METHOD OF TRAJECTORY CONTROL BY MULTI-POINT MEASURING COMPLEX OF MULTI-PULSE ORBITS OF SPACECRAFT INJECTION INTO HIGH-ELLIPTICAL, GEOSTATIONARY AND GEOSTATIONARY ORBITS USING ACCELERATING UNITS Russian patent published in 2025 - IPC B64G3/00 G01S19/03 

FIELD: spacecraft navigation.

SUBSTANCE: method for trajectory control of orbits of spacecraft injection into different orbits using GLONASS/GPS navigation systems. Navigation parameters of the booster unit are determined and transmitted to the ground complex, where statistical estimates of the orbit parameters are determined. Interrogation trajectory signal is conducted and the range and speed of the accelerating unit are measured. Refined estimates of navigation definitions are obtained using navigation systems and a multi-point measuring system. Corrections to measured values at slave ground stations are determined. Obtained data are used to determine parameters of spacecraft orbits.

EFFECT: increased volume of obtained measurements, accuracy and reliability of navigation determinations.

2 cl, 2 dwg