ДИНАМИЧЕСКОЕ ПОВЕДЕНИЕ РАКЕТНОГО ДВИГАТЕЛЯ ТВЕРДОГО ТОПЛИВА В ПРОЦЕССЕ ЭКСПУАТАЦИИ (ОБЗОР)

Abstract

One of the problems that has been solved for more than 80 years is the dynamic behavior both during the development of a rocket engine and during operation, these are oscillations that occur in the combustion chamber. Gas vibrations and mechanical vibrations of the rocket engine elements can cause vibration loads, which, under certain conditions, leads to resonance phenome-na. This can cause engine failures. An analysis of the behavior of a rocket engine as a dynamic system with an assessment of frequency interactions over the entire time of its operation has not been completely resolved today. Various options for studying the dynamic behavior of a rocket engine, algorithms for determining natural oscillation frequencies are considered. The analysis of existing approaches for solving the problem of determining the dynamic behavior of the rocket engine was carried out. In various works, the mechanical vibrations of the engine housing or its elements, such as a sliding nozzle, are calculated using various methods. In a number of works, the structure is considered as a model of discrete masses, where the elements are connected through the stiffness and viscosity coefficients. In other cases, fluctuations of the gas flow during combustion in the combustion chamber are considered, methods of numerical simulation of the process are developed that take into account the features of vor-tex formation and instability of the gas flow, as well as dependence on the shape of the charge. However, the joint problem has not been solved; in the presented works, the mutual influence of the vibrations of the rocket engine case with the fuel and gas flow during operation is not considered. To get a complete picture of the dynamic loads experienced in a solid propellant rocket engine, this interaction must be taken into account.