FIELD: space engineering; orientation of spacecraft. SUBSTANCE: proposed method includes determination, plotting and maintenance of initial orientation of spacecraft, measurement of initial and present parameters of signal sources and determination of present orientation of spacecraft by these parameters, as well as correction of spacecraft orientation. Initial orientation of spacecraft is plotted and maintained at axis of on-board radio technical complex antenna directed to preset point of sighting on planet surface. Initial signal is measured at measuring stations located in area of visibility of spacecraft; law of change of signal of on-board radio technical complex at measuring station is determined in the course of its measurement during change in spacecraft orientation, thus ensuring increment of initial signal of different signs and amplitudes. Preset spacecraft orientation whose parameters coincide with parameters of initial orientation is plotted and maintained; present signal is measured at measuring station and in case of its deviation from initial signal, position of antenna axis is calculated according to definite law of change of signal. Present orientation of spacecraft is determined by measured and calculated position of antenna axis and required correction is performed. EFFECT: possibility of ensuring control of spacecraft during motion over Sun lighted part of orbit; enhanced accuracy of determination of orientation of spacecraft. 4 dwg, 1 tbl
