RU94040134A - Method of orientation of space vehicle in space by means of solar-dynamic surfaces and device for realization of this method - Google Patents

Abstract

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

Claims (1)

Usage: space technology, the orientation system of spacecraft (SC) using solar-dynamic surfaces (SDP). The essence of the invention: when the spacecraft is oriented in space, its longitudinal axis is oriented in a given direction by deflecting the SDP in the tangential and radial directions to the first given angles, after which these surfaces are returned to a neutral position. On a given section of the interplanetary trajectory, the longitudinal axis of the spacecraft is directed to the Sun by deviating the SDP to a given angle, the spacecraft is twisted to a given angular velocity, and then the SDP is returned to a neutral position; in the next section of the trajectory, the longitudinal axis of the spacecraft is directed perpendicular to the plane of the spacecraft's orbit by deflecting the SDP to the second given angles in the tangential and radial directions, and after the precession of the spacecraft's longitudinal axis to the position perpendicular to the plane of the spacecraft's heliocentric orbit, these surfaces are returned to the neutral position. In the perihelion region, the longitudinal axis of the spacecraft is directed to the Earth by the deviation of the SDS to the third specified angles in the indicated directions and the direction to the Earth is monitored during the communication session with the Earth, after which these surfaces are again returned to the neutral position. The spacecraft orientation device in space contains at least a pair of SDPs mounted symmetrically on the spacecraft’s body with the possibility of rotation relative to the radial and tangential axes of the spacecraft, while the SDP area is selected in accordance with the modes of the operations described above.