An attitude-orbit coupling adjustment method based on high-thrust satellites

Abstract

The present invention is an attitude-orbit coupling adjustment method based on a high-thrust satellite. The steps are as follows: 1) On the basis of the satellite structure design, the satellite is designed symmetrically in the star, and there is no shelter around the propellant release nozzle outside the star, and the satellite is completed. Optimize the structural layout of the two parts inside and outside the star; 2) Analyze the impact of the large thrust generated when the satellite propellant is released on the satellite body, and design the attitude control system to ensure the normal operation of the satellite after the release of the propellant; 3) Propel the satellite onboard The propellant storage bottle is processed so that the propellant release meets the normal release requirements of high thrust; 4) The satellite attitude is controlled by the attitude control system to realize the attitude-orbit coupling control of the high-thrust satellite. The present invention adjusts the attitude of the satellite before each propellant release by optimizing the design of the satellite structure and calculating and analyzing the position of the center of mass of the satellite after the release of the propellant and the moment of inertia in the center of mass coordinate system.

Description

technical field [0001] The invention relates to an attitude-orbit coupling adjustment method based on high-thrust satellite maneuvering to realize high-mobility requirements of satellites by applying high-thrust. Background technique [0002] It is very important to use high thrust to realize rapid orbital maneuvering of satellites in applications such as deep space exploration and earth observation. [0003] At present, high-thrust is mainly used in the orbit change requirements of satellites in various missions. When the propellant is released, the impact of the high-thrust on the satellite itself is likely to cause attitude-orbit coupling problems. It shows that the high thrust is not only to meet the needs of orbit change, but also to produce impact and disturbance moment on the satellite body. At present, the attitude adjustment method for the application of high-thrust satellites mainly uses the momentum wheel for attitude control. The typical method is the PID contro...

AI Technical Summary

Problems solved by technology

However, for high-thrust satellites that release propellant multiple times in a row, it is impossible to control the satellite persistently through momentum wheels and thrusters

[0005] (2) For small satellites that need to use large thrust for orbital maneuvering, due to the small mass of small satellites, the commonly used momentum wheel attitude control method is adopted, and the interference torque generated by high thrust on the attitude of small satellites is too large, so that the satellite still has a large Risk of not continuing to function normally

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