| 摘要 |
FIELD: transport.SUBSTANCE: invention relates to aerospace engineering and can be used for independent collocation in geostationary orbit. Inclination and eccentricity vectors are changed to boundaries of aiming areas spaced apart relative to each other. Spacecraft orbit parameters are measured to define current orbital parameters of every spacecraft. Spacecraft with self-collocation is brought to preset retention area in latitude and longitude Pattern of control over adjacent spacecraft gravity centre control is revealed. Aiming area centre position is refined relative to adjacent spacecraft inclination. Inclinations of self-collocation spacecraft orbit in phase plane with allowance (current direct Sun climb), adjacent spacecraft orbit nodes lines and centre are corrected. Low-thrust engines are used to correct period of orbit revolution, inclination and eccentricity, or deviation in the case of dangerous approach.EFFECT: ruled out radio interferences, self-collocation by control centre.4 dwg |
