Sun capturing method based on plurality of solar cells

Abstract

A sun capturing method based on a plurality of solar cells comprises the following steps: arranging four solar cells with certain geometrical relationship on the Z surface of a satellite; then determining the initial rotation direction of the satellite through the size of a normalized current value, controlling the satellite to rotate and continuously adjusting the rotation direction of the satellite according to the size of the normalized current value during the rotation process, and enabling the Z axis of the satellite to rotate towards the sun direction all the time; when the normalized currents of three or four cells are greater than a given threshold value, determining the actually measured posture of the satellite; when the actually measured posture meets the condition, utilizing a gyroscope angular speed to estimate the posture, and utilizing the actually measured posture to amend so as to obtain an estimated posture; when the actually measured posture does not meet the condition, directly using the actually measured posture to update the estimated posture; finally, obtaining required control quantity of the satellite for orientation to sun through the estimated posture so as to achieve the purposes of sun orientation and tracking after closed-loop control. According to the method, the sun can be quickly captured and stably tracked.

Description

technical field [0001] The invention belongs to the field of spacecraft attitude control, and relates to a method for a spacecraft to capture the sun, in particular to a method for searching and capturing the sun based on the measured current of a plurality of solar cells. Background technique [0002] Sun capture is the process of controlling a spacecraft in any direction in space to search for the sun with a specific sensor, and controlling a certain direction on the spacecraft to point to the sun when the sun is found. [0003] At present, there are two types of sun acquisition methods commonly used by satellites. One is the known sun target vector position coordinates and current attitude information. For example, sun capture using a star sensor falls into this category, characterized by continuous acquisition of current attitude information throughout the capture process. The patent No. is CN201010509204.X, and the technical solution disclosed in the patent titled "A M...

AI Technical Summary

Problems solved by technology

The patent No. is CN201010509204.X, and the technical solution disclosed in the patent titled "A Method for Initial Sun Acquisition of a Satellite Initially Entering Orbit" belongs to this category. The disadvantage of this method is that it is necessary to use a star sensor. One type of measurement component with the ability to determine the attitude of the whole celestial body provides the current inertial attitude of the satellite. When capturing the sun, the exact position of the sun needs to be known in advance, so the solar ephemeris needs to be calculated on the star; the other type is the sun target vector and the current attitude The information is unknown. Only when the spacecraft rotates according to a certain rule, the sun sensor can see the sun will have the corresponding attitude information. After obtaining the attitude information, the spacecraft will be finally controlled to point to the sun.

Its disadvantage is that when the sun is parallel to the pitch axis, the sun cannot be searched around the pitch axis, and it takes at least 720 seconds to switch the search direction to search for the sun

Images