The experience of domestic and world rocket manufacturing is considered with interesting from the point of view of the used engineering solutions. Positive and negative sides of the introduced solutions are shown.
 The basic perspective directions of their development are shown among variety of the considered PSs. To them concern: increase of specific function ability of a pressurant gas; improvement physical-chemical and thermal-mass processes, occurring in a tank; regulation and correlation relation of PS parameters; rational selection of a design of pressurization devices; feature of PS experimental development and modelling. In the whole, their use results to increase of LV energy characteristics.

The subject of research in this article is the process of detonation propagation in the chamber of a pulse detonation engine. Experimental research on detonation engines is a complex and expensive process that requires high-speed, high-precision equipment to obtain high-quality reliable results. Therefore, to conduct preliminary research, numerical experiment methods using mathematical simulation tools should be used. This work analyzes the possibility of applying known calculation models to study the detonation propagation process in the chamber of a pulse detonation engine. The task: to study the influence of the application of existing calculation models on the accuracy of numerical simulation of the detonation process; analyze the use of existing calculation models for the study of the detonation propagation process. The main method used in this work is the method of mathematical simulation using CFD technologies. The following results were obtained. The work considered the application of various turbulence models, chemical transition models, solvers and mesh sizes in modeling processes in the chamber of a pulse detonation engine. The application k-ε and k-ω turbulence models and their modifications are considered. The closest to the real result is obtained when applying k-ω model turbulence with SST modification. Generalized modification of this model averages the parameters on the front of the detonation wave, which leads to the destruction of the structure of the front. Taking into account the peculiarities of the processes occurring at the front of the detonation wave, the eddy-dissipation concept method will be better for modeling chemical transition, compared to the finite-rate method. Using the finite-rate method shows instantaneous combustion at the front of the detonation wave. This leads to a sharp increase in the parameters at the detonation front with its further separation from the main flow. To obtain a qualitatively reliable result of the parameters at the front of the detonation wave, cell dimensions of no more than 1/16 mm should be used. The application of the eddy-dissipation concept method with k-ω SST turbulence model allows obtaining the closest results to the experimental data. The deviation of pressure and velocity values obtained during modeling does not exceed 5% from their actual values. The temperature deviation does not exceed 10%. This is determined by the selected kinetic scheme of chemical transitions. All considered models and methods affect only the structure and development of the detonation wave front. There are no significant differences in the values of the parameters along the front (in the Taylor zone). Conclusion. The obtained results are of practical importance for the design and research of detonation engines. The use of the proposed calculation models will allow conducting numerical experiments for the pulse detonation engine chamber with sufficient accuracy, in comparison with experimental data.

Abstract The tensile test of steels St3 (GOST 380 − 94) and 40X (GOST 4543 − 2016) in an external constant magnetic field with an induction of 1,2 T was performed. Deformation energy absorption is a manifestation of the magnetoplastic effect. The similarity of the action of a magnetic field in tensile testing of samples and in the study of classical magnetic resonance is described. A new method for analyzing the magnetoplasticity of bulk samples by analogy with the construction of the energy absorption spectrum at magnetic resonance has been applied. The energy absorption spectrum is plotted in the coordinates of the metal flow stress – dislocation density. The characteristics of the spectrum line are determined: its depth as the value of the absolute decrease in the metal flow stress, as well as its width according to the FWHM (Full With at Half Maximum) value.

The offered operative method of an estimation of a functioning state of jacks of gas highways of pneumatic hydraulic systems (PHS), with the help, so-called, a power intensity indicator. The algorithm in the form of a number of the equations of gas dynamics for definition of current parametres of a gas stream is made. On concrete examples of designs of jacks, the sequence and results of the calculations are shown, allowing to reveal their most intense working sites, and necessity of their corresponding completion. Besides, for the purpose of economy and convenience of carrying out of technological operations of purges of knots of automatics or highways important parities for replacement of expenses, for example, helium on gases more simple and accessible to work (air, nitrogen) are received. The received recommendations and expressions are successfully confirmed in practice during working out and manufacturing of subsystems PHS of some LV «Zenith», «Cyclone», etc.

The pressurization system of the fuel tanks of launch vehicles is one of the important and critical subsystems of the pneumatic-hydro supply system. The pressurization system is designed to create the necessary pressures in the fuel tanks in order to ensure their required values at the engine inlets (both during launch and during operation in specified modes), as well as to ensure the strength and stability of the tanks during the flight of launch vehicles. These systems determine the configuration and appearance of launch vehicles, their energy characteristics and operating conditions. At the same time, the pressurization system is functionally interconnected with the operation of many other subsystems of the pneumatic-hydraulic supply system (refueling of fuel components, control systems, fuel consumption control systems, units of a liquid-propellant rocket propulsion system, etc.).
 One of the main functional elements of the pressurization system is the atomizer. The atomizer is designed to introduce pressurization gas into the tank in such a way that its speed and direction provide the required pressure and gas temperature distribution in the free volume of the tank, without causing unacceptable heating of the tank structure and fuel component, as well as possible disturbances (vibrations, etc.) .
 On the example of specific launch vehicles on high- and low-boiling fuel components, a generalizing review of the pressurization system sprayers developed in the Yuzhnoye State Design Office (YSDO) was carried out, as a result of which the authors determined and described in detail: their design features, requirements, classification, and the procedure for their development. The possibilities and tools for modeling the parameters of atomizers are shown. The experimental data of some of the developed atomizers are presented. Promising directions for the development of pressurization systems are outlined, which in the future will allow the development of highly efficient systems with optimal parameters.