METHOD OF ORIENTATION OF SPACE VEHICLE IN SPACE BY MEANS OF SOLAR-DYNAMIC SURFACES AND DEVICE FOR REALIZATION OF THIS METHOD

FIELD: space engineering. SUBSTANCE: during orientation of space vehicle in space, its longitudinal axis is oriented in preset direction through deflecting the solar-dynamic surfaces tangentially and radially through first preset angles, after which these surfaces are returned to neutral position. At preset section of interplanetary trajectory, longitudinal axis of space vehicle is directed to Sun by deflecting the solar-dynamic surfaces through preset angle, space vehicle is twisted to preset angular velocity, after which solar-dynamic surfaces are returned to neutral position; at the next section of trajectory, longitudinal axis of space vehicle is directed perpendicularly to plane of orbit of space vehicle through deflecting the solar-dynamic surface through second preset angles both tangentially and readily and after precession of longitudinal axis of space vehicle to position perpendicular to plane of heliocentric orbit of space vehicle, these surface are returned to neutral position. In area of periphelion, longitudinal axis of space vehicle is directed to Earth by deflecting the solar-dynamic surfaces through third preset angles in directions indicated and direction to Earth is tracked during communication session with Earth, after which these surfaces are returned to neutral position. Device for orientation of space vehicle in space contains at least one pair of solar-dynamic surfaces mounted symmetrically on casing of space vehicle for turn relative to radial and tangential axes of space vehicle; area of solar-dynamic surface is selected in accordance with above-mentioned operations. EFFECT: enhanced reliability. 3 cl, 2 dwg Использование: космическая техника, системы ориентации космических аппаратов (КА) с использованием солнечно-динамических поверхностей (СДП). Сущность изобретения: при ориентации КА в пространстве его продольную ось ориентируют в заданном направлении путем отклонения СДП в тангенциальном и радиальном направлениях на первые заданные углы, после чего эти поверхности возвращают в нейтральное положение. На заданном участке межпланетной траектории продольную ось КА направляют на Солнце путем отклонения СДП на заданный угол, закручивают КА до заданной угловой скорости, после чего возвращают СДП в нейтральное положение; на следующем участке траектории продольную ось КА направляют перпендикулярно плоскости орбиты КА путем отклонения СДП на вторые заданные углы в тангенциальном и радиальном направлениях, а после прецессии продольной оси