonance in Bertholette salt within the ±40°C temperature range.

Annotation: Considered is the application of the thermoelectric cooling modules to enhance the operating reliability of the spacecraft’s temperature control system in the severe climatic conditions, schematic diagram of the thermoelectric cooling system is given.