Patent
Self-contained on-board control system for space vehicle
TLDR
In this paper, an autonomous on-board satellite control system is proposed to achieve autonomous orientation control and autonomous determination of the satellite's altitude and location in relation to the Earth's longitude and latitude grid.Abstract:
PCT No. PCT/RU93/00262 Sec. 371 Date Aug. 23, 1995 Sec. 102(e) Date Aug. 23, 1995 PCT Filed Nov. 10, 1993 PCT Pub. No. WO94/18073 PCT Pub. Date Aug. 18, 1994An autonomous on-board satellite control system is to achieve autonomous orientation control and autonomous determination of the satellite's altitude and location in relation to the Earth's longitude and latitude grid. This is done with the aid of the following elements: an Earth sensor (1), a Pole-star sensor (2), a computer (4), a timing device (6) and actuator units (7). The system also includes a navigational star sensor (3) and a storage device (5), while the computer is designed so as to facilitate supplementary determinations. The orientation of the satellite is controlled by superimposing the general sensory plane (16) of the sensors (1 and 2) with the plane of the angle "center of Earth-satellite-Pole star" which defines latitude. The geovertical (11) rotates about a line to the Pole star (12) as the satellite (8) moves in its orbit (9) and this is equivalent to the revolution of the stars in the field of vision of the sensors (2 and 3). The rotation of the plan containing the lines to the stars (12 and 18) is measured in relation to a reference line (19) whose longitude and angular parameter ("B") are kept in the storage device (5). Inertial longitude is calculated as the sum of the angle of measurement and the right ascension of the Pole star as the base longitude and is converted to the geocentric longitude. The altitude of the plan (16) to the latitudinal plane is calculated as the product of the polar distance of the Pole star and the sine of the angle of measurement, while its development ( gamma ) when in misalignment with the longitudinal axis (17) is calculated as the product of the angular dimension of the Earth's radius, the sine of the angle is equal to the difference in longitudes of a target point (20) and the point below the satellite and the cosine of the latitude angle.read more
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