Determination of spacecraft electric jet engines altitude performance with the methods of experimental design

The testing technique is suggested, based on the theory of experimental design. The analysis is carried out of flight altitude and speed combinations required for optimal spacecraft control. The relevant values of space environment parameters in front of the satellite are presented. The regression model is obtained of electric jet engine flow characteristics – its parameters dependence on the specific thrust. Attention is paid to multifactorial approach to the experiment performed while managing the propulsion device resources. Illustrated is not successive, but simultaneous change of all relevant factors from one design point to another. Optimal designs of multifactorial experiment are obtained.