PROPELLANT TANK AMMONIAC PRESSURIZATION SYSTEM OF LAUNCH VEHICLES PROPULSION SYSTEMS

Abstract

Fuel tank pressurization systems are some of most science-intensive and expensive parts of rocket carriers. There is a lot of interest in usage of structurally simple pressurization systems, including those, which don't use working bodies from the start, such as gas-generating and chemical. The possibilities of using liquid ammonia in fuel-boost systems tanks as a working fluid had been researched. The analysis of earlier and modern systems of pressurization of tanks oxidant and hot carrier rockets whose propulsion systems use liquid oxygen and kerosene had been analysed with examination of advantages and drawbacks. The purpose of conducted research is finding effective modes and simplific design of fuel tank pressurization systems with kerosene while using as working pressure of liquid ammonia. It has long been successfully used in missile technology in stabilization systems of space vehicles. The operational characteristics of ammonia and thermal aspects of its decomposition into hydrogen and nitrogen. The rate of decomposition of ammonia  satisfies requirements pressurization. The gas constant of ammonia decomposition products is 978, 2 kJ. The notable disadvantage of this working body of pressurization with respect to the pressurization systems is a large the amount of heat necessary for its decomposition. The positive role of catalysts (iron, tungsten, ruthenium). Audited thermal energy on board the launch vehicle. There are offered schemes, using the heat of the engine's torch and the heat of the solid-fuel gas generator. Recommended azide gas generators, which generate pure high-temperature nitrogen. Such a scheme increases the possibility of being pressurized with helium. The possibilities of using decomposition products ammonia to pressurize the tank with oxidizer. The high efficiency of ammonia pressurizing systems example of the first stage of the medium-sized launch vehicle