METHOD OF CONTROLLING SPACE VEHICLE SUN BATTERY POSITION

摘要

FIELD: aerospace engineering. ^ SUBSTANCE: proposed invention relates to systems of supplying space vehicles (SV) and can be used aboard various geostationary satellites. The proposed method comprises measuring the current angle of sub battery (SB) that defines the position of normal to SB operating surface in coupled coordinate axes. In control, SB is revolved relative to SV housing, opposite the direction the said housing revolves relative to the Sun. SV complete geostationary orbit is determined. Note here that zero time is taken to be the moment at which aforesaid normal to SB surface coincides with projection of unit vector of direction to the Sun onto the said normal plane of rotation at zero current angle of SB. Current orbital time is count from zero to SV period around the Earth. Note also that the SB rotation circle is divided into equal arcs proceeding from maximum and minimum tolerable currents generated by SB at its certain orientation relative to the Sun. Bisectrix of SB rotation initial angular segment is taken to make the SB current angle zero value. SV complete period around the Earth is divided into time intervals, the number being equal to the number of the said segments. Each time interval is brought into correspondence with the current angle at a certain boundary between angular segments. SB rotation is terminated every time the aforesaid segment coincides with the boundary between angular segments assigned to SB. ^ EFFECT: higher SB survivability and accuracy of its orientation to Sun. ^ 3 dwg