An Autonomous Control Method for Yaw Maneuvering of Inclined Orbit Satellites

Abstract

The invention discloses an autonomous control method for inclined orbit satellite yaw maneuvering. The method comprises the steps of measuring and calculating the solar altitude and the satellite yaw axis attitude at the current moment; obtaining the moving direction of the sun relative to a satellite according to the solar altitudes at two different moments; determining the expected attitude of the satellite yaw axis according to the solar altitude at the current moment; determining a yaw maneuvering target value and a yaw maneuvering mode according to the solar altitude at the current moment, the satellite yaw axis attitude at the current moment and the moving direction of the sun relative to the satellite; starting control through a satellite actuator, and controlling the satellite to change to the expected attitude of the satellite yaw axis from the satellite yaw axis attitude at the current moment to carry out yaw axis attitude maneuvering. According to the autonomous control method for the inclined orbit satellite yaw maneuvering, the satellite forms an approximately fixed nightside through the yaw axis attitude maneuvering of the satellite, layout and design of star sensors can allow the star sensors to avoid sun shine, the star sensors are protected, and continuous output of measured data of the star sensors is guaranteed.

Description

technical field [0001] The invention relates to a satellite control technology, in particular to an autonomous control method for yaw maneuvering of an inclined orbit satellite. Background technique [0002] Inclined-orbit satellites have more advantages to achieve a specific mission goal. In some fields such as electronic reconnaissance, scientific observation, and navigation constellations, inclined-orbit satellites have been widely used. [0003] But in an inclined orbit, the sun will move continuously from one side of the orbital plane to the other side, and the angle between the sunlight and the orbital plane (sun altitude angle β) will continuously change between -90° and 90°. The complexity of the in-orbit illumination situation of inclined orbit satellites is the difficulty of satellite development. [0004] Its disadvantages are: [0005] No matter how the star sensor is laid out for satellites in inclined orbits, sunlight will enter the field of view of the star ...

AI Technical Summary

Problems solved by technology

[0005] No matter how the star sensor is laid out for satellites in inclined orbits, sunlight will enter the field of view of the star sensor, which is difficult to meet the requirements for continuous output of attitude measurement data, and sunlight exposure will cause damage to the star sensor;

[0006] The position of the sun relative to the satellite on the inclined orbit changes into a two-dimensional movement, and the satellite only uses a one-dimensional drive solar array, which cannot ensure that the sailboard is always facing the sun and cannot meet the energy supply requirements;

[0007] All sides of a star in an inclined orbit can be exposed to sunlight, and it is difficult to choose a fixed cooling surface, which brings great difficulties to thermal control design

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