Annotation: The information is presented on the development of nuclear quadrupole resonace thermometry instruments at Yuzhnoye SDO and other Ukrainian companies. The problems are analyzed arising at the creation of standard wide-band nuclear quadrupole resonance temperature meters, the ways to overcome them, and the possibilities of improving due to the use of modern integrated electronics. It is shown that the methods of building the instruments based on nuclear quadrupole resonance proposed and implemented in Ukraine are not inferior to the foreign ones.

Annotation: The paper shows the peculiarities of modeling the vacuum conditions to simulate space environment when conducting various test types. Based on generalized experience, the practical criteria are recommended with consideration for accompanying physical phenomina.

Annotation: A developed, patented and proven method of producing supercooled cryogenic medium, required for testing for functional demonstration of space rocket automatic units and systems, is described herein.

Annotation: The paper presents the generalized experience of designing and development testing of the pneumatic system for nose aerodynamic fairing halves jettisoning. The algorithm of its parameters calculation is given. The satisfactory convergence of the pneumatic system parameters calculation results with the experimental data from the ground and flight tests is shown.

Annotation: The paper describes the experiments of cryogenic engine unit circulatory cooling system, considers the developed technique of circulation parameters evaluation and gives the comparison of calculated and experimental data on this system.

Annotation: The paper presents the results of comparative investigation into characteristics of methane, kerosene and hydrogen in pair with oxygen. The peculiarities of each of these components are shown. The optimal parameters are considered of pneumohydraulic supply system, including the designs of tanks, pressurization system and engine supply lines cooling system.

Annotation: The paper presents a complex of analytical calculation measures that allow increasing tanks useful volume and ensure engines’ additional operational lifetime by the example of a launch vehicle, one of Yuzhnoye SDO developments. The calculated-experimental confirmation is set forth of the operability of pneumohydraulic supply system in the changed conditions that ensure considerable increase of launch vehicle power and mass characteristics.

Annotation: Long-term experience in development, development testing and use of generating systems of fuel tanks pressurization for rockets powered by nitrogen tetroxide and unsymmetrical dimethylhydrazine is summarized. Replacement of gas bottle pressurization systems with generating ones on such launch vehicles as 15A14, 15A15, 11K68 (8K67), 15A18M substantially simplified operation, reduced the pneumohydraulic feed system mass at least twice and its cost – by five times. Typical stages of development and introduction of the pressurization generating systems are shown: development of generators, their development testing, study of the composition and parameters of gas. The important steps were the development of methodology for pressurization system parameters calculation, which enabled achievement of the substantial improvements of their characteristics, appearance of the high-performance hightemperature (up to ~ 1000o C) unsymmetrical dimethylhydrazine tank pressurization system, study of the degree of impact of each of the pressurization system parameters on the tank pressure. Accounting of the correlation between the flow rate and the generator gas temperature improved the output performance, as well as simplified and reduced the amount of development testing of the pressurization system. Important role of the gas sprayer design in pressurization system parametric configuration is described, and the advanced versions are shown taking into account g-loads, changes in temperature, pressure and propellant level inside the tank. Significant phase in the development of the generating pressurization system was the effective use of the high-temperature pressurization of the fuel tank with submerged propulsion system. Besides for the first time the effect of mechanical temperature destratification of the propellant in the tanks was observed, which occurs during the propulsion systems shutdown. Due to this effect, the Dnepr LV payload capability enhanced. Successful engineering solutions in the design of the pressurization system were defended by ~80 copyright certificates and patents of invention, ~40 of which were successfully implemented.