Satellite Rolling Attitude Planning Method Based on Line-of-Sight Pointing Considering Thermal Control, Measurement and Control Constraints

Abstract

The present invention provides a satellite rolling attitude planning method based on line-of-sight pointing and considering thermal control measurement and control constraints, including: (1) injecting the mission star position information and the target star position and attitude measurement information into the ground measurement and control station; (2) solving the task Sunlight unit vector in the star orbit coordinate system; (3) Solve the position vector of the measurement and control station under the J2000 geocentric inertial system; (4) Determine the thermal control and measurement and control constraints; (5) Determine the orbiting axis and the maximum orbiting (6) Obtain the value set of the flying angle; (7) Obtain the feasible region of the roll angle satisfying the thermal control constraint, the feasible region of the rolling angle satisfying the measurement and control constraint, and the rolling angle satisfying the thermal control measurement and control constraint for the flying angle (8) Obtain the feasible region of roll angle satisfying the thermal control constraint, the feasible region of roll angle satisfying the measurement and control constraint and the feasible region of roll angle satisfying the measurement and control constraint of thermal control during the whole flight process; (9) generate the mission star Scroll the angular expectation sequence, and put a star on it.

Description

technical field [0001] The invention relates to the field of space equipment manipulation, in particular to a satellite rolling attitude planning method based on line-of-sight pointing and considering thermal control measurement and control constraints. Background technique [0002] Space manipulation technology is currently a hotspot in the field of aerospace research. On-orbit maintenance of faulty satellites and capture and removal of abandoned satellites are both space manipulation technologies. Before the faulty satellite is repaired or the abandoned satellite is captured and removed, the mission star needs to fly around from the initial position to a specific position of the target star, during which the measuring device and control equipment on the mission star point to the target. [0003] The faulty satellite still has a certain attitude control capability, and its attitude is relatively stable; the abandoned satellite is in a state of out-of-control, but its attitu...

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At present, no description or report similar to the related technology of the present invention has been found, nor has similar information collected at home and abroad

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