Double-direction solar panel control method applicable to inclined orbit satellite

Abstract

The invention discloses a double-direction solar panel control method applicable to an inclined orbit satellite. The double-direction solar panel control method comprises the steps that a mathematic model of the positional relation between the inclined orbit satellite and the sun is built and used for quantitative description of the motion law of the sun relative to the satellite; a solar panel driving error is defined according to the mathematic model and used as input of solar panel driving control; the law of solar panel capture control is determined, so that a solar panel is made to find the sun; the law of solar panel tracing control is determined, so that solar panel sun-targeted orientation is realized through sun tracing. According to the double-direction solar panel control method applicable to the inclined orbit satellite, the solar panel driving law and satellite yawing maneuvering are combined, and the problem that the inclined orbit satellite realizes sun-targeted orientation through a one-dimensional solar panel driving mechanism is solved; judgment and adjustment can be carried out autonomously according to the motion direction of the sun according to the forward flight and inverted flight of the satellite, and correct capture of the sun by the solar panel under different initial conditions is realized; forward driving control and inverted driving control of sun-targeted orientation of the solar panel are realized according to the forward flight and inverted flight of the satellite.

Description

technical field [0001] The invention relates to a driving control method for a satellite solar sail, in particular to a two-way control method for a sail adapting to satellites in inclined orbits. Background technique [0002] The sunlight irradiation situation for satellites in inclined orbits is more complicated. The sun will move continuously from one side of the orbital plane to the other side, and the angle between the sun’s light and the orbital plane (sun altitude angle β) will be between -90° and 90° change continuously. That is, the motion of sunlight relative to the satellite body is a two-dimensional motion, which includes both the rotational motion around the pitch axis due to orbital motion and the rotational motion around the yaw axis due to orbital precession. In order to ensure that satellites in inclined orbits can obtain solar energy, the sail must always be oriented toward the sun. For two-dimensional motion, a two-dimensional driving mechanism must be u...

AI Technical Summary

Problems solved by technology

For two-dimensional motion, a two-dimensional driving mechanism must be used to drive the sailboard to achieve two-dimensional tracking motion, but the technology of the two-dimensional driving mechanism is not yet mature, and the cost is high, which is not conducive to the current satellite equipment

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