For solving non-traditional problems of rocket flight control, in particular, for the conditions of impact of a nuclear explosion, non-traditional approaches to the organization of the thrust vector control of a rocket engine are required. Various schemes of gas-dynamic thrust vector control systems that counteract impact actions on the rocket were studied. It was found that the dynamic characteristics of traditional gas-dynamic thrust vector control systems do not allow one to solve the problem of counteracting impact actions on the rocket. Appropriate dynamic characteristics can provide a perturbation of the supersonic flow by injecting into the nozzle the detonation products with the main shock wave propagating in the supersonic flow. This way to perturb the supersonic flow in a rocket engine nozzle is investigated in this paper. In order to identify the principles of producing control forces and provide a perturbation of the supersonic flow by injecting into the nozzle the detonation products with the main shock wave propagating in the supersonic flow, a computer simulation of the nozzle flow was performed. The nozzle of the 11D25 engine developed by Yuzhnoye State Design Office and used in the third stage of the Cyclone-3 launch vehicle was taken as a basis. The thrust vector control scheme relies on the use of the main fuel component detonation. The evolution of the detonation wave in the supersonic flow of the combustion chamber nozzle was simulated numerically. According to the nature of the perturbation propagation in the nozzle, the lateral force from the perturbation has an alternating character with the perturbation stabilization in sign and magnitude when approaching the critical nozzle section. The value of the relative lateral force is sufficient for counteracting large disturbing moments of short duration. Thus, the force factors that can be used to control the rocket engine thrust vector are identified. Further research should focus on finding the optimal location of the detonation product injection in order to prevent mutual compensation of force factors.

We have carried out numerical simulation of the flow in the jet mill ejector. The features of ejector are an annular unit for supplying an additional gas flow in the form of a confuser section at the inlet to the accelerating tube, as well as a confuser at the outlet of the accelerating tube. In the course of the study, we have varied the length of the confuser section at the inlet and the angle of an additional gas flow supply. We have established the optimal parameters of the unit for supplying an additional gas flow in the ejector, at which it has been the most uniform distribution of the flow velocity at the outlet of the accelerating tube. The use of the ejector scheme under study ensures the alignment of the vortex flow and a stable near-wall layer throughout the accelerating tube. The results of the study can be used to improve the efficiency of the grinding process in a jet mill.

Jet grinding considers a rather energy-intensive production. For obtaining high mill productivity, it is necessary to control the process in order to prevent the transfer the energy intensity value to a critical one. This work shows the possibilities of jet grinding studying based on the process acoustic signal analysis and to develop a mill mode control system to achieve optimum productivity. There were determined that decrease in the activity and maximum amplitudes of the acoustic signals in the grinding zone is a sign of deviation from the optimal fine grinding mode, which leads to a decrease in the mill productivity and requires timely material loading. For control of ground product quality it’s necessary to control the frequency dispersion of signals corresponding to the control class, and check the absence or presence of signals corresponding to other size classes for zone behind the classifier. The developed automated control system of jet grinding allows implementing the optimal parameters of the mill operation by control the acoustic parameters of the grinding zone for optimum jet loading with material. The dispersion control of the ready product is based on acoustic monitoring of a two-phase flow in the product transportation zone.

The results of numerical simulation of the flow in the jet mill ejector which is equipped with an additional gas supply channel have been presented. The influence of the supply system parameters on the nature of the flow in the ejector accelerating tube has been investigated. A comparative analysis of the change in the flow structure in the ejector for different values of the additional gas flow angle has been carried out. The dependences of the flow velocity at the outlet of the accelerating tube, the ejection coefficient and the thickness of the protective layer on the angle of the additional energy carrier supply have been scrutinized. The maximum values of the average output velocities for the given ranges of the additional flow parameters have been determined. Recommendations for the choice of geometric and gas-dynamic parameters of the additional gas flow to ensure the highest efficiency of the acceleration process in the jet mill ejector have been developed. The choice of the angle of the additional gas flow supply, which provides the highest average velocity at the outlet from the accelerating tube with the highest ejection coefficient, has been substantiated.