METHOD FOR SPACECRAFT ORIENTATION IN SOLAR-TERRESTRIAL COORDINATE SYSTEM

摘要

FIELD: astronautics.;SUBSTANCE: invention relates to orientation control of a spacecraft (SC) with solar batteries (SB). Method includes orienting the first axis of a spacecraft towards the center of the Earth by turning relatively to the second and third axes according to information from the orientation device to the Earth, as well as the orientation of SB panels to the Sun by rotating the SV relatively to the first axis until the second axis of the SV coincides with the Sun – SC plane – Earth according to information from the orientation-to-Sun device (OSD). SB panels orient to the Sun by turning them around an axis parallel to the third axis of the spacecraft, driven by the SB according to information from the OSD. At the same time, at each control cycle, the calculated angle between the normal to the surface of the SB and the second axis of the spacecraft is determined by integrating the calculated angular speed of the SB drive shaft, along which the SB control is formed on the previous control cycle. Magnitude of this angle control the speed of the SB drive shaft, specifying the value of this angle with each passing of the reference end contact.;EFFECT: technical result consists in the ability to provide orientation of the SB panels to the Sun in the absence of the sensor of the angle of rotation of the SB drive shaft or its malfunction.;1 cl, 3 dwg