Structure optimization and parameters of large energy propulsion systems

Energy propulsion spacecraft systems have a significant impact on the capabilities and effectiveness of the target solution. In recent years there is a tendency to increase electric power consume of spacecraft. It is connected with the significant increase of power of target systems. In addition, electric propulsion systems, which consume a lot of power in progress of working, are widely used for deducing satellites and correction of its orbit nowadays. To create a high specific power satellite it may be used energy propulsion spacecraft systems with different structures, including nuclear power plants (NPP). In addition to well-known nuclear power on the basis of thermionic converters, there is an interest in NPP with a gas turbine power converter. This type of power plants has a significantly higher efficiency of converting thermal energy into electrical energy. Due to the large number of alternative power systems, propulsion and electric energy storage there is a need to identify areas of rational use of the various structures of energy propulsion systems. The authors proposed a calculation procedure and obtained the areas of rational use of energy propulsion systems of various types. During the research it was found that the use of turbine based NPP expedient at high speeds characteristic costs, high frequency and high power maneuvering target system. For the NPP with a gas turbine power converter the authors propose a mathematical model which allows us to evaluate the basic design parameters and optimize on interesting criterion. On the basis of the mathematical model it is shown that the required temperature range for the heat exchanger-cooler practically does not change with the increase of input power. Also it has been found that the cycle efficiency largely depends on the temperature at the turbine entrance, and temperature at the compressor entrance.