Injection of the maximal payload under random perturbations of parameters

Consideration was given to determination of the maximal mass of the payload that can be inserted into an elliptical orbit by the ‘SOYUZ‐2’ launch vehicle with a probability not smaller than the predefined threshold and to the case where the launch vehicle parameters and the atmospheric characteristics are described by normally distributed random variables with certain expectations and rms deviations. A procedure was proposed to estimate the payload mass, and the results of numerical modeling on the multiprocessor computer system using the real data were presented.