Andriievskyi M. Development of Rocket Propulsion Systems Running on Highly Concentrated Hydrogen Peroxide and Kerosene

In the XXI century, three main factors, that make the development of rocket and space technology, were identified. The first factor is the active commercialization of space. It means that the creation of a launch vehicle is not based on the requirements of ensuring the prestige of the country, as it was in the XX century, but only on the requirements of the market. It is obvious that market interactions give a rise to competition, which changes the understanding of the effectiveness of the rocket and space complex (RSC). In the market aspect, the effectiveness of the RSC is determined by the mobility of launch services, the ability to adapt to specific market requirements, as well as the minimum price for the launch mission. The second significant factor that forms the direction of development of rocket and space technology is the miniaturization of electronics. This factor increases the demand for the launch of small launch vehicles. Obviously, the concept of a small launch vehicle should provide maximum autonomy from the spaceport to reduce the cost of operation and ensure the mobility of launch services. The third important factor is the requirements for environmental friendliness and safety of missile technology. This factor creates the need to find and use fuel components that would be safe not only during operation, but in the process of their manufacturing. The first two factors make the development of storable propellant launch vehicles relevant. However, the third factor makes it impossible to use classic storable propellant such as unsym-dimethylhydrazine and dinitrogen tetroxide. The only fuel that meets all the requirements is a match of hydrogen peroxide - kerosene. This fuel has a number of advantages over the classic cryogenic components. First, in the event of a start delay, there is no need to drain the fuel components, which ensures the mobility of the launch mission. Secondly, there is no need for constant refueling of the launch vehicle, which increases the independence of the launch vehicle from the spaceport. Third, there is no need for a complex system of thermostating and cooling units. The purpose and objectives of the study – to investigate the throttling and launch processes of the rocket engine running on hydrogen peroxide - kerosene, as well as the formation of recommendations for the design of modern rocket propulsion systems, taking into account trends in the market of the launch services. The object of the study is rocket engines running on fuel components hydrogen peroxide – kerosene. The subject of the study is a method of rocket engines thrust chamber manufacturing; processes of thrust chambers (TCh) cooling organization; static and dynamic processes occurring in rocket propulsion systems. Also the internal tank processes that occur during the inflation of the engine fuel tanks are the subject of the study.