The characteristics of the GLONASS integrated navigation and time field under the optimization of the placement of pseudo satellites (pseudolites) relative to the runway is discussed. The optimization criterion is based on the minimization of the geometric factor along the glide path. To solve the problem, the Hooke-Jeeves and Nelder-Mead methods were used for the time interval corresponding to the period of the recurrence of the GLONASS orbital motion. The gain in the average value of the geometric factor under the optimal placement of pseudo satellites is shown. The influence of the number of pseudo satellites on the characteristics of the accuracy field is shown.

pseudo satellite, glide path, geometric factor, GLONASS orbital grouping, mathematical modeling, placement optimization.